Minimize TRUTHS

TRUTHS (Traceable Radiometry Underpinning Terrestrial- and Helio-Studies)

Mission Architecture     Payload overview     On-Board Calibration System     Spacecraft
Development Status    Launch    References

The Earth’s climate is undoubtedly changing; however the time scale, consequences,and causal attribution remain the subject of significant debate and uncertainty. Detection of subtle indicators from a background of natural variability requires measurements over a time-base of decades. This places severe demands on the instrumentation used, requiring measurements of sufficient accuracy and sensitivity that can allow reliable judgements to be made decades apart. 1)

The 21st Conference of the Parties (COP 21 in Paris in November 2015) exemplified the intense political, scientific, and public debate about climate change. Observing the changing Earth is at the heart of the world’s space agencies agenda, none less so than that of UK space agency (UKSA) and that of its primary partner,European Space Agency, (ESA). Measurements made in support of this observation program must be universally accepted, robust, and of sufficient accuracy to ensure stability and trust of long-term records. Unfortunately, this must be achieved with an observation system built with technologies known to suffer unpredictable degradation, due to both launch and the harsh environment of space itself. This paper describes a new satellite mission, recently selected to start formal phase A/B1development in the ESA Earth Watch program, called TRUTHS (Traceable Radiometry Underpinning Terrestrial- and Helio- Studies), which is expressly designed to provide this missing assurance by directly anchoring the space-based Earth observing (EO) systems to the internationally accepted physical standards of the SI measurement system. In this way, guaranteeing the temporal consistency of data, even beyond the lifetime of individual systems, while simultaneously providing data of unprecedented quality and accuracy to address key challenges of data from the global EO system, including European infrastructure, such as instruments on-board the Copernicus Sentinels of the European Union, to create a foundation for a unified ”operational climate observing system.”

The ESA Earth Watch program facilitates the delivery of Earth observation data for use in operational services. TRUTHS not only delivers an operational global hyperspectral radiance product, but upgrades to ‘climate quality’ a broad range of operational sensors delivered from across
the international space agencies and facilitates the prospect of science quality data from ‘newspace’ constellations of microsatellites.

TRUTHS’ intrinsic space climate observatory dataset is the science objective that drives the payload performance requirements, but it is in the multi-domain application of the Level 1 (L1) and Level 2 and higher (L2+) datasets of collaborative sensors, fully integrated into the ESA family that cements its true operational credentials.

Mission Concept

The concept for space-based SI-traceable reference measurements was developed within the CEOS Working Group on Calibration and Validation (WGCV) and Global Space Intercalibration System (GSICS) of the operational agencies. Multiple space agencies see the need for reliable reference measurements at all the frequencies that are used by instruments to sense the Earth, including visible/near infrared (VIS/NIR), Infrared, and microwave. The principle application area for these measurements, at the highest accuracy levels, is climate; from both the direct sensor measurements and for the calibration of other space-based instruments. However, any application requiring data interoperability, combination of sensors, and other relative information from single scenes, inherently needs to address and understand differences and changes in radiometric accuracy and biases.

To date, two spacecraft mission concepts have emerged to address these top-level goals, TRUTHS, for the solar reflective spectral range (320 nm–2400 nm), led by the UK, and Climate Absolute Radiance and Refractivity Observatory (CLARREO), for the full spectral range, i.e., as TRUTHS but with the addition of thermal IR and no solar measurements, led by NASA, USA. An initial demonstrator mission of CLARREO (Pathfinder) on the International Space Station (ISS) addresses Solar reflective domain down to ~350 nm. So far, no mission has been proposed for the microwave part of the spectrum. More recently China has also announced plans to build a mission to fulfil similar goals. The increased number of such SI-Traceable mission concepts has led to the proposed generic name of SITSATS (SI Traceable Satellites).

SITSATS like TRUTHS and CLARREO are intended to provide highly accurate and trusted climate records and to help constrain the uncertainties in predictions of climate forecast models. The missions are highly complementary and whilst the solar reflective aspect of the two missions seek to fulfil similar objectives, they differ significantly in how the on-board SI-traceability is achieved and also in their native GIFOV (Ground Instantaneous Field of View), with TRUTHS additionally targeting higher spatial resolution sensors. TRUTHS additionally makes direct measurements of Earth incident solar irradiance, total and spectrally resolved, whereas CLARREO uses the Sun as part of its on-board calibration system. Simultaneous or overlapping flights of the two missions and/or indeed the new proposed Chinese mission, not only provide greater temporal coverage and opportunity to calibrate other EO sensors, but also the means to perform inter-comparisons between themselves to fully validate the uncertainties of the missions and the robustness of the SI scale realized in space. In this way, adopting the same strategy employed by NMIs on the ground to evidence and ensure integrity of the SI system and independent realization of the units.

International government policy for the adaptation to, and mitigation of, climate change, is informed by forecasts of future climate, provided by climate models. The IPCC (Inter-Governmental Panel for Climate Change) reporting structure is largely centered on the output of models, indicating the rate of change, effect of competing processes, and the timescales at which various thresholds will be met, under different (emission) scenarios.

All models are approximations of reality, parametrized to allow for limitations in various forms, be that; computational power, understanding of the underlying physics, interactions, and feedbacks; or the extent and availability of observational input data. Even in a scenario with perfect knowledge of all the above, the very stochastic nature of climate means there will be variance in model outputs.

The very nature of the problem means there will be a spread of predictions from an individual model and a spread of predictions between models, due to differences in how the models implement the parameterizations. This variance in model output is unavoidable and is captured as an uncertainty in the forecasts. This uncertainty is costly, and policymakers need to reconcile the economic and political cost of the degree and timeframe of action against immediate political priorities and drivers. In some quarters, this uncertainty in the forecasts is used as evidence to take a limited course of action, or not to act at all.

The uncertainty in, and discrepancies between, models therefore needs to be minimized. At the very heart of the scientific principle, is that models should be tested with quantifiable observations. These observations need as a minimum to enable the principle sources of uncertainties in these models to be tested and in practice these relate to how changes in radiative forcings, feedback to the radiation balance, most notably cloud and albedo. It is of course also critical that the observations can build-up sufficient magnitude above background noise to allow discrimination of any model dependency in as short a time a possible, noting that typical trends are very small and require decades to reach this level and thus in general require multiple time-series of data from different sensors. Robust unequivocal trust in these data sets and their linkage to form harmonized Fundamental Climate Data Records (FCDRs) lies at the heart of the metrology challenge.

Mission Objectives

TRUTHS has two primary objectives. To provide:

1) datasets of sufficient accuracy needed to observationally detect the signals of climate change (in the solar reflective domain) in the shortest possible time. Needed to critically test climate models and attribute the effects of climate change to geophysical processes by providing Top of the Atmosphere (ToA) measurements of incoming and reflected total and spectrally resolved solar radiation appropriately sampled and with uncertainties optimized to minimize time to detect a trend and consistent with goals of GCOS (Global Climate Observing System) specified requirements.

2) the means to upgrade the performance of the EO system through delivery of an operational high accuracy L1 nadir-looking hyperspectral Earth-reflected radiance product with sufficient spatial (~50 m (goal)), spectral (<8 nm), accuracy (goal 0.3%, k = 2), and agility that allows it to match (or address) the observational radiometric characteristics of a wide range of Earth viewing sensors so that it can validate and/or upgrade their calibration by ‘reference calibration’ (Cal) from space, primarily to address climate measurement needs.

The choice of a 90 degree’ precessing orbit provides the opportunity for multiple near simultaneous nadir observations (SNO) and an agile platform compliments this further allowing angle matching so as to remove normal sources of error resulting from view/illumination angles and atmospheric variations. TRUTHS additionally assigns calibration coefficients to existing CEOS/GSICS calibration methods and stable targets such as deserts and the moon enabling not only in-flight sensors to be calibrated, but also back correction of heritage sensors that viewed these targets. Through this reference calibration, SI traceability of the global earth observing system (solar reflective domain) is established; robust sensor to sensor interoperability and bias removal achieved (essential for future constellations such as for greenhouse gas (GHG) monitoring, and for many, uncertainty improved, to enable more robust climate quality observations and resilience to potential data gaps.

As a secondary objective, TRUTHS’ dataset can be used to provide a source of global hyperspectral data to address a range of applications and, constrain and improve retrieval algorithms.

TRUTHS accuracy has been optimised to be within 20 % of the perfect observing system; i.e., the ratio of the ability to detect a trend from a real observing system with that of the perfect observing system, limited only by natural variability, facilitating the detection of trends in key climate parameters, in as short a time as possible, i.e., to meet objective 1. For example, it will detect a trend in climate change driven cloud radiative forcing (CRF), the dominant and most uncertain climate feedback, in half the time of other sensors with current levels of achievable radiometric accuracy. 2)

Mission Products and Requirements: Summary

Climate ‘Top-Level’ Requirements

In the context of the primary objectives, climate, we take from GCOS (Global Climate Observation System) ,3) the specific requirements for radiation balance, in the ‘short-wave’ domain as these are the most demanding and arguably most urgent. They are presented in Table 1:

TRUTHS_Auto10

Figure 1: Essential Climate Variables (image credit: WMO)

Parameter

Accuracy

Stability (Decade)

Total Solar Irradiance (TSI)

0.04%

0.01%

Solar Spectral Irradiance (SSI)

0.3% (200–2400 nm)

1%

Reflected solar radiance (integrated)

1 W/m2 = ~1%

0.3 W/m2 = ~0.3%

Table 1: Global climate observing system (GCOS) requirements driving the radiometric performance drivers of TRUTHS

Note: 1/Instantaneous accuracy although demanding, is in the case of TSI < than the requirement for long-term stability. In practice, to have confidence and remove dependencies on a continuous ‘overlapping’ time-series it is preferable to target the stability requirement;

Note: 2/In the context of reflected solar radiance, to aid understanding of attribution, mitigation, and to constrain and test climate forecast models, the reflected solar radiance needs to be spectrally resolved. In particular, for the key radiation feedbacks which drive uncertainty and variance in the models; cloud and albedo and natural carbon sinks such as the oceans and land vegetation.

Mission Data Products and Performance Requirements

The mission data products and associated performance requirements derived to achieve the mission objectives are listed in Table 2 and the driving requirements are shown in red.

The most demanding of the driving mission requirements is uncertainty and this stems from TRUTHS’ intrinsic space climate observatory dataset applications. For more conventional, instantaneous applications e.g., imagery and to some extent cross-calibration, spectral bandwidth, GIFOV (Global Instantaneous Field of View), and SNR (all interdependent) become more critical whilst overall uncertainty can in general be more relaxed.

The evidence for these requirements, derived from user need and the propagation of required uncertainties to the operational geophysical product, is given in the remainder of this section, approached from an operational science area basis. Not all operational science areas are covered, with only key examples, sampled across the disciplines and where the observational characteristics and particularly the accuracy of observations are key drivers for the mission’s technical requirements. Further work to explicitly link the full range of user drivers needs to be undertaken, but these are illustrative of those and are driven by those indicated in Table 1, which stem from the GCOS requirements for the corresponding essential climate variables (ECVs).

