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Method of using satellite rolling-axis rapid attitude manoeuvre to unload angular momentum of rolling axis and yawing axis

A technology of attitude maneuvering and rolling axis, which is applied in the direction of motor vehicles, space navigation equipment, space navigation aircraft, etc., can solve the problems of satellite cost increase, increase satellite volume and weight, etc., to ensure accuracy, save cost and space, Simple and feasible effect of unloading algorithm

Active Publication Date: 2013-07-24
哈尔滨工大卫星技术有限公司
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Problems solved by technology

[0004] In order to solve the angular momentum absorbed by the momentum exchange actuator of the existing unloading satellite, an additional unloading device needs to be installed on the satellite, resulting in an increase in the cost of the satellite, increasing the volume and weight of the satellite, thereby providing a fast attitude maneuver using the satellite rolling axis Method of Unloading Angular Momentum of Roll Axis and Yaw Axis

Method used

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  • Method of using satellite rolling-axis rapid attitude manoeuvre to unload angular momentum of rolling axis and yawing axis
  • Method of using satellite rolling-axis rapid attitude manoeuvre to unload angular momentum of rolling axis and yawing axis
  • Method of using satellite rolling-axis rapid attitude manoeuvre to unload angular momentum of rolling axis and yawing axis

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specific Embodiment approach 1

[0029] Specific implementation mode 1. Combination Figure 1-Figure 7 This specific embodiment will be described. A method for unloading the angular momentum of the rolling axis and the yaw axis by utilizing the rapid attitude maneuver of the satellite rolling axis, comprising the following steps:

[0030] Step 1: Define the satellite's own system ox b the y b z b and the inertial coordinate system ox I the y I z I and determine the initial unloading time t 0 ;

[0031] The inertial coordinate system ox I the y I z I : Take the center of mass at the initial unloading moment of the satellite as the origin, oz I Axis in satellite orbital plane, oz I The direction is the same as the direction of the total angular momentum that the satellite needs to unload, oy I The axis is perpendicular to the orbital plane of the satellite, and is opposite to the direction of the orbital angular velocity, ox I 、oy I with oz I The axes form a right-handed coordinate system;

[0...

specific Embodiment

[0103] Specific examples: combining Figure 4-Figure 6 This specific example will be described.

[0104] Taking the satellite that needs to unload the pitch axis as an example, the rationality of the designed unloading method is illustrated. The specific process is as follows:

[0105] Satellite moment of inertia: I = 4000 0 0 0 4000 0 0 0 1000 kg · m 2 , The maximum output torque of the rolling axis actuator is 0.4Nm, the maximum angular momentum is 50Nms, the satellite is running in a circular orbit, and the orbi...

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Abstract

The invention provides a method of using satellite rolling-axis rapid attitude manoeuvre to unload the angular momentum of a rolling axis and a yawing axis, and belongs to the technical field of spacecraft attitude control. The method resolves the problems that at present, an unloading device needs to be additionally installed on a satellite to unload the angular momentum absorbed by momentum exchange actuating mechanisms of the satellite, and therefore manufacturing cost of the satellite is increased, and the size and the weight of the satellite are increased. A body system and an inertial coordinate system of the satellite are defined, and an initial unloading moment is confirmed; and unloading is conducted by means of confirmation of the gravity gradient force moment borne by the satellite, accumulated angular momentum vectors of the gravity gradient force moment inside each orbital period, the angular momentum, needing to be unloaded, of all the momentum exchange actuating mechanisms on the rolling axis, the angular momentum, needing to be unloaded, of all the momentum exchange actuating mechanisms on the yawing axis, the number of turns of unloaded orbits of the satellite, the maneuvering angle in a satellite unloading process, and time used by the satellite rolling-axis maneuvering angle. The method can be widely applied to accumulated angular momentum unloading requirements of the actuating mechanisms.

Description

technical field [0001] The invention relates to a method for unloading the angular momentum of a rolling axis and a yaw axis by using a satellite rolling axis to perform rapid attitude maneuvering, and belongs to the technical field of spacecraft attitude control. Background technique [0002] Since the orbiting satellite is usually affected by the space disturbance torque, if the direction of the disturbance torque is fixed in the inertial space, the corresponding angular momentum will be accumulated inside the satellite. Usually, this part of the angular momentum is carried out by the momentum exchange actuator of the satellite. However, the ability of the actuator to absorb angular momentum is limited, so when the angular momentum accumulated by the actuator of the satellite is close to saturation, it is necessary to unload the accumulated angular momentum of the actuator. [0003] Satellites usually use magnetic torque devices, jet devices, etc. to generate external torq...

Claims

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Application Information

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IPC IPC(8): B64G1/22
Inventor 耿云海侯志立孙亚辉
Owner 哈尔滨工大卫星技术有限公司
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