Ship-borne high-precision star sensor setting angle calibrating method

A technology of star sensor and calibration method, which is applied to instruments, measuring devices, etc., can solve problems such as accurate calibration, inability to realize the installation angle of shipborne star sensor, etc. Effect

Inactive Publication Date: 2016-03-09
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0004] The present invention provides a method for calibrating the installation angle of the ship-borne high-precision star sensor in o

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  • Ship-borne high-precision star sensor setting angle calibrating method
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  • Ship-borne high-precision star sensor setting angle calibrating method

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specific Embodiment approach 1

[0025] Specific implementation mode 1. Combination Figure 1 to Figure 4 To illustrate this embodiment, the coordinate systems involved in this embodiment include CIS—earth-centered inertial coordinate system (J2000.0 coordinate system), MT—instantaneous flat equatorial earth-centered system, CT—instantaneous true equatorial earth-centered system, ET—quasi Earth-fixed coordinate system, CTS—ground-fixed coordinate system, DP—inertial navigation horizon system, b—deck coordinate system, s—star sensor coordinate system.

[0026] Table 1 Parameter information of the star sensor optical system in this embodiment.

[0027] Table 1

[0028]

[0029] Basic Euler angle rotation transformation matrix R x (θ),R y (θ),R z (θ) represent the matrices formed by rotating θ counterclockwise around the X, Y, and Z axes, respectively, and have the following standard form:

[0030] R x ( θ ) = ...

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Abstract

The invention discloses a ship-borne high-precision star sensor setting angle calibrating method, and relates to the field of spacecraft attitude control ground application to solve the problem of unable reaction of accurate calibration of the setting angle of a ship-borne star sensor in the prior art. A ship-borne radar equipment pedestal is provided with a star sensor; when a ship docks, a ship-borne alignment calibration theodolite determines the course angle of a measurement ship through a star measurement or azimuth vane tracking technology, and the horizontal reference pitching angle and rolling angle of a whole ship are calibrated to obtain an inertial navigation horizontal system to deck coordinate system transformation matrix; and the star sensor shoots a star atlas, the observation vectors and the reference vectors of i fixed stars are obtained, the azimuths and the pitching angles of the i fixed stars in a view field are calculated, the pitching angles undergo atmospheric refraction correction one by one, the inertial navigation horizontal system reference vectors of the i fixed stars are reconstructed, and star sensor attitude matrix and the ship-borne star sensor setting matrix under the inertial navigation horizontal system are calculated to resolve the setting angle. The method improves the measurement precision of the attitude of the body of a spaceflight measurement ship.

Description

technical field [0001] The invention relates to the ground application field of spacecraft attitude control, in particular to a method for calibrating the mounting angle of a ship-borne high-precision star sensor. According to the star sensor attitude determination algorithm principle, the installation angle of the shipborne star sensor relative to the deck coordinate system is accurately calibrated. Background technique [0002] The aerospace survey ship is a measurement and control station set up on the sea to adapt to the development of missile and spacecraft tests. Its measurement and control equipment uses the ship as a platform. The measurement is under dynamic conditions. The position and attitude of the equipment are constantly changing. The measurement accuracy is not only It depends on the external measurement equipment itself, and also depends on the measurement accuracy of the ship attitude and ship position system. The aerospace survey ship is equipped with a h...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 郭敬明赵金宇杨轻云贾建禄
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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