摘要
针对传统热约束方式存在表征不合理的问题,通过热响应方程变换和热环境近似拟合,建立包含热响应模型的高速飞行器增广动力学模型,实现以飞行器防隔热层外壁温度和内壁温度作为热约束的目标。针对定常攻角飞行方案存在跳跃高度衰减较快的问题,提出一种高度-速度(H-V)反馈控制的轨迹设计方法,使用高度和速度信息联合调节攻角,实现大空域反复穿梭跳跃飞行,进一步降低高速飞行器防隔热层内壁温度。针对拉偏情况下内壁温度上边界不确定的问题,提出一种具有内壁温度边界线特征的标称轨迹设计方法,使用最严峻的极值拉偏条件作为输入进行设计,实现对高速飞行器防隔热层内壁温度的上边界约束。针对拉偏情况下大空域反复穿梭跳跃飞行轨迹跟踪误差较大的问题,提出一种H-V反馈跟踪的在线制导方法,通过高度和速度偏差信息分别调节倾侧角和攻角,实现对高速飞行器标称轨迹的精确跟踪并满足内壁温度上边界约束,蒙特卡罗仿真表明其具备较好的鲁棒性。
To address the problem of unreasonable representation of traditional thermal constraint,an augmented high speed flight vehicle dynamic model including a thermal response model is established by thermal response equa⁃tion transformation and thermal environment approximate fitting,so as to realize the thermal constraint by outer and in⁃ner wall temperature of high speed flight vehicle thermal insulation layer.To overcome the problem that leaping height attenuates quickly in the flight scheme with constant angle of attack,a trajectory design method is proposed based on Height-Velocity(H-V)feedback control.By adjusting the angle of attack with both height and velocity information,the method can realize reciprocating shuttle and leaping flight in large airspace,and further reduce the inner wall tempera⁃ture of the thermal insulation layer of high speed flight vehicle.For the uncertainty of the upper boundary of the inner wall temperature under the condition of deviation,a nominal trajectory design method with the characteristics of inner wall temperature boundary is proposed.By using the most severe deviation condition of the extreme value as the in⁃put,the upper boundary constraint of the inner wall temperature of the high speed flight vehicle thermal insulation layer is realized.For the problem of large tracking error of reciprocating shuttle and leaping flight trajectory in large airspace under the condition of deviation,an online guidance method is proposed based on H-V feedback tracking.By adjust⁃ing the bank angle and the angle of attack respectively with height and velocity deviation information,the method can realize accurate tracking of nominal trajectory and satisfy the inner wall temperature upper boundary constraint.Monte Carlo simulation results show that the guidance method proposed has good robustness.
作者
许昱
贺峥光
薛鹏飞
陈万春
陈峰
XU Yu;HE Zhengguang;XUE Pengfei;CHEN Wanchun;CHEN Feng(Science and Technology on Space Physics Laboratory,Beijing 100076,China;China Academy of Launch Vehicle Technology,Beijing 100076,China;School of Astronautics,Beihang University,Beijing 100191,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2023年第22期213-222,共10页
Acta Aeronautica et Astronautica Sinica
关键词
高速飞行器
热约束
热响应
轨迹设计
在线制导
跳跃飞行
高度-速度反馈
high speed flight vehicle
thermal constraint
thermal response
trajectory design
online guidance
leaping flight
height-velocity feedback
