Non-decoupled motion assignment method for continuous on-orbit linkage trajectory capture experiments

A technology of trajectory capture and motion distribution, which is used in aerodynamic testing, testing of machine/structural components, instruments, etc., to achieve the effect of improving utilization, simple and fast calculation, and strong adaptability

Active Publication Date: 2021-04-27
中国空气动力研究与发展中心超高速空气动力研究所 +1
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Problems solved by technology

However, in the actual continuous on-orbit linkage trajectory capture experiment, it often occurs that the motion distribution of the model when running at the uncoupled point

Method used

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  • Non-decoupled motion assignment method for continuous on-orbit linkage trajectory capture experiments
  • Non-decoupled motion assignment method for continuous on-orbit linkage trajectory capture experiments
  • Non-decoupled motion assignment method for continuous on-orbit linkage trajectory capture experiments

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Embodiment 1

[0088] Such as figure 1 As shown, the separation body mechanism and the main body mechanism of this embodiment are installed in the form of upper and lower structures, and the separation body model and the main body model are placed in the flow field of the hypersonic wind tunnel during the experiment.

[0089] The main body mechanism has six degrees of freedom, which are respectively controlled by six parts in series, including the main body X-direction linear movement mechanism, the main body Y-direction linear movement mechanism, the main body Z-direction linear movement mechanism, the main body α pitch rotation mechanism, the main body The β yaw rotation mechanism and the main body γ roll mechanism; the main body X-direction linear movement mechanism, the main body Z-direction linear movement mechanism, and the main body Y-direction linear movement mechanism are all driven by the motor and the lead screw. The main body α pitch rotation mechanism, the main body β yaw The ro...

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Abstract

The invention discloses a non-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiments. This method collects the current pose of the main body model and the separated body model, and gives the homogeneous transformation matrix between the wind tunnel coordinate system, the model center of mass coordinate system, and the decoupling point coordinate system, and obtains the next position of the main body model and the separated body model. Time step pose, and then calculate the relative position change distance in the X, Y, and Z directions; distribute the non-decoupling motion of the main body and the separated body mechanism according to the proportion of the stroke margin; control the main body and the separated body mechanism to complete the X, Y, and Z directions The uncoupled motion of , and their respective angular motions, arrive at the next time-step pose of the main body model and the separated body model. This method can avoid the movement of the main mechanism and the separation body mechanism in the same direction, improve the utilization rate of the experimental space, obtain longer experiment time and more captured track points, and improve the service life of the main body mechanism and the separation body mechanism. The advantages of simple and fast, efficient and reliable operation.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a non-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiments. Background technique [0002] At present, research on aircraft, spacecraft, and flying weapons around the world is inseparable from wind tunnel experiments. Wind tunnel experiments are an effective way to analyze the aerodynamic characteristics of objects, study airflow laws, and study the aerodynamic interaction of adjacent aircraft. The wind tunnel experiment reduces the size of the aircraft, creates a stable hypersonic flow field, and obtains the most realistic and reliable aerodynamic data to verify the aerodynamic characteristics of the aircraft. [0003] The current wind tunnel experiments are not satisfied with only obtaining the aerodynamic characteristics of the aircraft in a fixed attitude, but also need to further study the trajec...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00G01M9/02G01M9/06G01M9/08
CPCG01M9/00G01M9/02G01M9/06G01M9/08
Inventor 林敬周张建钟俊皮阳军解福田张德炜谢志江李佳鑫许晓斌邹东阳赵健王雄宋代平
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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