Double-strap-down inertial set orientation deviation calibration device and method of rocket launcher

Abstract

The invention provides a double-strap-down inertial set orientation deviation calibration device of a rocket launcher. A double-strap-down inertial set of the rocket launcher comprises two strap-down inertial sets which are installed on one integrated support in parallel so that a complete strap-down inertial set can be formed; the two strap-down inertial sets are movably placed on a horizontal flat plate calibration table; a standard hexahedron and right-angle prisms of the two strap-down inertial sets are arranged at equal height; the standard hexahedron and the strap-down inertial sets are alternately located in the view fields of a first theodolite and a second theodolite as a whole; the first theodolite and the second theodolite are arranged on the two sides of the flat plate calibration table respectively. Meanwhile, a calibration method of the calibration device is provided. The calibration device and the calibration method of the calibration device achieve the purpose that after double-strap-down inertial measurement combination main and salve redundancy is adopted for a control system of the rocket launcher, the orientation deviation of the two strap-down inertial sets is determined. After the main strap-down inertial set is aimed at at the initial orientation in front of the rocket launcher, the orientation of the slave strap-down inertial set is determined through the calibration deviation, the initial alignment and launching process of the rocket launcher provided with the redundant strap-down inertial sets can be simplified, and engineering practicability is high.

Description

technical field [0001] The invention relates to a redundant strapdown inertial group azimuth deviation calibration technology for a launch vehicle control system, in particular to a dual redundant and integrated installation of a launch vehicle double strapdown inertial group azimuth deviation calibration device and method. Background technique [0002] The initial alignment of the launch vehicle to determine the initial value of the navigation is divided into horizontal alignment and azimuth alignment. The azimuth alignment is generally achieved by optical aiming equipment for the rectangular prism installed on the inertial navigation system. Facing the high reliability requirements of the launch vehicle, the inertial navigation system of its key sensitive measurement device generally adopts redundant configuration. The redundancy configuration scheme of the inertial navigation system includes double redundancy, triple redundancy and so on. In order to facilitate redundant...

AI Technical Summary

Problems solved by technology

[0004] 1) Calibration operation is complex and has high requirements for operators

[0005] 2) It is impossible to effectively eliminate the influence of instruments, human operations and other factors on the calibration results

[0006] 3) It is necessary to aim at the arrow, and the operation of the arrow test is complicated

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