Flat plate-rudder local model device for realizing multi-attitude simulation

Abstract

The invention relates to mechanical design and wind tunnel tests, in particular to a flat plate-rudder local model device capable of realizing multi-attitude simulation, and belongs to the field of mechanical design and aerospace engineering. According to the device, a flexible model design scheme is adopted; a flat plate-rudder model for simulating a local aerodynamic environment of an aircraft wing/rudder is split into a plurality of movable modules; the device specifically comprises a flat plate, a rudder substrate, a turntable, a rudder shaft and a rudder, realizes model multi-degree-of-freedom attitude change, simulates aircraft wing/rudder local multi-attitude parameter (attack angle, sideslip angle, rudder deflection angle and the like) change in a wind tunnel, and provides a more effective technical approach for aircraft local pressure and thermal environment measurement test.

Description

technical field [0001] The invention relates to mechanical design and wind tunnel test, in particular to a plate-rudder partial model device capable of realizing multi-attitude simulation, which belongs to the fields of machinery and aerospace engineering. Background technique [0002] There are various shapes and sizes of parts, surface protrusions, pits and gaps on the surface of hypersonic vehicles, such as cable covers, lifting lugs, air rudders and rudder base plates, etc. The existence of protrusions may cause complex flows such as shock wave boundary layer interference or shock wave and shock wave interference. The complex flow field caused by the mutual interference between protrusions will generate local heat flow and pressure peaks, making the thermal environment very bad. The existence of dimples will interfere with the flow field and cause the increase of local heat flow, which will bring great safety hazards to flight. At present, it is still difficult to pred...

AI Technical Summary

Problems solved by technology

However, limited by the diameter of the wind tunnel, the size of the scaled model is usually small, which brings certain restrictions on the installation of sensors, and the spatial distribution rate of the measurement is not high enough; The thickness is an order of magnitude. After a large scale reduction, the ratio of the height of the protrusion on the wind tunnel model to the thickness of the boundary layer is quite different from the real flight situation, which loses the similarity of the wind tunnel simulation.

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