共查询到19条相似文献,搜索用时 140 毫秒
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基于纯比例导引的拦截碰撞角约束制导策略 总被引:1,自引:0,他引:1
拦截碰撞角约束制导是当前导弹制导研究的关键问题之一。首先基于理想比例导引(IPN)律拦截非机动目标的解析解,推导了纯比例导引律(PPN)拦截固定目标的解析解,得到了弹目相对距离、制导指令加速度和导弹前置角的显示表达式,并进一步得到了拦截碰撞角与弹目相对运动状态和比例导引系数之间的解析表达式。其次,基于该解析表达式,提出了基于PPN的拦截碰撞角约束制导策略(PPNIACG),并探讨了在铅垂面内进行落角约束打击和水平面内进行拦截碰撞角约束打击的2种实现方式。最后,以弹道成型制导律(TSG)和最优碰撞角约束制导律(OIACG)为参考,通过数值仿真算例,对PPNIAC的拦截性能进行了对比分析,验证了所提出制导策略的有效性和正确性。 相似文献
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针对现代导弹武器多约束、高精度制导的基本要求,在综合考虑带落角和末端攻角约束的条件下,用二次型最优控制推导出一种新的最优末制导律。仿真结果表明,该末制导律既能够满足高精度制导的要求,同时也能够满足对落角和末端攻角的控制要求。 相似文献
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基于一般弹目平面运动模型,以视线角、视线角速率为状态变量将弹目运动关系转换为二阶控制系统状态空间表达,把制导律设计转化为系统控制律的设计问题.在此控制模型的基础之上,利用Lyapunov稳定性定理,以视线角速率平方项作为能量函数设计了一种新型的扩展比例导引律,与其他扩展比例导引律相比,该导引律不需要增加任何制导观测信息,可以有效抑制噪声影响,并将基于Lyapunov稳定性的末制导律设计方法推广到有终端角约束的制导律设计中.仿真结果比较表明,该制导律可以提高制导精度、有效减小制导信息中的噪声影响. 相似文献
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本文利用微分对策理论方法研究了在三维空间里,以一阶惯性环节考虑导弹和目标动力学因素的最优制导律问题。给出了一个矢量形式的最优反馈制导律,并在反馈增益中引用了系统控制刚度参量k,进而给出了新的综合意义。 最后,在一定条件下,通过进一步近似还给出了一个次优制导律。 相似文献
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Optimal guidance of extended trajectory shaping 总被引:3,自引:1,他引:2
To control missile's miss distance as well as terminal impact angle, by involving the timeto-go-nth power in the cost function, an extended optimal guidance law against a constant maneuvering target or a stationary target is proposed using the linear quadratic optimal control theory.An extended trajectory shaping guidance(ETSG) law is then proposed under the assumption that the missile-target relative velocity is constant and the line of sight angle is small. For a lag-free ETSG system, closed-form solutions for the missile's acceleration command are derived by the method of Schwartz inequality and linear simulations are performed to verify the closed-form results. Normalized adjoint systems for miss distance and terminal impact angle error are presented independently for stationary targets and constant maneuvering targets, respectively. Detailed discussions about the terminal misses and impact angle errors induced by terminal impact angle constraint, initial heading error, seeker zero position errors and target maneuvering, are performed. 相似文献
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Generalized guidance law for homing missiles 总被引:1,自引:0,他引:1
Ciann-Dong Yang Fei-Bin Hsiao Fang-Bo Yeh 《IEEE transactions on aerospace and electronic systems》1989,25(2):197-212
The concept of a generalized guidance law is presented, and the closed-form solution for a homing missile pursuing a maneuvering target according to generalized guidance laws is given. It is shown that the guidance laws appearing in the literature are merely special cases of the one proposed by the authors. The derived generalized forms of capture area, missile acceleration, and homing time duration that are derived provide insight into the performance of the guidance laws being considered and lead to the discovery of new ones. The problem of finding a nonlinear optimal guidance law for a homing missile with controlled acceleration, applied so as to capture a maneuvering target with a predetermined trajectory while minimizing a weighted linear combination of time of capture and energy expenditures, is solved in closed form. The derived optimal control law is equal to the LOS (line of sight) rate multiplied by a trigonometric function of the aspect angle. Numerical simulation shows that the resulting guidance law appears to yield a significant advantage over true proportional navigation 相似文献
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针对打击机动目标的制导问题,设计了一种同时考虑攻击角度约束、自动驾驶仪动态特性和固定时间收敛的新型制导律。首先,基于非奇异终端滑模控制和固定时间稳定性理论,采用反步递推方法设计制导律。在制导律设计过程中,设计了一种固定时间收敛的非奇异终端滑模面,基于固定时间控制和滑模控制,设计虚拟控制律,构造一种非线性一阶滤波器解决传统反步设计中的"微分膨胀"问题。基于超螺旋算法和固定时间稳定性理论,设计了一种固定时间收敛的滑模干扰观测器,用于估计目标机动等干扰。然后,基于Lyapunov稳定性理论,对制导律的固定时间稳定性进行了证明,并给出了收敛时间的表达式。最后,通过仿真分析,验证了所提制导律的有效性,和现有制导律相比,所提制导律具有较高的制导精度和角度约束精度、较快的系统收敛速度以及较少的能量消耗。 相似文献
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Impact time control guidance against maneuvering targets based on a nonlinear virtual relative model
