ExoMars 2016

ExoMars 2016
Name	ExoMars 2016
Mission type	Planetary science
Operator	European Space Agency / Roscosmos
Launch date	14 March 2016
Launch vehicle	Proton-M
Launch site	Baikonur Cosmodrome
Orbit	Martian transfer
Mass	~4,300 kg

ExoMars 2016 was a Franco‑Russian–European robotic mission comprising an orbiter and a lander element developed jointly by the European Space Agency and Roscosmos. The mission combined contributions from national agencies including Italian Space Agency, UK Space Agency, and industry partners such as Thales Alenia Space and RKK Energia to study Mars' atmosphere and surface processes. Launched in March 2016, the mission sought to advance objectives set by programs like the Aurora Programme and to support follow‑on activities in cooperation with programmes such as Mars Sample Return planning.

Mission overview

The mission architecture included the Trace Gas Orbiter spacecraft and the Schiaparelli entry, descent, and landing demonstrator, coordinated through ESA's European Space Research and Technology Centre and Roscosmos' Russian Federal Space Agency engineering centres. Objectives built upon legacy data from Mars Express, Mars Reconnaissance Orbiter, and Mars Global Surveyor while complementing measurements from MAVEN and Mars Atmosphere and Volatile EvolutioN. The programme aimed to characterise trace gases including methane, to test technologies for precision landing demonstrated historically by missions such as Viking 1, Phoenix, and Pathfinder.

Spacecraft and instruments

The Trace Gas Orbiter, designed by an industrial consortium led by Thales Alenia Space, carried payloads including the Atmospheric Chemistry Suite, the Nadir and Occultation for MArs Discovery infrared spectrometer, and the Colour and Stereo Surface Imaging System, building on instrument heritage from Pioneer Venus and Mars Express/OMEGA. The TGO also integrated the CaSSIS camera and FREND neutron detector, with avionics influenced by designs from Rosetta and BepiColombo engineering teams. Schiaparelli, built by Thales Alenia Space Italia with descent elements from Finmeccanica partners and thruster technology related to Ariane programmes, carried a suite to validate entry, descent and landing systems including inertial measurement units used in projects like Ariane 5 and altimetry concepts tested on SMART-1.

Launch and trajectory

Launch was executed from Baikonur Cosmodrome using a Proton-M rocket with a Briz-M upper stage, following trajectory planning informed by missions such as Mars Reconnaissance Orbiter and Mars Odyssey. The interplanetary transfer exploited a Hohmann-like window also utilised by previous launches including Mars Express and was managed by ESA mission control at European Space Operations Centre in coordination with TsNIIMash and Energiya specialists. Mid‑course corrections mirrored navigation practices from Voyager and Cassini–Huygens with deep space tracking from networks including Deep Space Network and European Tracking Station at New Norcia.

Operations and mission timeline

Cruise phase operations incorporated cruise‑phase checkout procedures similar to Rosetta and Giotto campaigns, with instrument calibrations and trajectory correction manoeuvres. After Mars arrival, orbital insertion for the TGO adopted strategies comparable to Mars Express aerobraking and orbital capture methods used by Galileo at Jupiter. Schiaparelli separated prior to entry, with EDL sequencing reflecting heritage from Soviet Mars 3 and the Curiosity mission's sky crane concept in procedural complexity, while TGO commenced aerobraking activities to reach final science orbit over subsequent months.

Scientific objectives and results

Primary science goals targeted the detection, mapping and source attribution of trace gases, especially methane, to investigate possible geological or biological processes similar in scientific impetus to investigations by Curiosity and Viking 2. The TGO's spectrometers and neutron detectors provided high‑sensitivity datasets that complemented orbital climatology from MRO and compositional baselines from Mars Odyssey. Results refined constraints on atmospheric methane, informed models developed in studies associated with IPCC style assessments of planetary atmospheres, and supported site characterisation efforts relevant to future missions under international collaborations like International Space Station partners and planned Mars Sample Return architecture.

Failures and anomaly investigation

Schiaparelli's descent ended with a failure to achieve a controlled landing; telemetry and telemetry analysis involved teams from European Space Operations Centre, Roscosmos engineering bureaus, and independent investigators with precedent in mishap inquiries such as Columbia disaster and Mars Climate Orbiter reviews. Post‑flight investigation attributed anomalies to software misinterpretation of accelerometer and inertial measurement data and premature parachute and thruster shutdown similar in investigative approach to assessments conducted after Ariane 5 Flight 501. Findings informed changes to flight software, attitude control algorithms, and verification procedures used across ESA and Russian spacecraft projects, and influenced design choices for the subsequent ExoMars rover phase involving partners including Airbus Defence and Space and national space agencies.

Category:Missions to Mars Category:European Space Agency missions Category:Roscosmos missions