It should be noted that signal to noise ratio (SNR) values in Table 2 are largely defined to be ‘commensurate with the overall uncertainty required by the application and its observational characteristics’ and are of course highly dependent on the choice of GIFOV and spectral bandwidth.

For Earth viewing, they are instantaneous with values given relative to a nominal average Earth albedo of 0.3 and for the corresponding GIFOV specified, for the Sun/Moon it is with respect to several seconds of integration time. Simplistically, the higher the SNR, the smaller the bandwidth and the highest spatial resolution the better but contrasted to this is the complexity of the camera, particularly driven by the size of the telescope needed to collect enough photons.

Unlike many conventional satellite missions where the instantaneous observation is the primary measure and thus where SNR is a key component of the overall uncertainty budget, for climate benchmark applications this is not the case as the product of interest will always be temporally/spatially averaged to remove effects of localized anomalies. Although a GIFOV of <250 m is desired for these applications, this is primarily to aid in assessing scene type and degree of cloud contamination. Most of the benchmark applications are concerned with scene aggregated observations over relatively large spatial and/or temporal scales. In these cases, effects of instrumental or observational noise, the dominant detrimental component of SNR, are effectively randomized and reduced significantly so that SNR makes little overall contribution to the uncertainty budget. Instead, instrument systematic effects and/or biases and drifts dominate the uncertainty achievable. Thus, the SNR for these applications can be <50 even at GIFOV of 250 m. Similarly, for solar or lunar observations because the spacecraft and its sensors can effectively stare at its target and accumulate signal, the instantaneous SNR does not need to be demanding. For some climate applications e.g., ocean color the SNR requirements can be more demanding i.e., >1000 but even here the spatial resolution can be relatively relaxed >1 km.

For applications where the instantaneous, spatially resolved measurement is of greater importance e.g., cross-calibration of a high-resolution land imager like Landsat or Sentinel-2 or imagery such as land use classification the radiometric uncertainty levels can be relaxed towards those of existing sensors but with the proviso that for the reference calibration process to be of value the reference sensor (TRUTHS) uncertainty should not dominate. Here, SNR will play a more significant role in the overall uncertainty budget and will likely be the ultimate limiter in terms of number of applications, when considering what is achievable for an affordable instrument design.

Level 1 Products

Mission Requirement

 

Spectral range (nm)

Bandwidth (nm)
(Spectral Sampling x 0.5)

Uncertainty
(%) (k = 2)

SNR (with Respect to
Earth Albedo of 0.3)

GIFOV (m)

Earth Spectral Radiance
(Climate)

320-2400

8-25 nm

Goal
0.3

Threshold
<1.0

>50

250

Solar Spectral Irradiance

<320-2400

<1 (<400),
<5 (<1000),
<10 (<2400)

0.3

<1.0

>300

NA

Total Solar Irradiance

Total

200-30000

<0.02

<0.05

>500

NA

 

 

 

 

 

Threshold

Threshold

Earth Spectral
Radiance
(Cal/Val/other)

<380-2400

<8 (< 1000 nm)
<16 (>1000 nm)

0.3

<1.0

>80 (<500 nm)
>150 (500–1000 nm)
>100 (>100 nm)

Goal: >300

100 (>500 nm)
250 (<500 nm)


Goal: <50

Lunar Spectral
Irradiance

<350-2400

<8 (< 1000 nm)
<16 (>1000 nm)

0.3

<2.0

Goal
>~300

NA

Table 2: Mission performance requirements (climate and calibration) red indicates a driving requirement. Signal to noise ratio (SNR) values are given with respect to an average Earth albedo of 0.3 and for the corresponding ground instantaneous field of view (GIFOV)

In terms of cross-calibration, the most demanding will be the ocean color sensors like Sentinel-3 OLCI (Ocean and Land Color Imager) and NASA PACE (Plankton, Aerosol, Cloud, ocean Ecosystem) missions, where overall uncertainty requirements at ToA is equivalent to a few tenths of a percent. At present, this effective uncertainty can only be approached as part of the overall retrieval process and requires the tuning of the sensor and algorithm to surface measurements made at one of two open ocean system vicarious calibration references, the buoys, MOBY and Bousolle.

TRUTHS, with an agile platform, can both spatially integrate and employ satellite motion compensation (rotating the satellite to compensate for its orbital movement to allow it to stare and temporally integrate over the target) to increase SNR for the specific measurement.

Science User Requirements

The operational and science user requirements are summarised here for the primary objectives, together with some example secondary objectives. With the development of the mission, towards launch and the increased engagement of the prospective user community, the breadth of potential identified secondary objectives is expected to increase significantly.

Space Climate Observatory and Model Validation

The most significant societal challenge facing mankind relates to the impact of climate change. Much of the uncertainty in climate forecasting results from the degree of modelled sensitivity of the climate response or ‘feedbacks’ to anthropogenic carbon emissions; the most significant being the modelled response of clouds, surface albedo, and aerosols. High-accuracy observations of perturbations in the energetic inputs and outputs to the climate system over decadal timescales are essential to extract the long-term climate trend from the ambiguity of natural variability, with each of the key components allowing detailed attribution analysis from its own unique spectral signature.

TRUTHS’ observations provide a benchmark of the climate state from which such a trend may be determined by a subsequent mission of similar performance in a decadal timescale and provide a standard against which climate models can be tested and compared. Such testing is essential to improve confidence and reliability of future climate forecasts by reducing variance and uncertainty in the models [1]. Whilst confirming any trend requires a time-interval longer than a mission duration, the societal necessity of establishing an initial benchmark is thus an urgent priority. TRUTHS provides such a benchmark.

Observing both incoming and outgoing spectrally resolved solar radiation is a unique aspect of this mission and will improve our understanding of many processes where reflectance is a key parameter, including radiation budget and those requiring atmospheric correction.

Modern climate models directly use both the incoming and outgoing spectrally resolved solar radiation as constraints of the models’ internal processes. Therefore, models can directly assimilate the TRUTHS products as a test of the models, with the spectrally resolved aspect allowing attribution of specific processes to the underlying model process ; not only verifying if the model produces an accurate overall radiative balance, but also ensuring the model is attributing the strength of the competing processes consistently. Essentially, it is not just about having a globally correct model, but that the model is correct for the right reasons.

The space climate observatory drivers for TRUTHS is long-term referencing of the climate change signal, enabling the observational measurement of the expected small trends (compared to their absolute reference value). The uncertainty requirements, that at first glance may seem excessively strict, are necessary to allow detection of these decadal level signals in as short a timescale as possible i.e., ‘establish a reference with sufficiently small uncertainty that the signal from the accumulated trend can be reliably distinguished from it’, and reflect those identified by GCOS following assessments from the science community.

Mission Requirement

Parameter: Proposed Value

Driving Mission Objective

Required

Desired

 

 

 

 

SI traceable
measurement of
the solar reflected
spectrum

 

Nadir Reflectance Spectral
Climate Change Benchmarks

<350 nm–2300 nm

 

Spectral range:
320 nm–2400 nm

Earth Radiation budget

 

From 320 nm to
2400 nm

 

Plant optical traits and
minerals

380 nm–2400 nm

Up to 2500 nm

Accuracy:
0.3% (k = 2)

Trend estimation of cloud
feedback

0.3% (k = 2)

 

Spectral resolution:
1 nm–10 nm

Nadir Reflectance Spectral
Climate Change Benchmarks

1 nm–10 nm

 

50 m (land) 250 m (ocean)

Cloud masking

<250 m

<150 m

SI traceable
measurement of
total solar
irradiance

Spectral range: 0.2–>30
µm

Solar variability and Earth
Radiation Budget

0.2–>30 µm

 

Accuracy:
0.02% (k = 2)

Solar variability and Earth
Radiation Budget

<0.02% (k = 2)

 

SI traceable
measurement of
solar spectral
irradiance

Total Spectral range:
320 nm–2400 nm

Solar variability and ozone

<350 nm–2400 nm

200 nm–2400 nm

Accuracy: 0.3% (k = 2)

Solar variability

0.3% (k = 2)

 

Reference
calibrations

As for radiance above

Reference Intercalibration:
particularly for ocean color
monitoring sensors

<400 nm–>1000 nm

200 nm–2400 nm

Table 3: Mission requirements for climate benchmark observations of reflected solar radiance, and total and spectral solar irradiance. Spectral resolution is driven by the various climate variables. Accuracy is driven by the climate-benchmarking requirement to detect trends above natural variability.

Scene Type

Percent Error due to Limitation of Spectral Range

32–2300 nm

320–2400 nm

310–2300 nm

310–2400 nm

Global

0.09%

0.07%

0.05%

0.03%

All-sky Ocean

0.10%

0.08%

0.04%

0.03%

All-sky Land

0.08%

0.06%

0.05%

0.04%

Clear Ocean

0.16%

0.15%

0.05%

0.04%

Clear Desert

0.10%

0.07%

0.07%

0.04%

Table 4: Estimated error in total reflected solar energy

This leads to the goal requirement on spectral extent of <320 nm–2400 nm. The UV extent is particularly important for the solar spectral irradiance application where measurements to below the atmospheric ozone band at 290 nm would be ideal but can be limited to 320 nm to avoid overly driving the mission specification, with the Earth-reflected radiance requirement of spectrally resolved data >320 nm.

Spectral Bandwidth—the Earth-reflected radiance spectral resolution is driven by the need to resolve the spectral signature of climate processes and is modest at 8 nm to 25 nm full width at half-maximum (FWHM). Improved information content is only gained with a spectral resolution <3 nm, where gas-phase processes start to be resolved. Cloud processes require <10 nm spectral resolution so as not to degrade information content. However, the SSI measurement is the key driver for the climate space observatory driver, with ideally <1 nm resolution below 400 nm, and 5 nm to 10 nm resolution throughout the visible-ShortWave Infra-Red (SWIR) to allow models to adequately make use of the data. The latter Vis/SWIR bandwidths are also close to optimum for reference calibration requirements of most operational sensors, where the requirement is to enable adequate spectral matching of ‘customer’ sensor bands, and/or to enable spectral characterization of a spectrally smooth calibration target (e.g., desert, deep convective cloud, etc.) to allow interpolation for high spectral resolution sensors including those used for atmospheric chemistry related applications e.g., GHG sensors.

Radiometric accuracy—the 0.3% (k = 2) applied to an average global albedo of 0.3, implies a 0.001 reflectance uncertainty requirement. The 0.3% (k = 2) spectrally integrated driver (needed to determine cloud radiative forcings and feedbacks), translates to a 0.3% to 1% (k = 2) spectrally resolved requirement, dependent on the wavelength. The less strict requirements are in the strong absorption bands that contain less information content.

Signal to noise ratio (SNR)—the climate observatory native SNR goal requirement is ~300 in the vis-NIR, commensurate with the 0.3% (k = 2) accuracy requirement in the vis-NIR. However, as this is linked to IFOV, it should be noted that this instantaneous SNR level is not required for most of the earth viewing benchmark requirements, which will average over much larger spatial and/or temporal zones. This allows significant relaxation in SNR as the random component of the measurement is reduced. The instantaneous SNR requirement is higher for ocean colour and low signal water leaving applications, but this can be achieved with appropriate spectral and spatial binning and an increased dwell time attained from the platform agility.

