Main body and separation body track capture experiment motion distribution method for continuous on-orbit motion

A motion distribution and trajectory capture technology, which is applied in aerodynamic tests, machine/structural component testing, instruments, etc., can solve problems such as limited degrees of freedom travel, reducing the number of captured trajectory points, and low utilization of experimental space

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

Because the main body model and the separation body model are in the same flow field, it is very easy to produce the same direction movement, and the degrees of freedom of the main body and the separation body mechanism are limited, the main body or the separation body mechanism w

Method used

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  • Main body and separation body track capture experiment motion distribution method for continuous on-orbit motion
  • Main body and separation body track capture experiment motion distribution method for continuous on-orbit motion
  • Main body and separation body track capture experiment motion distribution method for continuous on-orbit motion

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Embodiment 1

[0055] like 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.

[0056] 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 rotat...

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Abstract

The invention discloses a main body and separation body track capture experiment motion distribution method for continuous on-orbit motion. The method comprises the following steps: acquiring the current poses of a separation body model and a main body model at the current moment to obtain the theoretical poses of the separation body model and the main body model at the next time step length, andcalculating the relative position change distances in the X, Y and Z directions; distributing the movement of the main body mechanism and the separation body mechanism according to the stroke allowance proportion; and controlling the main body mechanism and the separation body mechanism to complete X-direction, Y-direction and Z-direction movement and respective angle movement to reach the theoretical poses of the main body model and the separation body model of the next time step length. 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 simple and 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 motion distribution method for a track capture experiment of a main body and a separate body moving continuously on orbit. 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...

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 林敬周张涛钟俊谢志江李佳鑫皮阳军解福田张德炜许晓斌王雄邹东阳赵健宋代平
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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