Guidance munition flight attitude correction simulation system and method based on cyber-physical system

Abstract

The invention discloses a guidance ammunition flight attitude correction simulation system based on a cyber-physical system. The flight attitude error injection module is used to generate corresponding non-ideal flight attitude information; the three-axis turntable is used to control the guided ammunition entity according to the non-ideal flight attitude information. The flight attitude of the model; the attitude sensor is used to perceive the actual flight attitude information of the guided munition entity model; the real-time analysis module is used to filter the actual flight attitude information to obtain the real-time actual flight attitude information of the guided munition entity model; the decision module is used to obtain The deviation of the real-time actual flight attitude information of the guided munitions entity model from the ideal flight attitude of the guided munitions at the corresponding moment; the three-axis turntable realizes the flight attitude of the guided munitions entity model at the corresponding moment under the control of the three-axis turntable control command for the correction of the flight attitude Corrected simulation. The invention can form a closed-loop simulation for accurate correction of the flight attitude of the guided ammunition.

Description

technical field [0001] The invention relates to the field of guided munitions and the technical field of cyber-physical systems, in particular to a simulation system and method for correcting the flight attitude of guided munitions based on cyber-physical systems. Background technique [0002] Due to the existence of random errors such as air density, ballistic wind, and meteorological changes, the flight attitude of guided munitions changes complicatedly. Generally, it is required to have fast response characteristics to achieve rapid correction of flight attitude, but the premise is the real-time perception of the flight attitude of guided munitions. [0003] At present, the measurement technologies for the flight attitude of guided munitions mainly include magnetic detection technology, micro-mechanical gyroscope technology, and photogrammetry technology. The measurement results are used to correct the flight attitude through an automatic control system, which is a classic...

AI Technical Summary

Problems solved by technology

However, this classic closed-loop control system has the following disadvantages: first, it may produce "overshoot" phenomenon, second, the control result may fall into local optimum, and third, the control effect cannot be accurately predicted. Accuracy correction, and further affects the accuracy correction of the outer trajectory of the guided munition, which ultimately affects its hit probability

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