Satellite steady sun-facing orientation method taking earth pointing deviation as constraint

A satellite, stable technology, applied in space navigation equipment, space navigation aircraft, space navigation vehicle guidance devices, etc., can solve the problem of satellite expected attitude flip, improve stability and reliability, overcome strange phenomena, reduce Effects of Peak Desired Angular Velocity and Peak Energy Consumption

Active Publication Date: 2020-03-24
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0004] The main purpose of the present invention is to provide a stable satellite orientation method to the sun with the constraint of the ground pointing deviation, ai...

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  • Satellite steady sun-facing orientation method taking earth pointing deviation as constraint
  • Satellite steady sun-facing orientation method taking earth pointing deviation as constraint
  • Satellite steady sun-facing orientation method taking earth pointing deviation as constraint

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Embodiment Construction

[0040] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are not all embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0041] It should be noted that all scalars, vectors and coordinate system names in the embodiments of the present invention, such as Euler angle α, Euler axis E, inertial coordinate system I, etc., are all set for the convenience of description, while the present invention implements In the example, the selection of certain variables and spatial orientations, such as the constraint angle η is 90°, the -y b It is set as the expectation of the date axis, etc., and cannot be understood as ind...

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Abstract

The invention discloses a satellite steady sun-facing orientation method taking earth pointing deviation as constraint, and belongs to the technical field of spacecraft attitude control. The stable sun-facing orientation method comprises the following two steps: establishing an expected attitude of a satellite by two steps: firstly, establishing an intermediate attitude of the satellite on the basis of a satellite-geocentric connecting line direction, a satellite orbital plane normal direction and a satellite advancing direction; and then rotating the middle attitude around an Euler axis for acertain angle to reduce the sun pointing deviation of the satellite and ensure that the included angle between the expected earth axis and the earth center direction is not greater than the constraint angle. The expected attitude of the satellite obtained according to the strategy can keep stable change, the singular phenomenon that the expected attitude of the satellite violently changes in a short time under the sun-earth-satellite collinear condition caused by a traditional strategy is avoided, and therefore peak energy consumption in the sun-oriented process of the satellite is greatly reduced.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and in particular relates to a method for a satellite's steady sun-alignment orientation constrained by a ground-pointing deviation. Background technique [0002] Orientation to the sun is one of the attitude control mission modes commonly used by satellites. It sets the expected attitude of the satellite so that the plane of the satellite solar array is fully aligned with the sun to provide sufficient energy, and at the same time, it can also set appropriate constraints to meet other components of the satellite. , equipment or payload requirements for satellite attitude. Among them, the sun-orientation mode constrained by the ground pointing deviation is a relatively common satellite-to-sun orientation mode. It can not only meet the charging requirements of satellites for sun-orientation, but also ensure that important components such as antennas and cameras have the ability ...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 张斌斌季浩然
Owner NAT UNIV OF DEFENSE TECH
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