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Angular momentum unloading method and system for orbit-changing process of all-electric propulsion satellite

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

Active Publication Date: 2018-09-11
CHINA ACADEMY OF SPACE TECHNOLOGY
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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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  • Angular momentum unloading method and system for orbit-changing process of all-electric propulsion satellite
  • Angular momentum unloading method and system for orbit-changing process of all-electric propulsion satellite
  • Angular momentum unloading method and system for orbit-changing process of 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 an angular momentum unloading method for an orbit-changing process of an all-electric propulsion satellite. The method comprises the following steps: setting an unloading arc segment A and an unloading arc segment B before each orbit period starts; determining adjusting angles in thrust directions of electric thrusters by calculations; determining whether adjusting angles in the thrust directions of the electric thrusters of the unloading arc segment A exceed the critical value or not, and entering the unlading arc segment A if not; if so, adjusting angular momentum unloading amount of the unloading arc segment A again, then calculating adjusting angles in the thrust directions of the electric thrusters again, entering the unloading arc segment A, determining a newangular momentum unloading amount through new accumulation of wheel-angular momentum after the unloading arc segment A finishes unloading, calculating adjusting angles in thrust directions of new electric thrusters and entering the unloading arc segment B. The angular momentum unloading problem is resolved when the electric thrusters perform an orbit maneuvering control task during the orbit-changing process. Therefore, combined control over orbit maneuvering and angular momentum unloading is achieved by 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 Applications(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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