Aiming at the problem of high-precision interception of air-maneuvering targets with impact time constraints, this paper proposes a novel guidance law based on a nonlinear virtual relative model in which the origin is attached to the target. In this way, the original maneuvering target is transformed into a stationary one. A polynomial function of the guidance command in the range domain with two unknown coefficients is introduced into the virtual model, one of the coefficients is determined to ... 相似文献
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一种新型三维制导律设计的非线性方法 总被引:6,自引:1,他引:6
结合微分几何和李群方法的优点,设计了一种非解耦的新型三维(3D)制导律。首先,基于微分几何理论,得到了导弹运动的微分几何描述方程,无需估计剩余飞行时间。然后,通过李群旋量描述,建立了视线方位角与视线角速率之间的联系。最后,在以上工作的基础上,利用李雅普诺夫稳定理论,针对导弹制导的无终端约束和有终端约束情况分别进行了相应制导律设计。该制导律不需要估算剩余飞行时间,并且能够满足终端角度约束的要求。仿真结果表明:所设计制导律能够适应于高速、大机动倾斜转弯(BTT)导弹精确制导。 相似文献
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Three-dimensional adaptive finite-time guidance law for intercepting maneuvering targets 总被引:1,自引:0,他引:1
《中国航空学报》2017,(6)
To intercept maneuvering targets at desired impact angles, a three-dimensional terminal guidance problem is investigated in this study. Because of a short terminal guidance time, a finitetime impact angle control guidance law is developed using the fast nonsingular terminal sliding mode control theory. However, the guidance law requires the upper bound of lumped uncertainty including target acceleration, which may not be accurately obtained. Therefore, by adopting a novel reaching law, an adaptive sliding mode guidance law is provided to release the drawback. At the same time, this method can accelerate the convergence rate and weaken the chattering phenomenon to a certain extent. In addition, another novel adaptive guidance law is also derived; this ensures systems asymptotic and finite-time stability without the knowledge of perturbations bounds.Numerical simulations have demonstrated that all the three guidance laws have effective performances and outperform the traditional terminal guidance laws. 相似文献
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An adaptive fast fixed-time guidance law with an impact angle constraint for intercepting maneuvering targets 总被引:1,自引:0,他引:1
Sliding mode guidance laws based on a conventional terminal sliding mode guarantees only finite-time convergence, which verifies that the settling time is required to be estimated by selecting appropriate initial launched conditions. However, rapid convergence to a desired impact angle within a uniform bounded finite time is important in most practical guidance applications. A uniformly finite-time/fixed-time convergent guidance law means that the convergence (settling) time is predefined independently on initial conditions, that is, a closed-loop convergence time can be estimated a priori by guidance parameters. In this paper, a novel adaptive fast fixed-time sliding mode guidance law to intercept maneuver targets at a desired impact angle from any initial heading angle, with no problems of singularity and chattering, is designed. The proposed guidance law achieves system stabilization within bounded settling time independent on initial conditions and achieves more rapid convergence than those of fixed-time stable control methods by accelerating the convergence rate when the system is close to the origin. The achieved acceleration-magnitude constraints are rigorously enforced, and the chattering-free property is guaranteed by adaptive switching gains. Extensive numerical simulations are presented to validate the efficiency and superiority of the proposed guidance law for different initial engagement geometries and impact angles. 相似文献
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This paper deals with the problem of guidance law design for the single moving mass controlled reentry vehicle when impact angle constraints and maneuvering target are taken into consideration. More specifically, a modified rolling guidance law is proposed with the interactive virtual target and the landing point prediction strategy. First, considering the fact that the roll channel can be controlled directly, the relative motion between the single moving mass controlled reentry vehicle and the ... 相似文献