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An Orbit Control Method Using Attitude Rotation to Disturb Angular Momentum Self-Balance

An orbit control and self-balancing technology, applied in space navigation equipment, space navigation aircraft, motor vehicles, etc., can solve the problems of angular momentum saturation of the whole star, affecting satellite orbit control ability, etc., and achieve the effect of improving orbit control ability.

Active Publication Date: 2022-01-07
CHANGGUANG SATELLITE TECH CO LTD
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to propose an orbit control method that utilizes attitude rotation to disturb the angular momentum self-balancing, utilizes the principle of the periodic exchange of angular momentum of the remaining two axes during the rotation of the satellite around the thrust direction, and converts the entire star angle in the orbit control task The momentum is controlled within a certain range, so as to solve the problem that the continuous long-term orbit control mission will cause the angular momentum saturation of the whole star and affect the orbit control ability of the satellite

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  • An Orbit Control Method Using Attitude Rotation to Disturb Angular Momentum Self-Balance
  • An Orbit Control Method Using Attitude Rotation to Disturb Angular Momentum Self-Balance
  • An Orbit Control Method Using Attitude Rotation to Disturb Angular Momentum Self-Balance

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specific Embodiment

[0073] A satellite with a mass of 60kg is equipped with only one orbit control thruster with a thrust of 0.1N. The thruster is installed in the -X direction of the satellite body system, and the interference moment of the thruster thrust on each axis of the satellite body coordinate system is [M x , M y , M z ]=[0.014, 1.55, -2.16]mN·m, the maximum angular momentum control capability of each axis of the satellite is 0.5N·m·s.

[0074] In the orbit control mission, the thrust of the thruster is along the +X direction of the satellite body. The satellite first establishes a three-axis attitude to the ground, and then on the basis of the three-axis attitude to the ground, the satellite rotates around the X-axis of the orbital coordinate system at a rotational angular velocity of 1° / s. The thruster starts to work from the satellite's rotation, and the orbit control lasts for 5800s, about one orbital period.

[0075] During the orbit control mission, the angular momentum of eac...

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Abstract

The invention discloses an orbit control method for self-balancing disturbance angular momentum by attitude rotation, belonging to the technical field of spacecraft orbit control. The method includes the following steps: step 1, establishing the attitude of the satellite orbit control task and keeping it stable; step 2, performing attitude rotation around the thrust vector axis; step 3, performing orbit control with the thruster working. For satellites that are not equipped with an attitude control thruster or are damaged by an attitude control thruster, the present invention makes the attitude of the satellite rotate around the vector axis of the thruster during the satellite orbit control task, so as to ensure that the satellite continues to act on the propulsion disturbance torque , the angular momentum of each axis of the satellite is always controlled within a certain range. This enables the satellite to work continuously for a long time with only the orbit control thruster, which greatly improves the orbit control capability of the satellite.

Description

technical field [0001] The invention relates to an orbit control method using attitude rotation to self-balance disturbance angular momentum, and belongs to the technical field of spacecraft orbit control. Background technique [0002] In the satellite orbit control mission, due to the existence of thruster installation error, the orbit control thruster will generate disturbance torque when it is working. For satellites without attitude control thrusters or with damaged attitude control thrusters, the disturbance angular momentum generated by the accumulation of orbit control disturbance moments can only be absorbed by the satellite's angular momentum management devices, such as flywheels and control moment gyroscopes. Due to the limited angular momentum that can be absorbed by the angular momentum management device of the satellite, the cumulative angular momentum generated by the propulsion disturbance torque will cause the saturation of the angular momentum of the entire ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/244
Inventor 胡建龙范林东戴路徐开王国刚孟德利郑鸿儒刘东宸
Owner CHANGGUANG SATELLITE TECH CO LTD
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