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Exomars David Bartolo, Shazib Elahi, Aaron Tun, Junyi Zhang Department of Mechanical and Aerospace Engineering University of California, Davis

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Exomars David Bartolo, Shazib Elahi, Aaron Tun, Junyi Zhang Department of Mechanical and Aerospace Engineering University of California, Davis ExoMars David Bartolo, Shazib Elahi, Aaron Tun, Junyi Zhang Department of Mechanical and Aerospace Engineering University of California, Davis Objectives Enter Mars Orbit at an Entry Orbits and Trajectories • Trace Gas Orbiter (TGO) Deploy EDM altitude of 400 km Velocimeter • Trace Gas Orbiter (TGO) • Perform detailed, remote observations of the Martian atmosphere • Inserted into an elliptical orbit around Mars, then sweep through atmosphere Atmospheric Chemistry Suite (ACS): Characterize Mission Atmospheric Mars Entry IMU • Observe the atmosphere of Mars for trace gases of biological and image features on Martian surface to supply Trace Gas Orbiter (TGO) Descent to finally settle into a circular, approximately 400-km altitude orbit ready to Requirements and Landing (AMELIA) significance, such as methane, and their sources information on the geological and dynamical Parachute conduct its scientific mission • Act as a data relay for the future ExoMars rover mission context. • Schiaparelli EDM Carry Scientific Payloads Landing • Schiaparelli EDM Release front heat shield • Ejected from orbiter three days before reaching Martian atmosphere, • Achieve a controlled landing on the surface of Mars to prove the Nadir and Occultation for Mars Discovery coasting towards its destination and entering the atmosphere at 21,000 km/h, CASSIS: High-resolution camera Propulsion Structure Payload: DREAMS ESA’s capabilities for future missions to Mars (NOMAD): Map distribution on trace gases, RDA decelerating using aerobraking and a parachute, and then brake with aid of a • Entry, Descent, and Landing (EDL) of a payload on the identifying sources, to establish atmospheric Fine Resolution Epithermal Neutron Detector thruster system before landing on the surface of the planet surface of Mars inventory. Perform high sensitivity orbital (FREND): Map hydrogen a mater deep in the identification of atmosphere. surface, revealing deposits of potential ice-water. Timescale and Technical Characteristics Launch Date March 14th, 2016 09:31 UTC Launch Site Baikonur Cosmodrome, Kazakhstan Launch Vehicle Proton-M/Briz-M Size 3.2 m x 2 m x 2 m, with solar wings spanning 17.5 m tip-to-tip providing ~ 2000 W of power Launch Mass 3755 kg Payload Mass 113.8 kg of science payload and 577 kg Schiaparelli Propulsion Bipropellant, with 424 N main engine for Mars orbit insertion and major maneuvers Nominal Mission 2022 End Stakeholders The stakeholders for the ExoMars program are primarily the Potential Improvements and Analyses European Space Agency (ESA), the Russian Federal Space Concept of Operations • Improvements Agency (Roscosmos), in addition to the scientific community and ExoMars 2016 comprises the TGO plus an entry, descent and landing demonstrator (EDM), dubbed the Schiaparelli. • Schiaparelli Lander: implement a radioisotope thermoelectric generator (RTG) power source and rechargeable humankind. The requirements are as follows: batteries. This would extend the mission to a year or longer instead of a few sols. • Requirements: Achieving mission objectives. • Schiaparelli Lander: implement a second parachute for redundancy. Ground • Schiaparelli Lander: implement a safety check code within the GNC software that validates the integrated value of the segment The benefits of this mission are as follows: Entry of Descent of Landing of IMU; in the case of Schiaparelli, the IMU recorded an angular attitude with an error of 165 degrees, thus leading to the Mid-course • Address important scientific questions Commissionin Schiaparelli Schiaparelli Schiaparelli RDA recording a negative altitude. Both instances were implausible because with a parachute deployed, the EDM Launch deep-space Separation: Operations • Demonstrate key flight and technology for future exploration g and cruise would not have changed such a drastic attitude, and the RDA would not transmit recordings under the Martian surface. maneuver to dispatch occurring on Aerobraking missions phase: almost TGO maneuver to • Analyses adjust Schiaparelli to the same to lower TGO • For ESA, benefits Aurora Exploration Program (explore Solar System 500 million km be captured by • Power system analysis: investigate power generation capacity of RTG. trajectory for the surface Earth day: to its final 400 Objects that have high potential for the emergence of life). to go Mars gravity into • Develop a model consisting of an applied oscillating force on the EDM to simulate the motion during parachute Mars arrival x 400 km • For Roscosmos, benefits Russian Academy of Sciences’ Russian its final orbit deployment. Perform further parachute deployment tests in wind tunnels, with the expected Mach numbers in the science orbit Federal Space Program Martian atmosphere, because such high angular rates above the IMU saturation level were to be expected. • Propulsion analysis, to account for added weight of the power system and the second parachute. Aluminum with Sun Sensors (2x) Ablative Material Subsystems Breakdown Carbon Fiber UHF System Gyroscopes Reinforced Polymer Descent Camera (DECA) Back Shell Lithium-ion Battery (2x) Solar Wings (2x) Back Shell Front Shell Communication System Inertial Measurement Skin Accelerometers Thermal Protection Guidance, Navigation, Units (IMUS) 424 N Bi-propellant Main Engine Propulsion System Power Systems External Structure Systems and Control ExoMars Avionics Systems Infrared Instruments (3x) ACS Atmospheric Mars Entry Trace Gas Orbiter (TGO) Power Systems Radar Doppler and Landing (AMELIA) Neutron Detector FREND 2016 MetHumi Non-rechargeable EDL Battery Antennas (4x) Landing Systems Ultraviolet Spectrometer Scientific Payloads Avionics Systems MicroARES Crushable Landing Structure Scientific Payloads MarsTem Rechargeable EDL Battery Electronic Units (2x) Propulsion System Infrared Spectrometer (2x) NOMAD Communication System DREAMS Mortar Deployed MetBaro Surface Operations Primary Battery A High Resolution Camera Parachute System CaSSIS 3 Clusters of 3 Hydrazine (5 Meters per Pixel) Electra UHF Band Transceivers (2x) Low-Gain Antenna (3x) MetWind SIS Surface Payload Battery High-Gain Antenna Pulse Engines.
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