Mixed sine maneuvering path guiding method for high-paddle fundamental frequency satellite

A path guidance and sailboard-based technology, which is applied in the field of path guidance during the rapid maneuvering of flexible satellites, can solve the problems of insignificant contribution to the rapid maneuvering performance

Active Publication Date: 2012-06-27
BEIJING INST OF CONTROL ENG
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  • Application Information

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Problems solved by technology

However, for the situation where the fundamental frequency is high and the maneuvering time is required to be fast, the effect of using the sinusoidal maneuvering path in terms of less vibration of the sailboard is compared with the sacrifice of the maneuvering time, and the contribution to the fast maneuvering performance is not obvious.

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  • Mixed sine maneuvering path guiding method for high-paddle fundamental frequency satellite
  • Mixed sine maneuvering path guiding method for high-paddle fundamental frequency satellite
  • Mixed sine maneuvering path guiding method for high-paddle fundamental frequency satellite

Examples

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Effect test

Embodiment 1

[0063] Take the path design of a typical complex satellite rolling axis maneuvering 70° as an example, assuming that the satellite moment of inertia is 2962kg.m 2 , the actuator is a control moment gyro, the maximum torque that can be provided is 20Nm, the angular momentum capacity is Nms, the sensor is a gyro, the maximum measured angular rate is 2.5° / s, and the required maneuvering and stabilization time is 80s. Then the maximum maneuvering time of the satellite obtained according to step (1) is 40s, and the maximum maneuvering angular acceleration of the satellite obtained according to step (2) is 0.3869° / s 2 , the maximum angular velocity obtained according to step (3) is 2.5° / s. Considering the need to leave a certain margin for gyro measurement and actuators in engineering implementation, the maximum maneuvering angular acceleration is selected as a when designing the path max =0.3° / s 2 , the maximum angular velocity ω max =2.4° / s. According to step (4), calculate th...

Embodiment 2

[0088] Taking a typical complex satellite rolling axis 80s fast maneuvering 70° process as an example, assuming the satellite's moment of inertia is 2962kg.m 2 , the fundamental frequency of the flexible sailboard is 0.5Hz, and the control period is 0.1s. Through calculation, the period of the sinusoidal trigonometric function T=20s is selected, and the maximum angular acceleration a max =0.3° / s 2 , the maximum angular velocity ω max 2.4° / s. Through mathematical simulations, it is found that image 3 As shown, based on the bang-bang maneuvering path, the maximum tracking error of the attitude angular velocity during the maneuvering process is 1.2° / s; as Figure 4 As shown, under the maneuvering path based on the sinusoidal curve, the maximum tracking error of the attitude angular velocity during the maneuvering process is 0.7° / s; Figure 5 As shown, under the maneuvering path based on the sinusoidal hybrid step curve, the maximum tracking error of the attitude angular velo...

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Abstract

The invention relates to a mixed sine maneuvering path guiding method for a high-paddle fundamental frequency satellite. The mixed sine maneuvering path guiding method for a high-paddle fundamental frequency satellite is characterized in that based on reasonable distribution of maneuvering time and stabilization time, according to a moment and an angular momentum capacity of an execution mechanism, an angular acceleration curve is designed, wherein the angular acceleration curve shows an angular acceleration change rule that an angular acceleration is changed into zero from a positive value, then is changed into a negative value from zero and then is changed into zero from the negative value; and one half of a whole period of a sine curve mixed step function is a positive value curve part and the other half is a negative value curve part. The mixed sine maneuvering path guiding method for a high-paddle fundamental frequency satellite retains the advantage of small excitation of a sine maneuvering path on a flexible paddle, combines the advantage of time optimality of a step function, harmonizes the contradiction between maneuvering rapidity and paddle excitation smoothness, is especially suitable for providing path program for a large-angle, rapid and high-paddle fundamental frequency satellite in imaging breadth increasing, instant observation on a emergency area or stereo imaging rapid maneuvering, and satisfies requirements of rapid and stable maneuvering performances of a high-paddle fundamental frequency satellite.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a path guidance method for a flexible satellite during fast maneuvering. Background technique [0002] In terms of rapid maneuvering of satellites, in order to increase the imaging width, realize real-time observation of emergency areas, or perform stereoscopic imaging, frequent side swing maneuvers and pitch maneuvers are required. When the maneuvering angle of the satellite is large, the stabilization time is short, and the stability index is high, the flexible vibration of the sailboard caused by the maneuvering process will become the main factor restricting the maneuverability. For satellites with low sailboard fundamental frequency, the sinusoidal maneuvering path can effectively reduce the excitation of large-angle maneuvering to flexible attachments and obtain higher stability. Although the sinusoidal maneuvering path requires a longer maneuvering time than the t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 谈树萍何英姿魏春岭宗红雷拥军
Owner BEIJING INST OF CONTROL ENG
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