Thales Alenia Space Research Articles

Testing the Limits of Biosignature Detection in Ca-sulphate Mixtures Through a Simulated Martian Environment

Mixtures of cyanobacterial microbial mat and Ca-sulphate minerals were exposed to a simulated Martian environment via the Thales Alenia Space's “MARSBalloon” Project in partnership with St Bernard’s High School via the Orbyts science inclusivity program. FTIR spectroscopic analyses identified that at 50% Ca-sulphate, most microbial mat biosignatures were obscured under Earth conditions, except for the C–O stretch and polysaccharide O–H vibrational modes. At 75% Ca-sulphate concentrations, no spectral biosignatures were observed. However, after exposure to a simulated stratospheric Martian environment, partial dehydration of the Ca-sulphate occurred to reveal the spectral biosignatures. This has implications in the search for life on Mars, particularly within evaporite-rich environments similar to those being investigated by the Curiosity rover.

Reliability tests on millimetre wave 100 nm gate length process for safe operating area evaluation methodology

This paper presents a reliability evaluation of a low noise amplifier (Thales Alenia Space design) based on PHEMT GaAs 100 nm technology from a European foundry. The methodology relies on two kinds of test: an RF step stress (cumulative gradual increase stress test) to evaluate a safe operating area then an RF life test (long term stress test) to validate the safe operating area. Degradations are evaluated by typical static and dynamic measurements. In this paper, the methodology is enriched by an additional low field static measurement analysis which allows a better understanding of degradation mechanisms.

Molecular contamination control for Exomars 2022 Mission

The ExoMars 2022 integration facility has been built at the Thales Alenia Space Italy in Turin. The facility includes a GBT (Glove Box Train), that is an ISO3 class facility, totally aseptic and characterized by controlled airborne molecular organic contamination. This new facility provides an environment strictly controlled for what concerns cleanliness and contamination, specifically conceived to perform AIT of The Ultra Clean Zone (UCZ) of the ExoMars Rover Analytical Laboratory Drawer.Indeed, standard methods as per ECSS-Q-ST-70-05C and ECSS-Q-ST-70-50C are not suitable for the monitoring of integration facility and Flight H/W. The environment of GBT has been required to be monitored in terms of airborne molecular contamination (AMC) on the basis of ISO 14644-8. The maximum contamination levels allowable on flight H/W after accelerated CO2 snow cleaning and at the end of integration activities are one order of magnitude less than the detection limit of standard FT-IR techniques for molecular contamination.For these reasons a dedicated method has been set up for molecular contamination monitoring. This paper shows the development of Thermal Desoprtion-Gas Cromatography/Mass Spectrometer (TD-GC/MS) method for the monitoring of extremely low organic contamination levels both on air samples and on witnesses representative of the Flight H/W, providing also the most recent results obtained in the frame of ExoMars 2022 UCZ QM and FM AIT Campaign.

An Approach to the Preliminary Sizing and Performance Assessment of Spaceplanes’ Landing Parafoils

In this new era of space exploration, reusability and lower environmental impact are critical drivers in pursuing innovative solutions for access to space. One of these leading solutions is the Space Rider, a European reusable space plane with the ability to be both an “access to space” and a “return from space”. Following the lesson learned from the Intermediate eXperimental Vehicle (IXV) design and testing, the Space Rider will be equipped with a parafoil to enhance manoeuvrability during landing. Politecnico di Torino (PoliTO), in collaboration with Thales Alenia Space Italy (TAS-I), has developed an integrated tool to assess the landing performances of spaceplanes equipped with parafoils during conceptual design. The presented approach fuses sizing, dynamic models, guidance and control algorithms to provide a software suite for the rapid prototyping, sizing and performance assessment of spaceplanes’ parafoils. This paper details the implementation, mathematical background, validation and lessons learned behind the different software modules.

