Journal of Astronautics ›› 2019, Vol. 40 ›› Issue (6): 655-665.doi: 10.3873/j.issn.1000-1328.2019.06.006

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Terminal Guidance with Impact Angle Constraint and Deceleration Control for a Hypersonic Glide Reentry Vehicle

WANG Rong gang, XU Zhi, TANG Shuo, JIA Sheng wei   

  1. 1. Northwestern Polytechnical University, School of Astronautics, Xi’an 710072, China; 2. Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Nanjing 210016, China; 3. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2018-03-20 Revised:2018-08-31 Online:2019-06-15 Published:2019-06-25


 A short-range low-lift-to-drag ratio hypersonic glide-reentry vehicle with impact angle constraint and deceleration control is selected as the object of study. By introducing a trajectory adjustment phase to make the vehicle satisfy the capturability condition of the terminal guidance phase, the problem of the hypersonic glide-reentry vehicle which is difficult to attack the target directly with impact angle constraint and deceleration control is solved. In order to push down the trajectory and maintain the field of view, a biased proportional guidance law is proposed by adjusting the coefficient of the error feedback. On this foundation, a velocity control order generation method is established based on the estimation of the angle of attack and flight-path angle, to solve the problem of the ideal velocity control order generation method which has a low accuracy. Extensive simulations are conducted to verify the design features of the algorithm.

Key words: Hypersonic glide-reentry vehicle, Terminal guidance, Impact angle control, Deceleration control

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