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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2020, Vol. 41 ›› Issue (12): 124059-124059.doi: 10.7527/S1000-6893.2020.24059

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Numerical simulation of stable deceleration and safe separation of integral escape module for aerospace vehicles

LIU Yuan1,2, CHEN Chuan3, QIAN Zhansen1,2   

  1. 1. AVIC Aerodynamics Research Institute, Shenyang 110034, China;
    2. Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang 110034, China;
    3. AVIC Chengdu Aircraft Design Institute, Chengdu 510100, China
  • Received:2020-04-07 Revised:2020-04-28 Published:2020-05-21
  • Supported by:
    Aeronautical Science Foundation of China (2017ZA7005)

Abstract: The integral escape module concept integrates the seat and the cockpit in order to obtain an independent aerodynamic configuration after ejection. A maximum protection can be offered for the crew from high-speed wind blast. Therefore, the integral escape module will be one of the important approaches for the design of the escape system for the aerospace vehicle. In this study, we first conduct numerical simulation of an integral escape module to evaluate its basic aerodynamic performance. Then a rigid brake parachute scheme is proposed to improve the stability and deceleration efficiency of the integral escape module. Finally, the unsteady computational method with a dynamic chimera grid technique is applied to the simulation of the escape process. The numerical results reveal a lack of static stability of the single integral escape module. However, both static and dynamic stability can be significantly improved by using the brake parachute combination scheme in the wide flight envelop of Ma=0.3~4.0. With the growth of Mach number, the stability increases at subsonic speed, while decreases at supersonic speed. The dynamic stability can be further improved by reducing the flying altitude to increase the dynamic pressure at high Mach numbers (e.g. Ma=4.0). In the wide flight envelope, the ejection escape trajectory of the integral escape module shows that the module combined with the brake parachute can be safely separated from the aerospace vehicle assisted by the ejection force and rocket thrust, with its attitude converging gradually.

Key words: integral escape modules, wide speed range, stability, brake parachute, chimera grid

CLC Number: