共查询到19条相似文献,搜索用时 125 毫秒
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针对不确定性定常系统,在非线性运动学基础上,提出了一种基于全程滑动模态的制导律;该方法将目标机动加速度视为有界干扰,并在控制律中引入与状态有关的变因子项,改善了系统的瞬态性能,消除了能达阶段,克服了未知参数摄动的影响,提高了系统的鲁棒稳定性;比较了相同初始条件下基于全程滑动模态的变结构制导和比例制导的脱靶量、视线角速度及控制律;结果表明,基于全程滑模动态的变结构制导律具有精度高、鲁棒性强以及便于工程设计的特点. 相似文献
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针对导弹拦截机动目标的末制导问题,基于有限时间滑模控制理论设计一种带有攻击角度和导弹视场角约束的制导律.首先,将导弹末制导问题转化为带有状态约束的制导系统稳定问题,设计一种新型的非奇异终端滑模面和时变的障碍Lyapunov函数,给出一种终端滑模制导律的设计方法,并针对目标机动的不确定性设计一种对目标机动上界的自适应估计;然后,通过稳定性理论证明制导系统的状态变量最终是有限时间收敛的,并且结合时变的障碍Lyapunov函数和滑模面的设计特性证明在末制导过程中视场角约束条件始终不会被违背,相比于现有的考虑视场角约束的制导律,该制导律不存在指令转换,能够加快制导系统收敛速率,增强制导系统的抗干扰能力;最后,通过仿真实验验证所提出制导方法的有效性. 相似文献
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针对反辐射无人机攻击空中机动目标的特点,提出了一种利用MGEKF滤波算法估计无人机-目标接近速度信息的变结构导引律;该导引律利用变结构控制的干扰不变性特性,将目标机动看成是未知的有界干扰,实现了目标有界机动条件下视线角速度的零化;同时针对无人机和目标的接近速度信息不能直接测量的特点,对典型的目标运动模式进行运动状态估计;最后在无人机非线性六自由度仿真模型上仿真证明,其末制导精度优于传统广义比例导引律,且具有较好的工程应用前景。 相似文献
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针对导弹和目标相对运动学关系,利用许瓦兹不等式,提出了一种新的基于制导品质最优的末制导律。在导弹和目标的三维相对运动关系的基础上,忽略三维制导平面的耦合因素,同时考虑二阶的弹体响应环节,建立了导弹制导系统的数学模型。基于在有限时间内零化弹目相对距离和零化弹目视线角速率,以及导弹机动能量最小的优化制导品质的思想,利用许瓦兹不等式推导出一种用解析形式表示的最优末制导律。这种最优制导律通过估算剩余时间,实现对目标的有效拦截。最后通过数字仿真,验证了在脱靶量、弹目视线角速率和机动能量的制导品质方面,所提出的最优制导律要优于一般的比例制导律。 相似文献
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针对拦截机动目标的末制导问题,设计一种带攻击角度约束的末制导律.该制导律构造一种新型的固定时间收敛非奇异终端滑模面,能够在解决终端滑模面奇异性问题的同时使得滑模面、弹目视线角和弹目视线角速率在固定时间内收敛,保证收敛时间的上界是独立于弹目初始条件,可以被预先设定的.与传统的固定时间收敛控制相比,该制导律通过调节滑膜面和弹目视线角误差的趋近律指数使得制导系统收敛速率更快.同时,针对目标机动引起的未知扰动,引入一种扩张状态观测器进行估计,能够增强制导系统的鲁棒性,避免震颤现象的发生.最后,通过仿真实验验证所提出制导律能够以不同的攻击角度对机动目标进行有效拦截,且与其他制导律相比,所提出的制导律使得制导系统收敛更快,导弹拦截时间更短,拦截精度更高. 相似文献
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针对单舵控制导弹舵角在大攻角下易饱和的问题, 提出一种适用于双舵控制导弹的制导控制一体化模糊滑模方法. 分析具有鸭舵/尾舵结构导弹动力学特性, 建立制导控制一体化模型, 利用双滑模变结构控制方法, 分别选取零控脱靶量和控制相关量作为滑动模态, 前者保证脱靶量趋于零, 后者提供阻尼响应, 将制导律嵌入在控制器的设计之中. 为了克服滑模抖振问题, 利用指数趋近率方法设计控制器, 并将模糊环节加入控制器中. 最后, 对拦截蛇形机动目标的过程进行仿真, 仿真结果验证了所提出方法的有效性.
相似文献11.
A new formulation of the proportional navigation guidance law using the continuous time nonlinear predictive control approach is proposed. The guidance law needs information about the target acceleration for its implementation, which is generally not available. In this paper, this problem is addressed by estimating the target acceleration using the time delay control (TDC). The effectiveness of the guidance law and the estimation of the target acceleration is demonstrated by simulation in a realistic scenario against a highly maneuvering target. 相似文献
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考虑导弹自动驾驶仪动态特性的带攻击角度约束制导律 总被引:1,自引:0,他引:1
针对打击机动目标时带攻击角度约束的制导问题,采用扩张状态观测器和动态面控制方法设计一种考虑自动驾驶仪动态特性的制导律.考虑期望视线角的变化率正比于未知的目标加速度,采用扩张状态观测器对未知目标加速度进行估计.为了避免奇异问题,并克服非匹配不确定项对系统性能的影响,采用非奇异终端滑模和动态面控制方法进行制导律设计.与传统的将目标加速度设为零的制导律相比较,仿真结果表明所提出的制导律具有良好的制导性能. 相似文献
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Xinxin Wang Ge Lan Yefeng Yang Hongqian Lu Xianlin Huang 《Asian journal of control》2023,25(2):1130-1144
To intercept the maneuvering target at a desired terminal angle, this paper presents a time-varying sliding mode guidance law with consideration of the second-order autopilot dynamics and input saturation. To achieve the finite-time interception and satisfactory overload characteristics, a time-varying sliding mode guidance law is developed, which enables the line-of-sight (LOS) angle error to converge into a small neighborhood of the origin at the interception time. An auxiliary system is constructed to reduce the adverse effect generated from the input saturation. Moreover, with the aid of extended state observers, the proposed guidance law requires no information on the target acceleration and the acceleration derivative of the interceptor. The performance of this guidance law is verified via the numerical simulations. 相似文献
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Proportional navigation (PN) is an effective guidance law in chasing a constant speed target. However, intercepting a maneuvering target requires extra provisions to contain target acceleration. This is observed in the next generation of guidance laws, namely augmented proportional navigation (APN) and the optimal guidance law (OGL). The other advanced guidance method is integral sliding mode (ISM), which exhibits superb low miss distance (MD), but unfortunately at the cost of disappointing effective lateral acceleration (Ceff), higher than the modest level that APN and OGL demand. Reducing both MD and Ceff can be achieved using a multiphase algorithm. A setup of APN, OGL and ISM is proposed to integrate the strength of each and overcome their weaknesses. Hybrid algorithm smooth management is conducted by an optimally tuned fuzzy supervisory controller. The results indicate that in facing a constant acceleration target, an APN‐ISM twin yields the best results, while in case of a constant jerk target an APN‐OGL‐ISM triplet renders excellent interception. Miss distance as low as 0.012m can be achieved with significantly lower control effort than required by ISM alone. The simulations results confirm the conclusions and illustrate the capacity of the algorithm in combating maneuvering targets. 相似文献
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This paper proposes a novel three‐dimensional missile guidance law design based on nonlinear H∞ control. The complete nonlinear kinematics of pursuit–evasion motion is considered in the three‐dimensional spherical co‐ordinates system; neither linearization nor small angle assumption is made here. The nonlinear H∞ guidance law is expressed in a simple form by solving the associated Hamilton–Jacobi partial differential inequality analytically. Unlike adaptive guidance laws, the implement of the proposed robust H∞ guidance law does not require the information of target acceleration, while ensuring acceptable interceptive performance for arbitrary target with finite acceleration. The resulting pursuit–evasion trajectories for both the H∞‐guided missile and the worst‐case target are determined in closed form, and the performance robustness against variations in target acceleration, in engagement condition, and in control loop gain, is verified by numerical simulations. Copyright © 2001 John Wiley & Sons, Ltd. 相似文献
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Adaptive nonsingular fast terminal sliding mode guidance law with impact angle constraints 总被引:2,自引:0,他引:2
Junhong Song Shenmin Song Huibo Zhou 《International Journal of Control, Automation and Systems》2016,14(1):99-114
This paper considers the terminal guidance problem of missiles intercepting maneuvering targets with impact angle constraints. Based on an advanced nonsingular fast terminal sliding mode control scheme and adaptive control, an adaptive nonsingular fast terminal sliding mode guidance law is proposed in the presence of the target acceleration as an unknown bounded external disturbance. In the design procedure, an adaptive law is presented to estimate the unknown upper bound of the external disturbance. Theoretical analysis shows that the proposed guidance law can guarantee the finite-time convergence in both the reaching phase and the sliding phase by applying a Lyapunov-based approach. Numerical simulations are presented to demonstrate the effectiveness of the proposed guidance law. Although the proposed guidance law is developed for the constant speed missiles, by the extensive numerical simulations with a realistic missile model, the performance is shown to be equally good for the varying speed missiles. 相似文献
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在舰炮网络化弹药打击近岸机动目标的末制导段,提出了一种考虑攻击角约束的有限时间分布式模糊协同制导律.构建网络化弹药–目标相对运动模型,设计扩张状态观测器估计目标的切向、法向加速度.在视线切向,为保证命中时刻在有限时间内趋于一致,采用积分滑模设计分布式有限时间协同制导律;在视线法向,为在有限时间内零化视线角误差、视线角速率并改善控制指令终端发散现象,采用非奇异终端滑模设计两阶段制导律.为削弱控制指令抖振、补偿干扰,设计模糊自适应系统,并通过Lyapunov理论证明了全系统状态的一致最终有界性与有限时间收敛性.仿真实验表明:该制导律使网络化弹药在打击机动形式不同的目标时,均具备较好的协同制导性能. 相似文献