Ground instantaneous field of view (GIFOV)—the space climate observatory GIFOV is driven by the need to identify and differentiate clouds within the dataset, with a requirement of ~250 m spatial resolution as a maximum. However, for cloud-free land applications, a higher 50 m GIFOV is valuable for many secondary applications involving land classification in some form and cross-calibration of higher resolution sensors.

Orbit—for climate benchmarking applications there is a preference (in the reflected solar spectral region) for measurements over a full diurnal cycle and therefore a precessing orbit of 90º, to minimize the sampling aliasing in the data record.

Pointing—The pointing requirement is split into two components:

• Nadir Earth-viewing pointing requirement for climate applications is only ~1º.

• Solar observations need a pointing accuracy of <0.1º, maintained over one minute, to provide the TSI, allowing for the CSAR time constant with the proviso that the FoV is entirely within the solar disc, achieved with a simple quadrant detector on the instrument front-plate, as flown in heritage PMOD (Physikalisch-Meteorologisches Observatorium Davos) missions.

Climate Change Services

A secondary objective for TRUTHS’ space climate observatory data is to improve the accuracy and usefulness of downstream value-added services, expediting the European Commission’s goal of leading the development of the climate services market [4)] and contributing significantly to the quality of data feeding into the Copernicus Climate Change Service (C3S).

The broad range of benefits and long timescales needed to detect trends reliably and to establish robust climate data records (CDRs) highlights the value of an early launch. Delaying the creation of such a system extends the time needed to establish reliable climate records and creates the constant risk of time-series being lost completely should an adequate overlap of missions be missed (due to lack of robust traceability/stability of current sensors). The ‘value of information’ that climate observing systems such as TRUTHS provide was modelled at trillions of dollars due to damages avoided from better-informed decision making [5)]. TRUTHS is proposed as a minimum five-year mission, which is adequate to establish the key climate and calibration benchmarks and demonstrate the benefits at cost-compliance, although a longer duration of eight or more years is targeted.

Although the technical specification of TRUTHS is unlikely to be driven by the needs of any one specific ECV, it is helpful to consider where the mission can play a valuable role if only to ensure that potential small modifications are appropriately evaluated. Our current selection of candidate ECVs is based on the following criteria: (1) Importance to global-scale climate change and (2) accessible to the technical scope of the mission. Table 5 provides a summary of the main ECVs, key elements of the primary societal benefit area (climate) addressed by TRUTHS by its own observations or through reference calibration of other sensors. The fiducial nature, and, the broad spectral/spatial coverage of the mission ensures it also provides significant impact to food and water, natural resources and energy, and disasters, health and pollution. The solar reflective domain is a rich source of information and the hyperspectral capabilities of TRUTHS, together with its high accuracy allows the various signatures to be extracted and de-coupled.

Commercial end-users have been consulted to understand the potential economic value of TRUTHS’ data and its impact on the EO observing system as a whole, with globally significant insurance companies commenting that TRUTHS could ‘underpin robust and credible products used across the industry’.

Climate Variable

Role

TRUTHS Providing
Direct Observation

TRUTHS Providing
Reference Calibration

Solar Irradiance

Climate forcing

yes

yes

Earth Radiation Budget

Climate forcing, feedback

yes

yes

Surface Albedo

Albedo feedback

yes

yes

Cloud Cover

Cloud feedback

yes

yes

Cloud Particle Size
Distribution

 

yes, through spectral
benchmarking

yes

Cloud Effective Particle Size

 

 

yes

Cloud Ice/Water Content

 

 

yes

Cloud Optical Thickness

 

 

yes

Water Vapor

Column water vapor response

yes

yes

Ozone

Stratospheric ozone feedback

no (limited spectral resolution)

yes

Aerosols Optical Depth

Climate forcing
Atmospheric correction

(limited temporal/ spatial coverage)
yes

yes
yes

Ocean & Lake Color

Carbon cycle

yes

yes

Ice and Snow Cover

Albedo feedback

yes

yes

Vegetation Indices

Carbon Cycle & Albedo feedback

yes

yes

Land Cover/Land Use

Surface Radiative Forcing

yes

yes

GHGs (Greenhouse Gases)

CO2/CH4 emissions monitoring

Yes but only large scale emitters

Yes

Table 5: A summary of climate change variables where TRUTHS can have significant impact either directly or via reference inter-calibration. The selection of variables is based on the following criteria: (1) Importance to global-scale climate change, (2) availability of satellite-based climate data records, and (3) measurability from passive sensors in the spectral range of TRUTHS i.e., near UV to SWIR.

Reference Calibration of Sensors—Test-Site Characterization

The satellite community has sought to establish well-characterised ‘test-sites’ and associated methods of use, ideally instrumented at ground level, to provide a means of both calibration and validation of level 1 radiances and, in some cases, level 2 or higher products.

In recent years, significant efforts have been made by the international community (through CEOS and GSICS) to consolidate and focus efforts on a sub-set of these sites/methods to aid sensor inter-operability and harmonisation. Efforts have started to establish true calibration networks at these ‘CEOS reference standard test sites’, analogous to the long established AERONET sites for aerosols, together with developing the tools needed to facilitate cross-calibration between sensors at these sites.

• The RadCalNet instrumented land network [6), 7)];

• Non-instrumented stable (usually desert, but also snowfields) land sites known generically as Pseudo-Invariant Calibration Sites (PICS) [8)];

• Ocean buoys at Moby and Bousolle [9)];

• The Aeronet-OC network;

• Extra-terrestrially, the Moon is a commonly used reference site [10)].

In addition, there are the use of Rayleigh scattering over the oceans, deep convective clouds, and Simultaneous Nadir Observation over any of the above or indeed any other suitable location on the Earth.

Calibration using PICS has historically provided highly reproducible calibrations, when suitably averaged to remove unknown effects due to atmosphere, spectral, and residual uncorrected surface Bi-directional Reflectance Factor (BRF) but are limited in terms of absolute accuracy through lack of any reference measurement.

There is a fundamental need for accurate hyperspectral referencing, provided by TRUTHS, as a means to make a huge step change in long-term performance characterization. Even with a minimal improvement in uncertainty but with high confidence level in its SI traceability, an anchoring reference would allow harmonization and certainty in the true reference value.

Current cross-comparison strategies assume the site surface reflectance is stable (reasonable and proven for some sites) and by taking multiple samples, variables like solar/sensor view (after correction) and atmosphere are sufficiently randomized. Chander et al. [11)] provides an analysis of what can be achieved for a range of sensor types using Landsat and MODIS as examples. This study concludes that for all geometric/positioning sources of error in the cross-comparison process, the uncertainties are <~0.3% confirming the analysis summarized below in Table 6 by Gorono et al [12)], in the worst case for one spectral band a miss-registration error (lack of knowledge) of three pixels contributed <0.5% uncertainty. The only significant source of uncertainty in their analysis stems from the prospect of unknown spectral change in the sensors band pass due to ageing of the filter. In their analysis, they assumed relatively large shifts of ±5 nm, which in turn led to uncertainties of up to 2.4%. Such shifts may occur in practice on any sensor. However, they would be considered relatively extreme for a well-designed sensor and consequently such potential effects are in general not accounted for in the uncertainty budgets of sensors like Sentinel-2. It could therefore be misleading to consider this the limiting aspect of the uncertainty achievable in using such test-sites. Therefore, at present, this potential source of error is not included in the uncertainty budget attributed to the use of TRUTHS for cross-calibration. It may be, however, that cross-calibration with TRUTHS over a range of terrain types, with different spectral properties, may be able to assess if such changes are occurring, but this analysis has not as yet been undertaken.

TRUTHS will use a similar philosophy for the PICS site characterization but will calibrate to an absolute reference, so determining the bias of each sensor from the actual reflectance, resulting in reliable harmonization of the data record from multiple sensors. This SI-traceable anchoring of the true reference reflectance can not only be applied to current sensors but also to historical and future PICS site companions, long after the TRUTHS sensor mission life. The agility of TRUTHS would also allow the surface/ToA BRF of the PICS sites to be evaluated leading to improved corrections of seasonal variability.

The requirement drivers from this activity do not exceed that given in Table 2 as the overall uncertainty will be limited by the site BRF (Bidirectional Reflectance Factor) knowledge and atmospheric correction contribution i.e., the knowledge of the atmospheric state at the time of both the reference and target sensor overpass.

Calibration of sensors — SNO (Simultaneous Nadir Observations) at PICS (Pseudo-Invariant Calibration Sites)

An enhancement to purely characterising the PICS sites comes from simultaneous nadir observations (SNO) viewing the nominally spatially uniform site. Although the discussion here focusses on a PICS site, the methodology is equally valid when using a deep convective cloud, a snowfield, or other site of sufficient size and characteristics for the field of view of the sensor under test and that of TRUTHS. The orbit and agility of TRUTHS provides additional opportunity for coincident (<30 min) view-matched sampling of a range of target sites, greatly reducing the number of samples needed to effectively randomise the unmatched residuals of associated contributors; with only a few matched overpasses needed to improve the absolute accuracy of a specific sensor (subject to respective SNR values), achievable on a relatively short timescale. Figure 2 shows the matched SNO between Sentinel- 2 and TRUTHS assuming a nominal Swath of 50 km for a time window of 30 min and for 1 year. The exact number of crossovers (pixel/scene) over good quality targets and/or PICS needs to be calculated. The exact number of crossovers (pixel/scene) over good quality targets and/or PICS needs to be calculated.

TRUTHS_AutoF

Figure 2: Multi-Spectral Imager (MSI) of Sentinel-2 and TRUTHS simulated overpasses for a one-year period with time interval of 30 min at nadir (image credit: ESA)

Table 6 provides the uncertainty budget from a study analyzing the radiometric calibration upgrade of Sentinel-2 achievable using the Libya 4 PICS and TRUTHS system performance (Table 2) as a calibration reference. The details of the underpinning analysis can be found in [Ref.12)]. This analysis accounts for spatial and spectral mismatch, solar and view angle variations, as well as atmospheric effects. The analysis concludes that for most bands a single coincident overpass of the two satellites enables a Sentinel-2 Multi-Spectral Imager (MSI) uncertainty upgrade in radiometric performance to ~0.5% (k=1). This assumes, as indicated in the MSI uncertainty budget, that the dominant uncertainty component is ‘in-flight, radiometric calibration.

Similar analysis can be done for other sensors. Of course, to extract optimum value from such an in-flight calibration strategy there needs to be a good level of pre-flight characterization of the sensor under test as this approach primarily only addresses radiometric gain/bias. However, through use of multiple sites it can also assess linearity, and some aspects of spectral performance although not necessarily fully correct for any errors that may be observed. This is not really a limitation as it reflects current practices—and addresses the principle uncertainty component listed in most sensor budgets. It is however true that with a reference sensor of the quality of TRUTHS in-orbit, future sensors may take account of this and ensure that design and pre-flight characterization will be optimized to fully utilize the benefits.

