Radiation open loop tethered satellite formation constant speed spinning deployment control method

A spin-deploying, tethered satellite technology, applied in attitude control, non-electric variable control, control/regulation system, etc., can solve the problem of lack of radiation open-loop tethered satellite formation dynamics and control

Active Publication Date: 2016-04-06
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Application Information

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Problems solved by technology

[0003] At present, in the technical field of dynamics and control of tethered satellite formations, the existing technical methods mostly focus on solving the dynamics and stability control of multi-body tethered satellite formations and the

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  • Radiation open loop tethered satellite formation constant speed spinning deployment control method
  • Radiation open loop tethered satellite formation constant speed spinning deployment control method
  • Radiation open loop tethered satellite formation constant speed spinning deployment control method

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Embodiment 1

[0051]A radiating open-loop tethered satellite formation uniform-speed spin deployment dynamics and control method, the purpose is to aim at the radiative open-loop tethered satellite formation running on the circular Kepler orbit in the gravitational field of the center of the earth, ignoring the orbits of the main star and the sub-star Out-of-plane motion and various perturbation factors; the main star is regarded as a rigid hub with a radius of rotation, and the connection points of the tether and the main star are located on the edge of the main star and are symmetrically distributed; the tether connecting the main star and the sub-star is regarded as a uniform distribution of mass Linear elastic body, ignoring the lateral stiffness and torsional stiffness, considers that the spin unfolding process is always in tension; considering the motion characteristics of the multi-body system and the gravity gradient moment, the dynamics of the spin unfolding of the system is establis...

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Abstract

The invention discloses a radiation open loop tethered satellite formation constant speed spinning deployment control method, relates to a dynamics construction and control strategy design in which the tethered satellite formation is spun and deployed at a constant speed into a radiation open loop form and belongs to the field of spacecraft formation control. In view of the radiation open loop tethered satellite formation running on a circular Kepler track in an earth center gravitational field, in consideration of multi-body system movement characteristics and gravity gradient moment effects, system spinning deployment dynamics is built via a Lagrange equation; on the basis, a closed loop control strategy is designed, the main satellite is spun and deployed at a constant speed, compensation in view of the gravity gradient moment is carried out, damping is added to the tail section of the deployment to restrain system oscillation; the dynamics and the control method are simple, effective and easy to realize; and the whole process of controlling the tethered satellite system to deploy at a constant speed is smooth, safe and high in reliability.

Description

technical field [0001] The invention relates to the dynamics and control strategy design of tethered satellite formation spin expansion into a radiation open-loop configuration, and belongs to the field of spacecraft formation control. Background technique [0002] Tethered satellite formations have special advantages in space power generation, space operations, and construction of large space structures. There are many types of tethered satellite formation configurations, and "radiation open loop" is a new type of formation configuration. The radiation open-loop tethered satellite formation is composed of a central main star and multiple sub-stars connected to the main star by tethers. The main star generates spin motion through the actuator, and uses the centrifugal force generated by the spin motion to tension the tether to drive the formation to a certain degree. Angular velocity spins in space. On the one hand, the design of this configuration maintained by centrifuga...

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCB64G1/244G05D1/101
Inventor 张景瑞翟光梁斌李雨阳
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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