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impact time control using biased proportional navigation for missiles with varying velocity

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Chinese Journal of Aeronautics 2020年第3期33卷 956-964页

作者： Guoxin SUN Qiuqiu WEN Zhiqiang XU Qunli XIA School of Aerospace Beijing Institute of TechnologyBeijing 100081China Harbin Jiancheng Industry Company Limited Harbin 150030China

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.

关键词： Guidance Homing missiles impact time Proportional navigation guidance time-varying velocity

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Sliding mode control and Lyapunov based guidance law with impact time constraints

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Journal of Systems Engineering and Electronics 2017年第6期28卷 1186-1192页

作者： Xiaojian Zhang Mingyong Liu Yang Li School of Marine Science and Technology Northwestern Polytechnical University Xi’an 710021 China

This paper analyses the issue of impact time control of super-cavitation weapons impact fixed targets which mainly refer to the ships or submarines who lost power, but still have combat capability. Control over impact time constraints of guidance law(ITCG) is derived by using sliding mode control(SMC) and Lyapunov stability theorem. The expected impact time is realized by using the notion of attack process and estimated time-to-go to design sliding mode surface(SMS). ITCG contains equivalent and discontinuous guidance laws, once state variables arrive at SMS,the equivalent guidance law keeps the state variables on SMS,then the discontinuous guidance law enforces state variables to move and reach SMS. The singularity problem of ITCG is also analyzed. Theoretical analysis and numerical simulation results are given to test the effectiveness of ITCG designed in this paper.

关键词： Lyapunov stability sliding mode control impact time salvo attack time-to-go guidance law

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impact time Constrained Cooperative Guidance Law Design via Line-of-Sight Shaping

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Impact Time Constrained Cooperative Guidance Law Design via ...

Three-Dimensional impact time and Angle Guidance via Controlling Line-of-Sight Dynamics

第40届中国控制会议

作者： Yadong Chen Xiangjun Ding Jianan Wang Chunyan Wang Jiayuan Shan School of Aerospace Engineering Beijing Institute of Technology

In this paper, impact time constrained guidance（ITCG） laws are proposed using a range-based line-of-sight（LOS）shaping strategy. The relative motion of missile and target is described in a polar coordinate, where the LOS angle can be shaped as a polynomial function of range-to-go. A third-order polynomial function is selected according to the number of constraints. Coefficients of the polynomial function are determined by the boundary conditions and solved through a simple integral equation, which facilitates the onboard implementation. Guidance command is designed in a state feedback form to track the shaped trajectory. The proposed guidance law shows advantageous features over several similar polynomial shaping based guidance laws. Multiple simulation studies demonstrate the effectiveness of the proposed guidance law.

关键词： impact time Cooperative Guidance Trajectory Shaping

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Three-Dimensional Impact Time and Angle Guidance via Control...

Cubic Range Shaping Guidance for Maneuvering Targets with impact time Constraint

第32届中国控制与决策会议

作者： Tuo Han Yong Xi Guangshan Chen Qinglei Hu School of Automation Science and Electrical Engineering Beihang University Shanghai Aerospace Control Technology Institute Beijing Advanced Innovation Center for Big-Data Based Precision Medicine Beihang University

In this paper,a three-dimensional guidance law is developed for intercepting a maneuvering target with impact angle constraint at a specified impact time.To achieve this goal,the LOS error dynamics is utilized to track a constant LOS signal and a quadratic LOS profile in the pitch and yaw planes,respectively.The designated LOS profile in the yaw plane has a simple structure,i.e.,a quadratic polynomial in time.To nullify the LOS tracking errors in finite time,the non-singular terminal sliding mode technique is utilized to obtain the guidance commands.Furthermore,a set of reliable LOS profiles are systematically determined to ensure the feasibility of the guidance law.The proposed guidance law can guarantee the desired impact angles and zero miss distance as mandatory requirements.Meanwhile,a single tuning parameter provides an additional freedom to meet the desired impact time.Finally,numerical results with various engagement scenarios are provided to validate effectiveness of the proposed guidance law.

关键词： Three-Dimensional Guidance impact time impact Angle Line-of-Sight Shaping

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Cubic Range Shaping Guidance for Maneuvering Targets with Im...

Obstacle avoidance for multi-missile network via distributed coordination algorithm

第32届中国控制与决策会议

In this paper,a cubic range shaping guidance with impact time constraint is proposed for intercepting maneuvering targets.To meet the desired impact time,the range dynamics is employed to track the desired range profiles created via a cubic range shaping approach.The coefficients involved in the range profiles are partially solved with boundary conditions.Then,a robust impact time guidance law is constructed to ensure bounded range tracking errors and estimate the target maneuvers as well using inertial delay control and sliding mode control.The implemented guidance law involves a single parameter that is limited in a compact region,thus making it easy to be tuned.Finally,numerical simulations with various cases are conducted to verify the proposed guidance law.

关键词： Guidance Law Range Shaping impact time

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Chinese Journal of Aeronautics 2016年第2期29卷 441-447页

作者： Zhao Jiang Zhou Rui School of Automation Science and Electrical Engineering Beihang University

A distributed coordination algorithm is proposed to enhance the engagement of the multi-missile network in consideration of obstacle avoidance. To achieve a cooperative interception, the guidance law is developed in a simple form that consists of three individual components for tar- get capture, time coordination and obstacle avoidance. The distributed coordination algorithm enables a group of interceptor missiles to reach the target simultaneously, even if some member in the multi-missile network can only collect the information from nearest neighbors. The simula- tion results show that the guidance strategy provides a feasible tool to implement obstacle avoid- ance for the multi-missile network with satisfactory accuracy of target capture. The effects of the gain parameters are also discussed to evaluate the proposed approach.

关键词： Cooperative guidance Distributed algorithms impact time Missile guidance Multiple missiles Obstacle avoidance Proportional navigation

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impact Force Attenuation Process during Landing in Simulated Parachute Jumping

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Journal of Medical Colleges of PLA 1987年第3期 286-290页

作者：冯文树刘铁汉何扬举简进章范建伟 Department of Aviation Biodynamics Fouth Military Medical College Xi’an

Under the simulating of parachute jumping,the landing impact forceson the segments of the human body of three parachuters were studied with thehelp of high-speed photography and theoretical calculation.The results show:(1)There was an attenuation process of the impact forces on the body segments.(2)The impact force on the body segments and the peak of the impact force on the feetat the time from 0.08 to 0.26 s attenuated by 40.6-64.1% as compared with thoseat 0.08s.(3)The attenuation curve of the peak of the impact force on the feet isclose to the curve of its regression equation.

关键词： parachute jumping aviation medicine biomechanics impact force impact time