期刊文献+
共找到271篇文章
< 1 2 14 >
每页显示 20 50 100
Proportional Navigation Guidance Law with Variable Coefficient Gravity Compensation 被引量:4
1
作者 杨春雷 唐胜景 师娇 《Journal of Beijing Institute of Technology》 EI CAS 2009年第3期304-308,共5页
Based upon a discussion on the merits and limitations of proportional navigation(PN)guidance law in which constant gravity compensation is included as a part,a counterpart having varying compensations,which changes ... Based upon a discussion on the merits and limitations of proportional navigation(PN)guidance law in which constant gravity compensation is included as a part,a counterpart having varying compensations,which changes with pitching angle and line-of-sight angle,is substituted.Flight trajectory simulation over a submissile model is conducted,resulting in increased impact angle,shorter miss distance,smaller maximum normal overload and narrower terminal angle of attack. 展开更多
关键词 gravity compensation proportional navigation (PN) guidance law tra)ectory simulation
下载PDF
Design and Analysis of Terminal Guidance Law for Kinetic Interceptors based on Pulse Engine
2
作者 Shixin Li Jia Ma Shuai Yue 《Journal of Electronic Research and Application》 2024年第5期95-108,共14页
A new terminal guidance law is proposed based on a solid propellant pulse engine and an improved proportional navigation method to address the terminal guidance issue for kinetic interceptors.On this basis,the start-s... A new terminal guidance law is proposed based on a solid propellant pulse engine and an improved proportional navigation method to address the terminal guidance issue for kinetic interceptors.On this basis,the start-stop curve of the pulse motor during the terminal guidance process is designed,along with its start-up logic.The effectiveness of the proposed guidance strategy is verified through simulation. 展开更多
关键词 Pulse engine Terminal guidance law Kinetic interceptor proportional navigation method
下载PDF
Extended differential geometric guidance law for intercepting maneuvering targets 被引量:4
3
作者 HUANG Jingshuai ZHANG Hongbo +1 位作者 TANG Guojian BAO Weimin 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2018年第5期1046-1057,共12页
Without assumptions made on motion states of missile and target, an extended differential geometric guidance law is derived. Through introducing a line of sight rotation coordinate system, the derivation is simplified... Without assumptions made on motion states of missile and target, an extended differential geometric guidance law is derived. Through introducing a line of sight rotation coordinate system, the derivation is simplified and has more explicit physical significances. The extended law is theoretically applicable to any engagement scenarios. Then, on basis of the extended law, a modified one is designed without the requirement of target acceleration and an approach is proposed to determining the applied direction of commanded missile acceleration. Qualitative analysis is carried out to study the capture performance and a criterion for capture is given. Simulation results indicate the two laws are effective and make up the deficiency that pure proportional navigation suitable for endoatmospheric interceptions cannot deal with high-speed maneuvering targets. Furthermore, the correctness of the criterion is validated. 展开更多
关键词 missile guidance maneuvering target extended differential geometric guidance law capture performance proportional navigation
下载PDF
Multiconstraint adaptive three-dimensional guidance law using convex optimization 被引量:6
4
作者 FU Shengnan LIU Xiaodong +1 位作者 ZHANG Wenjie XIA Qunli 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2020年第4期791-803,共13页
