SDB小直径炸弹飞行控制系统设计与仿真研究

菜单

摘要小直径炸弹(SDB)是由美国最早提出的一种新型的无动力面对称远程空地攻击武器,它采用BTT控制方式使得制导弹箭通过滚转控制系统快速地将弹体最大升力面转到理想的机动方向,同时俯仰控制系统控制弹箭在最大升力面内产生需要的机动过载。这一控制技术可充分提高制导弹箭的气动效率,有效增强其飞行动力学性能,达到良好的战技指标要求。制导弹箭BTT飞行的气动外形和控制特点决定了它是一个具有运动学耦合、惯性耦合、气动耦合和控制作用耦合的多变量被控对象。本课题拟从小直径炸弹BTT控制特点出发,分别采用保主导极点配置法和特征结构配置法等方法,设计小直径炸弹滚转通道和俯仰/偏航通道的控制律。66238

主要内容如下：

第一，根据导弹运动学耦合、气动耦合以及惯性耦合等特性分析，在适当简化和假设的基础上，选择工程上易测量的变量作为状态变量建立了BTT导弹滚转通道和俯仰/偏航通道的数学模型。

第二，为SDB滚转通道设计带有前置滤波器PID控制器。首先，选择一些有代表性的特征点（在SDB飞行包线上）来构成子系统，然后，应用带有前置滤波器的主导极点配置PID控制器的设计方法来实现子系统精确的主导极点配置。最后，设计SDB滚转时变全空域的PID控制器和前置滤波器（通过一项平滑转换增益技术）。为了验证设计的控制系统的有效性，我们用SDB真实轨迹模型滚动通道的数值进行Matlab模拟分析。

第三，为俯仰/偏航通道设计带有前馈控制器的状态反馈特征结构配置控制系统，设计方法、步骤与滚转通道相近。仿真结果表明，给出的设计方法是有效的， SDB炸弹在整个飞行过程中俯仰/偏航通道具备全局稳定性并且满足动态响应所需的品质。

毕业论文关键词小直径炸弹；PID 控制器；主导极点；鲁棒性；根轨迹；特征结构配置；状态反馈；前馈控制；

毕业设计说明书（论文）外文摘要

Title Design and Simulation of Flight Control System of Small Diameter Bomb

Abstract

Small Diameter Bomb (SDB) was first proposed by the United States, a new type non-powered weapon with symmetric and remote ground attacking characteristics. It use the BTT control mode to adjust the maximum lifting surface of the elastomer to the satisfactory mechanical direction through the roll control system and it can also produce the desired motor overload at the maximum lifting surface of the elastomer through the pitch control system. This control technology can fully improve the aerodynamic efficiency of the system of missile Arrow and effectively enhance the performance of its flight dynamics to achieve a good tactical index. The aerodynamic shape and control characteristics of the BTT missile show us a conclusion that it is a kinematic coupling, inertial coupling, Pneumatic coupling and control coupling multivariable controlled object.

The topics intend to design rollover channel and pitch / yaw channel control law of the small diameter bomb Basing on the control characteristics of BTT through Paul dominant pole placement and eigenstructure assignment methods

The main contents are as follows:

First, according to the characteristics of the missile kinematic coupling, pneumatic coupling and inertial coupling suitably simplify and assumptions based on, We select the engineering easily measured variable as a state variable for the mathematical model of the BTT missile roll channel and the pitch / yaw channel basing on suitably simplify and assumptions.

Secondly，we design a PID controller with a pre-filter for the SDB rolling channel. First, select some representative point of the flight envelope to constitute a subsystem, then an improved PID controller design method was given，which introducing a pre-filter to guarantee the accurate dominance of the assigned poles based on dominant pole placement. Finally, the global time varying pre-filter and PID controller were constructed by a smooth gain-scheduled method. we use the values in the SDB's trajectory model rolling path in Matlab simulation analysis in order to verify the effectiveness of the control system design.