Yaw-angle free vibration test device with short and blunt appearance like spacecraft
A technology of vibration test and yaw angle, which is applied in the direction of aerodynamic test, measuring device, machine/structural component test, etc. It can solve the problems of changing the flow field structure of the test piece and affecting the yaw damping value of the test piece, etc.
Active Publication Date: 2012-12-12
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology
The disadvantage of this device is that in the case of a large yaw angle, the strut will change the flow field structure at the tail of the specimen, thereby affecting the yaw damping value of the specimen
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[0020] The present invention will be described in further detail below in conjunction with the drawings and specific embodiments:
[0021] The invention provides a free vibration test device for a short, blunt shape and large yaw angle of a spacecraft, such as figure 1 with figure 2 Shown, including: test piece 1, yaw dynamic balance 2, curved push rod 3, first double hinge 4, second double hinge 5, straight push rod 6, curved support rod 7, cylinder 8, shift rod 9 and firing pin 10;
[0022] The specimen 1 is fixed on the bending support rod 7 by the yaw dynamic balance 2. The center of gravity of the specimen 1 coincides with the rotation center of the yaw dynamic balance 2, so that the specimen 1 can vibrate around the rotation center of the yaw dynamic balance 2. The support rod 7 is bent 20° perpendicular to the yaw angle of the short and blunt shape of the spacecraft, the yaw dynamic balance 2 and the bent support rod 7 are connected by pins, and the yaw dynamic balance 2 a...
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The invention relates to a yaw-angle free vibration test device with a short and blunt appearance like a spacecraft. The yaw-angle free vibration test device comprises a test piece, a yaw dynamic balance, a bent push rod, first double hinges, second double hinges, a straight push rod, a bent support rod, an air cylinder, a pulling rod and a firing pin, wherein the test piece is fixedly arranged on the bent support rod through the yaw dynamic balance, so that the test piece can vibrate round the rotation center of the yaw dynamic balance; a resistance wire strain piece is attached on the yaw dynamic balance to be used for measuring the angular displacement of the test piece, and the tail part of the test piece is provided with the firing pin; and a trigger mechanism assembled in the bent support rod forces the test piece to generates initial angular displacement. The trigger mechanism comprises the air cylinder, the straight push rod, the first double hinges, the second double hinges, the bent push rod and the pulling rod. One end of the straight push rod is connected with the bent push rod through the first double hinges and the second double hinges, and the other end of the straight push rod is connected with the air cylinder together. The pulling rod is connected with the bent push rod together. The firing pin of the test piece is pulled by the pulling rod so that the test piece generates small free yaw oscillation. The maximum yaw angle ignoring the support rod interference is increased to 35 degrees through the device.
Description
Technical field [0001] The invention relates to a free vibration test device for the yaw angle of a spacecraft-like short blunt-shaped aircraft. Background technique [0002] The free vibration test of the short and blunt shape and large yaw angle of the similar spacecraft requires the test organization to have four characteristics: 1. The test piece can be installed on the support system of the wind tunnel; 2. The test organization must have sufficient rigidity to prevent it from being stressed. Fracture, damage to other components in the test system; 3. The test mechanism can achieve a certain range of yaw angle changes in conjunction with the angle of attack mechanism of the wind tunnel; 4. Under the conditions of large yaw angle test, the test mechanism must be in the wake of the specimen , Reduce the interference of the support rod to the flow field. [0003] There is a gap in the research on the large yaw angle dynamic test bending struts in early domestic. The reason is th...
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IPC IPC(8): G01M9/00
Inventor 陈农宋玉辉高清胡静解克赵小见
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS