Failed · landing failure Lander 2016

Schiaparelli EDM

Schiaparelli EDM (Entry, Descent and Landing Demonstrator Module), launched on March 14, 2016 as part of the ExoMars mission, was an ESA and Roscosmos technology demonstrator designed to validate entry, descent, and landing systems on Mars. After successfully separating from the TGO orbiter on October 16, the module began its atmospheric descent on October 19, but a saturation in the inertial measurement unit caused an erroneous altitude calculation, premature parachute deployment, and the subsequent fatal impact on the surface of Meridiani Planum.

Agency ESA
Launch SOL 3 OF HESPERO OF YEAR 33 · 04:56 MTC
Arrival at Mars SOL 27 OF MANGALO OF YEAR 33 · 15:17 MTC
Mission End SOL 30 OF MANGALO OF YEAR 33 · 10:44 MTC
of travel 216 days · ~210 sols
Cruise to Mars216 days
Operations3 days

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Technical Analysis of the Schiaparelli EDM Mission

  • Mission Designation: Schiaparelli EDM (Entry, Descent and Landing Demonstrator Module)
  • Operating Agency: ESA and Roscosmos
  • Launch Date: March 14, 2016, 09:31:00 UTC
  • Mars Arrival Date: October 16, 2016, 14:42:00 UTC (separation from TGO orbiter)
  • Landing Site: Meridiani Planum, Mars
  • Impact Coordinates: Latitude -2.047° S, Longitude 353.790° E
    • Launch Vehicle: Proton-M / Briz-M rocket
  • Launch Site: Pad 200/39 at the Baikonur Cosmodrome, Kazakhstan
  • Mission Status: Landing Failure

    • 1. Historical Context and Detailed Objectives

    The scientific and engineering gap that the Schiaparelli EDM mission intended to fill consisted of the autonomous validation of critical entry, descent, and controlled landing (EDL) technologies on the Martian surface to support future missions of the ExoMars program. Primary objectives focused on:

    Scientific:

    • Study local weather conditions and surface atmospheric dynamics during the anticipated brief operational lifetime.
    • Measure atmospheric electric fields close to the Martian ground using specialized instrumentation.

    Engineering:

    • Demonstrate the effectiveness of the heat shield and aerodynamic braking systems in the Martian atmosphere.
    • Test supersonic parachute deployment and the inertial guidance and navigation system.
    • Validate the operation of final braking retrorockets and a deformable shock-absorbing structure.

    2. Vehicle Architecture and Main Subsystems

    The Schiaparelli EDM module featured a launch mass of 577 kg, with a structural diameter of 2.4 m and a height of 1.8 m. Power supply depended on primary-use internal batteries with a nominal capacity of 6.9 Ah and a voltage of 33.6 V, optimized to power subsystems during a limited surface stay of 2 to 8 sols. Communications were based on a UHF-band radio frequency system designed to transmit recorded data to surrounding relay orbiters, such as the Trace Gas Orbiter (TGO) or Mars Express. The vehicle's mobility was zero, completely lacking any propulsion or surface traction elements.

    3. Payload and Scientific Instrumentation

    To fulfill its atmospheric analysis and trajectory reconstruction duties, the module integrated the following instrument suite:

    • AMELIA (Atmospheric Mars Entry and Landing Investigation Analyst): Engineering sensor set intended to reconstruct atmospheric entry dynamics and the spacecraft's aerodynamic profile.
    • COMARS+ (Combined Aerothermal and Radiometer Sensors Instrument Package): Instrumental package for recording pressures, surface temperatures, and radiative and convective heat fluxes on the back cover.
    • DECA (Descent Camera): Descent camera configured to capture overhead images of the approach site and Meridiani Planum.
    • DREAMS (Dust Characterization, Risk Assessment and Environment Analyzer on the Martian Surface): Surface meteorological and environmental station integrating specific sensors such as MetWind for wind, DREAMS-H for humidity, DREAMS-P for pressure, MarsTem for near-surface atmospheric temperature, SIS (Solar Irradiance Sensor) for atmospheric transparency, and MicroARES for electric fields.
    • Laser retroreflectors: High-precision passive array oriented toward geodetic localization via future Martian orbiters.

    4. Mission Chronology and Phases

    The mission developed according to the following critical time milestones:

    • March 14, 2016: Successful launch from the Baikonur Cosmodrome aboard a Proton-M rocket.
    • October 16, 2016: Nominal separation of the Schiaparelli module from the TGO orbiter, initiating its ballistic cruise phase toward Mars.
    • October 19, 2016: Entry into the Martian atmosphere at hyperbolic velocity, deployment of the subsonic parachute, ejection of the heat shield, and subsequent critical anomaly due to inertial saturation which concluded with direct impact against the surface at 14:48 UTC.

    5. Results and Discoveries

    Despite the tragic outcome of the mission, the capsule successfully transmitted a massive flow of telemetry and technical information during the first six minutes of atmospheric descent. This record allowed for the extremely precise evaluation of the aerodynamic behavior of the heat shield, the validation of numerical models of atmospheric friction, and the analysis of the performance of navigation algorithms before the saturation of the inertial system occurred.

    6. Legacy and Importance

    The forensic analysis of Schiaparelli's telemetry data provided the European Space Agency (ESA) with a wealth of critical knowledge regarding Martian atmospheric entry dynamics. The failures identified in the inertial measurement unit served to correct and redesign the guidance, navigation, and control (GNC) subsystems applied in subsequent planetary missions.

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