Guided ammunition flight attitude correction simulation system and method based on information physical system

Abstract

The invention discloses a guided ammunition flight attitude correction simulation system based on an information physical system. A flight attitude error input module is used for generating corresponding non-ideal flight attitude information. A three-axis rotary table is used for controlling the flight attitude of a guided ammunition entity model according to the non-ideal flight attitude information. An attitude sensor is used for sensing actual flight attitude information of the guided ammunition entity model. A real-time analysis module is used for conducting filtering on the actual flight attitude information to obtain the real-time actual flight attitude information of the guided ammunition entity model. A decision making module is used for the deviation of the real-time actual flight attitude information of the guided ammunition entity model relative to the guided ammunition ideal flight attitude at corresponding moment. The three-axis rotary table is controlled through a three-axis rotary table control instruction for flight attitude correction to simulate guided ammunition entity model flight attitude correction at the corresponding moment. The guided ammunition flight attitude correction simulation system based on the information physical system can realize closed-loop simulation on guided ammunition flight attitude accurate correction.

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

Images