Digital sun sensor for stable-spinning micro/nano satellite

A sun sensor and micro-nano-satellite technology, which is applied in the direction of transmitting sensing components, instruments, simulators, etc. using optical devices, can solve the constraints of accuracy and field of view, and it is difficult to meet the high-precision of micro-nano satellites and the small omni-directional angle measurement. Volume and other issues, to achieve the effect of improved field of view and accuracy, low cost, and simplified difficulty

Inactive Publication Date: 2009-11-25
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

The accuracy and field of view of the digital code disc sun sensor are mutually restricted, and its traditional design is dif

Method used

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  • Digital sun sensor for stable-spinning micro/nano satellite
  • Digital sun sensor for stable-spinning micro/nano satellite
  • Digital sun sensor for stable-spinning micro/nano satellite

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Embodiment Construction

[0021] like figure 1 As shown, the present invention consists of a sensor housing 1, a measuring seam 2, an instruction seam 3, a front vertical photoelectric code disk 4, a rear vertical photoelectric code disk 5, a front horizontal photoelectric code disk 6, a rear horizontal photoelectric code disk 7, and a circuit processing unit. System 8. The sensor housing 1 is a cuboid made of aluminum alloy. Two slopes are processed on the front and rear edges of the upper surface of the cuboid. The angle between the slope and the upper surface is 30 degrees. The length of the slope is equal to the width of the sensor housing 1. The distance between the upper surface of the sensor shell 1 is 1 mm. The design of this structure makes it possible for the sensor to be sensitive to sun angles of 45°, 90°, 135° and 180°, which is useful for expanding the field of view of the sensor and measuring the sun angle in all directions. Plays an important role; the measuring seam 2 is engraved on ...

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Abstract

A digital sun sensor for stable-spinning micro/nano satellite comprises a detector, an instruction seam, a measuring seam and an electric circuit processing subsystem, wherein the detector is formed with two groups of orthogonal photoelectric coded discs by four photoelectric coded discs and comprises two vertical photoelectric coded discs and two horizontal photoelectric coded discs. The instruction seam is vertical with the measuring seam. The sun light vertical with the measuring seam penetrates the measuring seam and irradiates to the photoelectric coded discs. A voltage signal is output after the sensitization of the photoelectric battery. The included angle between the solar vector direction and the spinning shaft direction of the satellite can be obtained through executing amplifying, comparing, quantifying and matching processing to the signal by the circuit processing subsystem. The invention realizes the digital sun sensor which has the advantages of large viewing field, high precision, small volume and simple structure, and has important practical meaning for realizing high-precision solar zenith measuring by the stable-spinning micro/nano satellite.

Description

technical field [0001] The invention relates to a digital sun sensor used for spin-stabilized micro-nano satellites and using a photoelectric code disc as a detector, which is suitable for attitude determination of spin-stabilized micro-nano satellites. Background technique [0002] The high brightness and high signal-to-noise ratio of the sun make it easier to capture the sun. Whether it is a three-axis stabilized satellite or a spin-stabilized satellite, the sun sensor is used as one of the main devices for attitude determination. With the development of satellite miniaturization research and the increasing accuracy of spacecraft attitude control, the traditional analog sun sensor cannot meet the requirements in terms of volume, mass and power consumption. In particular, after the spin-stabilized satellite is in the rate damping mode (before spin-up), the spin rate of the satellite is only 2° / s, and the "V" type slit sun sensor cannot determine the attitude of the satellit...

Claims

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Application Information

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IPC IPC(8): G01C1/00G01D5/30G05B19/042
Inventor 郭雷崔培玲张翠全伟杨照华
Owner BEIHANG UNIV
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