Low-damping pitching dynamic supporting device for wind tunnel free oscillation test

Abstract

The invention discloses a low-damping pitching dynamic supporting device for a wind tunnel free oscillation test. A test model is divided into a test model front section and a test model rear section, the test model front section is fixed at one end of the test model rear section, the pitching dynamic adjustment mechanism is connected in the test model rear section, and the pitching dynamic adjustment mechanism is connected in the test model rear section. The automatic locking mechanism is connected to one end of the pitching dynamic adjusting mechanism, the end, away from the pitching dynamic adjusting mechanism, of the automatic locking mechanism is connected with the other end of the ventilation tail supporting rod assembly, and the angular displacement measuring assembly is embedded in the pitching dynamic adjusting mechanism. Compared with existing dynamic supporting devices such as a bracing wire, a strip, a mechanical bearing and a conventional air bearing, the pitching dynamic supporting device is compact in structure and small in size, can be arranged in a small installation space allowed near the mass center of a test model and does not interfere with a wind tunnel flow field, thereby satisfying basic requirements of a hypersonic wind tunnel test.

Description

technical field [0001] The invention relates to the technical field of hypersonic wind tunnel tests, in particular to a low-damping pitching dynamic support device for free oscillation tests in wind tunnels. Background technique [0002] Hypersonic aircraft has significant advantages such as strong maneuverability and strong reentry and follow-up endurance capabilities. It can adapt to various complex and changeable flight trajectories, perform various rapid strike missions, and has a high success rate of penetration, which can effectively control countermeasures. function of the guiding system. The flight performance of a hypersonic vehicle is excellent, but its aerodynamic layout design faces great challenges: during the flight, flow phenomena such as separation and transition will occur on the surface of the vehicle, and the coupling effect of factors such as aerodynamics, motion and inertia of the vehicle is significant, and it is easy to appear in actual flight. Contro...

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Problems solved by technology

[0004] Tension lines and strips are easy to generate shock waves in the hypersonic wind tunnel flow field, which will affect the structure of the wind tunnel flow field and greatly interfere with the aerodynamic force of the test model

The frictional damping of the mechanical bearing is much greater than the aerodynamic coupling effect that causes the free oscillation of the aircraft, which does not meet the requirements of the wind tunnel pitch free oscillation simulation test

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