Byung Soo Kim和Jang Gyu Lee基于LOS的比例导引变形方式制导,设计了一种带落角约束的鲁棒制导律。考虑到导弹速度时变和目标机动对制导带来的影响,Song T. L., Shin S. J.和Cho H研究了一种二维平面内的最优主动寻的制导律。将有限时间内的非线性约束问题转化为等效的无限时间内的线性规划问题,Manchester LR.和Savkin A.V.设计了一种循环迭代的比例导引律,并通过理论分析,保证了交汇角误差和终端脱靶量为零。Jeong S.K., Cho S.J.和Kim E.G则充分利用偏置比例导引的优良性能,利用终端角度偏差和视线角速率为零的条件设计了一种带落角限制的偏置比例导引律。Yong-In Lee, Chang-Kyung Ryoo,Eulgon Kim等人考虑二维平面内的弹目相对运动情况,在笛卡尔坐标下将导弹速度直接进行分解,将导弹的动态特性引入制导方程,借鉴文献中求解有制导问题的方法及文献所给的求解黎卡提方程方法,得到了一种带落角约束的最优制导律。Ming Xin, S.N. Balakrishnan和Ernest J. Ohlmeyer在基于极坐标系的二维平面上,利用非线性最优控制方法设计了一种适用于低成本武器的制导律。Priya G. Das和Radhakant Padhi基于攻击静止目标假设,考虑飞行器自动驾驶仪的一阶时延,利用用于转弯的横向指令加速度和实际加速度之间的传递关系建立制导模型,并利用模型预测控制理论迭代优化的方法实时更新制导参数,推导出了一种非线性准最优的带落角的制导律。
To ensure an effective attack to various underground military targets, it is of urgentmilitary demand and realistic significance to develop aerial penetrating bomb, of whichguidance scheme design is a crucial part. Based on aerial penetrating bomb trajectorydesign, combining scheme guidance and navigation guidance, this thesis researches on acompound guidance scheme adaptable to aerial penetrating bomb.
The thesis is mainly concerned with the follows:
Firstly, the trajectory model of air-to-surface guided weapon and the simulation system are presented for the deficiencies of the tradition guidance law in the dissertation. Accordingly, the deficiencies of the tradition guidance law were analyzed from the simulation results.
Secondly,in general, verifying the design of the guidance law needs simulation analysis. In the simulation process, it needs to build aircraft’s spatial ballistic equation. In order to describe the trajectory of space weapons during the flight and build the space trajectory equation, it must define some basic coordinate systemand establish the conversion relation between the coordinate system. According to the flight dynamics principle, establishing the trajectory equation, the program can implement numerical simulation on trajectory, verify the actual performance of guidance law.
So, the second main task of the test is to establish complete aircraft trajectory equation, provides the convenience for the later chapters guidance trajectory simulation validation. The task mainly discuss the establishment of air to ground guided weapon trajectory equations of the problem, describes the basic coordinate system, ballistic trajectory simulation equations and three aspects of the work.
Thirdly, the design of aerial penetrating bomb flight trajectory.From acomprehensive consideration of the relationship between aerial penetrating bombend-games constraint conditions and its trajectory, this thesis designs a trajectoryconsisting of turn phase, terminal guidance phase, and attitude control phase, and theirrespective guidance methods, i.e.,fixed overload scheme guidance, optimal guidance lawand attitude scheme guidance.
Fourthly,the design of an optimal guidance law. To solve problems in terminalguidance phase,on the basis of optimal control theory, this thesis introducesmissileoverload information to optimal guidance law and designs an optimal guidance law withcomprehensive consideration of restraints from terminalimpactangular(orientation angular)to terminal velocity.
Fifthly, the design of terminal active attitude control scheme. For attitude controlphase, active attitude aiming guidance scheme is designed to realize small attack angelin end-games.
In the end,through simulation program, a simulation test is done to check the