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Maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude

A technology of attitude maneuvering and pitching axis, which is applied in the direction of aerospace vehicle guidance devices, etc., and can solve the problem of expensive unloading devices

Active Publication Date: 2013-08-07
哈尔滨工大卫星技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention is to solve the problem that the existing method uses a device to unload and the unloading device is expensive, and proposes a method for unloading the angular momentum of the pitch axis by using the attitude of the satellite pitch axis to maneuver

Method used

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  • Maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude
  • Maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude
  • Maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude

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specific Embodiment approach 1

[0042] Specific implementation mode one: combine Figure 1 to Figure 5 Description of this embodiment: a method for unloading angular momentum of the pitch axis using satellite pitch axis attitude maneuvering, the specific process is as follows:

[0043] Step 1. Measure and determine the angular momentum h of the pitch axis that the satellite needs to unload un_y , the specific steps are:

[0044] Measure the angular momentum component of each momentum exchange actuator in the body coordinate system, and express the angular momentum component of the ith momentum exchange actuator in the body coordinate system as From this, the component h of the total angular momentum of all momentum exchange actuators on the pitch axis can be obtained un_y , the expression is:

[0045] h un _ y = - Σ i = 1 ...

specific Embodiment approach 2

[0078] Specific embodiment two: the difference between this embodiment and specific embodiment one is: in step 3, the time t required for satellite maneuvering is solved end The specific process is:

[0079] Step 31: The form of satellite maneuvering is: start to accelerate with the maximum torque, when the satellite speed reaches ω ymax After that, stop exerting torque on the satellite, let the satellite take ω ymax Roll at a constant speed at the angular velocity, and finally decelerate the maximum moment in the time direction of the satellite to ensure that the satellite's attitude angle reaches the specified value, and the attitude angular velocity is 0;

[0080] Step 32: According to the maneuvering form of the satellite, the maximum maneuvering angular velocity ω ymax and the satellite's maximum angular acceleration a ymax , it can be estimated that the time spent by the satellite acceleration segment and the acceleration segment is

[0081] t 1 = t end -t 2 = ω ...

specific Embodiment approach 3

[0088] Specific implementation mode three: the difference between this implementation mode and specific implementation mode one or two is: the specific process of step four is:

[0089] Step 41: Make the magnitude of the gravity gradient moment take the maximum value, that is, θ m = 45°, calculate the angular momentum h accumulated during the satellite maneuvering from 0° to 45° manu (45°), the angular momentum accumulated in the process of the satellite maneuvering from 0° to 45° is the same as the angular momentum accumulated in the process of the satellite maneuvering from 45° to 0°, therefore, when the maneuvering angle θ m = 45°, the sum of angular momentum accumulated during satellite maneuvering is 2h manu (45°);

[0090] Step 42: Compare|2h manu (45°)|with|h un_y |Size:

[0091] if h un_y |≥|2h manu (45°)|Then take θ m = 45°;

[0092] if h un_y |manu (45°)|, then θ m should satisfy the equation:

[0093] h un ...

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Abstract

The invention relates to the technical field of the spacecraft attitude control and provides a maneuvering unloading pitch axis angular momentum method by satellite pitching axis attitude. The maneuvering unloading the pitch axis angular momentum method by the satellite pitching axis attitude comprises step one, measuring and confirming the satellite pitch axis angular momentum hun-y needs to be unloaded; step two, confirming gravity gradient torque the satellite bears according to satellite rotational inertia; step three, estimating time tend needed by the maneuvering thetam of the satellite pitch axis and angular momentum humanu which is accumulated by the gravity gradient torque on the pitch axis in the maneuvering process; step four, solving an angle thetam the satellite needs to be maneuvered according to the hun-y and the humanu; step five, calculating time thold the angle thetam needs to be kept according to the hun-y, the humanu and the confirmed thetam in step four; and step six, confirming satellite rotational inertia distribution forms which guarantee that the satellite can perform maneuvering with enough angular momentum space. The maneuvering unloading the pitch axis angular momentum method by the satellite pitching axis attitude is applied to the technical field of the spacecraft attitude control and solves the problems that devices are utilized to unload in the prior art and the costs of unloading devices are high.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control, in particular to a method for unloading the angular momentum of the pitch axis by using the rapid attitude maneuver of the satellite pitch axis. Background technique [0002] Satellites with fast maneuvering capabilities can complete large-angle maneuvers in a short period of time and can accurately track targets. In order to meet the requirements of satellite maneuvering speed and accuracy at the same time, the momentum exchange device is usually used as the actuator. At the same time, the rapidity of satellite maneuvering requires the satellite actuator to have enough angular momentum space. Therefore, how to conveniently and quickly adjust the satellite actuator Performing uninstallation is a topic worthy of study. [0003] Usually satellites are unloaded using a magnetic torquer or jet device. Although the magnetic torquer can provide continuous unloading torque in real t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 耿云海侯志立李诚良
Owner 哈尔滨工大卫星技术有限公司
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