The traditional guidance law only guarantees the accuracy of attacking a target. However, the look angle and acceleration constraints are indispensable in applications. A new adaptive three-dimensional proportional na... The traditional guidance law only guarantees the accuracy of attacking a target. However, the look angle and acceleration constraints are indispensable in applications. A new adaptive three-dimensional proportional navigation(PN) guidance law is proposed based on convex optimization. Decomposition of the three-dimensional space is carried out to establish threedimensional kinematic engagements. The constraints and the performance index are disposed by using the convex optimization method. PN guidance gains can be obtained by solving the optimization problem. This solution is more rapid and programmatic than the traditional method and provides a foundation for future online guidance methods, which is of great value for engineering applications. 展开更多
关键词 proportional navigation(PN) adaptive guidance law three-dimensional space second-order cone programming(SOCP) convex optimal control
下载PDF
Design of Closed Loop Optimal Guidance Law Using Neural Networks 被引量:1
5
作者 ZHOU Rui 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2002年第2期98-102,共5页
It is generally impossible to obtain the analytic optimal guidance law for complex nonlinear guidance systems of homing missiles,and the open loop optimal guidance law is often obtained by numerical methods,which can ... It is generally impossible to obtain the analytic optimal guidance law for complex nonlinear guidance systems of homing missiles,and the open loop optimal guidance law is often obtained by numerical methods,which can not be used directly in practice.The neural networks are trained off line using the optimal trajectory of the missile produced by the numerical open loop optimal guidance law,and then,the converged neural networks are used on line as the feedback optimal guidance law in real time.The research shows that different selections of the neural networks inputs,such as the system state variables or the rate of LOS(line of sight),may have great effect on the performances of the guidance systems for homing missiles.The robustness for several guidance laws is investigated by simulations,and the modular neural networks architectures are used to increase the approximating and generalizing abilities in the large state space.Some useful conclusions are obtained by simulation results. 展开更多
关键词 neural networks missile guidance optimal guidance law proportional navigation guidance
下载PDF
Guidance Law Design Under Impact Angle Constraint Based on Nussbaum-type Gain Technique 被引量:1
6
作者 郭建国 周军 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第4期253-257,共5页
Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic re... Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic relationship between the missile and target in vertical plane,a mathematic model was formulated while the motion of target and the system structure perturbation were regarded as limited disturbances.Based on the ideas of zeroing the rate of line-of-sight(LOS)angle and the impact angular tracking error,a nonlinear control strategy was contrived to obtain adaptive robust guidance law by adopting Nussbaum-type gain technique under a desired impact angle.The stability of guidance system in finite time is strictly proven by using Lyapunov stability theory.Finally,the numerical simulation verifies the effectiveness of the proposed scheme. 展开更多
关键词 control and navigation technology of aerocraft STABILITY guidance law impact angle adaptive control
下载PDF
Optimum PN Guidance Law for Maneuvering Target
7