A summary of the impact of TRUTHS’ key performance parameters on the cross-calibration of a sensor like Sentinel-2 is given in Table 6 and below is a discussion on considerations needed for the specification of TRUTHS (Tables 2 and 7).

Source of Uncertainty

Resultant Uncertainty on Sentinel-2 TOA Reflectance % (k = 1)

Comments

Single Overpass

Mean of Multiple Overpasses

Best S2 Band

Worst S2 Band

Best S2 Band

Worst S2 Band

Spectral Resolution/
Accuracy of TRUTHS

<0.1*

0.1–0.6 *

<0.1 *

0.1–0.6 *

For all sites and interpolations
studied. Worst cases are B1, B5
and B6 but large variability
depending on site, interpolation
and spectral binning pattern.

Spectral Knowledge of TRUTHS

<0.1*

~0.2*

<0.1*

~0.2 *

For a 0.2 nm k = 1 central
wavelength and bandwidth
knowledge. Worst S2 bands are
B6 and B1

Non-Spatial Co-Alignment of
TRUTHS with Sensor under Test
(site A)

<0.12

0.5

<0.1

<0.1

For a single overpass over La
Crau site with a positioning
knowledge of 32 x 44 m2. Best
band is B1 and worst one is B12.

Non-Spatial Co-Alignment of
TRUTHS with Sensor under Test
(site B)

<0.1*

<0.1*

<0.1*

<0.1*

For a single overpass over Libya-4
site with a positioning knowledge
of 50 x 50 m2

Error due to 30-min Difference in
Overpass Times: Solar/View
Angle: Atmosphere

<0.1*

<0.1*

<0.1*

<0.2*

Result of Aerosol path difference
between 6SV1 and MODTRAN v5
calculated for mean of annual
Aerosol optical thickness. Worst
case is B1.

Error due to 30-min Difference in
overpass Times: Solar/View Angle:
Atmosphere (Some Knowledge)

<0.1*

<0.1*

<0.1*

<<0.1*

Assume mean of annual atmospheric
variations for Libya 4 test site: Requires
knowledge of atmosphere around time of
overpass. Can be reduced further by
correction of time difference

Error due to 30-min Difference in
overpass Time for Full Range of
Potential Annual Atmospheric
Properties (No Knowledge Upper Limit)

0.3

2

<<0.1*

<<0.1*

Equivalent to no knowledge of
atmosphere parameters but can be
reduced by knowledge of time
difference. Worst case in the SWIR bands

Error due to Lack of Knowledge
of Surface BRF for 30-min
Difference in Overpass Time

0.2–0.4*

0.2–0.4*

<0.1*

<0.1*

Model would improve with experimental
data from TRUTHS and also with multiple
measurements effect would tend to zero.
Impact at TOA is assumed half for B1.

Total Achievable Uncertainty due
to Cross-Comparison Process for
Anticipated Level of Knowledge
& Conditions

0.4–0.5

0.4–0.7

0.2

0.3–0.7

Reduction in uncertainty due to multiple
overpasses would include multiple sites
and does not take account of correlations
(uncertainty sources included in
total are marked with an asterisk)

Table 6: Uncertainty budget (k = 1) achievable for the upgrade of the radiometric performance of Sentinel-2 using TRUTHS as a reference sensor and the Libya-4 PICS. The contributions marked with an asterisk are included in the total at the bottom of the table. Some contributions are calculated based on a potential range of conditions and only one variant is used in the total.

TRUTHS specifications resulting from reference calibration using test-sites

The following discussion summarizes the mission requirements resulting from the needs of the reference calibration objective and where appropriate contrasts them with those needed for climate.

Spectral range—the spectral range should cover that of the sensors being cross-calibrated. This is less strict than the Space climate observatory spectral requirement and could be limited to ~380/400 to 2400 nm.

Spectral Bandwidth—the Earth-reflected radiance spectral resolution is driven by the need to match the spectral resolution of the sensors under test with an acceptable residual uncertainty in the spectral matching. The spectral bandwidth (spectral sampling interval is half the bandwidth) requirement of 8 nm <1000 nm and 16 nm >1000 nm allows this spectral matching for the band type sensors (non-spectrometer) and is of a similar magnitude to the new generation of hyperspectral imaging spectrometers. This is consummate with those needed for cloud processes identified for the space climate observatory requirement.

Radiometric accuracy—the reference sensor radiometric accuracy should be considered alongside the other uncertainties in matching the inter-calibration signal. These other considerations are typically of the 0.5% (k = 2) magnitude. The reference sensor radiometric uncertainty is the main budget contributor for values above 0.5% (k = 2) but values ≤1% (k = 2) are acceptable for most sensors studied. The SCO requirement is the driving requirement on the radiometric accuracy.

Signal to noise ratio (SNR)—the SNR requirements is convolved with other factors including the sampling regime, number of samples, and the spectral and spatial binning needed to match the sensor under-test. Generally, the SNR requirement is related to the GIFOV, brightness of target, and/or number of samples and radiometric accuracy requirements ~300 in the visible reflects the goal uncertainty so that it is not limiting for a direct instantaneous observation. For specific ocean color applications, this requirement rises to >1000 and ideally 2000 in the blue, but as the observational pixel size for most Ocean Color applications is >1 km, this higher SNR can be achieved with appropriate spectral and spatial binning and an increased dwell time attained from the platform agility. As a threshold, values commensurate with those of other sensors e.g., Sentinel 2, accounting for spectral bandwidth differences etc., are chosen so that SNR of TRUTHS does not limit the calibration or corresponding application. This requirement is more demanding than that of the space climate observatory and drives the mission design. However, achieving at least threshold should not present significant challenges.

Ground instantaneous field of view (GIFOV)—the cross-calibration GIFOV is driven by the need to match the spatial resolution of the sensors under calibration, together with optimizing the use of the L1 data for land surface applications. The goal GIFOV requirement is 50 m, however there is some advantage of reducing this to 30 m (match other hyperspectral sensors) if detectors arrays do not compromise the overall swath significantly. This requirement is stricter for GIFOV than the space climate observatory.

Orbit—A precessing asynchronous orbit of 90º facilitates a maximal number of SNO with other sensors for reference calibration. It should be noted that a high number of SNO’ (for the reference calibration application) can also be achieved with other asynchronous orbits. The orbit altitude ideally needs to be >100 km separated from the target sensor, ideally >~200 km, to allow adequate time at the orbit crossing to match the views and increase overlap time for reference calibration. Sentinel-2/3 are at ~800 km altitude, with Landsat-8 around 700 km altitude. Too low an orbit increases drag and fuel lifetime and radiation damage. The baseline has at this stage been chosen to be optimal as a precessing polar orbit (90º) at a height of 609 km with a repeat time of 61 days.

Pointing—The pointing requirement for cross-calibration application is to match the partner sensor FOV, with an accuracy of ~<0.1º, and knowledge typically <2 x the GIFOV, so 100 m (≤1 arcmin). However, this is no more demanding than the navigation pointing knowledge. For special sites of interest, there is the ability to motion compensate and take multiple angle views and also take account of ground control points.

Observational plan—from a mission perspective, all that is additional in terms of specification is that regular observation of key CEOS test-sites should be built into the acquisition program. Calibration of the instrumented sites allows these sites to provide improved calibrations on timescales independent of intervals between TRUTHS overpass and that of the sensor under calibration. TRUTHS will target these CEOS endorsed sites providing high accuracy TOA spectrally, spatially, and angularly resolved radiances to maximize their potential usage and ensure SI traceability.


Calibration of Sensors—Global SNOs

An alternative approach to calibration of sensors using test-sites, is to use the matched, SNO overpasses over a wide variety of surface (and cloud-top) types. This strategy will provide many more matchups over a shorter time, spanning the full dynamic range of signal levels. The uncertainty budget will mirror that given in Table 6, with a slightly increased uncertainty for the BRF terms over less stable surfaces, in-homogeneity, and potentially the selection of the ‘no knowledge’ upper limit assumption on atmospheric correction variation within the temporal mismatch. However, as this approach takes advantage of the increase in matchups afforded by the increase in coincident occurrences, the mean of multiple overpasses budget is the valid one in this scenario.

Calibration of Ocean Color Sensors

The WMO and GCOS requirement for water leaving radiance (ocean color) is ‘better than 5% (k = 2)’. Although there is some variation with wavelength and water type, in the blue-green, this translates to an absolute radiometric accuracy at ToA of ~0.5% (k = 2). This scaling results from the water leaving signal being only 10% of the total observed by the satellite, the dominant signal coming from the atmosphere. TRUTHS incorporates this requirement in Table 2, although it should be noted that with threshold values this may only be achieved through reference calibration of other sensors, although with goal values for SNR this may also be globally achievable by TRUTHS, but the temporal coverage may not be adequate for some applications. For existing sensors, this resultant high accuracy is only achievable in an indirect manner through a process known as ‘system vicarious calibration’ using ocean buoys fitted with well-calibrated radiometers at very specific locations namely, MOBY and Boussole. TRUTHS enables sensor performance to be calibrated directly and algorithms to be tuned over a range of locations and water types. The TRUTHS SNR and GIFOV also allow analysis in coastal zones and inland waters that have previously not been readily accessible.

Calibration for GHG (Greenhouse Gas) Source and Sink Monitoring

Although the spectral resolution of TRUTHS is not sufficient to directly derive gaseous-phase products, except for relatively large-scale emitters, the transfer of radiometric accuracy through cross-calibration does provide some significant benefit for the GHG community. To meet the goals of the Paris Accord of 2015, an international GHG virtual constellation is required, which will fundamentally require harmonization of the different sensors, which must start from the level 1 radiometry. For example, NASA/JPL ( Jet Propulsion Laboratory) have performed a series of studies to characterize the impact of uncertainties in the absolute radiometric calibration on the XCO2 retrievals from the Orbiting Carbon Observatory-2 (OCO-2) sensor. The study showed the retrieval to be most sensitive to the absolute radiometric accuracy in the O2 A-band channel. In that channel, a 1% error in the absolute radiometric calibration introduces a ~0.1 ppm (0.025%) error in XCO2 for an aerosol optical depth of 0.1 and a surface albedo of ~0.1, with the error increasing with increasing aerosol optical depth and surface albedo values. Principally, absolute radiometric errors can therefore manifest as spatially dependent biases while also contributing to the random error in the XCO2 soundings. Similar impacts would be expected in other GHG missions, with the value of a unified absolute calibration across missions best demonstrated in any international effort to inter-operate sensors as part of a future international constellation.

Lunar Calibration

The moon is a unique calibration test-site. As an extra-terrestrial site (with no atmosphere to characterize between sensor and target) it has been shown to be radiometrically stable, after taking account of libration etc., allowing the stability of a satellite sensor to be monitored in orbit and inter-compared.

The dominant work in this field to date has been carried out by the United States Geological Survey (USGS) and its program on the Robotic Lunar Observatory (ROLO) [13)]. This has now been incorporated into an international program of the WMO GSICS with the creation of GIRO (GSICS Implementation of ROLO) as an international reference model. However, the current absolute radiometric accuracy of the moon ~1% in terms of relative accuracy, but 5–10% in absolute radiometric terms [Ref.10)], is not sufficient to allow it to be used as an absolute standard at climate quality levels. The requirement is to reduce the absolute uncertainty to ~<1% to allow the moon to be used a long-term validation site.

