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Non-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiment

A trajectory capture and motion distribution technology, applied in aerodynamic tests, machine/structural component testing, instruments, etc.

Active Publication Date: 2020-09-22
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-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiment
  • Non-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiment
  • Non-decoupling motion distribution method for continuous on-orbit linkage trajectory capture experiment

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Embodiment 1

[0090] 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.

[0091] 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 a continuous on-orbit linkage trajectory capture experiment. The method comprises the following steps: acquiring the current poses of a main body model and a separation body model, giving a homogeneous transformation matrix among a wind tunnel coordinate system, a model centroid coordinate system and a decoupling point coordinate system, obtaining the poses of the main body model and the separation body model in the next time step length, and calculating the change distances of the relative positions in the X, Y and Z directions; distributing non-decoupling motion of the main body mechanism and the separation body mechanism according to the stroke allowance proportion; and controlling the main body and separation bodymechanism to complete non-decoupling motion in the X, Y and Z directions and respective angular motion to reach the next time step length poses of the main body model and the separation body model. According to the method, the main body mechanism and the separation body mechanism can be prevented from moving in the same direction, the utilization rate of experiment space is increased, longer experiment time and more captured track point positions are obtained, the service life of the main body mechanism and the separation body mechanism is prolonged, and the method has the advantages of simpleand rapid calculation and 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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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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