共查询到19条相似文献,搜索用时 93 毫秒
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根据便携式防空导弹控制系统的特点,分析了单通道旋转导弹的控制原理及系统组成,在模拟自动驾驶仪的基础上针对某型防空导弹提出了数字化自动驾驶仪的改进设计方案,通过仿真验证了数字驾驶仪有效的提高了导弹精度. 相似文献
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首先将导弹控制模型化成级联的结构。然后应用反演控制及鲁棒控制技术提出了一种新的非线性导弹自动驾驶仪控制算法,并应用Lyapunov稳定性理论证明了系统是全局指数稳定的,最后进行了数字仿真,结果表明该算法的有效性。 相似文献
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主要研究中继卫星H∞回路成形姿态稳定控制问题。中继卫星具有弱阻尼的柔性模态频率和晃动模态频率,并且模态频率具有不确定性,同时系统增益也存在有较大的变化。首先利用拉格朗日方程建立了该卫星的动力学方程,描述了系统存在的结构不确定性,然后设计了H∞回路成形控制器。在设计过程中,首先提出了控制系统所需要满足的鲁棒稳定性和鲁棒性能指标;随后利用H∞回路成形理论设计了卫星的姿态稳定控制器,利用ν间隔度量方法对所设计的控制器进行了降阶处理,并且对所设计的控制器进行了鲁棒稳定性和鲁棒性能分析;最后通过数学仿真证明了所设计的控制器的有效性。 相似文献
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李阳 《自动驾驶仪与红外技术》1994,(4):0021-0024,,50,
本文针对防空导弹气动参数大范围剧烈变化和静不稳定特点,运用变结构控制方法进行自动加强仪设计。数字仿真表明变结构自动驾驶仪具有良好的稳定和操纵性能。 相似文献
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在导弹俯仰通道中存在输入未建模动态情况下,提出了一种基于RBF神经网络和反演控制技术的神经网络自动驾驶仪的设计方法。首先应用两个RBF神经网络对输入未建模动态设计了神经网络逆补偿器,然后利用反演控制技术设计了导弹纵向自动驾驶仪。最后给出仿真结果显示了该设计方法的有效性。 相似文献
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陶健美 《自动驾驶仪与红外技术》2008,(2)
下一代近程空-空导弹将以在近程空-空战斗中具有很强的机动性为主要特征。而相应系统的强非线性和快速时变动态特性,都将为自动驾驶仪的设计带来巨大挑战。利用现代的鲁棒设计方法论,例如带有动压控制器调参的合成的综合设计法将产生一个完整的高性能的自动驾驶仪。全方位的仿真和几项飞行试验验证了整个飞行过程的鲁棒性和工作性能。 相似文献
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在电传飞机纵向自动驾驶仪控制律的初步设计过程中,以电传飞机的纵向低阶等效系统为控制对象,采用零极点偶配置方法合理地配置零极点偶,使纵向自动驾驶仪控制律的设计得到了最大程度的简化,用所获得的控制律进行了数字仿真,仿真结果表明,纵向自动驾驶仪各个功能模式获得了良好的动态响应特性,满足了各项指标的要求,从而证明了这种设计方法是简便可行的。 相似文献
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本文提出一种改进自动驾驶仪性能的方案。在导弹自动驾驶仪原回路的基础上增加Robust控制器,这种方案可提高驾驶仪对参数变化的Robust性能。本文详细叙述了Robust控制器结合自动驾驶仪的设计方法,并用仿真结果说明了Robust控制器在本算例中所起的作用。 相似文献
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基于自适应模糊滑模退步控制的直接力/气动力复合控制导弹自动驾驶仪设计 总被引:2,自引:0,他引:2
针对直接力/气动力复合控制导弹所具有的强耦合非线性特性,提出了一种基于自适应模糊滑模退步控制的自动驾驶仪设计方法.该方法利用自适应模糊系统所具有的万能逼近特性,对大迎角飞行过程中导弹动力学方程中存在的非线性函数进行逼近,并利用变结构控制所具有对干扰的强鲁棒性,构造误差系统滑模面,克服了逼近误差和外界干扰对控制系统的影响,实现了对大机动指令的精确跟踪.仿真结果表明,所设计的自动驾驶仪对过载指令有良好的跟踪效果,对模型不确定性和外界干扰具有鲁棒性. 相似文献
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Adaptive block dynamic surface control for integrated missile guidance and autopilot 总被引:3,自引:3,他引:0
A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach. The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space. The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties. A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem. The stability of the closed-loop system is proven based on the Lyapunov theory. The six degrees of freedom (6DOF) nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics. 相似文献
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White B.A. Bruyere L. Tsourdos A. 《IEEE transactions on aerospace and electronic systems》2007,43(4):1470-1483
This paper presents the design of a missile autopilot over its flight envelop using quasi-linear parameter-varying polynomial eigenstructure assignment (PEA). The paper describes the extension of PEA to parameter-varying systems using a nonlinear missile model developed by Horton as an example. The autopilot is designed for a single-plane lateral acceleration control and a 5 degree of freedom (DOF) autopilot is also designed. Both lateral acceleration and augmented lateral acceleration outputs are considered. The lateral acceleration autopilot has nonminimum phase characteristics, and it is shown that the quasi-linear parameter-varying PEA approach can handle nonminimum phase systems unlike classic dynamic inversion techniques. Simulation results are presented over fast variations in Mach number and show that the design is robust. 相似文献
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《中国航空学报》2016,(5):1302-1312
The acceleration autopilot design for skid-to-turn (STT) missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of inte-grated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC) with a partial state nonlinear observer (PSNLO) for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The pro-posed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are mod-eled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simula-tion is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature. 相似文献
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Jin Young Choi Dongkyoung Chwa Min-Soo Kim 《IEEE transactions on aerospace and electronic systems》2000,36(2):467-481
A robust adaptive control scheme is proposed that can be applied to a practical autopilot design for feedback-linearized skid-to-turn (STT) missiles with aerodynamic uncertainties. The approach is to add a robust adaptive controller to a feedback-linearizing controller in order to reduce the influence of the aerodynamic uncertainties. The proposed robust adaptive control scheme is based on a sliding mode control technique with an adaptive law for estimating the unknown upper bounds of uncertain parameters. A feature of the proposed scheme is that missile systems with aerodynamic uncertainties can be controlled effectively over a wide operating range of flight conditions. It is shown, using Lyapunov stability theory, that the proposed scheme can give sufficient tracking capability and stability for a feedback-linearized STT missile with aerodynamic uncertainties. The six-degree-of-freedom nonlinear simulation results also show that good performance for several uncertainty models and engagement scenarios can be achieved by the proposed scheme in practical night conditions 相似文献