TRUTHS will radiometrically calibrate the moon allowing it to be used as a true SI transfer standard. This only requires that the platform regularly views the moon with its HIS at a range of libration conditions to build up a correction database for the GIRO model. This early achievement from the mission, the L1 lunar spectral irradiance data product, would allow historic missions to be re-calibrated and Fundamental Climate Data Records (FCDRs) to be extended backwards in time with greater accuracy, since many sensors have been observing the moon.

Calibration to Support Atmospheric Correction

For most geophysical applications, knowledge of the state of the atmospheric column—aerosols and water vapor content in particular—are critical to enable high accuracy retrievals over land and oceans, as well as for cross-calibration. TRUTHS will have the additional capability through its hyperspectral measurements to determine Aerosol optical depth and water vapor in a similar but enhanced manner to OLCI through its additional SWIR bands, and for dedicated targets the agile platform can also allow multiple angle observations to add additional constraints. This will not only provide some measure of the atmosphere for direct L1 dataset applications but will subsequently allow existing atmospheric codes to be tested, constrained, and improved, under a range of conditions. In addition, it will facilitate testing of other aerosol measuring networks for example the sensors of AERONET itself can be constrained by the improved accuracy of TRUTHS. It should also be noted that the SI-traceable ground measurements of RadCalNet, [Ref.6)] linked to the SI-traceable ToA measurements of TRUTHS, allow rigorous validation of atmospheric correction over such sites.

Vegetation Indices

The TRUTHS spectral range covers a great number of vegetation indices at a spectral resolution capable of providing direct products. However, the orbit period and coverage would limit the usefulness of any such product to an instantaneous map or long-term monitoring. The continuous hyperspectral coverage and high accuracy would however be useful in algorithm development and as a testbed for other missions.

The benefit is the absolute cross-calibration and the magnitude of the decadal-scale climate change signals expected in these indices. For example, a typical normalized difference vegetation index (NDVI) value of 0.3, against which a 1% calibration accuracy may not seem significant. However, the change in NDVI might be less than 0.005 per year over 10 years i.e., less than 0.05 in a decade. Absolute uncertainties of the order of 1% are a significant contribution over these longer timeframes. One of the limiting factors in vegetation indices products are uncertainties in the atmospheric correction, and knowledge of the state of the atmosphere used to provide bottom of the atmosphere (BoA) radiances.




Mission Architecture

This section briefly describes the key components of the mission architecture, which have evolved and simplified since the mission was first conceived in 2001 [14), 15)].

Mission Requirement

Parameter

Spectral coverage (Earth and Sun)
(spectrometer)

320–2400 nm (potential relaxation of spectral range if technology drivers are too great but would limit
value at shorter band for solar applications) with continuous coverage

Radiometric Accuracy (spectrometer)

Spectrally integrated reflectance product - 0.3% (k = 2) on the reflectance of 0.3

Radiometric Accuracy

Spectrally resolved reflectance product - 0.3% for the key spectral regions, extending to 0.5–1.0% in
less sensitive or energetically low-contributing spectral positions

Radiometric Accuracy (total combined
uncertainty)

Spectrally integrated (0.32 to 2.4 µm) Earth reflected solar radiance product 0.3% (k = 2)

Radiometric Accuracy

Spectrally resolved (0.32 to 2.4 µm) solar irradiance 0.3% (k = 2)

Radiometric Accuracy (TSI)

0.2 µm to 30 µm integrated total irradiance 0.02% accuracy (k = 2)

Spectral Resolved Spectral Range

320 to 2400 nm continuous

Spectral Resolution

For reference calibration need to match customer sensor: 8 nm bandwidth ~4 nm steps) Can be relaxed to
25 nm for some non-critical wavelength regions.

Signal to Noise Ratio

Adequate to meet accuracy levels in products with appropriate averaging. Reference calibration and level 2
retrievals require >100 and ideally > 300 for at least visible spectral region at highest resolution

Instantaneous Spatial Resolution (IFOV)

< 250 m. ideally 30–50 m

Polarization Sensitivity

0.5% (k = 2) for λ<1000 nm
0.75% (k = 2) for λ>1000 nm (Although for many applications these can be relaxed. They are primarily to
support off-axis reference calibrations of other sensors and associated atmospheric corrections).

Orbit

polar 90º inclination with altitude of 609 km (±200 m)

Reference inter comparison samples
(large FOV climate focused sensors)

2000 samples (assuming SNR <50 will reduce with improved SNR) within 1º and ±5 min.
(this assumes non selected targets for calibration). For higher GIFOV sensors and higher
SNR using SNO this value can reduce significantly to <10

Continuity of operation

Sufficiently continuous to not increase the sampling bias error contribution to represent
a significant uncertainty contribution.

Revisit

As frequent as possible but <61-day revisit as determined by the 90º polar orbit.

Coverage

Global nadir spectral radiances

Sampling time

Continuous during sunlit phase of the Earth

Swath

50 to 100 km minimum

Quantization

14 bit

Pointing Accuracy

<1 km

Pointing Knowledge

<3 x GIFOV (<150 m) Goal of 50 m

Table 7: TRUTHS mission requirements

The mission requirements in Table 7 are achieved through:

a) The payload instrument: A hyperspectral imaging spectrometer (HIS), which can be used to measure the Earth, Sun, and Moon.

b) The radiometric calibration of that HIS directly, regularly, and traceably to an on-board SI primary standard.

c) The choice of an orbit that supports climate benchmark measurements and increases the number of simultaneous cross-calibrations.

d) The use of a small, agile platform.




Payload overview (HSI, CSAR)

The main observational instrument in TRUTHS is a hyperspectral imaging spectrometer (HIS), with continuous spectral sampling extending across the UV-VIS-SWIR (320 nm to 2400 nm) and 50–100 m GIFOV, not dissimilar in headline capability to the DLR EnMap, NASA Hyperion and HyspIRI, ASI PRISMA or the future CHIME (Copernicus Hyperspectral Imaging Mission for the Environment) mission. Although as a baseline, TRUTHS’ HIS is able to employ a much smaller telescope aperture of ~50 mm diameter compared to the 200 mm aperture required by EnMap, as TRUTHS is not seeking to address all the same goals as these sensors, for instance high instantaneous SNR at 30 m GIFOV.

The disruptive innovation of TRUTHS stems from incorporating a space-adapted primary SI-standard onto the satellite bus and its use with a novel on-board calibration system. This mimics the method used terrestrially at NMIs, allowing TRUTHS to provide hyperspectral data immune from drift or biases for the lifetime of the mission. The method, which will be described below, enables TRUTHS to meet the performance requirements summarised in Tables 2 and 7, which are needed to address the mission objectives and science applications outlined.

Table 2 shows the L1 product mission requirements that need to be achieved from the TRUTHS payload. The goal uncertainties specified, whilst challenging and unprecedented, are achievable using the disruptive on-board calibration system. The goal values for all the parameters would ensure that maximum science benefit is achieved, however some relaxation can be allowed towards a threshold value (close to that of the best current/planned sensors) and still achieve significant value, particularly from its cross-calibration function of the mission. However, from a climate perspective, the decrease in science benefit is non-linear in relation to uncertainty relaxation.

A summary of the payload instruments is provided below together with an overview of the on-board calibration method. It should be noted that the relatively unique asynchronous orbit of TRUTHS, whilst providing many observational benefits presents significant additional challenge to both the spacecraft and payload. Varying thermal and solar viewing (power) conditions add complexity to the mission. Thus, as part of the pre-flight calibration/characterization and during the commissioning phase, calibrations of the HIS will be performed under a variety of simulated/real orbit conditions to assess any variances due to inadequate thermal stabilities.


HIS (Hyperspectral Imaging Spectrometer)

The primary measurand of TRUTHS is spectrally resolved incoming and Earth-reflected solar radiation. The spectral range, resolution, and accuracy are key boundary conditions, which ultimately limit the range of applications of the dataset.

The HIS instrument, through a novel approach, can be used both to image the Earth, measuring its spectral radiance, the Moon, measuring its spectral irradiance, and also to measure incident solar spectral irradiance. This concept not only minimizes the instrumentation needed, but also allows us to derive ToA reflectance with the added confidence of exact spectral matching, through use of a common spectrometer. It also has the advantage that solar features can provide additional anchor points for spectral calibration. As an illustration of the viability the details of one indicative implementation of the HIS, with its specification, is given in Table 8.

Designs for the HIS have been produced by several organizations and Figure 3 shows a version from SSTL (UK). However, this is indicative and not necessarily the final design that will be implemented following the Phase AB1 studies.

Parameter

Value

Comment

Spectral bands

320 nm–400 nm
400 nm–2450 nm

Assumes use of a wide spectral band HgCdTe detector and a separate
Si detector through a common telescope with a prism based spectrometer

Swath

100 km

Corresponding GIFOV will depend on choice of detector (number of
pixels) 2000 and 3000 options are now readily available

Spatial resolution

50–100 m GIFOV

Depends on detector and SNR

Spectral resolution

4 nm < 1000 nm
8 nm > 1000 nm

UV native spectral resolution ~1 nm, with bandwidth
typically 2X this value

SNR

>150

Climate benchmarking only require ~50 due to zonal averaging but
higher values required for cross-calibration and secondary applications

Detector technology

UV: Si CMOS
VIS-SWIR: MCT

Teledyne e2v CIS115/CIS120 (250K)
Teledyne e2v CHROMA-D 1/2/3k x 512 (135K)

Imager configuration

Refractive (prism)

 

Telescope

1 telecentric 5 Al mirror
telescope

One common entrance pupil for calibration

Entrance pupil

45 mm diameter

 

Dwell Period (@50 m GIFOV)

7.25 ms

 

Polarization control

Polarization scrambler

With telescope mirror configuration compensation

Spectral image slit

At spectrometer focal plane

Potentially dual slit (one for each detector) (UV can
be larger GIFOV and co-registration not as critical)

Table 8: Indicative hyperspectral imaging spectrometer (HIS) specifications based on an indicative implementation

TRUTHS_AutoE

Figure 3: HIS on optical bench. Two views of an initial Surrey Satellite Technology Ltd (SSTL) concept design, which is subject to change as the mission undergoes detailed design during a formal Phase AB1 (image credit: SSTL)


CSAR (Cryogenic Solar Absolute Radiometer)

The heart of the calibration system is the primary SI standard, the cryogenic solar absolute radiometer (CSAR). CSAR is a flight version of the primary standard cryogenic, adopted by most NMIs (National Metrology Institutes) worldwide and recommended as the means to achieve SI traceability [16)]. The cryogenic radiometer is an extension of the ESR (Electrical Substitution Radiometer) concept, typically cooled terrestrially to <~30K reducing uncertainty levels to <0.01 % (k = 2). Due to constraints with availability of space coolers with adequate performance CSAR will operate at a slightly higher temperature <60 K (higher temperature increases the time constant and reduces sensitivity a little), when flown it will be the first cryogenic radiometer, and consequentially optical primary SI radiometric standard flown in space and is a key element of the calibration system of TRUTHS.

