Method for regulating propeller direction to point to combined-body spacecraft centroid

A technology for thrusters and spacecraft, which is applied in attitude control and other directions, and can solve the problem that the direction of the thruster jet no longer points to the center of mass.

Inactive Publication Date: 2013-08-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the jet direction of the thruster no longer points to the center of mass due to the change of the center of mass of the combined spacecraft after rendezvous and docking in the on-orbit service mission. The method of the center of m

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  • Method for regulating propeller direction to point to combined-body spacecraft centroid
  • Method for regulating propeller direction to point to combined-body spacecraft centroid
  • Method for regulating propeller direction to point to combined-body spacecraft centroid

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Embodiment

[0039] A method for adjusting the direction of the thruster to point to the center of mass of the combined spacecraft. Two thruster combination devices 3 with universal joints are installed at both ends of the mast 4, and the mast 4 is connected to the tracking spacecraft body. Two symmetrical thrusters that can be driven by universal joints are installed on the thruster combination device. The initial jet direction of the adjustable thruster points to the center of mass of the tracking spacecraft. By identifying the position of the center of mass of the combined spacecraft online, the deviation of the center of mass between the tracking spacecraft and the combined spacecraft is calculated. The universal joint is driven by a brushless DC motor. Driving the DC motor turns the gimbal, thereby reorienting the thrusters so that they are pointing back to the center of mass of the assembly.

[0040] The method for adjusting the direction of the thruster by the universal joint is as ...

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Abstract

The invention discloses a method for regulating a propeller direction to point to a combined-body spacecraft centroid, relating to a propeller control method of a combined-body spacecraft in on-orbit service, and the method further comprises a quality and characteristic identification method of the combined-body spacecraft, belonging to the field of posture control of a spacecraft. The method comprises the following specific implementing steps of 1, online identifying a centroid position of the combined-body spacecraft, and obtaining a centroid deviation of a tracking spacecraft and the combined-body spacecraft; 2, obtaining a regulation angle of the propeller according to the centroid deviation; and 3, adjusting the propeller direction according to the regulation angle of the propeller obtained in the step 2, and enabling a spray nozzle of the propeller to repeatedly point to the centroid of the combined-body spacecraft. According to the method, the combined-body centroid can be identified, and the propeller direction can be regulated and is enabled to point to the combined-body centroid, and the regulated propeller can be used for integrated control of a combined-body spacecraft attitude and orbit.

Description

technical field [0001] The invention relates to a method for adjusting the thruster direction to point to the center of mass of an assembled spacecraft, in particular to a thruster control method for an assembled spacecraft in on-orbit service, which also includes a method for identifying mass characteristics of an assembled spacecraft, belonging to The field of attitude control for spacecraft. technical background [0002] In the process of on-orbit service of space spacecraft, attitude-orbit integrated control is the process of spacecraft in-orbit operation, while considering the orbit and attitude maneuver tasks of the spacecraft, and realizing simultaneous control of the orbit box attitude by sharing a set of actuator configurations The integrated control of attitude and orbit can make the best use of the excitation ability of the actuator, save some hardware resources, and improve the efficiency of fuel utilization. [0003] In the rendezvous and docking mission of the...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 许涛张尧张景瑞翟光赵书阁
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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