【武器系统】【2005.09】寻的导弹动力学建模、制导与控制
本文为土耳其中东技术大学（作者：BüLENT ÖZKAN）的博士论文，共273页。
本文主要研究具有两个相对转动部件的导弹动力学建模、制导和控制问题。导弹的两部分通过滚柱轴承相互连接。在研究的第一部分，我们推导了导弹的运动微分方程。然后，考虑弹体之间的相对旋转，利用TüBİTAK-SAGE中的导弹Datcom软件，建立了导弹的气动模型。利用生成的气动数据得到所需的气动稳定性导数后，根据导弹的运动方程确定了所需的传递函数。其次，制定了本研究所考虑的导引律。
本文介绍了线性寻的制导律和抛物线寻的制导律作为比例导引律的替代。在此基础上，对比例导引律进行了空间推导。然后，利用确定的传递函数设计了横滚、俯仰和偏航自动驾驶仪。由于横滚自动驾驶仪是用来调节导弹前体滚转角的，因此俯仰和偏航自动驾驶仪的设计是为了实现由制导律产生的指令信号。制导指令以导弹的横向加速度分量或飞行轨迹角的形式存在，然后，针对一个典型的曲面目标建立了目标运动学模型。作为工作的补充，目标状态估计器的设计是作为一阶衰退记忆滤波器。最后，综合上述模型，构建了整个制导控制系统。利用整个系统模型，利用Matlab-simulink软件进行了计算机仿真，并与比例导引律进行了比较。对于选定的单体导弹，这种比较是重复的。最后对仿真结果进行了讨论，并对研究结果进行了评价。
In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then, regarding the relative rotation between the bodies, the aerodynamic model of the missile is constructed by means of the Missile Datcom software available in TüBİTAK-SAGE. After obtaining the required aerodynamic stability derivatives using the generated aerodynamic data, the necessary transfer functions are determined based on the equations of motion of the missile. Next, the guidance laws that are considered in this study are formulated. Here, the Linear Homing Guidance and the Parabolic Homing Guidance laws are introduced as alternatives to the Proportional Navigation Guidance law. On this occasion, the spatial derivation ofthe Proportional Navigation Guidance law is also done. Afterwards, the roll, pitch and yaw autopilots are designed using the determined transfer functions. As the roll autopilot is constructed to regulate the roll angle of the front body of the missile which is the controlled part, the pitch and yaw autopilots are designed to realize the command signals generated by the guidance laws. The guidance commands are in the form of either the lateral acceleration components or the flight path angles of the missile. Then, the target kinematics is modeled for a typical surface target. As a complementary part of the work, the design of a target state estimator is made as a first order fading memory filter. Finally, the entire guidance and control system is built by integrating all the models mentioned above. Using the entire system model, the computer simulations are carried out using the Matlab-Simulink software and the proposed guidance laws are compared with the Proportional Navigation Guidance law. The comparison is repeated for a selected single-body missile as well. Consequently, the simulation results are discussed and the study is evaluated.
- 引言
- 导弹模型
- 导弹导引
- 导弹控制
- 目标运动估计
- 案例研究
- 讨论与结论
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