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Volume 42 Issue 1
Jan.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(1): 120-129.
SHI Linan, LI Huifeng, ZHANG Ranet al. Gliding reentry vehicle lateral/directional coupling attitude control strategy[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(1): 120-129. doi: 10.13700/j.bh.1001-5965.2015.0037(in Chinese)
Citation: SHI Linan, LI Huifeng, ZHANG Ranet al. Gliding reentry vehicle lateral/directional coupling attitude control strategy[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(1): 120-129. doi: 10.13700/j.bh.1001-5965.2015.0037(in Chinese)
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Gliding reentry vehicle lateral/directional coupling attitude control strategy

doi: 10.13700/j.bh.1001-5965.2015.0037

  • School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:  National Natural Science Foundation of China (61174221, 11272062)
  • Received Date: 20 Jan 2015
  • Publish Date: 20 Jan 2016
    Abstract
  • A lateral/directional coupling control strategy based on the analysis of coupling characteristics was proposed for a class of under-actuated reusable launch vehicle (RLV) with only two body flaps and strongly coupling phenomena. Several common coupling mechanisms and evasion modes were described, including the inertial coupling, the motion coupling, the Dutch coupling and the control coupling. A rapid roll stability boundary was calculated along a nominal trajectory to limit the angular rate of bank angle command, and aiming at the problem that the existing Dutch-roll forecast formula is not suitable for this aircraft, a criterion of the Dutch-roll motion stabilization was proposed in order to adjust the controller gain in different situations. Based on the analysis of the coupling characteristics, a RLV longitudinal and lateral/directional motion control strategy was designed: elevators were used to trim and control on the longitudinal channel; body flaps and reaction control system (RCS) were used to hybrid control on the lateral/direction channel at low dynamic pressure and at high dynamic pressure body flaps can work alone. The 6 degree of freedom (6-DOF) numerical simulation results have demonstrated the control strategy proposed can track the guidance command well and maximize the using of aerodynamic actuators to reduce the consumption of RCS fuel.

     

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