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

A technology for launch vehicles and strapdown inertial groups, which is applied to measurement devices, instruments, etc., can solve the problems of complex calibration operations, complicated test operations on the rocket, and high requirements for operators, and achieves high calibration accuracy and simple and easy calibration operations. Effect

Active Publication Date: 2016-01-06
SHANGHAI XINYUE METER FACTORY
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  • Abstract
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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

Method used

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

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Embodiment

[0045] This embodiment provides a calibration device for the azimuth deviation of the double strapdown inertial group of the carrier rocket. The double strapdown inertial group of the carrier rocket is installed on the integrated bracket, and the inertial group and the integrated bracket are combined (the overall strapdown inertial group) Place it on a horizontal marble slab (tablet calibration platform), and use two theodolites (the first theodolite and the second theodolite) to aim at the two sets of strapdown inertial groups (the main strapdown inertial group and the secondary strapdown inertial group) in the horizontal direction. ) rectangular prism, at this time as the initial state of the two theodolites, the readings are cleared; the inertial group and the integrated bracket assembly are moved out of the field of view of the theodolite, and the two theodolites are aimed at the two parallel surfaces of the standard hexahedron respectively, and the readings of the two theod...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 王鹏周如好裴忠海周静黄飞盛宏媛桂亮王建清
Owner SHANGHAI XINYUE METER FACTORY
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