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Journal of Systems Engineering and Electronics 2018年第6期29卷 1263-1270页

作者： FU Bin GUO Hang CHEN Kang FU Wenxing WU Xingyu YAN Jie School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China Xi’an Microelectronic Technology Institute Xi’an 710065China

This paper proposes a multiple-constraints-guaranteed midcourse guidance law for the interception of the hypersonic targets. In traditional midcourse law design, the constraints of the aero-thermal heating are rarely taken into consideration. The performance of the infrared detection system may be degraded and the instability of the flight control system may be induced.To address this problem, a state-constrained model predictive static programming method is introduced such that both terminal constraints(position and angle) and optimal energy consumption can be ensured. As a result, a sub-optimal midcourse guidance,guaranteeing the aforementioned multiple-constraints to be never violated, is synthesized. Simulation results demonstrate the effectiveness of the proposed method.

关键词： midcourse guidance model predictive control optimal control state constraint

INVESTIGATION OF TIGHTLY COUPLED SINS/GPS INTEGRATION midcourse guidance FOR AIR-TO-AIR MISSILES

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Chinese Journal of Aeronautics 1998年第3期11卷 47-54页

作者：富立范耀祖宁文如 Faculty 301 Beijing Univ. Aero. and Astronaut. Beijing 100083 China

The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air to air missiles have been investigated recently. In comparison with those investigations existing in current publications, a new tightly coupled SINS/GPS integration navigation system for air to air missiles, based on the decorrelated pseudo range approach, is presented in this paper. Because of high jamming and dynamic of air to air missiles, inertial velocity aiding GPS receiver is used to provide a more accurate, jam resistant measurement for midcourse guidance systems. A tracking error estimator is designed to distinguish the correlation that existed between pseudo range measurements and inertial information. It is found better to regard inertial velocity aiding errors as the noise of which statistical properties are unknown. So using mixed Kalman/minimax filtering theory, one can obtain the new tracking error estimator with simple and robust algorithm through constructing a composite filter consisting of two parts: Kalman filter for the noise of known statistics and minimax filter for the unknown. In order to ensure this simple estimator stability, a new method is proposed to choose its parameters, based on Khargonekars work. Moreover, it is demonstrated that the given method also ensures the proposed estimator optimality. All the work mentioned above is involved in the tightly coupled SINS/GPS integration midcourse system design in which a set of low accuracy inertial components is shared by SINS and autopilot. Simulation results of a certain type of air to air missile are presented. Due to decorrelation by the tracking error estimator, only small white noise of pseudo range measurements remains. So it is shown that application of the new midcourse guidance system results in better guidance accuracy, higher jam resistance.

关键词： SINS/GPS navigation systems navigation aids midcourse guidance Kalman/minimax filtering theory Kalman filters

Discussion on neighborhood optimal trajectory online correction algorithm and its application range

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Journal of Systems Engineering and Electronics 2023年第4期34卷 1053-1062页

作者： LI Wanli LI Jiong LEI Humin Graduate School Air Force Engineering UniversityXi’an 710051China Air and Missile Defense College Air Force Engineering UniversityXi’an 710051China

This paper presents a neighborhood optimal trajectory online correction algorithm considering terminal time variation,and investigates its application range.Firstly,the motion model of midcourse guidance is established,and the online trajectory correction-regenerating strategy is introduced.Secondly,based on the neighborhood optimal control theory,a neighborhood optimal trajectory online correction algorithm considering the terminal time variation is proposed by adding the consideration of terminal time variation to the traditional neighborhood optimal trajectory correction method.Thirdly,the Monte Carlo simulation method is used to analyze the application range of the algorithm,which provides a basis for the division of application domain of the online correction algorithm and the online regeneration algorithm of midcourse guidance trajectory.Finally,the simulation results show that the algorithm has high real-time performance,and the online correction trajectory can meet the requirements of terminal constraint change.The application range of the algorithm is obtained through Monte Carlo simulation.

关键词： midcourse guidance online correction neighborhood optimal control application range

Optimal midcourse trajectory cluster generation and trajectory modification for hypersonic interceptions

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Journal of Systems Engineering and Electronics 2017年第6期28卷 1162-1173页

作者： Humin Lei Jin Zhou Dailiang Zhai Lei Shao Dayuan Zhang Air and Missile Defense College Air Force Engineering University Xi’an 710051 China Unit 95948 of the PLA Jiuquan 732750 China

The hypersonic interception in near space is a great challenge because of the target’s unpredictable trajectory, which demands the interceptors of trajectory cluster coverage of the predicted area and optimal trajectory modification capability aiming at the consistently updating predicted impact point(PIP) in the midcourse phase. A novel midcourse optimal trajectory cluster generation and trajectory modification algorithm is proposed based on the neighboring optimal control theory. Firstly, the midcourse trajectory optimization problem is introduced; the necessary conditions for the optimal control and the transversality constraints are given.Secondly, with the description of the neighboring optimal trajectory existence theory(NOTET), the neighboring optimal control(NOC)algorithm is derived by taking the second order partial derivations with the necessary conditions and transversality conditions. The revised terminal constraints are reversely integrated to the initial time and the perturbations of the co-states are further expressed with the states deviations and terminal constraints modifications.Thirdly, the simulations of two different scenarios are carried out and the results prove the effectiveness and optimality of the proposed method.

关键词： neighboring optimal control(NOC) midcourse guidance trajectory cluster generation optimal trajectory modification

Optimal midcourse trajectory planning considering the capture region

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Journal of Systems Engineering and Electronics 2018年第3期29卷 587-600页

作者： ZHOU Jin SHAO Lei WANG Huaji ZHANG Dayuan LEI Humin Air and Missile Defense College Air Force Engineering UniversityXi'an 710051China Unit 95948 of the PLA Jiuquan 732750China

An optimal midcourse trajectory planning approach that considers the capture region（CR） of the terminal guidance is proposed in this article based on the Gauss pseudospectral method（GPM）. Firstly, the planar CR of the proportional navigation in terminal guidance is analyzed and innovatively introduced in the midcourse trajectory planning problems, with the collision triangle（CT） serving as the ideal terminal states parameters of the midcourse phase, and the CR area serving as the robustness against target maneuvers. Secondly, the midcourse trajectory planning problem that considers the path, terminal and control constraints is formulated and the well-developed GPM is used to generate the nominal trajectory that meets the CR demands. The interceptor will reshape the trajectory only when the former CR fails to cover the target, which has loosened the critical demand for frequent trajectory modification. Finally, the simulations of four different scenarios are carried out and the results prove the effectiveness and optimality of the proposed method.

关键词： capture region（CR） collision triangle（CT） midcourse guidance trajectory planning hypersonic interception trajectory modification