Applicable to the joint measurement method of initial attitude and velocity of rotating projectile

Abstract

The invention discloses a spinning projectile initial posture and speed joint measuring method. The method comprises the following steps of (1) building of a projectile-borne sensor measuring scheme and coordinate system transformation, (2) adopting of a spinning projectile rolling speed resolving method, (3) arrangement of a spinning projectile rolling angle rate filter, (4) adopting of a spinning projectile mouth initial speed resolving method, (5) adopting of a spinning projectile mouth initial posture resolving method, and (6) calculating of initial speeds upsilonx, upsilony and upsilonz when spinning projectiles are ejected out of the mouth through the velocity vector projection relationship, that is, according to the following speed. Through the method, accurate measuring of spinningprojectile initial posture parameters is achieved.

Description

technical field [0001] The invention relates to the technical field of measuring the initial parameters of the muzzle of a high-speed rotating projectile, in particular to a joint measurement method for the initial attitude and velocity of the muzzle of a rotating projectile based on a three-axis magnetic sensor and two single-axis gyroscopes. Background technique [0002] The guided transformation of rotating bombs is the development direction of conventional weapons at home and abroad, and the real-time and accurate measurement of the attitude angle of rotating bombs during flight is the key premise for realizing its precise control flight. Restricted by the high-speed rotation of the rotating projectile, large launch overload and small space volume, the missile-borne system must meet the requirements of high overload resistance, small size and low cost. The spin energy of the rotating projectile can be as high as 40 revolutions per second, and the axial angular rate can r...

AI Technical Summary

Problems solved by technology

The spin energy of the rotating projectile can be as high as 40 revolutions per second, and the axial angular rate can reach 14400° / s. However, the range and accuracy of the current gyroscope used for the projectile are difficult to meet the requirements of this type of application at the same time, and the large overload generated at the moment of projectile launch is also easy. Short-term saturation, distortion, or failure of missile-borne sensors

These unfavorable factors make it difficult to transplant the existing attitude test system directly to the navigation test of the rotary bomb

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