A model predictive control for attitude stabilization and spin control of a spacecraft with a flexible rotating payload

Many Earth Observation missions, implementing space-based microwave sensing techniques for collecting surface information, employ spinning sensors to cover large swaths of terrestrial areas, thus improving the rate at which global maps of those measured data are generated. These spacecraft (as Soil Moisture Active Passive (SMAP) developed by NASA or Copernicus Imaging Microwave Radiometer (CIMR) currently under development by Thales Alenia Space) consist of a main non-spun platform and a rotating part composed of an antenna boom, a deployable reflector and a rotation mechanism. As the reflector is designated to rotate about the nadir axis producing conically scanned antenna beams with precise surface incidence angle, the payload pointing accuracy needs to be addressed at both spin subsystem and platform level. In this work, a representative model of the dynamic behaviour of SMAP satellite is developed as a study case to design the proposed control strategies; in particular, a SMAP-like payload structural model is built using FEM commercial codes. The spacecraft is equipped with a Reaction Wheels Assembly (RWA) to accomplish both momentum compensation for the spun element and three-axis attitude control and a motor for the spin mechanism. The objective of the study is to develop the spacecraft control architecture in the frame of Model Predictive Control (MPC) theory. MPC refers to a class of algorithms in which the control action is obtained by computing an open-loop optimal sequence of control moves over a predefined time horizon; moreover, the ability to set constraints on process inputs and outputs directly in the problem formulation allows to account for actuators’ limits. In the study two operative phases of the satellite are addressed: the Spin-up, in which the 6-meter diameter antenna is spun-up to the operative condition of 14.6 RPM, and the Science Phase, in which precise nadir pointing and stability of the flexible system must be kept for acquiring high-resolution measurements. To this purpose, control–structure interaction between attitude/spin control system and flexible dynamics, as well as system’s imbalances, are carefully addressed by the proposed control architecture. The nonlinear in-orbit dynamics of the flexible spacecraft is then used to evaluate the performance of the MPC controller in terms of pointing accuracy and robustness to uncertainties.

Общие подходы оценки стойкости к воздействию ионизирующего излучения космического пространства для зарубежной электронной компонентной базы предприятий –разработчиков

The analysis of information on the stability of the electronic component base (ECB) in the development of radio-electronic equipment (REE) of spacecraft (spacecraft) is an important and urgent task. The paper considers the main components of the approaches of foreign organizations developing radio space technology to ensure its radiation resistance. The design approaches of Thales Alenia Space, Airbus Defense and Space, and the European Space Agency are presented. The article outlines the main directions for optimizing the procedures for the preliminary selection of ECB, which consist in ensuring the required resistance of REE SC at the ECB level with ensuring the reliability of data on durability, in minimizing the costs of applying resistance enhancement measures (through the use of a promising ECB with increased resistance characteristics), to replace ECB.

Robust Collocated Control of Large Flexible Space Structures

Agile maneuvering and precise pointing control require special attention for spacecraft equipped with large flexible appendages. A joint academia-industry research involving Sapienza University of Rome, Thales Alenia Space in France and the European Space Agency (ESA), investigates the use of innovative solutions to counteract the deterioration in pointing accuracy stemming from interactions between a rigid bus and the flexible structures during operations. Specifically, this paper aims at presenting the design of an attitude/vibration control architecture in a μ-synthesis framework. The architecture consists of an attitude control system combined with a distributed network of actuators/sensors at structural level for active vibration control purposes. A spacecraft equipped with an interferometric Ka-band SAR payload and two solar arrays is considered as a useful and challenging benchmark problem to assess the proposed methodology. The numerical simulations, carried out via both a linearized setting and a nonlinear simulator, have proved the effectiveness of the robust collocated control in comparison with a baseline PID controller.

