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Satellite attitude maneuvering method based on polynomial

A technology of attitude maneuvering and satellite attitude, which is applied in the control field of spacecraft when maneuvering with arbitrary trajectory and attitude, and achieves the effect of avoiding flexible modal vibration, stable attitude transition and ensuring smoothness.

Active Publication Date: 2014-07-23
BEIJING INST OF CONTROL ENG
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  • Abstract
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Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the limitations of existing satellite point-to-point attitude maneuver control methods, and to provide a polynomial-based satellite attitude maneuver method with a smooth maneuver process and smooth maneuver ends

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  • Satellite attitude maneuvering method based on polynomial
  • Satellite attitude maneuvering method based on polynomial
  • Satellite attitude maneuvering method based on polynomial

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Embodiment

[0071] Take the roll axis attitude maneuver control of a complex satellite as an example. Assuming that the attitude angle, angular velocity and angular acceleration at the initial moment of satellite maneuvering are all zero, after 25 seconds, the satellite needs to have a rolling attitude of 20 degrees, with a rolling angular velocity of -0.5 degrees per second and a rolling angular velocity of 0.005 degrees per second 2 the angular velocity.

[0072] If a 6th-order polynomial is selected, the coefficients of the 6th-order polynomial are first calculated at the starting moment of the maneuver, and the calculated polynomial coefficients are: a 6 =-1.9997e -8 , a 5 =1.7841e -6 , a 4 =-5.4950e -5 , a 3 =5.9349e -4 , a 2 =0,a 1 =0,a 0 =0, thus the trajectory of the maneuvering process is obtained. The target curves of attitude angle, angular velocity and angular acceleration in the whole process of satellite maneuver calculated according to the 6th order polynomial ar...

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Abstract

Disclosed is a satellite attitude maneuvering method based on polynomial. The attitude angle, the angular speed and the angular acceleration at the start moment of the satellite attitude can be appointed at will, and meanwhile the attitude angle, the angular speed and the angular acceleration at the end moment of satellite maneuvering can also be appointed at will. The method can ensure that the satellite attitude is guided to a target value at the appointed moment and can also ensure the stability of the whole maneuvering path. Meanwhile, due to the utilization of the smoothing technology at the tail end, smooth transition of the attitude angle, the angular speed and the angular acceleration at the end moment of satellite maneuvering can be ensured, the control error of the satellite attitude at the end moment of satellite maneuvering is small, and consequently the performance is ensured when maneuvering is finished. The satellite attitude maneuvering method based on polynomial is particularly suitable for the state establishment stage of maneuvering tasks such as movement imaging observation and target tracking of an agile satellite, and can easily meet the requirement that maneuvering is stable the moment when in place.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a control method for a spacecraft performing arbitrary track attitude maneuvers. Background technique [0002] With the development of spacecraft control technology, the spacecraft attitude maneuver requires not only the traditional point-to-point attitude rapid maneuvering and stability ability, but also the spacecraft has a certain dynamic tracking ability. The specific requirements are: starting from the specified maneuvering moment, within the specified time period, establish the specified satellite attitude and have the specified satellite attitude angular velocity. This is completely different from the traditional spacecraft's point-to-point attitude maneuver, which quickly maneuvers into place and then retains a certain stabilization time. Under this requirement, the attitude and angular velocity control accuracy of the satellite at the moment of arrival are requi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 田科丰姚宁宗红何海锋王淑一朱琦吕高见傅秀涛綦艳霞潘立鑫李晶心
Owner BEIJING INST OF CONTROL ENG
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