An Autonomous Ascent Guidance Method for Multi-Stage Solid Launch Vehicles

In order to achieve the high precision orbit injection satisfied with the terminal multi-constrained orbit elements, an autonomous guidance method based upon the "burn-coast-burn" task model is generated to solve the guidance problem of the solid launch vehicles which shut off by the fuel exhaustion in vacuum. In terms of the law of conservation of orbital momentum, a pointing algorithm (PA) with the constraints of the velocity vectors and the position vectors is derived. On this foundation, the nonlinear system of the equations of the sliding track satisfied with the energy constraints is established, the order of which is reduced, one-dimension iterative solution obtained by solving the two-point boundary value problems with the given arc length constraint. The results of the Monte Carlo simulation demonstrate that the proposed guidance algorithm has strong robustness and excellent performance to the deviations and uncertainties of the solid launch vehicles and also has powerful adaptability to the multiple terminal orbit tasks, which has the important theoretical significance and a certain reference value for practical engineering applications. © 2019, Editorial Dept. of JA. All right reserved.