Most NMIs have adopted the cryogenic radiometer as the primary standard for radiometric measurements [17) 18) 19)]. The cryogenic radiometer is an extension of the concepts of the ESR, which were independently developed by the meteorologist Ångström (1893) [20)] and the metrologist, Kurlbaum (1894) [21)] and are in essence the basis of instruments currently flying in space measuring TSI, e.g., PMO6 on SOHO. Cooling the technology to cryogenic temperatures (originally <30 K) reduces uncertainty levels to <0.01 % (k = 2) as first shown by NPL in the 1980s [22) 23)]. For TRUTHS, CSAR v2 will operate at <60 K and provide traceability of Earth spectral radiance measurements to SI to an absolute accuracy of <0.3 % (k = 2). In addition to serving as a primary standard for radiance and irradiance, CSAR will also provide science measurements in its own right, TSI with an accuracy of 0.02 % (k = 2), a significant improvement over most existing ambient temperature radiometers.

Because CSAR is both critical to the TRUTHS mission's ability to achieve its aims and the key novel aspect of TRUTHS, the instrument was first prototyped (CSAR_v1) in 2010 and has successfully undergone both laboratory and field tests. A second version of the instrument (CSAR_v2), an evolved and simplified design, making direct use of an upgraded Airbus space cooler (currently flying on Sentinel-3) was built and tested together with a breadboard of the full OBCS (On-Board Calibration System) in 2016. Note that because of the cryogenic components, all cryogenic radiometers are designed for vacuum operation and the CSAR_V1/2 can be considered TRL 5/6.

TRUTHS_AutoD

Figure 4: Operating principle of electrical substitution radiometers (image credit: TRUTHS collaboration)

A cryogenic radiometer is an ESR that is cooled down to cryogenic temperatures. Figure 4 illustrates the operation principle of ESRs. A cavity that is connected to a heat sink via a thermally weak heat link is first heated up by incoming optical radiation (Figure 4, left hand side); subsequently,the radiation is blocked and the cavity is electrically heated to the same temperature (Figure 4, right hand side). This procedure allows the determination of radiant power through the measurement of electrical power applied to the heater. The thermometer serves only as a null detector and thus it is only short-term stability and resolution that are factors that need to be considered. Figure 5 illustrates how the radiometer and cooler integrate, and the link between the compressor and cold head is flexible, allowing their respective locations and orientations to be independently selected.

TRUTHS_AutoC

Figure 5: Schematic diagram showing the overall layout for the TRUTHS cryogenic solar absolute radiometer (CSAR), image credit: TRUTHS collaboration

The main reason for cooling the radiometer is that the cavity can be larger than one at ambient temperature, while keeping the natural time constant similar and maintaining an adequate sensitivity. This is due to the much-reduced heat capacity of the cavity material (copper) at low temperatures. A physically larger cavity has much higher absorptivity, with less sensitivity to any degradation of the black surface coating of the cavity. Being able to make the cavity larger also means that for the TSI measurements, the larger FOV limiting aperture can be placed in front of the cavity instead of at the front of the instrument; with significantly reduced bias due to stray light caused by interaction of the light with the front aperture. Other reasons for operating the detector at low temperatures are reduced background radiation and elimination of bias in the electrical substitution by using superconducting leads to the electrical heater.

A CSAR-V1, built in 2010 and tested as a fully working ‘engineering model’ for TRUTHS, currently operates in Davos as a WMO world reference for terrestrial TSI measurements. A more optimized (low mass) flight representational CSAR-V2, fully coupled to a flight demonstrated space cooler, has more recently been built and tested with an Airbus high-power Stirling cooler (HPSC) space cooler, Figure 6.

TRUTHS_AutoB

Figure 6: Photographs of the assembly of CSAR_V2 showing, from left to right, (a) two cavities mounted on the temperature reference block, (b) the radiometer head coupled to the high-power Stirling cooler (HPSC) and mounted inside the cryostat and terrestrial vacuum can (c) close up of cavities showing thermal link to the HPSC (image credit: TRUTHS collaboration)

One of the principles underpinning CSAR’s ability to establish SI-traceability in-flight is that the only optical interface that is subject to potential change is a blackened cavity. The use of a carbon nanotube black coating with resultant absorptance of >0.99995 makes it inherently insensitive to change. This is further enhanced through the inclusion of three cavities for redundancy and to limit any exposure to sunlight for at least one cavity to minimize any ageing effects. The measurement electronics of CSAR are based on modified versions of existing flight systems used for TSI measurements and e.g., the recent CLARA on NorSAT-1. Earlier versions of the electronics have shown to be stable to the uncertainties required. Independently, Airbus have performed a reliability study (five- and seven-year timeframes) on key electronic components and indicated that existing qualified components meet the requirement even for the extended lifetime.




On-Board Calibration System (OBCS) Overview

Central to the TRUTHS philosophy is the calibration system which puts SI traceability into orbit. The OBCS mimics the steps used by NMIs (National Metrology Institutes) around the world to transfer calibration traceability from the SI defining power measurement (the cryogenic radiometer) to a full spectrally resolved radiance calibration of an instrument, spectrometer/radiometer, etc. The calibration system designed for TRUTHS has been simplified relative to those used at NMIs to minimize the number of components, and in particular, the number of moving parts compared to measurements in the laboratory and also to reflect the use, where possible, of heritage space components or heritage constituent technologies (Figure 7).

The calibration of the HIS for Earth radiance and SSI measurements is performed, traceably to the CSAR, using a system that consists of a transfer radiometer (TR), a small number of (~8–10) low power laser diodes (LDs), an integrating sphere (IS), and a diffuser wheel with two diffusers (D1, D2) for redundancy. Calibration generally takes place during the Earth shadow part of the orbit allowing the systems to be well-protected from solar and other radiation damage. However, during the commissioning phase at least, evaluations of the calibration process will be undertaken at various parts of the orbit including sun-lit and for nominal pointing configurations of the platform.

The full OBCS together with the CSAR v2, shown in Figure 7, has been fully demonstrated under vacuum and is ready for implementation and can largely be considered as TRL 5/6. A lifetime analysis of the full calibration system has been carried out by Airbus resulting in a value of 0.97 for a five-year mission.

TRUTHS_AutoA

Figure 7: Computer-aided design drawing of laboratory breadboard of the TRUTHS OBCS together with a photograph of its engineering realisation before testing in a vacuum tank (image credit: TRUTHS collaboration)

On-Board Calibration Procedure

Figure 8 describes the calibration sequence and a video representation can be found here [24)]. This is performed with just two mechanisms within the calibration system. A diffuser wheel, common on heritage sensors, and a rotating laser arm are used to distribute the laser power into three of the calibration sub-systems.

Here, we discuss, in outline, the calibration steps. Note that the diagrams here are schematic, and in the actual flight implementation, for example, additional turning mirrors may be used, which do not affect the overall calibration principle. Similarly, the exact design of subsystems such as transfer radiometer and laser illumination systems may also differ in detail. It is also likely that, without adding any additional rotational mechanisms, further redundancy can be achieved for all of the critical subsystems.

An example layout used as the breadboard is shown in Figure 7 and in a more cartoon style in Figure 9. The primary calibration is performed at a small number of wavelengths corresponding to the chosen LDs. These LDs can illuminate either of two (identical) cavities of the CSAR (providing redundancy), the TR, and the IS (which is used as part of the illumination of the HIS during calibration). The LDs illuminate each instrument/sub-system in turn using an illumination system based on a rotating pair of rooftop prisms serving as mirrors, with the central axis (mirror) being fed by laser radiation from a common optical rod conjoiner linking LDs via optical fiber (Figure 9). An alternative realization may involve the LDs or at least coupled fibers attached directly to the perimeter of the rotation wheel, avoiding the prism mirrors. The optical fiber in either case is wound around the compressor of the cryocooler of CSAR where the micro-vibrations helps to reduce the effect of speckle.

The monochromatic radiation from the LDs illuminates the full aperture of HIS in a Lambertian manner via a flat plate diffuser in a similar manner to existing on-board systems, the difference being the use of monochromatic LD radiation rather than the Sun. The radiance of the diffuser can be measured directly inflight by the on-board calibrated TR. The responsivity at all other intermediate wavelengths is obtained using a white light source e.g., incandescent lamp, which is radiometrically anchored at the LD wavelengths. The following steps scope the calibration procedure, which mimics that carried out terrestrially. It should also be noted that in addition to radiometric calibration the use of LDs allows wavelength accuracy of HIS to be checked and also of particular interest, stray-light. The latter, while not having enough LDs to provide a full calibration matrix as can be done on ground using tuneable lasers, does provide sufficient spectral sampling to allow the pre-flight correction matrix to be at least monitored in flight.

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Figure 8: The TRUTHS calibration system calibration sequence (TRUTHS collaboration)

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Figure 9: LD (Laser Diode) schematic illumination system (TRUTHS collaboration)


Step 1: Calibration of TR (Transfer Radiometer) against CSAR using LDs (Laser Diodes)

The optical power of the temperature-and-current-stabilized LD is measured absolutely by the CSAR (Figure 10a) and the beam underfilling the CSAR irradiance defining aperture and then used to calibrate the response of the TR to this now measured power level by rotation of the prism assembly (Figure 10b). The TR in this illustration is a small integrating sphere with integral Si and InGaAs semiconductor photodiodes viewing its internal wall. The integrating sphere provides a convenient means to reduce any alignment or source non-uniformity issues (although alternative methods to achieve the same goal can be envisaged and may in practise be utilized). It has two field-of-view (FOV) defining apertures (radiance), but for this phase of the calibration, they are underfilled. This step is repeated for each of the LD wavelengths in turn. The calibration process requires the LD output to be of known wavelength (controlled with an etalon) and stable in intensity (<0.1%) during the transfer from the CSAR to TR (about 1 min, which is easily achieved). Individual wavelength calibrations can take place sequentially or on different orbits. However, it is probably likely to be optimum to perform the full calibration sequence step 1 and 2 for each wavelength individually.

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Figure 10: Schematic of step 1. The LDs illuminate (underfill) first (a) the CSAR cavity and then (b) the transfer radiometer (TR), by rotating the mirror assembly (image credit: TRUTHS collaboration)

Step 2: HIS (Earth Radiance view) calibrated against the TR at each LD wavelength (radiance mode)

The radiance responsivity of the HIS is determined by comparison with the radiance responsivity of the TR using the LDs. In this step, the LD source is allowed to expand and then collimated to create a uniform illumination on a flat plate Lambertian diffuser, using an IS and mirrors (for alignment purposes). The IS not only helps to pre-condition the LD radiation, removing effects of non-uniformity, but also reduces significantly the effect of speckle, from both spatial and temporal coherence. The diffuser can move in and out of the FOV of the HIS by rotation of its mounting plate shown in Figure 11 with a second redundant diffuser and also mirror. When illuminated, normal to the diffuser as shown (Figure 11), the TR and HIS simultaneously view the diffuser at reciprocal angles.