Retrospective Review of a Two-Phase Mechanically Pumped Loop for Spacecraft Thermal Control Systems

The main issues associated with the development of two-phase mechanically pumped loops (2-MPL) for thermal control systems of spacecraft with large heat dissipation were formulated back in the early 80s. They have undeniable advantages over single-phase loops with mechanical pumping and two-phase capillary pumped loops at power more than 6 kW and heat transfer distance more than 10 meters. Intensive research and development of such systems started in the USA together with European, Canadian and Japanese specialists due to plans to build new high-power spacecraft and the Space Station Freedom project. In the 90's, S. P. Korolev Rocket and Space Corporation Energia (Russia) was developing a 2-MPL for the Russian segment of the International Space Station with the capacity of 20...30 kW. For this purpose, leading research organizations of the former Soviet Union were involved. In the last two decades, interest in two-phase heat transfer loops has significantly increased because of high-power stationary communications satellites and autonomous spacecraft for Lunar and Martian missions. The paper presents a retrospective review of worldwide developments of 2-MPLs for thermal control systems of spacecraft with large heat dissipation from the early 80's to the present. The participation of scientists and engineers of the Ukrainian National Aerospace University "KhAI" and the Center of Technical Physics is considered. The main directions of research, development results, and scientific and technical problems on the way to the practical implementation of such system are considered. Despite a large amount of research and development work done, there were no practically implemented projects of spacecraft with the high-power thermal control system until recent days. The first powerful stationary satellite with the 2-MPL was SES-17 satellite on the NEOSAT platform by Thales Alenia Space - France. The satellite was successfully launched into space on October 24, 2021 by onboard Ariane 5 launcher operated by Arianespace from the Europe’s Spaceport in Kourou, French Guiana.

Report on First Inflight Data of BepiColombo's Mercury Orbiter Radio Science Experiment

BepiColombo's Mercury orbiter radio science experiment (MORE) was conceived to enable extremely accurate radio tracking measurements of the Mercury Planetary Orbiter to precisely determine the gravity field and the rotational state of Mercury, and to test theories of gravitation (e.g., Einstein's theory of general relativity). The design accuracy of the radio tracking data was 0.004 mm/s (at 1000 s integration time) for the range-rate measurements and 20 cm for the range (at a few seconds of the integration time). These accuracies are attained due to a combination of simultaneous two-way microwave links at X (7.2–8.4 GHz) and Ka-band (32–34 GHz) to calibrate the dispersive plasma noise component. In this letter, we present the first analysis of the range and range-rate data collected by ESA's deep-space antenna (DSA) during the initial cruise phase of BepiColombo. The novel 24 Mcps pseudonoise (PN) modulation of the Ka-band carrier, enabled by MORE's Ka-band transponder, built by Thales Alenia Space Italy, Rome, Italy, provided two-way range measurements to the centimeter-level accuracy, with an integration time of 4.2 s at 0.29 astronomical units. In tracking passes with favorable weather conditions, the range-rate measurements attained an average accuracy of 0.01 mm/s at 60 s integration time. Data from May 20–24, 2019 were combined in a multi-pass analysis to test the link stability on a longer timescale. The results confirm the noise level observed with the single-pass analysis and provide a preliminary indication that the MORE PN ranging system at 24 Mcps is compatible with the realization of an absolute measurement, where the need to introduce the range biases in the orbital fit is much more limited than in the past. We show that in the initial cruise test the BepiColombo radio link provided the range measurements of unprecedented accuracy for a planetary mission, and that, in general, all target accuracies for radio-metric measurements were exceeded.

