标题: | 拦截飞弹的导引与姿态控制 Guidance and Attitude Control of Missile Interceptor |
作者: | 何威德 Wei-Te He 林清安 Ching-An Lin 电控工程研究所 |
关键字: | 拦截飞弹;姿态控制;真比例导引律;missile;interceptor;attitude control |
公开日期: | 2007 |
摘要: | 本论文的主旨是探讨拦截飞弹中途与终端三维导引律以及转向与姿态控制系统的设计。因为在中途及终端阶段的导引加速度均须由弹体侧向的推力器来达成,而在终端阶段红外线寻标器必须一直锁定目标,真比例导引律似为最恰当的选择。本文推导三维真比例导引律的公式,并以模拟分析系统参数如雷达量测误差大小、红外线寻标器的锁定距离、飞行控制系统的频宽等对拦截效能的影响。拦截飞弹的转向与姿态控制均以开关式推力器为致动器。转向控制系统是单纯以脉冲宽度调变的方式来达到导引加速度的需求。维持三轴稳定的姿态控制系统是以线性化的模式进行线性设计,采姿态角及角速度回授,并以脉冲宽度调变的方式合成。数值模拟以标准飞弹三型为蓝本。模拟结果可提供未来硬体发展的参考。 The thesis investigates three-dimensional midcourse and terminal guidance laws for missile interceptor and the associated divert and attitude control system design. Since the commanded guidance acceleration, in both the midcourse phase and terminal phase, is achieved using divert thrusters and in the terminal phase the infrared seeker needs to continuously lock-on to the target, true proportional navigation guidance law seems to be the most appropriate choice among the various guidance laws. We derive the three-dimensional true proportional navigation guidance law and analyze, via simulations, various system parameters such as radar measurement errors, seeker lock-on range, and flight control system bandwidth, have on the performance of the interceptor. Divert and attitude control system use on-off thrusters as actuators. Divert control achieves the command guidance acceleration using pulse width modulation (PWM), in which the pulse duration is proportional to the magnitude of acceleration command. Attitude control system is linear and designed using linearized model, it uses angle and rate feedback, achieves three-axis stabilization and is implemented using PWM. Simulations for both guidance and control use Standard Missile III as a prototype. Results from this research should be useful for future system and hardware development. |
URI: | http://140.113.39.130/cdrfb3/record/nctu/#GT009512574 http://hdl.handle.net/11536/38281 |
显示于类别: | Thesis |