In this step, the TR measures the absolute radiance of the LD-illuminated diffuser; its absolute radiance responsivity having been determined from its power responsivity (step 1) and knowledge of the areas of the two FOV-defining apertures, which are never directly exposed to the space environment. Note that, because the TR measures the radiance of the diffuser directly, the transmittance of the IS and reflectance of any turning mirrors (optics) do not need to be known. It is advantageous to limit the FOV differences between the TR and the HIS, but such differences and their small effect and can be characterized pre-flight and therefore an exact match is not required.

Thus, the HIS is calibrated for radiance responsivity at the LD wavelengths. Note also that by comparing the TR signals in Step 1 and Step 2 (assuming a stable laser source between these two measurements) the TR also directly calibrates the throughput of the IS, mirrors, and diffuser at these wavelengths. This provides an irradiance responsivity calibration of the system comprising the IS (underfilling an irradiance defining aperture on the entrance port), mirrors, diffuser, and HIS (this allows it to become the SSI measuring system, when the aperture is overfilled by solar radiation, see step 4).

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Figure 11: LD illuminates the diffuser, via the IS (Integrating Sphere), and this is viewed by the HIS and IS (image credit: TRUTHS collaboration)

Step 3: HIS (Earth radiance view) calibrated at intermediate wavelengths with a lamp.

An incandescent lamp (with a smooth spectral output) illuminates the IS and consequently the diffuser and is viewed by the HIS in a similar manner to the LDs. At the end of step 2, the HIS has been calibrated at the wavelengths of the LDs for absolute radiance responsivity. It is now only necessary to interpolate between these laser wavelengths. This will be achieved using a white light source/lamp with a broadband, smooth spectral output. Although the lamp will change during operation, it will do so in a spectrally smooth manner. The absolute level and the basic spectral shape are determined at the LD wavelengths in step 2; this step (Figure 12) is primarily used for interpolation although at the extremes of the wavelength range of HIS, beyond the final anchoring wavelengths of the LDs the spectral shape is extrapolated. There are many examples of such lamps being used for space calibration, but here we only need functionality, short-term (< 10 s) stability, and of course, spectrally smooth output.

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Figure 12: Lamp illuminates the diffuser via the integrating sphere and mirrors to provide calibration of the HIS at intermediate wavelengths (image credit: TRUTHS collaboration)

The HIS can be considered calibrated for making spectral radiance measurements of the Earth. Similarly, the system comprising the IS, mirrors, diffuser, and HIS can be considered calibrated for making spectral irradiance measurements of the sun/moon where the aperture on the IS is the defining aperture.

Step 4: Measurements of the Earth and Sun

Measurements of the radiance of the Earth are made with the HIS directly. The diffuser disc rotates to allow light from the Earth to enter the HIS telescope (Figure 13). When the TRUTHS satellite is rotated to allow CSAR to face the Sun, then the CSAR can measure TSI and the IS (illuminating the mirrors, diffuser, and HIS) can measure SSI and similarly for the moon. For UV measurements of SSI, where the signal levels are very low, the mirror (M1) rather than diffuser (D1/D2) is used in the path between the IS and HIS.

These measurements are fully SI-traceable because of this calibration scheme for their radiometric responsivity. Full traceability to SI also needs traceability for the defining aperture areas (the two apertures on the TR, the aperture on the IS, and the aperture on CSAR). These apertures will be calibrated on the ground. In orbit, apertures on CSAR and IS will both be subject to direct exposure to space and the sun and so there is a need therefore to monitor the stability of those aperture areas. CSAR will have redundant apertures (different apertures on each cavity, which can have varying degrees of exposure). For the IS and in principle the TR, a dedicated LD beam (at one wavelength since geometry has no spectral dependency) is expanded with optics to a size that overfills the defining apertures of CSAR and the IS. By illuminating each CSAR aperture (redundant options) in turn, it can compare these apertures and calibrate the IS in irradiance (rather than power) mode. The same LD irradiance beam can also be used to check the smaller TR aperture as a relative comparison. It is also envisaged that there will be two IS’ on TRUTHS each with their own aperture and again these will be used in a manner that allows reduced solar exposure time for one of the redundant pair.

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Figure 13: Measurements of the Earth and Sun (image credit: TRUTHS collaboration)

Calibration procedure summary

Figure 14 shows a schematic representation of the above calibration sequence for TRUTHS, Each complete iteration through the cycle (single wavelength) is estimated to take, at most, 5 min including time for any motions and stabilization of the system.

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Figure 14: Schematic showing overall calibration sequence (image credit: TRUTHS collaboration)

All the sub-components of the OBCS, IS, TR, diffusers, detectors, and optical fibers can in themselves suffer degradation. The effects of this are removed by the calibration process, which effectively spectrally calibrates each component as part of the system. The Cal process relies on short term radiometric (power) stability of the LD radiation, which is largely related to temperature and drive current, both of which can be readily achieved for the <1min timescales required. Wavelength stability or knowledge to 0.1 nm is required for the life of the mission. The calibration system, with the exception of the CSAR and the IS, are in an enclosed environment and never exposed to direct sunlight. Although in this baseline design only LDs, diffuser plate, and cavities of the CSAR are fully redundant, this is likely to change in the flight version and most of the subsystems are also passive in nature, reducing failure risk; the exception being a rotation of the diffuser (similar to most Solar reflective EO imagers) and additionally the movement of laser radiation between the OBCS components.

Payload Performance

Table 9 shows the uncertainty budget for the calibration system, comparing the traditional NMI laboratory-based performance with the TRUTHS OBCS breadboard to the expected flight model performance. This table presents the principle sources of uncertainty in the calibration process of the HIS but does not account for any potential residual stray-light or non-linearity of the HIS. The latter will be evaluated by varying calibration radiance levels (laser diode power) and stray light will be evaluated as part of the calibration using the monochromatic wavelengths on-board to monitor the more detailed pre-flight characterization using a full spectral calibration with a tunable laser facility. The OBCS is designed to be non-polarized—the LDs themselves, the optical fibers, and scatter from the walls of the IS and diffusers ensuring that this is the case and so no component has been included for this in the uncertainty budget.

Uncertainty
Source

Lab-Based
Uncertainty

Breadboard-Based
Uncertainty

Space-Based
Uncertainty

Notes

Laser (diodes)
Radiometric
Stability (60 s)

0.01%

0.07–0.3%

<0.07%

Space qualified, stabilized DFB lasers. Note for the
breadboard testing not all lasers were of DFB
quality resulting in poor stability

CSAR/Primary Std

0.02%

0.06%

<0.06%

Worst-case scenario for laser diode power levels

Prism Arm

<0.01%

<0.01%

<0.01%

Negligible

Transfer Radiometer

0.02%

0.03%

<0.03%

Voltage measurement uncertainty

External Aperture

0.02%

0.02%

0.02%

Calibrated pre-flight

Traceability

0.01%

0.08%

<0.08%

Worst-case scenario and largely due to potential
residual non-uniformity effects

HIS Thermal
Control (1K)

 

 

0.01–0.20%

<0.05% at all wavelengths, except at
extremes (<350 nm & >2200 nm)

HIS SNR

 

 

0.03%

Required laser source integration times from 7–60 sec,
and some spatial binning for solar spectral irradiance

Total

0.04%

0.16–0.32%

0.16–0.26%

Uncertainties added in quadrature

Table 9: Calibration system and HIS radiometric uncertainty (k = 2)

Figure 15 shows the progression of uncertainty propagation, with typical uncertainty budgets from the SI-traceable CSAR instrument, through to the HIS on-board calibration, sensor-to-sensor SNO cross calibration (see Table 6), and final example L2 product upgrade for the TRUTHS mission.

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Figure 15: Uncertainty (k = 2) propagation to inter-calibration and L2+ products (image credit: TRUTHS collaboration)




Spacecraft

A TRUTHS satellite platform has been defined and specified independently by both SSTL and Airbus to demonstrate the achievability using largely existing and heritage designs (Figure 16). The baseline system is an Airbus Astrobus-S although the M platform is also viable and the main alternative option is the SSTL spacecraft based on that used for Formosat-7, but there are alternatives.

A relatively detailed analysis, particularly related to avionics, for a low-cost platform has been carried out by SSTL and a similar one for the Astrobus-S but this will now be undertaken with greater rigour as part of on-going Phase AB1 studies and so not reported here.

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Figure 16: Images of possible platforms and payload integration: (a) payload integrated on SSTL Formosat-7 platform, (b) Formosat-7 candidate platform, (c) PeruSat-1 on Airbus-S (baseline platform for TRUTHS), (d) TRUTHS payload configured on Astrobus-S (image credit: TRUTHS collaborotion)

Operational Modes

Table 10 provides an outline of the observational plan for TRUTHS. The full calibration mode indicated to nominally take place bi-monthly will vary from beginning to end of life as a degradation profile is established. This full calibration mode includes all wavelengths traceable back to the CSAR and will be carried out in a continuous cyclic manner. However, calibrations of the imager can take place daily using coefficients of the calibration system established on an ongoing basis. Not all spectral channels need to be calibrated each cycle unless significant degradation is found, and similarly, at least one wavelength can be done per orbit on the earth shadow side of the orbit. On occasions, particularly during commissioning phase, some HIS calibrations at some wavelengths are likely to be carried out to assess any intra-orbital and or pointing effects.

Operational Mode

View

Frequency

Length of Operation

Notes

Solar measurements

Solar

Every orbit

5–10 min per orbit

Probably polar views

Calibration of the
OBCS to CSAR

Internal satellite
diffuser

Potentially every orbit.
Frequency to be defined based
on observed ageing

30 min, one or two
wavelengths per orbit

Carried out during Earth
shadow side, builds a
calibration of the TR so that
it can be used with diffuser
on a daily basis

Full Calibration of
HIS Earth Shadow

Internal Satellite
diffuser

Nominally achieved Bimonthly
(timed defined following
in-orbit degradation
monitoring). Can be carried
out on as needs basis

1 day accumulated
(over several orbits)

Performed during shadow
phase wavelength by
wavelength

Calibration
Monitoring of HIS

Laser/lamp
illuminated
diffuser

Daily using ongoing updates of
OBCS coefficients

Few minutes

Generally Performed in
shadow but can be carried
out at any part of orbit

Climate
Benchmarking

Earth (nadir view)

Bulk of operations—most
of the orbit

~35% duty cycle

 

Cross–Calibration
of Sensors Using
Angular Movement

Earth—test-sites
(non-nadir)

~1/day (but could be orbital)

~ 5 min

Only when required

Table 10: TRUTHS operational modes




Development status

• November 3, 2020: ESA and Airbus UK have signed a contract for the TRUTHS satellite mission. Under the contract, Airbus UK will lead the ‘system feasibility and predevelopment’ phase of this new mission. When launched this new mission will establish a climate and calibration observing system to improve confidence in climate-change forecasts. 25)

- TRUTHS (Traceable Radiometry Underpinning Terrestrial and Hello Studies) was proposed by the UK through ESA’s Earth Observation Earth Watch program.