DeepLO: Multi-projection deep LIDAR odometry for space orbital robotics rendezvous relative navigation

This work proposes a new Light Detection and Ranging (LIDAR) based navigation architecture that is appropriate for uncooperative relative robotic space navigation applications. In contrast to current solutions that exploit 3D LIDAR data, our architecture suggests a Deep Recurrent Convolutional Neural Network (DRCNN) that exploits multi-projected imagery of the acquired 3D LIDAR data. Advantages of the proposed DRCNN are; an effective feature representation facilitated by the Convolutional Neural Network module within DRCNN, a robust modeling of the navigation dynamics due to the Recurrent Neural Network incorporated in the DRCNN, and a low processing time. Our trials evaluate several current state-of-the-art space navigation methods on various simulated but credible scenarios that involve a satellite model developed by Thales Alenia Space (France). Additionally, we evaluate real satellite LIDAR data acquired in our lab. Results demonstrate that the proposed architecture, although trained solely on simulated data, is highly adaptable and is more appealing compared to current algorithms on both simulated and real LIDAR data scenarios affording better odometry accuracy at lower computational requirements.

A study of a rover wheel for Martian explorations, based on a flexible multibody approach

Vehicles for planetary exploration have to operate in completely different environments from Earth. For this reason, the design process of the exploration unit has an important role and can affect the requirements of the entire mission for the different space agencies involved. These operations are very expensive and time consuming, so that, over the years, ad hoc CAE methods have been developed to help engineers in the design stage. These methods are used to simulate several working conditions, evaluating which manoeuvres robots can safely perform during their mission. In this framework, a study was performed by Politecnico di Torino and Thales Alenia Space Italia. The goal was to find an efficient way to implement flexibility properties of a special wheel of a Rover for Martian explorations in a commercial (general purpose) MTB code. The ExoMars Rover was considered as case study of this work. When dealing with manoeuvres feasibility analysis, the best compromise between solution accuracy and computational time required must be found. The aim of this study was to explore pros and cons of several techniques which could allow modelling a complex flexible wheel using a commercial general-purpose MTB code. The absolute nodal coordinate formulation was compared with the other reduced-order modelling strategies proposed by the authors to implement the flexibility of a wheel in a multibody model of the full vehicle. Numerical results show good performance of the reduced morphing model in terms of computational time versus numerical accuracy.

A new interval diagnosis method: Application to the spacecraft rendezvous phase of the Mars sample return mission

SummaryThis paper presents a new optimized interval principal component analysis applied to detect and isolate actuators faults of an autonomous spacecraft involved in the rendezvous phase of the Mars sample return mission. Based on the exploitation of various arithmetic and interval analysis properties, the new interval model is built by solving the interval eigenpairs problem via a resolution of a parametric linear programming problem. The detection and isolation phases are performed by extending the classic methods to interval‐valued data. The proposed method is applied to detect and isolate actuators faults that can occur on the spacecraft's thrusters. Based on data provided by a “high fidelity” industrial simulator developed by Thales Alenia Space, the obtained results proved the effectiveness of the proposed interval fault diagnosis method on detecting and isolating thrusters' faults.

High-speed multi-dimensional relative navigation for uncooperative space objects

This work proposes a high-speed Light Detection and Ranging (LIDAR) based navigation architecture that is appropriate for uncooperative relative space navigation applications. In contrast to current solutions that exploit 3D LIDAR data, our architecture transforms the odometry problem from the 3D space into multiple 2.5D ones and completes the odometry problem by utilizing a recursive filtering scheme. Trials evaluate several current state-of-the-art 2D keypoint detection and local feature description methods as well as recursive filtering techniques on a number of simulated but credible scenarios that involve a satellite model developed by Thales Alenia Space (France). Most appealing performance is attained by the 2D keypoint detector Good Features to Track (GFFT) combined with the feature descriptor KAZE, that are further combined with either the H∞ or the Kalman recursive filter. Experimental results demonstrate that compared to current algorithms, the GFTT/KAZE combination is highly appealing affording one order of magnitude more accurate odometry and a very low processing burden, which depending on the competitor method, may exceed one order of magnitude faster computation.

