Angular momentum coupling unloading method based on orbit control interference
A technology of coupling unloading and angular momentum, which is applied in the direction of space navigation vehicle guidance devices, etc., can solve the problem of inability to perform long-term orbit control, and achieve the effect of achieving high-precision trajectory capture, reducing jet volume, and improving the efficiency of satellite orbit change.
Active Publication Date: 2015-03-18
BEIJING INST OF CONTROL ENG
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[0003] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide an angular momentum coupling unloading method based on orbit control interference, and to solve the problem that long-term orbit control cannot be carried out when the satellite loses the jet control in the X-axis or Z-axis direction , to achieve satellite high-precision trajectory capture
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[0018] Suppose the orbital angular velocity of the satellite ω 0 , when the orbit control thruster is working, the disturbance moment on the +Z axis of the star body is T d . Assuming that the orbit control engine works continuously on a circle of orbit, an inertial coordinate system is established at the beginning of orbit control. The relationship between this coordinate system and the satellite body coordinate system is as follows: figure 1 As shown in the figure, Xb and Zb are the coordinate axes corresponding to the satellite body coordinate system, and X and Z are the coordinate axes corresponding to the satellite inertial coordinate system, then the angular momentum generated by the orbit control disturbance moment is:
[0019] H x = T d ∫ 0 θ ω 0 sin ω ...
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The invention discloses an angular momentum coupling unloading method based on orbit control interference. According to the method, accumulated angular momentum generated in the process of satellite orbit control is absorbed through the method of momentum wheel control, the characteristic that the angular momentum of a momentum wheel in the X direction and the angular momentum of a momentum wheel in the Z direction of a satellite are exchanged every 1 / 4 period due to orbit control disturbance torque is utilized, the accumulated orbit control angular momentum generated in the Z direction is unloaded through air injection in the X direction, the purpose of orbit control under the condition without air injection control in the Z direction for the satellite is achieved, the accumulated orbit control angular momentum generated in the X direction is unloaded through air injection in the Z direction, the purpose of orbit control under the condition without air injection control in the X direction for the satellite is achieved, and high-precision capture of satellite trails can be achieved. The momentum coupling unloading technology based on the orbit control interference can be used in orbit control of common satellites and can also be used in orbit control of on-orbit under-actuated satellites without X-axis air injection control or Z-axis air injection control, the application fields of the momentum coupling unloading technology can be extended to magnetism unloading from air injection coupling unloading, air injection amounts in the process of satellite orbit control can be reduced, and satellite orbital transfer efficiency can be improved.
Description
technical field [0001] The invention relates to an angular momentum coupling unloading method, in particular to an angular momentum coupling unloading method based on orbit control interference, which is mainly used for momentum management and disturbance angular momentum unloading in the orbit control process of spacecraft, and belongs to aerospace orbit control technology. Background technique [0002] In order to realize the high-precision frozen return orbit capture of sun-synchronous orbit spacecraft, when determining the orbit change strategy, the double-pulse orbit change method is generally adopted to realize the coordinated control of orbit eccentricity and perigee angle to ensure that the spacecraft orbit meets the freeze return requirements. During the long-term orbit control process of the spacecraft, the direct jet attitude control method is generally adopted to eliminate the disturbance torque generated by the orbit control engine, realize the attitude control ...
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IPC IPC(8): B64G1/26
Inventor 周剑敏袁军张笃周袁利曹永梅王胜刚王新民赵性颂王哲姚宁刘捷刘彤潘立鑫
Owner BEIJING INST OF CONTROL ENG