Real-time sun avoidance method of camera with cylindrical hood for geostationary orbit satellite

A geostationary orbit and sunshade technology, which is used in motor vehicles, space navigation equipment, space navigation aircraft, etc., can solve problems such as the inability to meet the needs of imaging tasks, eliminate hidden dangers of jet unloading, avoid a smooth process, and improve use safety. sexual effect

Inactive Publication Date: 2018-03-06
BEIJING INST OF CONTROL ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This obviously cannot meet the growing demand for optical imag

Method used

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  • Real-time sun avoidance method of camera with cylindrical hood for geostationary orbit satellite
  • Real-time sun avoidance method of camera with cylindrical hood for geostationary orbit satellite
  • Real-time sun avoidance method of camera with cylindrical hood for geostationary orbit satellite

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Embodiment 1

[0051] The specific parameters of geostationary orbit satellites are as follows:

[0052] Avoidance parameters: sunlight avoidance safety angle α = 30°, Δ = 2.5° indicates the avoidance margin angle, a and b indicate parabolic coefficients, here select a = -6, b = 1.025.

[0053] Orbit initial value:

[0054] orbital epoch March 20, 2010 15:00:00,

[0055] Semi-major axis (km) 42164.238885703373,

[0056] Eccentricity 0.00013534077386388930,

[0057] Orbit inclination (degrees) 0.0026285532110204346,

[0058] Ascending node right ascension (degrees) 131.49687827859242,

[0059] Argument of perigee (degrees) 95.486669826235925,

[0060] Mean anomaly (degrees) 267.65066999183171.

[0061] Calculated according to the steps given earlier,

[0062] (1) According to the solar orbit coordinate So, the sun avoidance offset angle can be calculated in real time, for example, at the starting point of the sun avoidance,

[0063] So=[-0.537264370964670 0.000039568429893 0.84341389346...

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Abstract

A real-time sun avoidance method of a camera with a cylindrical hood for a geostationary orbit satellite includes a first step of calculating, according to the orbital information, an included angle [beta] between the direction of the sun and the Z axis of an orbital coordinate system, and a sun avoidance offset angle [phi]sunavoid before optimization; a second step of determining the trajectory of a parabola A: for dA>0, then A=ax2+bx, otherwise, A remains unchanged, where the parabola independent variable x=[alpha]+[delta]-[beta], [delta] denotes a selected avoidance margin angle and a and bdenote parabolic coefficients respectively; a third step of calculating a camera safety angle [tau] after optimization; and a fourth step of calculating a sun avoidance offset angle [phi]<[tau]>sunavoid after optimization according to the calculated camera safety angle [tau] after optimization in the third step. The method in the invention ensures that the included angle between the direction ofthe sun and the optical axis of the camera transitions smoothly at the sun avoidance starting point and ending point in accordance with the pre-designed parabolic trajectory, thereby eliminating the risk of jet unloading due to the sun avoidance and improving the service life of the camera.

Description

technical field [0001] The invention belongs to the field of attitude control of spacecraft, and relates to a method for avoiding sunlight in real time for a camera in a geostationary orbit with a cylindrical shade camera. Background technique [0002] In the field of high-resolution area array remote sensing in geosynchronous orbit, a national major special project, for the first time in the geosynchronous orbit imaging process, the angle between the camera optical axis and the direction of the sun is small around midnight at the sub-satellite point. Judging from the disclosed technical data both at home and abroad, there is no relevant method for avoiding real-time sunlight of the camera lens with a cylindrical shading cover, and it is even more impossible to optimize its design. This obviously cannot meet the growing demand for optical imaging missions of high-orbit remote sensing stars in my country; [0003] With the rapid development of science and technology, more an...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 乔国栋刘新彦宗立森黎康史晓霞彭洲
Owner BEIJING INST OF CONTROL ENG
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