- The mission will collect measurements of incoming solar radiation and solar radiation reflected from Earth's surface, traced to an absolute metrological reference. These data will then be used to improve climate datasets and to calibrate observations from other satellites.

- To do this, the TRUTHS satellite will carry a cryogenic solar absolute radiometer and a hyperspectral imaging sensor.

- Richard Franklin, Managing Director of Airbus Defence and Space in the UK said, “Validating data on Earth’s changing climate is at the heart of this exciting mission, which will have a profound impact on future studies.

- “It will provide the gold standard of calibration for space-based Earth observation – a kind of standards laboratory in space. For the first time, the international scientific community will be able to cross-reference their measurements and data, enabling much more accurate forecasts and analysis, especially from the European Copernicus program.”

- ESA’s Director of Earth Observation Programs, Josef Aschbacher, added, “We are thrilled to have signed the contract with Airbus that will define the mission system implementation concept as well as focus on the preparation of critical technologies prior to implementing the mission’s full development, which we envisage in 2023.

- “The benchmark data that TRUTHS will supply are going to bring real benefits for climate science – and we will be extremely proud to have it in our suite of satellite missions.”

- UK Science Minister, Amanda Holloway, noted, “Data has been one of our most powerful and versatile weapons against coronavirus, and it is among our most potent weapons in countering climate change.

- “This mission, with Airbus leading the charge, will not only give us the first ever absolute measurement of the light reflected off Earth’s surface, it will reduce the uncertainty in future climate projections while arming our scientists with the most reliable data and insight we have ever had access to.”

TRUTHS_Auto0

Figure 17: The TRUTHS mission aims to establish an SI-traceable space-based climate and calibration observing system to improve confidence in climate-change forecasts – a kind of ‘standards laboratory in space’. It would carry a hyperspectral imager to provide benchmark measurements of both incoming solar radiation and outgoing reflected radiation with an unprecedented accuracy. These benchmark measurements would improve our ability to estimate radiative imbalance underlying climate change and, importantly, in a shorter time than is currently possible. Reference datasets from TRUTHS would also serve to calibrate other satellite sensors, such as those carried on the Copernicus missions [image credit: NPL (National Physical Laboratory)]

• February 20, 2020: TRUTHS is a climate mission, led by the UK Space Agency (UKSA), which will be delivered by the European Space Agency (ESA) to enable in-flight calibration of Earth observation (EO) satellites. TRUTHS will help deliver improved confidence in Earth Observation data gathered from space and the forecasts driven by this data. 26) 27)

- TRUTHS will enable upgrade of the performance of the EO system, both in space and on the ground. The mission aims to enhance by an order of magnitude, our ability to estimate the Earth’s radiation budget through direct measurement, establishing an SI-traceable reference data set which ban be used to cross calibrate other satellites and improve overall data quality from the EO system.

- TRUTHS will allow rigorous testing of model forecasts to support decision-making on climate adaption strategies. The mission will enable a 10 fold improvement in accuracy of EO data, which will, in turn, drive a halving of the time required for climate scientists to make unequivocal determinations of changes to the earth’s temperature. The mission provides 'benchmark' measurements with uncertainties small enough that future change, from a background of natural variability, can be detected in as short a time as possible.

Figure 18: TRUTHS satellite calibration mission (video credit: NPL)

The next stage of TRUTHS development 28)

- Incorporating technology initially conceived at NPL almost 20 years ago, the TRUTHS mission was accepted into the ESA Earthwatch program in November 2019. As a UK led, European Space Agency mission. TRUTHS will be delivered by a multi-national consortium which will include resources not only from the UK but include global partners from Greece, Spain, Romania and the Czech Republic.

- The A/B1 testing phase which will be initiated in early 2020 will begin with the establishment of a delivery consortium who will then undertake a series of mission design studies including performance simulation alongside the design and build of the hyperspectral imager elegant breadboard which will be tested with the calibration system.

- The Earth observation satellite data from TRUTHS will be directly downloaded to a single receiver station likely to be in Svalbard and from there transmitted to a data processing centre in the UK. As the TRUTHS data is considered a ‘public good’ it will be provided free and open to any user. In addition to improving our understanding of the planet and the effectiveness of strategies to mitigate against climate change, it is expected that TRUTHS will help facilitate further growth in commercial services for Earth observation and climate data benefiting the UK economy.

- Professor Nigel Fox, NPL states: ”The TRUTHS mission can be thought of as ‘putting NPL into space’ a ‘gold standard’ reference which will enable SI traceability to be established in space for Earth Observation data in the same way that we do for other terrestrial products and services such as time, mass and length, leading to increased trust in Earth observation, as well as climate data and services.”

Missions goals: TRUTHS improves climate data for better decision making 29)

- While there is no doubt that the Earth's climate is changing and near-global consensus that mankind is playing a major role, the timescale and nature of our impact remains uncertain. Assessments of climate change depend on data collected over decades so that small, often subtle, changes are reliably detected. TRUTHS aims to enhance by an order of magnitude, our ability to estimate the earth’s radiation budget and to establish a ‘metrology laboratory in space’.

- The Intergovernmental Panel on Climate Change (IPCC) has highlighted the uncertainty in the ensemble of climate models, which forecast a range of potential further temperature rises of the Earth, from 0.5°C to 5°C by 2100. For policy-makers to accept and act upon the data with any degree of confidence, it must be referenced to a traceable and internationally-accepted standard and have a significantly narrower range in potential outcomes. TRUTHS helps achieve this by providing a 'gold standard' to underpin a new era in Earth Observation from space.

- Many Earth Observation satellites are used to provide inputs and developments of models that advise policy-makers. The goal of TRUTHS is to improve the accuracy, reliability and integrity of this data through:

a) Measurement of both the incoming solar and reflected (Earth/Moon) radiation with sufficient accuracy and spectral resolution to allow an order of magnitude increase in our ability to estimate the earth’s radiation budget creating an SI-traceable reference data set to cross calibrate other sensors and improve the quality of their data.

b) Delivery of the first satellite to calibrate itself – directly traceable to SI units via a primary standard – in orbit.

c) Absolute, high-accuracy traceable calibration for other EO missions.

d) Making global nadir hyperspectral observations of the Earth's reflectance.

TRUTHS satellite calibration mission 30)

- TRUTHS is a climate mission, led by the UK Space Agency (UKSA), which will be delivered by the European Space Agency (ESA) to enable in-flight calibration of Earth observation (EO) satellites. TRUTHS will help deliver improved confidence in Earth Observation data gathered from space and the forecasts driven by this data.

- TRUTHS will allow rigorous testing of model forecasts to support decision-making on climate adaption strategies. The mission will enable a 10 fold improvement in accuracy of EO data, which will, in turn, drive a halving of the time required for climate scientists to make unequivocal determinations of changes to the earth’s temperature. The mission provides 'benchmark' measurements with uncertainties small enough that future change, from a background of natural variability, can be detected in as short a time as possible.

How TRUTHS works 31)

- The TRUTHS mission is unique in establishing high-accuracy, SI traceable data in-flight enabling a 'calibration laboratory in space'. At the heart of the TRUTHS calibration capability is the Cryogenic Solar Absolute Radiometer (CSAR) which can mimic in space, the same calibration capability and associated measurement accuracy that is delivered using this type of technology on Earth.

- Alongside the SI-traceable calibration capability of the CSAR, the hyperspectral imager will also make nadir and multi-angular spectrally-resolved measurements of the ocean and land surfaces. This will support studies of the carbon cycle and underpin improvements in observations which support agriculture or pollution monitoring. It will also provide data to improve atmospheric radiative transfer codes by anchoring boundary conditions at the top of the atmosphere. In this way TRUTHS will provide the basis to improve the performance and accuracy of other EO optical missions significantly.

- TRUTHS will also utilize Simultaneous Nadir Overpass (SNO) where the Earth viewing imager of TRUTHS can simultaneously, or within a few minutes, view the same part of the Earth as another in-flight satellite.

- TRUTHS utilizes many strategies for providing 'reference calibrations'. These include:

a) Using dedicated Earth-based reference standard sites such as those of CEOS

b) Near simultaneous observations of 'targets' at orbital cross-overs (the orbit of TRUTHS allows these to take place regularly over different parts of the globe)

c) Calibration of the moon.

- In addition to establishing benchmark measurements of the Earth itself, the TRUTHS mission plans to establish a set of internationally-accepted SI-traceable reference targets, including the sun, moon and the earth’s deserts. These could be used to provide calibrations for EO data collected by other satellites. Such reference targets are highly stable, and many have been observed by previous satellites, so could be used to back-correct archived data.

- TRUTHS is a complementary mission to other satellite based Earth observation missions providing a more complete picture of the Earth’s radiation imbalance which drives global warming. Alongside the FORUM and IASI-NG missions TRUTHS will enable a complete picture of the Earth’s irradiation imbalance.

• May 29, 2019: With ESA’s Space19+ Ministerial Council meeting set for November, a new satellite mission called TRUTHS will be added to the list of missions to be financed in the Earth Observation Earth Watch program. 32)

- On 27–28 November 2019, government ministers responsible for space activities in ESA Member States will gather in Seville, Spain, to decide on ESA’s programs and funding for the coming years.

- As well as the two main proposals, FutureEO and the Copernicus space component, that will be put forward for Earth Observation, TRUTHS will be proposed as an additional operational mission.

- TRUTHS is short for Traceable Radiometry Underpinning Terrestrial- and Helio- Studies.

- Proposed by the UK, the mission would establish an SI-traceable space-based climate and calibration observing system to improve confidence in climate-change forecasts – a kind of ‘standards laboratory in space’.

- To do this, TRUTHS would carry a hyperspectral imager to provide benchmark measurements of both incoming solar radiation and outgoing reflected radiation with an unprecedented accuracy achieved through a novel on-board calibration system conceived by the National Physical Laboratory (NPL) of the UK.

- These benchmark measurements would improve our ability to estimate radiative imbalance underlying climate change – importantly, in a shorter time than is currently possible.

- Reference datasets from TRUTHS would also serve to calibrate other satellite sensors, such as those carried on the Copernicus missions and the emerging constellations of small satellites.

- Furthermore, TRUTHS would contribute to the Global Climate Observing System, the Committee on Earth Observation Satellites, the World Meteorological Organization, the Copernicus Climate Change Service and the Group on Earth Observations by offering an important element of an international space-based climate observing system proposed in the Strategy Towards an Architecture for Climate Monitoring from Space.

- It would also provide observations that meet requirements for the key radiation balance essential climate variables and underpin many others, particularly those related to Earth’s carbon cycle.

- ESA’s Director of Earth Observation Programs, Josef Aschbacher, said, “ESA is happy to include the TRUTHS mission in our package of program proposals for Space19+. It is a very interesting mission that will bring many benefits to better understand climate change and offer well-calibrated measurements for cross-reference with other missions.

- “It is now up to ESA Member States to take up this offer and participate in this exciting program.”


Launch: A launch of the TRUTHS mission is expected in the timeframe 2026-2028.



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The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: ”Observation of the Earth and Its Environment: Survey of Missions and Sensors” (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (herb.kramer@gmx.net).

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