Applying Active Diagnosis to Space Systems by On-Board Control Procedures

The instrumentation of real systems is often designed for control purposes and control inputs are designed to achieve nominal control objectives. Hence, the available measurements may not be sufficient to isolate faults with certainty and diagnoses are ambiguous. Active diagnosis formulates a planning problem to generate a sequence of actions that, applied to the system, enforces diagnosability and allows to iteratively refine ambiguous diagnoses. This paper analyzes the requirements for applying active diagnosis to space systems and proposes ActHyDiag as an effective framework to solve this problem. It presents the results of applying ActHyDiag to a real-space case study and of implementing the generated plans in the form of on-board control procedures. The case study is a redundant SpaceWire network where up to six instruments, monitored and controlled by the on-board software hosted in the satellite management unit, are transferring science data to a mass memory unit through SpaceWire routers. Experiments have been conducted on a real physical benchmark developed by Thales Alenia Space and demonstrate the effectiveness of the plans proposed by ActHyDiag.

Robotic Gripper for Payload Capture in Low Earth Orbit

The consensus to a study phase for an Intermediate eXperimental Vehicle (IXV) successor, a preoperational vehicle called Space Reusable Integrated Demonstrator for European Return (SPACE RIDER), has been recently enlarged, as approved during last EU Ministerial Council. One of the main project tasks consists in developing SPACE RIDER to conduct on orbit servicing activity with no docking. SPACE RIDER would be provided with a robotic manipulator system (arm and gripper) able to transfer cargos, such as scientific payloads, from low Earth orbiting platforms to the SPACE RIDER cargo bay. The platform is a part of a space tug designed to move small satellites and other payloads from Low Earth Orbit to Geosynchronous Equatorial Orbit and vice versa. A study on this robotic technology is here presented. This research is carried out by Politecnico di Torino and Thales Alenia Space Italy. The system configuration of the robotic manipulator is first described in terms of volumes and masses. The considered housing cargo bay requirements in terms of volume (< 100 l) and mass (< 50 kg) combined with the required overall arm dimensions (4 m length), and mass of the cargo (5–30 kg) force to developing an innovative robotic manipulator with the task-oriented end-effector. It results in a 7df arm to ensure a high degree of dexterity and a dedicated end-effector designed to grasp the cargo interface. The gripper concept here developed consists in a multi-finger hand able to lock both translational and rotational cargo degrees of freedom through an innovative under-actuation strategy to limit its mass and volume. A configuration study on the cargo handle interface has also been performed together with some computer-aided design models and multibody analysis of the whole system to prove its feasibility. Finally, the concept of system control architecture is defined.

State-owned enterprises as knowledge-explorer agents

ABSTRACTThis paper deals with the role of the State Owned enterprises (SOEs) in innovation processes. Only a few studies focus on the contribution SOEs as companies might give to produce new knowledge and technological innovation. We argue, however, that SOEs are a pillar of the innovation process and we explore conditions that can make SOEs very effective. Through two in-depth case studies in two different industries (STMicroelectronics in the semiconductor and Thales Alenia Space in the space industry) we illustrate how SOEs can contribute to innovation by exploring new opportunities and recombining different sources of knowledge. We highlight the conditions that can make exploration and recombination possible. We also highlight the ability of the two companies to change their boundaries through a continuous wave of agreements, mergers and acquisitions. This way, they were able to expand beyond their domains in a way that matched the evolution of their original industries.

