All-electric stability control method for large-orbit eccentricity ratio multi-body tethered satellite

A stable control method and tethered satellite technology, applied in the field of satellite control, can solve problems such as the consumption of working fluid, the limited working fluid that the satellite can carry, and the inability to meet the needs of long-term detection tasks, so as to achieve good versatility and solve the problem of stable control problem effect

Active Publication Date: 2021-03-19
SUN YAT SEN UNIV
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Problems solved by technology

This control method needs to consume working fluid. Since the satellite can carry limited working fluid, it cannot meet the needs of long-term detection missions.

Method used

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  • All-electric stability control method for large-orbit eccentricity ratio multi-body tethered satellite
  • All-electric stability control method for large-orbit eccentricity ratio multi-body tethered satellite
  • All-electric stability control method for large-orbit eccentricity ratio multi-body tethered satellite

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Embodiment Construction

[0032] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. For the step numbers in the following embodiments, it is only set for the convenience of illustration and description, and the order between the steps is not limited in any way. The execution order of each step in the embodiments can be adapted according to the understanding of those skilled in the art sexual adjustment.

[0033] Such as figure 1 As shown, the present invention provides an all-electric stability control method for a multi-body tethered satellite with a large orbital eccentricity, comprising the following steps:

[0034] S1. Construct the dynamic model of the space multi-body tethered satellite system based on the Lagrangian method;

[0035] Specifically, the modeling coordinate system of the system model is the earth-centered inertial system Oxy, and the dynamic coordinate system in, The system takes the parent st...

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Abstract

The invention discloses an all-electric stability control method for a large-orbit eccentricity ratio multi-body tethered satellite. The system comprises the steps that a space multi-body tethered satellite system power model is constructed based on a Lagrange method; according to the space multi-body tethered satellite system power model, the relation between the tether winding and unwinding speed and stable sine swing is obtained, and the stable winding and unwinding rate is obtained; and the tether is recovered and released according to the stable recovery and release rate. The stability control problem of the multi-body tethered satellite is solved by adjusting the take-up and pay-off speed of electric rope shafts installed on satellites in the system on tethers. The all-electric stability control method for the large-orbit eccentricity ratio multi-body tethered satellite can be widely applied to the field of satellite control.

Description

technical field [0001] The invention belongs to the field of satellite control, in particular to an all-electric stability control method for a multi-body tethered satellite with a large orbital eccentricity. Background technique [0002] A space multi-body tethered satellite system usually consists of multiple satellites connected in series through tethers. In order to achieve large-scale space observation and atmospheric detection, the space multi-body tethered satellite system often needs to operate on an elliptical orbit with a large eccentricity. Larger orbital eccentricity will cause non-periodic swing motion of the system, and the whole system moves like a pendulum. This kind of motion state will not only have a great negative impact on the stability of the system and even cause the system to overturn and become unstable, but will also be detrimental to the accuracy of space observation. Aiming at this problem, the conventional countermeasure is to use the thruster ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/24
CPCB64G1/10B64G1/24
Inventor 史格非
Owner SUN YAT SEN UNIV
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