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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (3): 626619-626619.doi: 10.7527/S1000-6893.2021.26619

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Air data sensing technology of Mars probe

CHEN Guangqiang1, DOU Guohui1, WEI Haogong2, ZOU Xin2, LI Qi2, LIU Zhou1, ZHOU Weijiang1   

  1. 1. China Academy of Aerospace Aerodynamics, Beijing 100074, China;
    2. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China
  • Received:2021-11-04 Revised:2021-11-26 Online:2022-03-15 Published:2021-12-24
  • Supported by:
    National Numerical Wind Tunnel Project

Abstract: According to characteristics such as high Mach number, chemical non-equilibrium effect, and low dynamic pressure of the Mars probe entering the flight trajectory, a data measurement method upon entering atmosphere based on MEADS/IMU coupling is proposed to measure Mars atmosphere data in the area below 60 km altitude.Using the chemical non-equilibrium model/complete gas model of the independently developed CACFD software platform, we calculate the surface pressure point data of the wide velocity domain flight flow field of the probe, and creatively establish the MEADS algorithm model based on the BP neural network.In the high Mach section (Ma>12), the Mach number measured by IMU is used as the input condition, and the flight atmospheric parameters such as the total pressure, dynamic pressure, static pressure, angle of attack and sideslip angle are measured in combination with the MEADS algorithm, successfully overcoming the influence of Mach number independence on MEADS system measurement.In the low Mach number section (Ma ≤ 12), the MEADS algorithm is directly applied to measure the static pressure, Mach number, angle of attack and sideslip angle.The test results show that the conditions for the error of the pressure measuring unit in the MEADS system to be ≤ 7 Pa:the total pressure measurement error to be ≤ 14 Pa (1.5%), the angle of attack measurement error ≤ 0.9°, the side slip angle measurement error ≤ 0.9°, the dynamic pressure measurement error ≤ 10 Pa (1.5%), the static pressure measurement error ≤ 7 Pa (3%), and the Mach number measurement error ≤ 0.1.The flight test data show basic consistency of the MEADS measurement results with the Mach number, angle of attack and sideslip angle measured by IMU.

Key words: Mars probe, air data sensing, flight test, chemical non-equilibrium effect, computational fluid dynamics

CLC Number: