A method and system for unloading angular momentum during orbit change of an all-electric propulsion satellite

A technology of angular momentum unloading and electric propulsion, which is applied in the direction of motor vehicles, space navigation equipment, space navigation equipment, etc., to avoid the effect of attitude loss control

Active Publication Date: 2020-07-14
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and to provide a method and system for unloading angular momentum during the orbit change process of an all-electric propulsion satellite. The problem of angular momentum unloading in the case of orbital maneuver control tasks, realizing the joint control of orbital maneuvering and angular momentum unloading of all-electric propulsion satellites

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  • A method and system for unloading angular momentum during orbit change of an all-electric propulsion satellite
  • A method and system for unloading angular momentum during orbit change of an all-electric propulsion satellite
  • A method and system for unloading angular momentum during orbit change of an all-electric propulsion satellite

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Embodiment Construction

[0045] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0046] During the orbit change process of the all-electric propulsion satellite, two electric thrusters are used to ignite the orbit change, and two unloading...

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Abstract

The invention discloses a method for unloading angular momentum during orbit change of an all-electric propulsion satellite. The method includes the following steps: before the start of each orbital period, setting the unloading arc segment A and the unloading arc segment B; calculating and determining the thrust direction of the electric thruster Adjust the angle; judge whether the thrust direction adjustment angle of the electric thruster in the unloading arc section A exceeds the critical value, if it does not exceed the critical value, enter the unloading arc section A; if it exceeds the critical value, it is necessary to readjust the angular momentum unloading of the unloading arc section A Then recalculate the thrust direction adjustment angle of the electric thruster and enter the unloading arc section A. After the unloading arc section A completes unloading, the new angular momentum unloading amount is determined again through the new wheel train angular momentum accumulation, and the new electric thruster is calculated and determined. Adjust the thrust direction of the thruster to enter the unloading arc section B. The invention solves the angular momentum unloading problem when the electric thruster performs the orbital maneuver control task during the orbit change process, and realizes the joint control of the orbital maneuvering and angular momentum unloading of the all-electric propulsion satellite.

Description

technical field [0001] The invention belongs to the technical field of satellite orbit attitude dynamics and control, and in particular relates to a method and system for unloading angular momentum during orbit change of an all-electric propulsion satellite. Background technique [0002] All-Electric Propulsion Satellite (All-Electric Propulsion Satellite) uses a high specific impulse electric propulsion system (such as ion electric propulsion or Hall electric propulsion, etc.) Tasks such as satellite transfer orbit change, on-orbit position maintenance after satellite entry, angular momentum unloading, and de-orbiting. For all-electric propulsion satellites, due to the limitation of the number of electric thrusters, installation location, and on-orbit power supply, the east-west, north-south position-keeping controls are coupled with each other, and the control parameters are reduced in the failure mode of the electric thrusters, so the position-keeping strategy design is v...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/242B64G1/245
Inventor 王敏李强袁俊刚胡照梁新刚
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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