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The demonstration of Inflatable Aerodynamic Decelerator (IAD) in RH300 sounding rocket platform took place successfully on September 3, 2022 from TERLS range of ISRO. The IAD was inflated after nose-cone ejection, the booster motor and fins were separated during descent and the IAD decelerated the rest of the vehicle till touchdown. Successful deployment of IAD and orientation of the body to the desired attitude was achieved. The mission demonstrated IAD’s capability to reduce the peak dynamic pressure and terminal speed during descent. The demonstrated IAD was a result of multidisciplinary design, analysis, and testing. In this paper, we first focus on the aerodynamic characterization of the IAD using computational fluid dynamics (CFD) at various Mach regimes (0.9–3.45), the results of which were validated using wind tunnel test and flight test results. Various flight measurements were available from multiple sensors and radar. This paper secondly focuses on an optimization-based approach to derive trajectory parameters from pressure sensor data. The trajectory thus obtained is seen to match closely with the reconstructed trajectory from traditional method with radar data. In addition, the new approach estimates the angle of attack as well.

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Aerodynamic Characterization and Flight Trajectory Reconstruction Using Pressure Measurements for a Spent Stage Re-entry with Inflatable Aerodynamic Decelerator

  • 会议论文

  • 发表日期：

    2026年

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  • Leya Joseph,
  • Padmanabha Prasanna Sinha,
  • Aman Chauhan,
  • Pankaj Priyadarshi

摘要

The demonstration of Inflatable Aerodynamic Decelerator (IAD) in RH300 sounding rocket platform took place successfully on September 3, 2022 from TERLS range of ISRO. The IAD was inflated after nose-cone ejection, the booster motor and fins were separated during descent and the IAD decelerated the rest of the vehicle till touchdown. Successful deployment of IAD and orientation of the body to the desired attitude was achieved. The mission demonstrated IAD’s capability to reduce the peak dynamic pressure and terminal speed during descent. The demonstrated IAD was a result of multidisciplinary design, analysis, and testing. In this paper, we first focus on the aerodynamic characterization of the IAD using computational fluid dynamics (CFD) at various Mach regimes (0.9–3.45), the results of which were validated using wind tunnel test and flight test results. Various flight measurements were available from multiple sensors and radar. This paper secondly focuses on an optimization-based approach to derive trajectory parameters from pressure sensor data. The trajectory thus obtained is seen to match closely with the reconstructed trajectory from traditional method with radar data. In addition, the new approach estimates the angle of attack as well.