Dynamic derivative test device for pitching and yawing free vibration of aircraft with large slenderness ratio

Abstract

Disclosed is a dynamic derivative test device for pitching yaw free vibration of an aircraft with a large slenderness ratio. A high-pressure driving device is mounted in a back support device, and anoutput shaft of the high-pressure driving device is connected with the tail end of a push rod (7) in an initial excitation device to drive the push rod (7) to move back and forth; the back support device comprises a back support arm (4), a connecting shaft (12), a back support arm pin (13), a back support arm screw (14), a wedge (16), a positioning key (17) and a middle shaft (18); one end of thepitching elastic hinge (2) is fixedly connected with the back supporting device, and the other end is connected with the large slenderness ratio aircraft test model (1); before and after the test, themovement of the pitching hinge is limited through a push rod (7); and, in the test process, the driving block (5) drives the tail of the model to move upwards through front-back movement of the pushrod, and then the aircraft test model (1) with the large slenderness ratio is driven to do free vibration movement around the rotating center of the pitching elastic hinge (2).

Description

Technical field [0001] The invention relates to a wind tunnel test device which adopts a free vibration dynamic derivative test method to obtain a dynamic derivative in a pitch / yaw direction for an aircraft with a large slenderness ratio profile. Background technique [0002] Both the aerodynamic design and the control system design of the aircraft require the provision of derivative data of the dynamic stability of the aircraft under its flight conditions. When the aircraft changes its attitude or is disturbed by air currents, it will deviate from its balanced attitude in pitch, yaw or roll vibration. The purpose of dynamic stability research is to predict the attenuation trends and laws of these vibrations. For passive damping control aircraft, the dynamic flight quality and reliability requirements of the aircraft put forward extremely high requirements for the prediction of the aircraft dynamic stability. Too low dynamic stability will easily cause the angular movement of t...

AI Technical Summary

Problems solved by technology

[0005] Large slenderness ratio aircraft generally refers to aircraft with a slenderness ratio greater than 15, such as air-to-air missiles, rockets, launch vehicles, etc., whose shape characteristics determine the size characteristics of its test model in the wind tunnel. To obtain the dynamic derivative of such aircraft , the traditional form of tail support can no longer meet the requirements of wind tunnel tests

Since the forced vibration test method needs to measure the aerodynamic force and angular displacement of the model at the same time, it needs a large internal space in the front and rear directions of the model, and has strict requirements on the mechanism. For the aircraft with a large slenderness ratio, the forced vibration test method is more complicated to implement

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