Schiaparelli lander

Schiaparelli lander
Name	Schiaparelli
Mission	ExoMars 2016
Operator	European Space Agency
Manufacturer	Thales Alenia Space
Launch mass	577 kg
Dry mass	600 kg
Payload mass	20 kg
Launch date	14 March 2016
Launch vehicle	Proton-M/Briz-M
Launch site	Baikonur Cosmodrome
Status	Impacted on Mars surface (2016)

Schiaparelli lander The Schiaparelli lander was a technology-demonstration entry, descent, and landing probe flown as part of the ExoMars 2016 mission, developed by the European Space Agency in collaboration with the Roscosmos State Corporation. Its primary role was to test hypersonic aerodynamics, parachute deployment, and braking engines during an attempted touchdown near Meridiani Planum on Mars. The module separated from the ExoMars 2016 orbiter and followed a ballistic and guided reentry trajectory; telemetry ceased shortly before the planned landing, and impact was later confirmed by imaging from Mars Reconnaissance Orbiter, Mars Express, and later datasets.

Overview

Schiaparelli was named after the Italian astronomer Giovanni Schiaparelli and formed one element of the joint European Space Agency–Roscosmos State Corporation ExoMars programme alongside the Trace Gas Orbiter spacecraft built by Airbus Defence and Space and partners. The lander was integrated at facilities run by Thales Alenia Space in Toulouse, drawing on subsystems and components from contractors including ArianeGroup, OHB SE, SENER, RUAG Space, EADS Astrium, and Leonardo S.p.A.. Mission operations were coordinated by the European Space Operations Centre at Darmstadt with flight dynamics support from ESOC teams and scientific oversight from ESTEC and the European Space Research and Technology Centre. The launch on 14 March 2016 used a Proton-M rocket with a Briz-M upper stage from Baikonur Cosmodrome.

Mission objectives

Primary objectives emphasized demonstration of atmosphere entry and soft-landing technologies required for the planned ExoMars 2020 rover effort. Specific goals included validation of heatshield performance derived from ArianeGroup wind-tunnel data, verification of a back shell and parachute sequence similar to those used by Mars Pathfinder, Mars Exploration Rover missions, and testing of retrorocket systems like those employed by Phoenix and Viking missions. The mission also sought to measure atmospheric electrical properties, weather patterns, and surface reflectivity through instruments analogous to payloads on Mars Science Laboratory and to support navigational techniques used by Mars Reconnaissance Orbiter and Mars Odyssey relay communications.

Design and instruments

The Schiaparelli descent module architecture combined a heatshield, a back shell with a supersonic and subsonic parachute, and a propulsion-assisted landing stage employing eight solid-fuel and hydrazine thrusters developed with assistance from Aerospace Corporation contractors. The avionics suite featured an inertial measurement unit tied to a Doppler radar altimeter and a radar speed sensor provided by teams including ISRO-style engineering consultants and European navigation groups. Scientific instruments comprised the Atmospheric Structure Package (ASP) from Imperial College London partners, the DREAMS (Dust Characterisation, Risk Assessment, and Environment Analyser on the Martian Surface) meteorological package contributed by INAF and Instituto Nazionale di Astrofisica members, and a small engineering camera derived from designs used on Rosetta and Venus Express. Thermal protection materials were selected using heritage from Space Shuttle tiles and tested in facilities such as Dundee University and ESTEC test chambers.

Entry, descent, and landing sequence

After separation from the Trace Gas Orbiter, Schiaparelli approached Mars on a trajectory planned by teams at European Space Operations Centre and navigated using star trackers like those produced by SSTL and Thales Alenia Space guidance systems. The entry phase began with hypersonic atmospheric entry at Mach numbers comparable to those experienced by Mars Science Laboratory; the heatshield absorbed peak heating monitored by instrumentation comparable to sensors used on Cassini–Huygens. At about Mach 2 the main parachute deployed in a sequence tested in wind tunnels at ONERA and by contractors including DLR. The back shell separation exposed the lander’s Doppler radar and braking thrusters; the planned final descent used pulsed engines to reduce vertical velocity to touchdown speeds similar to Phoenix. Communications during descent were relayed via Trace Gas Orbiter and directly to Earth via the Deep Space Network and European ground stations.

Anomaly and investigation

Telemetry from Schiaparelli ceased roughly 50 seconds before the scheduled touchdown, prompting an international investigation involving European Space Agency anomaly teams, Roscosmos State Corporation, and contractors such as Thales Alenia Space and Airbus Defence and Space. Post-event analysis used high-resolution imaging from Mars Reconnaissance Orbiter’s HiRISE camera, mapping data from Mars Express and radar from MRO and Mars Odyssey to locate the impact site and the parachute. The root cause analysis identified a combination of sensor misinterpretation, erroneous guidance software computations, and a short firing of the braking engines leading to premature shutdown — findings cross-validated with simulation work at ESTEC and flight-data reconstruction at European Space Agency technical centers. Lessons were incorporated into redesigns for the follow-on ExoMars rover mission and operations planning involving JPL collaboration.

Scientific results and legacy

Despite the failed soft landing, Schiaparelli returned valuable engineering and atmospheric data during entry and descent, contributing to models used by teams at NASA Jet Propulsion Laboratory and California Institute of Technology for hypersonic entry dynamics. The DREAMS package provided short-duration measurements of temperature, pressure, humidity proxies, and electric field fluctuations informing studies by University of Padua and Imperial College London. Imagery and telemetry supported improvements to parachute deployment algorithms used in subsequent missions by ESA, NASA, and Roscosmos State Corporation. The mission influenced international collaborations involving ISRO, JAXA, CNSA, and CNES on landing-system design, and its datasets are archived in repositories managed by European Space Agency and partners for use by research groups at University of Oxford, University of Cambridge, Massachusetts Institute of Technology, Stanford University, and other institutions. Schiaparelli’s legacy persists in enhanced entry, descent, and landing (EDL) engineering practices, informing the hardware and software of later Martian landers and rovers including designs considered for ExoMars and other robotic exploration initiatives.

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