Optimal Guidance Laws with Uncertain Time-of-Flight Against Maneuvering Target and Noisy Measurements

ABSTRACTThe paper presents a laser guided bomb guidance law based on the linear quadratic differential game theory, where a case of two perpendicular planes with two state variables in each plane has been considered. The Kalman filtering method has been used for noise removal from the measured signals and for estimation of the missing state variable values needed for the optimal guidance law. Optimisation has been conducted with respect to minimisation of the performance index. Comparative analysis of different guidance laws is done. A statistical analysis is performed to obtain the terminal miss distance in dependence on total flight time.

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Sinusoidal function weighted optimal guidance laws

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410014537470 ◽

2014 ◽

Vol 229 (3) ◽

pp. 534-542 ◽

Cited By ~ 8

Author(s):

Chang-Hun Lee ◽

Jin-Ik Lee ◽

Min-Jea Tahk

Keyword(s):

Optimal Guidance ◽

Guidance Laws ◽

Sinusoidal Function

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Cooperative guidance laws for simultaneous attack against a target with unknown maneuverability

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018782507 ◽

2018 ◽

Vol 233 (7) ◽

pp. 2518-2535 ◽

Cited By ~ 2

Author(s):

Xiaoqian Wei ◽

Jianying Yang

Keyword(s):

New Approach ◽

Maneuvering Target ◽

Guidance Law ◽

New Strategy ◽

Multi Agent ◽

Cooperation Protocol ◽

Distributed Cooperation ◽

Guidance Laws ◽

Simultaneous Attack ◽

Adaptive Control Law

This paper designs new guidance laws for the simultaneous multi-agent interception of a maneuvering target with unknown acceleration. The new approach achieves additional benefits as follows. (1) The completely distributed cooperation protocol ensures that the simultaneous attack task can be completed. (2) The disturbance observer and the adaptive control law can solve the coordinated attack problem with an unknown target acceleration. (3) The design of the guidance law requires only neighbor-derived information rather than global information, which increases the practicability of the new strategy. Numerical simulations with comparisons demonstrate the effectiveness and superiority of the proposed method.

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Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410017730250 ◽

2017 ◽

Vol 231 (14) ◽

pp. 2515-2536 ◽

Cited By ~ 3

Author(s):

Hui Wang ◽

Jiang Wang ◽

Defu Lin

Keyword(s):

General Expression ◽

Impact Angle ◽

Acceleration Response ◽

Proportional Navigation ◽

Guidance Law ◽

Optimal Guidance ◽

Terminal Constraints ◽

Miss Distance ◽

Guidance Laws ◽

Impact Angle Constraint

To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

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