基于分段高斯伪谱法的组合动力飞行器火箭挂飞轨迹规划  

The Trajectory Design on the Captive Flight Test of Booster Rocket and the Combined-Cycled Aircraft Based on Segmented Gaussian Pseudo-Spectral Method

作　　者：曲文慧 张晗祺 吴了泥 尤延铖 董一巍 Qu Wenhui;Zhang Hanqi;Wu Liaoni;You Yancheng;Dong Yiwei(School of Aircraft Engineering,Xiamen University,Xiamen 361102,China)

机构地区：[1]厦门大学航空航天学院,厦门361102

出　　处：《航天控制》2021年第4期28-35,共8页Aerospace Control

摘　　要：为解决受涡喷发动机技术水平限制,导致试验飞行器无法直接达到试验所需高度和马赫数的问题,采用可回收式助推火箭挂飞后分离的方法,基于分段式高斯伪谱法搭建弹道优化模型,结合引射火箭与飞行器特性设计试验窗口,设计了弹道优化模型的约束条件;以末端高度最高、速度最大及轨迹平滑作为单项性能指标,以其加权和作为总性能指标,通过改变单项性能指标的权重系数,改变了助推火箭与飞行器的分离点,建立了组合动力飞行器火箭挂飞最优轨迹。仿真结果表明,本文方法建立的弹道状态变量变化平缓,满足约束条件,可为组合动力飞行器高空飞行试验轨迹规划提供依据。In order to solve the problem that the test aircraft can not directly reach the required altitude and Mach number due to the limitation of the technical level of the turbojet engine,the method of separation of the recoverable booster rocket and the aircraft is adopted after captive flight test.The trajectory optimization model is established based on segmented gaussian pseudo-spectral method,the test window is designed in combination with the characteristics of ejector rocket and aircraft,and the constraint conditions of the trajectory optimization model are designed.The maximum terminal height,maximum speed and smooth trajectory are taken as the single performance indexes,and the weighted sum is taken as the overall performance indexes.By changing the weight coefficient of a single performance index,the separation point between the booster rocket and the aircraft can be changed for obtaining the optimal trajectory.The simulation results show that the trajectory state variables obtained by applying this method change gently and meet the constraint conditions,which can serve as a reference for the high-altitude flight test trajectory design of the combined-power aircraft.

关 键 词：轨迹规划 高斯伪谱法 火箭挂飞实验 组合动力飞行器 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]