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1.
Integrated Game Based Guidance with Nonlinear Autopilot Design for Maneuvering Target Interception
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Li‐Chen Fu 《Asian journal of control》2014,16(2):431-440
The integrated game theory based guidance law with nonlinear autopilot (GGNA) system is presented in this paper. The guidance law is designed based on linear differential game theory while considering the motion of the target in 3‐D space such that the distance between the missile and the target is minimized faster than before. The autopilot system based on quaternion representation is developed using sliding mode control method to generate the attitude command. The stability of the integrated guidance and nonlinear autopilot system is analyzed with Lyapunov stability theory. In addition, this research assumes wingless missiles in our context in order to reduce the nonlinear effect from the aerodynamics. Furthermore, in order to extend the operation range of missiles from endo‐atmosphere to exo‐atmosphere, the missiles are equipped with Thrust Vector Control (TVC) mechanisms and Divert Control System (DCS). Finally, extensive simulations incorporating aerodynamic models are demonstrated to verify the validity of the proposed integrated guidance/autopilot systems. Moreover, the simulation results reveal that the mission of intercepting a maneuvering target is successfully accomplished. 相似文献
2.
基于LQR最优控制思想提出一种针对巡航导弹BTT控制的设计方法。首先基于巡航导弹的气动外形及飞行特点建立数学模型,然后根据导弹控制器设计要求,合理选取状态变量,采用积分型LQR控制设计最优控制律,最后的仿真结果表明,导弹能够无静差的跟踪过载及滚转指令,并有效的抑制了侧滑角的产生。 相似文献
3.
To satisfy the terminal position and impact angel constraints, an optimal guidance problem was discussed for homing missiles. For a stationary or a slowly moving target on the ground, an extended trajectory shaping guidance law considering a first-order autopilot lag (ETSGL-CFAL) was proposed. To derive the ETSGL-CFAL, a time-to-go-nth power weighted objection function was adopted and three different derivation methods were demonstrated while the Schwartz inequality method was mainly demonstrated. The performance of the ETSGL-CFAL and the ETSGL guidance laws was compared through simulation. Simulation results show that although a first-order autopilot is introduced into the ETSGL-CFAL guidance system, the position miss distance and terminal impact angle error induced by the impact angle is zero for different guidance time. 相似文献
4.
BTT导弹变结构自适应控制仿真研究 总被引:3,自引:1,他引:2
一种变结构自适应控制律,可以不依赖于系统的精确数学模型,但对于BTT导弹气动参数不确定性具有良好的控制效果.采用Matlab,分别对BTT导弹滚转、偏航以及俯仰三个通道进行数值仿真,接着又对闭环系统进行了仿真验证,根据对仿真结果的分析,对该控制律进行了进一步的改进.所设计的改进控制律很好地解决了导弹数学模型不能精确获得以及参数大范围变化的问题,并且在很大程度上克服了导弹各通道间存在的耦合现象,与其它控制方法比较,具有算法相对简单,并且易于仿真验证的特点,对BTT导弹自动驾驶仪研究具有很好的指导意义. 相似文献
5.
基于自抗扰技术的高超声速飞行器控制系统设计 总被引:3,自引:3,他引:0
高超声速飞行器在飞行过程中超燃冲压发动机对攻角及侧滑角有较严格的要求,为实现对攻角及侧滑角的精确控制,文章采用自抗扰控制技术设计了高超声速飞行器的攻角自动驾驶仪;首先建立高超声速飞行器控制系统的数学模型,然后采用扩张状态观测器对受扰对象的状态和干扰进行观测,并对状态误差采用非线性反馈,对观测的干扰进行补偿,从而实现对干扰的快速抑制和对指令的精确跟踪,最后仿真表明所设计的自动驾驶仪满足性能要求,验证了该方法的正确性。 相似文献
6.
7.
自动驾驶仪是无人机飞行控制系统的核心装置。本文设计的自动驾驶仪采用了两个处理器,且导航控制系统与姿态控制系统控制是分开的。它不仅具有高精度、高效率的性能,同时还具有通用性。文中对所设计的自动驾驶仪的结构和主要部件进行了介绍,同时着重分析了自主飞行模块。最后对飞行姿态进行仿真分析,仿真结果表明该系统满足性能要求。 相似文献
8.
Accounting for the missile autopilot as second-order dynamics, an observer-based guidance law is designed based on the dynamic surface control method. Some first-order low-pass filters are introduced into the design process to avoid the occurrence of high-order derivatives of the line of sight angle in the expression of guidance law such that it can be implemented in practical applications. The proposed guidance law is effective in compensating the bad influence of the autopilot lag on guidance accuracy. In the simulations of intercepting non maneuvering targets, targets with step acceleration, and targets with sinusoidal acceleration respectively, the guidance law is compared with the adaptive sliding mode guidance law in the presence of missile autopilot lag. The simulation results show that the proposed guidance law is able to guide a missile to accurately intercept a maneuvering target, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag. 相似文献
9.
A novel model reference adaptive robust fuzzy control algorithm is presented for ship steering autopilot, which is an uncertain nonlinear system. In the proposed algorithm, fuzzy logic systems have been used to approximate lumped unknown function in the ship steering systems and the adaptive mechanism with minimal learning parameter, i.e. only one parameter, has been achieved by use of Lyapunov approach. The proposed methodology is verified using the simulation mode of the Dalian Maritime University's ocean-going training ship named Yulong. It is shown that the proposed algorithm guarantees that the ship steering autopilot system is asymptotically stable and its tracking error can approach to zero. 相似文献
10.
A multivariable missile autopilot is synthesized using an H∞ approach. A tradeoff is achieved between performance, actuators solicitation and uncertainties in the actuators and bending modes dynamics. Robust stability and performance of the control law are then studied in the face of large real parametric aerodynamic uncertainties: computational techniques for real and mixed μ analysis (namely De Gaston and Safonov's, Dailey's, Jones’, Young and Doyle's, Fan, Tits and Doyle's and Safonov and Lee's methods) are briefly reviewed before being used to compute either the exact value, or an interval of the structured singular value (SSV). For small amounts of parameters, the upper and lower bounds provided by these methods are compared to the exact value, computed by De Gaston and Safonov's method. For larger amounts of parameters, NP hardness of the problem prohibits the use of algorithms which compute the exact value: these algorithms are indeed necessarily exponential-time. As an alternative in this case, the use of polynomial-time methods for computing upper and lower bounds leads in our examples to accurate approximates of the real and mixed structured singular values. 相似文献