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Analog solar sensor and its installation structure and measurement method

A sun sensor and installation structure technology, applied in the direction of aerospace vehicle guides, aircraft, transportation and packaging, etc., can solve the problems of large invalid field of view, affecting use, increasing system design complexity and cost, etc.

Active Publication Date: 2020-03-17
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Under normal circumstances, when sunlight enters the effective field of view, the formed light spot moves on the cell to reflect the change of the incident angle of sunlight. However, due to the large size of the traditional analog solar sensor cell, it will produce a large invalid field of view. The interference of external reflected light after entering the invalid field of view will inevitably affect the measurement accuracy; in addition, stray light irradiating on the inner side wall of the diaphragm will also cause internal reflection interference, and further irradiating on the cell will also affect the measurement accuracy. measurement accuracy
[0007] 2) It is easily blocked by the surface components of the spacecraft, which affects the use
However, since the analog sun sensor is an optical measurement component, it is required that there is no obstruction in the entire field of view. However, modern spacecraft are usually equipped with two-wing solar panels, and the two-wing sail panels will inevitably enter the field of view of the measurement surface of the analog sun sensor in the corresponding direction. , affect its measurement accuracy, and even cause its measurement data to be wrong
[0009] In order to solve the above two problems, the traditional solution is to reduce the field of view of the sun sensor to reduce the interference of various reflected lights, and configure additional sensors to compensate for the sun vector measurement of the shading surface of the sail, increasing the System Design Complexity and Cost

Method used

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  • Analog solar sensor and its installation structure and measurement method
  • Analog solar sensor and its installation structure and measurement method
  • Analog solar sensor and its installation structure and measurement method

Examples

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example 1

[0056] For a class of ±X in spacecraft b The satellite with two-wing sailboards installed in the axial direction, this example provides the solar sensor installation structure on the spacecraft adopts the analog sun sensor provided by the embodiment of the present invention, the width of the upper square diaphragm is a, and the width of the lower cell mounting surface is 2a, and the width of the cell is a; establish a Cartesian coordinate system, and the cells located in the four quadrants have equal areas and are installed directly below the diaphragm, and the distance between the diaphragm and the cell is determined according to the size of the field of view; The above-mentioned analog sun sensor is installed orthogonally and integrated on one probe, and the sampling dual probes are installed obliquely.

[0057] Three analog sun sensors (numbered Taimin X, Taimin Y and Taimin Z) are installed orthogonally on a single probe, and the field of view of each sun sensor is designe...

example 1

[0058] Example 1 provides the measurement methods for the solar sensor installation structure on the provided spacecraft, including:

[0059] Step 1, take the sum of the output currents of the six solar sensor measuring surfaces of the two probes respectively, and obtain I sum_AX ,I sum_AY ,I sum_AZ ,I sum_BX ,I sum_BY ,I sum_BZ , to find the maximum value I max , I max The corresponding sun sensor is in an effective state, and the corresponding measurement surface is an effective measurement surface.

[0060] Step 2, according to the output current of the effective solar sensor determined in step 1, combined with the structural parameters, calculate the position (abscissa x and ordinate y) of the central point of the aperture mapped on the battery sheet along the sun incident light direction, the calculation formula is:

[0061]

[0062]

[0063] In the formula, a is the side length of the square aperture, i 1 , i 2 , i 3 and i 4 It is the output current of t...

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Abstract

The invention discloses an analog sun sensor as well as a mounting structure and a measurement method thereof. The analog sun sensor disclosed by the invention comprises a diaphragm and a battery piece, wherein the diaphragm is dead against the battery piece; and the area of the battery piece is the same as the area of the diaphragm.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude measurement, and relates to a novel analog sun sensor view field structure design and a sun sensor layout method for realizing sun vector measurement in the whole sky. Background technique [0002] The sun sensor is one of the most commonly used attitude sensors in the field of spacecraft attitude measurement. It determines the direction information of the sun by sensing the sun's illumination, and then fuses it with other vector information to calculate the attitude information of the satellite. [0003] The analog solar sensor is the most commonly used solar sensor, its basic structure and principle are as follows: figure 1 shown. The simulated sun sensor is mainly composed of an aperture 13 and a battery sheet 12; both the battery sheet 12 and the aperture 13 are square, and the side length of the battery sheet 12 is twice the width of the aperture. Sunlight irradiates from the up...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24B64G1/36
CPCB64G1/363G01C21/24
Inventor 谢祥华黄志伟何夏维张锐严玲玲祁海铭胡志强刘剑于晓至
Owner SHANGHAI ENG CENT FOR MICROSATELLITES