The exploration of PHOBOS: Design of a Sample Return mission

The long-term goal of enabling human exploration of the Moon and Mars drives International space exploration plans. Robotic space missions must therefore develop and demonstrate the feasibility and robustness of the enabling technologies and capabilities.The Phobos Sample Return mission is a candidate mission of the Mars Robotic Exploration Preparation programme. Its objective is to acquire and return a sample from the Mars moon Phobos. The main science goal of this mission will be to understand the formation of the Martian moons Phobos and Deimos and acquire further data on the evolution of the solar system. From a technology standpoint, it would be a big step forward in the development of many technologies, ranging from low-gravity body landing capabilities to Earth re-entry of samples from deep space, from semi-autonomous robotic acquisition of surface samples to sample preservation and further analysis in dedicated ground laboratories.Thales Alenia Space represents one of two industrial contractors studying the mission to Phase A level. This phase involves investigation of all aspects of the mission and spacecraft design to ensure its feasibility and robustness. The planned launch date for the mission is between 2025 and 2027. The Ariane 5 ECA launch vehicle will be launched from Kourou. A chemical propulsion module will transfer the spacecraft composite to the Martian system, and will then be separated at Phobos. A full characterization campaign of Phobos at different altitudes from orbit will follow. This will include quasi-satellite orbits and flybys, using a payload suite of cameras and spectrometers. When the preferred landing site is identified, a controlled descent and touchdown onto the surface of Phobos will be performed, with a touchdown accuracy of 50 m. A robotic arm and sampling mechanism will obtain and verify a sample of surface regolith, and insert it into the Earth re-entry capsule. Part of the Spacecraft will return to the Earth from Phobos and deliver the re-entry capsule to the Earth’s atmosphere. The capsule will perform a fully passive Earth entry, descent and landing in Woomera, Australia. It will then be recovered and transferred to a sample curation facility for sample extraction and analysis. This paper summarises the results of the Thales Alenia Space Phobos Sample Return mission and spacecraft design, with a focus on the key elements and mass drivers.

ExoMars 2016: Schiaparelli coasting, entry and descent post flight mission analysis

The ExoMars programme is pursued as part of a broad cooperation between ESA and Roscosmos with significant contribution from NASA. Two missions compose the ExoMars programme with launches in 2016 and 2020. The ExoMars 2016 mission, led by ESA, has been launched by the Russian Proton on March 14th, 2016. The mission includes the Trace Gas Orbiter (TGO) and the Entry, Descent, and Landing Demonstrator Module (EDM, named Schiaparelli), both supplied by ESA. Thales Alenia Space Italia (TASI) acted as prime contractor for the ExoMars2016 Mission, leading the Spacecraft Composite development and verification, including system design and verification of the EDM and key GNC/EDL technologies. DEIMOS Space has been involved in Exomars since 2004 providing more than 12 years of technical activities in Mission Engineering (from launch to landing) and GNC.Schiaparelli separated from TGO on October 16th, 2016, and reached Mars 3 days later: it successfully entered with a pre-defined FPA and performed a nominal hypersonic entry, decreasing its velocity until reaching subsonic regime under the parachute. During the descent phase an anomaly occurred, and the EDM separated from the backshell earlier than expected, compromising the landing phase. During the EDL, Schiaparelli was able to communicate with the TGO and with the Mars Reconnaissance Orbiter, transmitting its real time on-board telemetry. Data collected is extremely valuable in preparation to the 2020 mission.This paper focuses on the level 0/1 post-flight analyses of the Schiaparelli mission, presenting the activities performed by DEIMOS Space in strict collaboration with TASI and ESA, aimed to assess the main flight performance from the mission analysis perspective, and determine and compare the actual flight with the predicted one. The analyses covered: trajectory reconstruction, entry aerodynamic and flying qualities analyses, EDL performance reconstruction and assessment, descent data analysis and trajectory reconstruction.Post-flight results contributed to validate key technologies and design tools, including the DEIMOS Space Planetary Entry Toolbox (PETBox) for Mission Engineering and the related design methodology for Atmospheric Flight, now Flight Qualified for both missions on Earth and Mars.

