CAJ | 학술논문

为研究多种约束条件下的高超声速滑翔式飞行器快速突防轨迹优化问题，提出了基于hp自适应伪谱法的多段优化求解策略。建立了高超声速滑翔式飞行器的运动学模型，用三次样条插值拟合升力系数和阻力系数。综合考虑动压、过载和热流约束，建立了考虑禁飞区和航路点的约束模型。详细阐述了hp自适应伪谱法的求解原理，提出了以航路点为分段点的求解策略，最后以最小到达时间为代价函数对高超声速滑翔式飞行器再入突防过程进行了数字仿真。仿真结果表明，基于分段求解策略的最优轨迹能够有效满足各种约束条件的限制，达到了快速突防的目的。
위연구다충약속조건하적고초성속활상식비행기쾌속돌방궤적우화문제，제출료기우hp자괄응위보법적다단우화구해책략。건립료고초성속활상식비행기적운동학모형，용삼차양조삽치의합승력계수화조력계수。종합고필동압、과재화열류약속，건립료고필금비구화항로점적약속모형。상세천술료hp자괄응위보법적구해원리，제출료이항로점위분단점적구해책략，최후이최소도체시간위대개함수대고초성속활상식비행기재입돌방과정진행료수자방진。방진결과표명，기우분단구해책략적최우궤적능구유효만족각충약속조건적한제，체도료쾌속돌방적목적。
To study the rapid penetration trajectory optimization of the hypersonic gliding aircraft considering multiple constrains,a multi-phase optimization strategy was put forward based on hp adaptive pseudo -spectral method ( hpAPM ) .The kinetic model of the hypersonic gliding aircraft was built up,and the relationship between the lift coefficient and drag coefficient was fitted by using cubic spline interpolation .The models of no-fly zone and waypoint were found considering the constrains of dynamic press ,overload and heat flux .The principle of the hpAPM was expounded,then an idea was proposed,which taking the waypoints as the segment points of the trajectory .Simulation was made to the rapid penetration optimization trajectory of the hypersonic gliding aircraft with the objective of minimizing the arrival time .The results of the simulation indicated that the optimized trajectory using the multi-phase method can satisfy all of the constrains and meet the demand of rapid penetration .