Moment distribution method for rapid maneuvering satellite based on mixed actuating mechanism

A technology of mixed execution and maneuvering satellites, which is applied in the direction of artificial satellites and aerospace vehicle guidance devices, can solve the problems of reduced execution torque and low precision, and achieve the effect of fast maneuvering and optimal hybrid power consumption

Active Publication Date: 2012-08-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to solve the problem that the single-frame control moment gyroscope group falls into a dead zone after the rapid maneuvering and maneuvering of the satellite with the single-frame

Method used

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  • Moment distribution method for rapid maneuvering satellite based on mixed actuating mechanism
  • Moment distribution method for rapid maneuvering satellite based on mixed actuating mechanism
  • Moment distribution method for rapid maneuvering satellite based on mixed actuating mechanism

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specific Embodiment approach 1

[0028] Specific implementation mode one: the following combination figure 1 To describe this embodiment,

[0029] A torque distribution method for a fast maneuvering satellite based on a hybrid actuator, the specific implementation process is as follows:

[0030] Step 1. In each control cycle, obtain the command torque signal T output by the controller c , command torque signal T c is the component array of the command torque in the astral coordinate system;

[0031] Step 2. According to the command torque signal T obtained in step 1 c , to obtain the frame angular velocity assigned to the single frame control moment gyro group with the angular acceleration assigned to the flywheel

[0032] Step 3. The frame angular velocity of the single frame control moment gyroscope group obtained in step 2 The optimized frame angular velocity assigned to the single frame control moment gyro group

[0033] Step 4. According to the optimized frame angular velocity obtained in st...

specific Embodiment approach 2

[0039] Specific implementation mode two: the following combination figure 1 Describe this embodiment, this embodiment is a further description of Embodiment 1,

[0040] A torque distribution method for fast maneuvering satellites based on hybrid actuators, which obtains the frame angular velocity assigned to the single frame control moment gyro group Angular acceleration with flywheel The method is:

[0041] Step 21, write the optimization index with the weighting of the power consumption of n single-frame control moment gyroscopes and m flywheel systems and the angular momentum of the flywheel as the performance index:

[0042] J = 1 2 [ δ · T Q δ · + Ω · T W Ω · + ...

specific Embodiment approach 3

[0068] Specific implementation mode three: the following combination figure 1 Describe this embodiment, this embodiment is a further description of Embodiment 1,

[0069] A method for moment distribution of a fast maneuvering satellite based on a hybrid actuator, wherein step 4 is based on the optimized frame angular velocity obtained in step 3 The method of judging whether each single-frame control moment gyro falls into the dead zone is as follows: if the absolute value of the frame angular velocity of the single-frame control moment gyro is gradually decreasing,

[0070] The absolute value of the frame angular velocity of the single frame control moment gyro is reduced to the minimum speed of the frame angle of the single frame control moment gyro Then it is determined that the single-frame control moment gyroscope falls into the dead zone;

[0071] Or: if the absolute value of the frame angular velocity of the single-frame control moment gyro is gradually increasing, ...

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Abstract

A moment distribution method for a rapid maneuvering satellite based on a mixed actuating mechanism relates to the technical field of spacecraft attitude control and solves the problems that the precision is low due to the fact that single gimbal control moment gyroscopes are in a dead zone and the actuating force is weakened after the satellite taking single gimbal control moment gyroscopes and flywheels as actuating mechanisms is maneuvered rapidly and maneuvered. The realizing process of the moment distribution is as follows: obtaining the gimbal angular speed distributed to the single gimbal control moment gyroscopes and the angular acceleration speed distributed to the flywheels, and assigning value to the optimized gimbal angular speed, meanwhile, judging whether each single gimbal control moment gyroscope is in the dead zone or not, if so, stopping using the single gimbal control moment gyroscope, otherwise, returning to the step two to obtain a new gimbal angular speed, comparing the new gimbal angular speed with the optimized gimbal angular speed, if the new gimbal angular speed and the optimized gimbal angular speed are different, storing the new gimbal angular speed into the optimized gimbal angular speed and returning to the step two; and if the new gimbal angular speed and the optimized gimbal angular speed are the same, assigning the new gimbal angular speed to the final gimbal angular speed of the single gimbal control moment gyroscope, and assigning the angular acceleration speed of the flywheels to the final angular acceleratioin speed of the flywheels. According to the moment distribution method, the satellite attitude can be adjusted.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control. Background technique [0002] With the further exploration of space by humans, more and more space missions require spacecraft to be able to maneuver quickly and achieve precise pointing and tracking. For example, in the initial stage of satellite and rocket separation, it is necessary to quickly establish a stable attitude towards the ground, and the early warning satellite needs to perform rapid attitude maneuvers to track high-speed moving missiles. [0003] The rapid maneuvering of satellite attitude requires an actuator that can provide a large torque. The single frame control moment gyro (SGCMG) has gradually become the preferred actuator for fast maneuvering satellites due to its long life, large torque generation, and ability to provide continuous torque. Single-frame control moment gyroscopes (SGCMGs) change the direction of rotor angular momentum through the rotatio...

Claims

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Application Information

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IPC IPC(8): B64G1/28B64G1/10
Inventor 耿云海侯志立
Owner HARBIN INST OF TECH
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