作者 孙宝彩 祁载康 《Defence Technology(防务技术)》 SCIE EI CAS 2007年第2期121-124,共4页
An optimum PN guidance law for maneuvering target is developed using optimal control theory.By estimating the target position and setting the cost function,the guidance law can be deduced even without knowing the miss... An optimum PN guidance law for maneuvering target is developed using optimal control theory.By estimating the target position and setting the cost function,the guidance law can be deduced even without knowing the missile lateral acceleration.Since the quadratic cost function can make a compromise between the miss distance and the control constraint,the optimum guidance law obtained is more general.Also,introduced line of sight rate as the input,a practical form of this guidance law is derived.The simulation results show the effectiveness of the guidance laws. 展开更多
关键词 控制 导航技术 飞机 机动性能
下载PDF
Strapdown Homing Guidance System Design for Some Ammunition 被引量:1
8
作者 宋建梅 李全运 《Journal of Beijing Institute of Technology》 EI CAS 2006年第1期43-47,共5页
The strapdown homing guidance system for some ammunition was mainly studied. A strong tracking Kalman filter was designed for the strapdown homing guidance system using the information measured by the strapdown homing... The strapdown homing guidance system for some ammunition was mainly studied. A strong tracking Kalman filter was designed for the strapdown homing guidance system using the information measured by the strapdown homing seeker to estimate relative movement variables between the ammunition and target. Then the optimal proportional law, which using the estimated information, guided the ammunition. Simulation results show that the designed strapdown homing guidance system with strong tracking Kalman filter can attack the maneuvering target effectively, and satisfy the performance index for the guided ammunition system. 展开更多
关键词 strapdown homing guidance strong tracking Kalman filter optimal proportional law
下载PDF
Impact time control using biased proportional navigation for missiles with varying velocity 被引量:12
9
作者 Guoxin SUN Qiuqiu WEN +1 位作者 Zhiqiang XU Qunli XIA 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第3期956-964,共9页
A feasible guidance scheme with impact time constraint is proposed for attacking a stationary target by missiles with time-varying velocity.The main idea is to replace the constant velocity with the future mean veloci... A feasible guidance scheme with impact time constraint is proposed for attacking a stationary target by missiles with time-varying velocity.The main idea is to replace the constant velocity with the future mean velocity;therefore, the existing time-to-go estimation algorithm of the proportional navigation guidance law can be improved to adapt to varying conditions.In order to obtain the prediction of the velocity profile, the velocity differential equation to the downrange is derived, which can be numerically integrated between the current downrange and the target position by the on-board computer.Then, a third-order polynomial is introduced to fit the velocity profile in order to calculate the future mean velocity.At the beginning of each guidance loop, the future mean velocity is predicted and the time-to-go information is updated, based on which a novel biased proportional navigation guidance law is established to achieve the impact time constraint.Finally,numerical simulation results verified the effectiveness of the time-to-go estimation algorithm and the proposed law. 展开更多
关键词 guidance Homing missiles Impact time proportional navigation guidance Time-varying velocity
原文传递
Ideal proportional navigation for exoatmospheric interception 被引量:18
10
