CAJ | 학술논문

运用 Gauss 伪谱方法将运载器三自由度再入轨迹优化问题转化为非线性规划问题，选取 Gauss 节点上的状态量和控制量作为待优化参数，求解同时满足路径约束和终端约束条件下可重复使用运载器（RLV）的总吸热量最小再入轨迹。路径约束包括驻点热流峰值约束、最大动压约束、过载约束以及控制变量约束；终端约束为高度和速度等。选取优化控制变量为迎角和倾斜角。仿真过程表明，Gauss伪谱法对状态猜测值不敏感，算法容易收敛，适用于轨迹优化问题的求解。
운용 Gauss 위보방법장운재기삼자유도재입궤적우화문제전화위비선성규화문제，선취 Gauss 절점상적상태량화공제량작위대우화삼수，구해동시만족로경약속화종단약속조건하가중복사용운재기（RLV）적총흡열량최소재입궤적。로경약속포괄주점열류봉치약속、최대동압약속、과재약속이급공제변량약속；종단약속위고도화속도등。선취우화공제변량위영각화경사각。방진과정표명，Gauss위보법대상태시측치불민감，산법용역수렴，괄용우궤적우화문제적구해。
To obtain the reentry trajectory with minimum total heat absorption and which satisfied with path constraints and terminal constraints for Reusable Launch Vehicles (RLV), the Gauss Pseudo-spectral Method (GPM) was applied to convert 3 DOF entry trajectory optimization problem to nonlinear programming problem, and state variables and control variables of Gauss node were selected as optimal parameters. The path constraints include the heat flux peak on stagnation point, maximum dynamic pressure, overload and control variables constraints. The terminal constraints include the vehicle's height and velocity. The attack angle and inclination angle are chosen as optimal control variables. The simulation results indicate that GPM were not sensitive to guess value of state and arithmetic was easily convergence, which is suitable for solving the problem of trajectory optimization.