Satellite design for demise thermal characterisation in early re-entry for dismantlement mechanisms

Preliminary analyses at ESA have shown that space objects in LEO with masses above 500 kg might already imply an on-ground casualty risk higher than 1E-4 in case of uncontrolled re-entry. Compliance to this casualty risk requirement may be achieved through controlled re-entry, but this solution has a major impact at system level. Sometime it requires a full re-design of the spacecraft and may involve switching to a completely different launcher performance (consequently a significant mission cost impact).This option may be avoided with achievement of compliant ablation (demise) of the spacecraft upon uncontrolled atmospheric re-entry. The so-called Design-for-Demise discipline (D4D) is a highly multidisciplinary approach that can bring significant benefits in the future missions in the medium to long term. (Klinkrad, 2006; Johnson, 2012) [1,2].ESA created in 2012 the “Cleanspace” initiative and team to promote actions on green aspects and debris remediation (ESA Clean Space Team, 2015) [3]. Recently ALTRAN was involved inside THALES ALENIA Space consortium in those ESA activities on S/C D4D techniques and proposed several D4D concepts. This ESA D4D study had the objective to find D4D solutions for the Sentinel-1 study case (around 2 tons). This objective were about to be theoretically achieved.[4].The outcomes of those D4D studies performed in parallel at level of 3 LSI (Large System Integrator) were concluded in early 2016 [4,5] and used mainly ESA Sentinels S/C as study cases. Those studies all demonstrated that S/C dismantlement (controlled and earlier to natural break-up) has a major benefit in reduction of S/C Debris Casualty Area (DCA). Then this technique has to be considered with high priority in a global approach for D4D improvement. (ESA, 2015; CleanSat Workshop presentations, 2015) [6,7].The proposed ALTRAN/NIMESIS study CLEANSAT Building Block 10: Shape Memory Alloys (SMA) Dismantlement Mechanisms has investigated several technological devices and SMA material options for their suitability to be implemented in LEO satellite H/W of main European LSI for dismantlement during atmospheric re-entry.

Combined Instrumentation Package COMARS+ for the ExoMars Schiaparelli Lander

In order to measure aerothermal parameters on the back cover of the ExoMars Schiaparelli lander the instrumentation package COMARS+ was developed by DLR. Consisting of three combined aerothermal sensors, one broadband radiometer sensor and an electronic box the payload provides important data for future missions. The aerothermal sensors called COMARS combine four discrete sensors measuring static pressure, total heat flux, temperature and radiative heat flux at two specific spectral bands. The infrared radiation in a broadband spectral range is measured by the separate broadband radiometer sensor. The electronic box of the payload is used for amplification, conditioning and multiplexing of the sensor signals. The design of the payload was mainly carried out using numerical tools including structural analyses, to simulate the main mechanical loads which occur during launch and stage separation, and thermal analyses to simulate the temperature environment during cruise phase and Mars entry. To validate the design an extensive qualification test campaign was conducted on a set of qualification models. The tests included vibration and shock tests to simulate launch loads and stage separation shocks. Thermal tests under vacuum condition were performed to simulate the thermal environment of the capsule during the different flight phases. Furthermore electromagnetic compatibility tests were conducted to check that the payload is compatible with the electromagnetic environment of the capsule and does not emit electromagnetic energy that could cause electromagnetic interference in other devices. For the sensor heads located on the ExoMars back cover radiation tests were carried out to verify their radiation hardness. Finally the bioburden reduction process was demonstrated on the qualification hardware to show the compliance with the planetary protection requirements. To test the actual heat flux, pressure and infrared radiation measurement under representative conditions, aerothermal tests were performed in an arc-heated wind tunnel facility. After all qualification tests were passed successfully, the acceptance test campaign for the flight hardware at acceptance level included the same tests than the qualification campaign except shock, radiation hardness and aerothermal tests. After passing all acceptance tests, the COMARS+ flight hardware was integrated into the Schiaparelli capsule in January 2015 at the ExoMars integration site at Thales Alenia Space in Turin. Although the landing of Schiaparelli failed, resulting in the loss of most COMARS+ flight data because they were stored on the lander, some data points were directly transmitted to the orbiter at low sampling rate during the entry phase. These data indicate that all COMARS+ sensors delivered useful data until parachute deployment with the exception of the plasma black-out phase. Since measured structure and sensor housing temperatures are far below predicted pre-flight values, a new calibration using COMARS+ spare sensors at temperatures below 0 °C is necessary.