A Differential Game Guidance Law Design Method Considering Observation of Target Acceleration Direction

Abstract

The invention discloses a differential game guidance law design method considering the observation of the target acceleration direction. The steps are: 1) Obtain the dynamic equation of the missile and the target based on the terminal guidance premise; 2) Assume that the target maneuver includes disturbance maneuver and escape maneuver, and the missile maneuver includes Disturbance maneuvers and pursuit maneuvers, combined with related payoff functions to obtain a differential game problem considering disturbance maneuvers; 3) Using the state-dependent Riccati equation method to solve the above differential game problems, and obtaining a differential game guidance law considering disturbance maneuvers; 4 ) Assuming that the target only performs disturbance maneuvers and the missile only conducts pursuit maneuvers, the guidance law in 3) is simplified to obtain the differential game guidance law including real-time target acceleration; 5) Under the condition of delayed information, the target acceleration is obtained by compensating the target acceleration direction observation method Predicted value; 6) Replace the real-time target acceleration value in 4) with the predicted value of the target acceleration, and obtain the differential countermeasure guidance law considering the observation of the target acceleration direction.

Description

technical field [0001] The invention relates to a differential strategy guidance law design method considering target acceleration direction observation, and relates to the technical field of aircraft guidance. Background technique [0002] Missile terminal guidance means that at the end of the missile's flight, the missile is provided with flight control instructions through the guidance law to help the missile hit the target. The design of missile guidance law has a direct impact on the combat effectiveness of missiles, and has been the focus of current major military powers. [0003] The current missile guidance laws can be mainly divided into two categories: classical guidance laws and modern guidance laws. The classical guidance laws mainly include the tracking method, the parallel approach method, the proportional guidance method, the three-point method and the lead angle method. Among them, the tracking method always keeps the missile speed direction pointing to the...

AI Technical Summary

Problems solved by technology

The three-point method requires the base station to participate in the combat process, and always keep the missile on the connection line between the base station and the target. It has strong anti-interference performance, but the ballistic trajectory is curved, and the overload required when approaching the target is relatively large.

The interception model based on the zero miss amount takes the predicted miss amount of the missile and the target as the design object, but it often leads to a high state space dimension, which needs to use the state transition matrix to reduce the dimension, and needs to use the remaining time, which has a certain impact on the guidance accuracy.

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