一种空射火箭减载轨道设计方法  

A design method for low-load orbit of air-launched vehicle

作　　者：吕艳 张广勇 刘琳 王建滨 Lv Yan;Zhang Guangyong;Liu Lin;Wang Jianbin(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《战术导弹技术》2023年第2期34-38,45,共6页Tactical Missile Technology

摘　　要：空射火箭在稠密大气层飞行时受载荷约束显著,且大攻角的飞行特点使得传统轨道设计中利用攻角动压积来表征载荷的方法不再适用。提出了适用于空射火箭轨道设计过程的载荷表征手段,在轨道设计模型中加入特征截面的载荷约束,使得轨道设计时对攻角剖面的调整能够准确反应飞行轨道与载荷的耦合关系,通过一体化优化快速获得满足多约束的最优轨道。推导了空射火箭动力学和运动学微分方程,给出一级飞行段典型程序攻角设计剖面,推导了参与轨道迭代设计的特征截面载荷计算公式;结合hp自适应伪谱法,使用典型算例说明本方法的有效性。研究表明,本方法可减小解耦以及设计量降维造成的可行域损失,并提高了设计效率。The load constraint of the air-launched vehicle flying in the dense atmosphere is significant.It is no longer suitable for using attack angle product of dynamic pressure to represent the load in traditional orbital design because of the high attack angle.The load characterization applicable to the orbit design of airlaunched vehicle is proposed by adding load constraint of characteristic section to the orbital calculation model,so that the adjustment of attack angle can accurately reflect the coupling relationship between flight trajectory and load,and through integrated optimization with multiple constraints,the optimal trajectory can be quickly obtained.The dynamics and kinematics differential equations of the air-launched vehicle are derived,a typical attack angle design of first stage flight is given,and the load constraint formula of characteristic section involved in the iterative design is derived.Finally,a typical example is given to illustrate the effectiveness of the proposed method.After ananlysis,the proposed method can reduce the loss of the feasible domain by decoupling and dimensionality and improve design efficiency.

关 键 词：空射火箭 轨道设计 载荷 hp自适应伪谱法 减载 轨道优化 攻角 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]