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A star map simulation method for a composite three-field star sensor

A technology of star sensor and simulation method, which is applied in the field of astronomical navigation, can solve the problems of inability to realize star map simulation and high device requirements, and achieve the effects of improving design quality, low cost, and easy operation

Active Publication Date: 2018-04-10
江苏智行未来汽车研究院有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The focus of this method is to realize the real-time performance of star map recognition, which requires high equipment and cannot realize star map simulation.

Method used

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  • A star map simulation method for a composite three-field star sensor
  • A star map simulation method for a composite three-field star sensor
  • A star map simulation method for a composite three-field star sensor

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Embodiment

[0094] The field of view of the optical system of the three-field star sensor is 10°×10°, the aperture is 27.3mm, and the focal length is 43.89mm. The optical system is as follows: Figure 5 As shown, it contains 5 lenses, and the optical surface parameters are shown in Table 1, wherein the first and seventh optical surfaces are aspherical. The aspheric coefficient of the first optical surface is K 1 =-0.41, A 1，8 =3.12×10 -12 , and the rest are 0. The aspheric coefficient of the seventh optical surface is K 1 =-0.61, A 1，4 =4.85×10 -5 , A 1，6 =3.80×10 -7 , A 1，8 =1.26×10 -9 , and the rest are 0. The limit star magnitude is selected as 5.2, and the number of detector pixels is 1024×1024.

[0095] Table 1 Optical system parameters (unit: mm)

[0096] Face number

radius

thickness

Material

1

19.44

6.00

Silica

2

219.08

9.00

3

16.90

6.00

K9

4

-40.89

1.00

ZF1

5

9.24

9.00

...

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Abstract

The invention discloses a composite three-view-field star sensor star map simulation method. The composite three-view-field star sensor star map simulation method comprises the following steps that step 1, an observation star meeting the requirements is selected according to the limiting magnitude of a star sensor, and star number, star magnitude, right ascension and declination data of the observation star is extracted and stored in an observation star database; step 2, statistics is conducted on observation stars in three optical system view fields of the composite three-view-field star sensor, and incidence angles of the observation stars in subsystem coordinate systems the observation stars belongs to in the X and Y directions are calculated; step 3, the star magnitude, view field position data of fake stars is randomly produced according to the total number of the fake stars; step 4, imaging of the observation stars and the fake stars within the respective view fields performed by an optical system is simulated through ray tracing, and image plane information is calculated; step 5, the brightness of each pixel of a digital star map is calculated, and the digital star map is output. The composite three-view-field star sensor star map simulation method is simple and convenient to operate and low in cost, does not depend on a hardware system formed through machining and can provide rich simulation star map data for other technical research of the composite three-view-field star sensor.

Description

technical field [0001] The invention belongs to the technical field of celestial navigation, and relates to a technology for obtaining a simulated star map by using a computer to simulate the imaging process of a composite three-field star sensor. Background technique [0002] Effective attitude control is a necessary guarantee for the smooth flight of satellites and other spacecraft, and attitude measurement is the premise of attitude control. The star sensor takes stars as the working object, takes pictures of them and recognizes them, and then measures the attitude information, which is the current accuracy. One of the tallest attitude measuring instruments. At present, single-view star sensors are mainly used. These star sensors usually have a large field of view, are easily affected by stray light such as sunlight, and have low reliability. At the same time, the attitude measurement accuracy of the roll angle is lower than that of the pitch and yaw angles. Spacecraft ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02
CPCG01C21/025
Inventor 吴峰朱锡芳相入喜许清泉李辉邹全
Owner 江苏智行未来汽车研究院有限公司
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