Design for Terminal Guidance Law of Combined Control Interceptor in Aerosphere

The air-to-ground missile with strapdown seeker may have the problems, including small field of view(FOV), limited overload, and fall angle constraint. To solve the above mentioned problem, a phased guidance scheme is proposed. In this scheme, the attack trajectory is divided into the following six stages, including glided stage, fall angle constraint stage, target acquisition and adjustment stage, terminal guidance stage and blind zone stage. The glided stage is designed to increase range, the terminal fall angle is attained ahead of time at fall angle constraint stage. The aim of target acquisition and adjustment stage is to adjust the missile attitude, so that the target will fall within the FOV of the seeker. It creates good condition to capture the target for strapdown seeker. In the terminal stage, the guidance law of proportional navigation and attitude track are used to fit the needs of FOV constraint and attack accuracy. The simulation result shows that the project trajectory can solve the application of attacking moving targets for air-to-ground missile with strapdown seeker under multi constraints.

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Design and Instruction Solution of an Optimal Guidance Law for Ship-Air Missile beyond Visual Range

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.433-440.3831 ◽

2012 ◽

Vol 433-440 ◽

pp. 3831-3836

Author(s):

Yong Tao Zhao ◽

Yun An Hu

Keyword(s):

Control Variable ◽

Linear Quadratic ◽

Linear Quadratic Optimal Control ◽

Guidance Law ◽

The Earth ◽

Optimal Guidance ◽

Quadratic Optimal Control ◽

Simulation Results ◽

Visual Range ◽

Terminal Guidance

For the case of ship-air missile intercepting the low target beyond visual range by ship-ship coordination, the instruction solution model was presented and an optimal guidance law was designed considering the effect of the curvature of the earth. In the midcourse and terminal guidance segment, the optimal guidance law was designed through applying the concept of the pseudo control variable and the theory of the linear quadratic optimal control. The information of the target was described in the launch coordinates through coordinate transformation to realize the instruction solution for the designed guidance law. The simulation results show that the model of the instruction solution is correct and the designed guidance law is feasible.

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Analysis of the Influence of Trace Point Step-Jump Behavior

International Journal of Aerospace Engineering ◽

10.1155/2020/3906375 ◽

2020 ◽

Vol 2020 ◽

pp. 1-14

Author(s):

Yao Yang ◽

Yang Xu ◽

Pei Wang

Keyword(s):

Recovery Time ◽

Sliding Mode ◽

Initial Step ◽

Guidance System ◽

Adjoint Model ◽

Proportional Navigation ◽

Guidance Law ◽

Optimal Guidance ◽

Fundamental Reason ◽

Terminal Guidance

To explore the influence of the trace point step-jump behavior on a terminal guidance system, an analysis is performed from the line-of-sight rate (LOS rate) and guidance accuracy views for designing an anti-step-jump guidance law. First, the linear terminal guidance model under the trace point jump circumstance is constructed, and then the fundamental reason for the miss distance is investigated by deriving the upper bound of the LOS rate at the initial step-jump moment. Following this, the novel proposed analytical differential adjoint model is established with the adjoint method, and its validity is demonstrated comparing with the numeric derivative model. Based on the adjoint model, the effects of the ratio coefficient, the time constant, and the jump amplitude on the guidance accuracy are explored. Finally, a novel anti-step-jump guidance law is designed to shorten the recovery time of the overload. The simulations have shown that the faster recovery time and higher accuracy are achieved in comparison with the proportional navigation guidance, optimal guidance, and adaptive sliding mode guidance.

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