Short-Range Reentry Guidance With Impact Angle and Impact Velocity Constraints for Hypersonic Gliding Reentry Vehicle

Abstract

In order to ensure the normal operation of the guidance system and achieve precise reentry strike, it is necessary to complete the reentry guidance in a very short range of several hundred kilometers. Furthermore, the process constraints, including the field of view and overload, and the terminal constraints, such as the impact velocity and impact angle, need to be met. To solve these problems, a guidance strategy for short-range gliding with maneuvering deceleration capability is proposed. First, the flight-path angle command is generated in real time using a reference trajectory in the longitudinal plane of the gliding flight phase to ensure the timely convergence of the trajectory and meet the handover conditions. Second, in the terminal attack phase, a weight coefficient of the angle control command is introduced and adjusted according to the vertical field-of-view deviation to force down the trajectory and maintain the field-of-view constraint. Finally, the deceleration angle of attack and the additional angle of attack are selected as the control variables, and the deceleration requirements of the gliding flight phase and the terminal attack phase are met using the predictor-corrector method. The numerical simulations verify that the proposed guidance strategy exhibit good guidance performance and robustness.

Keywords

• Hypersonic gliding reentry vehicle
• short-range reentry guidance
• impact angle constraint
• impact velocity constraint