作者 Li Kebo Zhang Taotao Chen Lei 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2013年第4期976-985,共10页
Ideal proportional navigation (IPN) is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional n... Ideal proportional navigation (IPN) is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional navigation was conducted in previous public literature, whereas the practical interception happens in the three-dimensional space. A novel set of relative dynamic equations is adopted in this paper, which is with the advantage of decoupling relative motion in the instantaneous rotation plane of the line of sight from the rotation of this plane. The dimension-reduced IPN is constructed in this instantaneous plane, which functions as a three-dimensional guidance law. The trajectory features of dimension-reduced IPN are explored, and the capture regions of dimension-reduced IPN with limited acceleration against nonmaneuvering and maneuvering targets are analyzed by using phase plane method. It is proved that the capture capability of IPN is much stronger than true proportional navigation (TPN), no matter the target maneuvers or not. Finally, simulation results indicate that IPN is more effective than TPN in exoatmospheric interception scenarios. 展开更多
关键词 Capture region Exoatmospheric interception Ideal proportional navigation Instantaneous rotation plane of line of sight Missile guidance Phase plane method
原文传递
基于协同滤波轨迹预测的机动目标RTPN拦截制导律 被引量:2
11
作者 李继广 陈欣 +3 位作者 董彦非 屈高敏 赵成功 张阿龙 《北京航空航天大学学报》 EI CAS CSCD 北大核心 2024年第1期86-96,共11页
针对当前空中威胁目标拦截的实际需求,结合拦截器本身的机动能力,基于全覆盖协同策略,提出一种协同探测的现实真比例导引律(RTPN)制导拦截方法。所提方法解决了传统RTPN方法未考虑拦截器饱和过载限制及对任意机动目标捕获区域的确定问... 针对当前空中威胁目标拦截的实际需求,结合拦截器本身的机动能力,基于全覆盖协同策略,提出一种协同探测的现实真比例导引律(RTPN)制导拦截方法。所提方法解决了传统RTPN方法未考虑拦截器饱和过载限制及对任意机动目标捕获区域的确定问题。此外,针对拦截过程中对目标运动轨迹测量误差及协同探测数据丢包所引起的数据融合精度和鲁棒性问题,提出一种分布式协同滤波算法;针对数据传输和拦截器本身动力学响应延迟等问题,提出一种航迹预测算法。仿真结果验证所提方法能够有效解决饱和过载下的捕获区域确定及动力学延迟问题,及协同探测数据融合中数据丢包所引起的鲁棒性和精度问题。 展开更多
关键词 协同拦截 机动目标 现实真比例导引律 过载限制 滤波算法 航迹预测 数据融合
下载PDF
基于粒子群优化的组合导引律模型
12
作者 许人可 龙波 +1 位作者 彭晓乐 王嘉楠 《弹箭与制导学报》 北大核心 2024年第4期53-61,共9页
针对导弹打击机动目标的问题,提出了一种基于组合导引律的粒子群优化算法以应对战场环境中的机动目标打击问题。首先对三维弹目运动关系进行分析,设计了一种包含角度和时间偏置项的比例导引律,旨在有效抑制终端角度变化,同时确保打击时... 针对导弹打击机动目标的问题,提出了一种基于组合导引律的粒子群优化算法以应对战场环境中的机动目标打击问题。首先对三维弹目运动关系进行分析,设计了一种包含角度和时间偏置项的比例导引律,旨在有效抑制终端角度变化,同时确保打击时间的精确控制。为实现最优导引律参数的求解,研究构建了以打击角、打击时间、法向加速度和脱靶量等约束条件为基础的代价函数。采用标准粒子群算法进行自适应寻优,通过迭代计算确定使代价函数最小化的最优导引律参数,进而得到满足约束条件的最优弹道。为验证算法的有效性,设置了机动目标场景,并设计了与原始比例导引律的对比仿真实验以及多种打击时间测试实验。实验结果表明,相较于传统比例导引律,基于粒子群优化的组合导引律算法在应对机动目标时能够生成满足打击时间要求及其他约束条件的弹道,并在不同打击时间设定下均展现出良好的打击效果,具有广阔的应用前景。 展开更多
关键词 组合导引律 粒子群优化 比例导引律 导航制导 滑模控制
下载PDF
远程机动飞行器地心角修正的制导方法
13
作者 王煜东 方岳 +2 位作者 郭珂 颜楚雄 李瑾 《导弹与航天运载技术(中英文)》 CSCD 北大核心 2024年第6期42-46,62,共6页
针对远程机动飞行器长时间在大气层内飞行,传统的带落角约束的比例导引法在末制导段的期望落角受飞行航程地心角的影响较大,不能较好地适应远程机动飞行器落角约束的问题,故提出一种地心角修正的落角约束最优制导律。仿真结果表明该制... 针对远程机动飞行器长时间在大气层内飞行,传统的带落角约束的比例导引法在末制导段的期望落角受飞行航程地心角的影响较大,不能较好地适应远程机动飞行器落角约束的问题,故提出一种地心角修正的落角约束最优制导律。仿真结果表明该制导方法可以使远程机动飞行器的落角满足落角约束,并且具有一定的鲁棒性。 展开更多
关键词 飞行器 比例导引 地心角 落角 最优制导律
下载PDF
一种基于迁移学习的多任务制导算法 被引量:1
14
作者 罗皓文 何绍溟 亢有为 《兵工学报》 EI CAS CSCD 北大核心 2024年第6期1787-1798,共12页
针对典型的飞行器制导任务,利用深度学习算法可以有效地拟合导弹飞行状态与制导指令之间的函数关系。然而当制导任务发生变化时,其二者之间的映射关系也会随之改变,从而导致在当前环境下预训练好的模型无法直接作用于新环境,重新训练制... 针对典型的飞行器制导任务,利用深度学习算法可以有效地拟合导弹飞行状态与制导指令之间的函数关系。然而当制导任务发生变化时,其二者之间的映射关系也会随之改变,从而导致在当前环境下预训练好的模型无法直接作用于新环境,重新训练制导模型需要大量的弹道数据和巨额的时间成本。为解决上述问题,基于迁移学习的思想引入域对抗神经网络,提出基于迁移学习的多任务制导算法。以1个含有大量标签数据的源域任务辅助2个含有极少量标签数据的目标域任务进行迁移学习,从而克服预训练与在线控制之间的环境差异。使用特征提取器和域判别器提取出对任务环境不敏感的关键特征,使神经网络学习到各个任务所共享的底层信息;为提高预测精度,分别设计针对不同任务的偏置加速度预测器。数值仿真结果表明:基于迁移学习的多任务制导算法实现了导弹在不同任务中的加速度指令预测。 展开更多
关键词 多约束制导 计算制导 深度学习 迁移学习 偏置比例导引
下载PDF
Guidance law with impact time and impact angle constraints 被引量:55
15
作者 Zhang Youan Ma Guoxin Liu Aili 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2013年第4期960-966,共7页
