High-temperature-resistant excitation measurement integrated test device

Abstract

The invention relates to a high-temperature-resistant excitation measurement integrated test device. A test piece is arranged at the top of the device, the lower portion of the test piece is connectedwith one end of a ceramic vibration excitation rod, and the other end of the ceramic vibration excitation rod sequentially penetrates through a heat insulation air cooling assembly, a box type vibration exciter fixing frame, a spring piece and a vibration exciter. The heat insulation air cooling assembly is arranged above the vibration exciter fixing frame; the spring piece is arranged on the upper portion in the vibration exciter fixing frame, the vibration exciter is arranged on the lower portion in the vibration exciter fixing frame, and an impedance head and a displacement sensor are further arranged between the spring piece and the vibration exciter. The test device integrates displacement, acceleration and force sensors, the vibration exciter can be fixedly installed at the bottom of the frame of the test device to achieve synchronous vibration excitation and measurement, an attached thermal protection system can achieve vibration excitation and measurement work in the environment with the highest temperature of 1000 DEG C, and important technical support is provided for construction of a ground flutter test system.

Description

technical field [0001] The invention relates to an integrated test device for high temperature resistance excitation and vibration measurement, which belongs to the field of dynamic tests. Background technique [0002] The common characteristics of space-to-ground shuttle aircraft and hypersonic winged missiles are large angle of attack, hypersonic flight and high maneuverability. During flight, aeroelastic flutter due to unsteady aerodynamic force coupled with structural bending and torsional vibration modes is prone to occur. lead to sudden catastrophic accidents. In addition, space-to-ground vehicles and hypersonic vehicles have serious aerodynamic heating due to their high flight speeds. Under the condition of large angle of attack, the temperature difference between the windward side and the leeward side is very large, and the transient temperature field produces a large thermal stress, which causes the structural stiffness to decrease. , the flutter safety margin is l...

AI Technical Summary

Problems solved by technology

[0003] At present, there are two main ways to carry out research on wing flutter problems: one is numerical calculation, that is, modeling is carried out according to the flight state of the aircraft, the aerodynamic modeling method can use CFD or the theoretical model of the lifting surface, and the structural modeling mainly uses finite element method, but due to the need to simplify the model or assume nonlinear linearization in the structural modeling process, the error between the calculated results and the actual results is large, which cannot meet the engineering requirements

Another type of method is to use test methods, including flight tests and scale-down tests. Flight tests are costly and risky. Once flutter occurs, the consequences will be catastrophic. Therefore, it is always hoped to check the aeroelastic stability before the flight test. assessment; scale model wind tunnel test can consider aerodynamic influence, but this method requires the test object to be designed in scale, there is a certain difference between the scale model and the real structure, and due to the interference aerodynamic force of the wind tunnel wall and bracket Unavoidable distortion, and because the similarity number cannot be fully simulated, there are still uncertainties between the results obtained by the scaled model and the actual situation

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