Method and system for measuring flight parameters of spinning projectile based on ballistic prior knowledge

Abstract

According to the rotating missile flight parameter filtering method and system based on ballistic prior knowledge, a system state equation taking a rotating missile attitude quaternion q as a filter state variable and a system observation equation taking a magnetic survey resolving system quaternion qMR as a filter observation variable are selected; resolving the quaternion qMR of the magnetic survey resolving system through the missile body attitude quaternion matrix; further constructing a projectile attitude filtering model, completing optimal filtering estimation calculation of the state equation X (k) by adopting a Kalman filtering algorithm to obtain rotating projectile attitude quaternion optimal estimation, substituting the rotating projectile attitude quaternion optimal estimation into a projectile attitude quaternion matrix, calculating to obtain an optimal projectile attitude quaternion matrix, and calculating a projectile speed Vn and a projectile flight position Pn; and real-time flight parameter measurement of the spinning projectile is completed, so that the accuracy and reliability of testing the state of the spinning projectile are effectively improved.

Description

technical field [0001] The invention relates to the technical field of measuring methods for flight attitude, speed and position of aircraft or rotary missiles, in particular to a method and system for measuring flight parameters of rotary missiles based on ballistic prior knowledge. Background technique [0002] Due to the special application environment of the "three highs" of high overload, high self-rotation and high speed launched by the rotating projectile, the existing mature projectile-borne measurement system cannot be directly transplanted to the test application of the rotating projectile. problems such as low accuracy and poor reliability. Therefore, the high-precision attitude measurement technology of high-speed rotating missiles is the difficulty of its guidance transformation. It is urgent to find a low-cost, high-precision, and suitable technology for the flight attitude measurement of rotating missiles. The problem of attitude measurement has important the...

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Problems solved by technology

[0002] Due to the special application environment of the "three highs" of high overload, high spin and high speed of the rotating projectile, the existing mature missile-borne measurement system cannot be directly transplanted to the test application of the rotating projectile, and there are difficulties in survival, incomplete measurement parameters, Problems such as low accuracy and poor reliability

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