A novel closed-form guidance law with impact time and impact angle constraints is pro- posed for salvo attack of anti-ship missiles, which employs missile's normal acceleration (not jerk) as the control command dir... A novel closed-form guidance law with impact time and impact angle constraints is pro- posed for salvo attack of anti-ship missiles, which employs missile's normal acceleration (not jerk) as the control command directly. Firstly, the impact time control problem is formulated as tracking the designated time-to-go (the difference between the designated impact time and the current flight time) for the actual time-to-go of missile, and the impact angle control problem is formulated as tracking the designated heading angle for the actual heading angle of missile. Secondly, a biased proportional navigation guidance (BPNG) law with designated heading angle constraint is constructed, and the actual time-to-go estimation for this BPNG is derived analytically by solving the system differential equations. Thirdly, by adding a feedback control to this constructed BPNG to eliminate the time-to-go errorthe difference between the standard time-to-go and the actual time-to-go, a guidance law with adjustable coefficients to control the impact time and impact angle simultaneously is developed. Finally, simulation results demonstrate the performance and feasibility of the proposed approach. 展开更多
关键词 Feedback control guidance law Impact angle Impact time Missiles proportional navigation guidance
原文传递
比例导引律研究现状及其发展 被引量:34
16
作者 王亚飞 方洋旺 周晓滨 《火力与指挥控制》 CSCD 北大核心 2007年第10期8-12,共5页
在研究和分析国内外大量关于比例导引律的研究成果基础上,系统地论述了纯比例导引、理想比例导引、扩展P ID型比例导引,变结构比例导引和修正比例导引等改进型比例导引的研究现状。分析了它们的原理、性能及特点,讨论了在理论与实践中... 在研究和分析国内外大量关于比例导引律的研究成果基础上,系统地论述了纯比例导引、理想比例导引、扩展P ID型比例导引,变结构比例导引和修正比例导引等改进型比例导引的研究现状。分析了它们的原理、性能及特点,讨论了在理论与实践中的优缺点,对其发展进行了展望,为导弹制导与控制及相关问题研究提供了参考。 展开更多
关键词 比例导引 导引律 制导精度 机动性
下载PDF
激光末制导炮弹比例导引律性能研究 被引量:12
17
作者 牟宇 林德福 +1 位作者 祁载康 程振轩 《红外与激光工程》 EI CSCD 北大核心 2009年第2期250-255,共6页
通过分析激光末制导炮弹比例导引制导律几何关系和原理,研究了激光末制导炮弹的工作原理,建立了含非线性进动的激光陀螺式导引头动力学模型和线性化弹体模型的末制导炮弹比例导引回路模型。根据制导控制系统是否利用导引头非线性进动信... 通过分析激光末制导炮弹比例导引制导律几何关系和原理,研究了激光末制导炮弹的工作原理,建立了含非线性进动的激光陀螺式导引头动力学模型和线性化弹体模型的末制导炮弹比例导引回路模型。根据制导控制系统是否利用导引头非线性进动信号作为制导信号,建立了两种制导控制系统数学模型,采用不同的制导时间以及弹体参数,进行了末制导炮弹比例导引回路仿真,对比分析了两种制导控制系统的性能。最后,针对非线性系统易引起弹体姿态较大摆动的问题,提出了在制导时间有限时的基于衰减系数的激光末制导炮弹改进制导方案。 展开更多
关键词 激光制导 比例导引律 制导控制系统 导引头 非线性进动
下载PDF
带过重力补偿的比例导引制导律参数设计与辨识 被引量:26
18
作者 林德福 祁载康 夏群力 《系统仿真学报》 EI CAS CSCD 北大核心 2006年第10期2753-2756,共4页
研究以增大导弹落角为目标的过重力补偿比例导引律及其工程应用。将重力补偿信号作为加速度补偿指令引入线性比例导引回路,从而建立了仿真数学模型,分析了重力补偿系数、比例导引系数等参数对制导系统性能的影响,并根据遥测数据给出实... 研究以增大导弹落角为目标的过重力补偿比例导引律及其工程应用。将重力补偿信号作为加速度补偿指令引入线性比例导引回路,从而建立了仿真数学模型,分析了重力补偿系数、比例导引系数等参数对制导系统性能的影响,并根据遥测数据给出实际系统的过重力补偿系数、比例导引系数的辨识结果从而验证了理论设计结果,得到过重力补偿比例导引律的一般设计方法。 展开更多
关键词 过重力补偿 比例导引律 落角 辨识
下载PDF
攻击机动目标的多导弹分布式协同制导律 被引量:23
19
作者 孙雪娇 周锐 +1 位作者 吴江 陈哨东 《北京航空航天大学学报》 EI CAS CSCD 北大核心 2013年第10期1403-1407,共5页
在分布式通信和增广比例导引的基础上,基于网络同步原理设计了一种多导弹拦截机动目标的分布式协同制导律.该分布式协同制导律由导弹本地导引律和分布式协调策略两部分组成:本地导引律由增广比例导引得到;基于网络同步原理设计了导弹之... 在分布式通信和增广比例导引的基础上,基于网络同步原理设计了一种多导弹拦截机动目标的分布式协同制导律.该分布式协同制导律由导弹本地导引律和分布式协调策略两部分组成:本地导引律由增广比例导引得到;基于网络同步原理设计了导弹之间的分布式协调策略,实现多弹对机动目标的同时协同攻击.该分布式协同制导律只需要视距内相邻导弹之间传输状态信息,具有通信量小、可扩展性好等特点.仿真结果表明多弹网络系统采用该制导律能够有效地协同攻击机动目标. 展开更多
关键词 机动目标 增广比例导引 协同制导 分布式通信
下载PDF
制导规律研究现状及展望 被引量:23
20
作者 聂永芳 周卿吉 张涛 《飞行力学》 CSCD 2001年第3期7-11,共5页
系统地论述了古典和现代的一些制导规律的研究现状 ,分析了它们的优点和不足、适应范围和局限性 ,并讨论了它们的发展前景。其中着重论述了比例导引、最优导引、微分对策和近年来热门研究的神经网络控制。可供从事导弹制导的科研人员对... 系统地论述了古典和现代的一些制导规律的研究现状 ,分析了它们的优点和不足、适应范围和局限性 ,并讨论了它们的发展前景。其中着重论述了比例导引、最优导引、微分对策和近年来热门研究的神经网络控制。可供从事导弹制导的科研人员对现有制导规律有一个全面的认识 ,以便于更深入地研究。 展开更多
关键词 最优制导律 比例导引 微分对策 神经网络 非线性系统 导弹制导
下载PDF
上一页 1 2 14 下一页 到第
使用帮助 返回顶部