亚轨道飞行器上升段轨迹快速生成方法研究

摘要

Mission diversity and short preparation time are the main features of suborbital launch vehicle.Therefore, it is very important for its mission completion to generate an optimal trajectory. Aiming at the limitations of the traditional ascent trajectory design method. such as spending too much time and poor adaptability, the SLV ascent rapid trajectory generation based on optimal control theory is studied. The performance index is minimum fuel consumption. The angle of attack, sideslip angle and bank angle are treated as control variables to derive the optimal conditions. By adopting the classical finite difference method. the two-point boundary value problem represented by derivative equations of states and costates are transformed to nonlinear equations. The roots are obtained through modified Newton method. The simulation results show the method proposed in this paper is very rapid.%亚轨道飞行器飞行任务的主要特点是任务多样,任务时间间隔短.因此快速生成最优轨迹对保障亚轨道飞行器任务的完成至关重要.针对传统上升轨迹设计方法中存在的时间花销大、任务适应性较差等问题,基于最优控制理论对亚轨道飞行器上升段轨迹生成方法进行了研究.以上升段燃料消耗量最少作为性能指标,选取攻角、侧滑角和倾斜角作为控制变量求解最优性条件.采用经典的有限差分法将状态和伴随状态表示的两点边值常微分方程问题转化为非线性方程组,并使用改进型牛顿法求根.最后通过仿真分析,验证了给出的轨迹生成方法的快速性.