Sun sensor and measuring method thereof

A technology of a solar sensor and a photosensitive sensor, which is applied in the direction of a combined navigator and the like, can solve the problems such as the inability of the digital solar sensor to be suitable for the aerospace environment and damage, and achieve the effect of being beneficial to popularization and application, preventing bombardment damage and being cheap.

Inactive Publication Date: 2010-06-23
SUZHOU UNIV +1
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Problems solved by technology

However, because cosmic high-energy particles in space are easy to cause damage to the bombardment...

Method used

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  • Sun sensor and measuring method thereof
  • Sun sensor and measuring method thereof
  • Sun sensor and measuring method thereof

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Embodiment 1

[0031] This embodiment provides a sun sensor, which includes an optical path introducer, a photosensitive sensor and a signal processor.

[0032] See attached figure 1 And attached figure 2 , is a structural schematic diagram and a top view of a sun sensor optical path introducer provided by an embodiment of the present invention; the reference optical fiber 1 is placed in the center of the optical path introducer, with the reference optical fiber as the center of the circle, and 4 pairs (8 root) lead-in optical fiber 2, each pair of lead-in fibers consists of 2 fibers, and the 2 lead-in fibers are symmetrically distributed about the center of the circle; in the plane between each pair of lead-in fibers and the reference fiber, the end face normal of each lead-in fiber and the reference The normal line of the end surface of the optical fiber is at an angle of 60°, and they are fixed on the light introducer mount 3; the output end of each optical fiber is connected with a pho...

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Abstract

The invention discloses a sun sensor and a measuring method thereof, relating to a device of an attitude sensor for measuring the relative positions of an aerocraft such as a satellite and the like and the sun and a measuring method thereof. The device comprises a light path introducer, a photosensor and a signal processor. The light path introducer consists of a reference optical fiber and introducing optical fibers, wherein the reference optical fiber is arranged at the center of the light path introducer, 2-2n pairs of introducing optical fibers are uniformly distributed on a circular track taking the reference optical fiber as the center of the a circle, wherein n is 2, 4 or 8, each pair of the introducing optical fibers comprise two optical fibers which are symmetrically distributed based on the center of the circle, and the end face normal of each introducing optical fiber and the end face normal of the reference optical fiber form an included angle of 15-60 degrees. The photosensor consists of photoelectric sensing elements with the same number as that of optical fiber, and the output end of each optical fiber is in butt joint with a photoelectric sensing element. The invention has the characteristics of high-precision resolution ratio, small volume, light weight, simple structure, low price and suitability for aerospace environment, and has wide generalization and application prospects.

Description

technical field [0001] The invention relates to a device and a measuring method of an attitude sensor between the position of an aircraft such as a satellite and the sun, and in particular to a sun sensor using a multi-channel light-guiding optical fiber as a light introducer and a measuring method thereof. Background technique [0002] The sun sensor is the most widely used type of positioning sensor in the field of aviation and aerospace, and the sun sensor must be equipped on the aircraft and the satellite. Determine its own attitude by measuring the position of the sun relative to the aircraft body coordinate system. The sun is chosen as the reference target because the angular radius of the apparent disk of the sun is almost independent of the orbit of the aircraft. Therefore, for most applications, treating the sun as a point light source simplifies the sun sensor design and the aircraft attitude determination algorithm . In addition to providing attitude information...

Claims

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Application Information

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IPC IPC(8): G01C21/24
Inventor 周望余建军李烨李丹周建康陈新华陈宇恒
Owner SUZHOU UNIV
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