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Aerothermal Measurements from the ExoMars Schiaparelli Capsule Entry

机译：ExoMars Schiaparelli胶囊入口的空气热测量

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摘要

The instrumentation package COMARS+ was developed to measure aerothermal parameters on the back cover of the ExoMars Schiaparelli lander during Martian entry. The aerothermal sensors called Combined Aerothermal and Radiometer Sensor (COMARS) combine four discrete sensors, measuring static pressure, total heat flux, temperature, and radiative heat flux. After passing all acceptance tests, the Schiaparelli capsule was launched on top of the Proton launcher on March 14, 2016. All COMARS+ sensors operated nominally during the complete entry phase. But the complete data package is not available due to an anomaly that led to the failure of Schiaparelli shortly before landing. Nevertheless, a subset of the COMARS+ flight data was transmitted real-time during the entry and was received by the ExoMars 2016 orbiter, with the exception of the plasma blackout phase. The radiative heat flux on the back cover close to the vehicle shoulder was measured successfully for the first time on a Mars entry vehicle. The measured maximum radiative contribution was 61% of the total heat flux at the first measurement point after the blackout phase and 33% for the next measured trajectory point 10 s later. These measurements confirm recent findings that radiative heating can be a significant portion of total heating on the back cover during Mars entry. The maximum back cover total heat flux rate was measured at approximately 9% of the calculated stagnation point heat flux on the front cover. All measured heat fluxes on the back cover were below the levels that were used to design the thermal protection system.
机译：开发了COMARS +仪器套件，用于在火星人进入期间测量ExoMars Schiaparelli着陆器后盖上的空气热参数。称为热空气与辐射计组合传感器（COMARS）的空气热传感器结合了四个离散传感器，可测量静压，总热通量，温度和辐射热通量。在通过所有验收测试后，Schiaparelli胶囊于2016年3月14日在质子发射器顶部发射。所有COMARS +传感器在整个进入阶段均正常运行。但是由于异常导致Schiaparelli着陆前不久发生故障，因此无法获得完整的数据包。然而，除等离子体停电阶段外，COMARS +飞行数据的子集在进入过程中被实时传输，并被ExoMars 2016轨道飞行器接收。在火星进入车辆上，首次成功测量了靠近车肩的后盖上的辐射热通量。在停电阶段后的第一个测量点处测得的最大辐射贡献为总热通量的61％，在10s之后的下一个测量轨迹点处测得的总辐射通量为33％。这些测量结果证实了最近的发现：在火星进入期间，辐射加热可能是后盖总加热的重要部分。测得的最大后盖总热通量约为前盖上计算的停滞点热通量的9％。后盖上所有测得的热通量均低于用于设计热保护系统的水平。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2019年第1期|68-81|共14页
  • 作者

    Guelhan A.; Thiele T.; Siebe F.; Kronen R.; Schleutker T.;

  • 作者单位

    German Aerosp Ctr, DLR, Superson & Hyperson Technol Dept, Inst Aerodynam & Flow Technol, D-51147 Cologne, Germany|COMARS Instrumentat Package, Cologne, Germany;

    German Aerosp Ctr, DLR, Superson & Hyperson Technol Dept, Inst Aerodynam & Flow Technol, D-51147 Cologne, Germany;

    German Aerosp Ctr, DLR, Superson & Hyperson Technol Dept, Inst Aerodynam & Flow Technol, D-51147 Cologne, Germany;

    German Aerosp Ctr, DLR, Superson & Hyperson Technol Dept, Inst Aerodynam & Flow Technol, D-51147 Cologne, Germany;

    German Aerosp Ctr, DLR, Superson & Hyperson Technol Dept, Inst Aerodynam & Flow Technol, D-51147 Cologne, Germany;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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