Vertical wind tunnel model pitching-rolling test device and use method

Abstract

The invention is suitable for the technical field of wind tunnel tests, and provides a vertical wind tunnel model pitching-rolling test device and a use method, and the test device comprises a base which is fixedly installed on a vertical wind tunnel test section tunnel wall platform; a stand column, the bottom end of the stand column being fixedly connected with the base; a supporting rod, located between the stand column and the web supporting bent rod, one end of the supporting rod being fixedly connected with the top end of the stand column, the other end of the supporting rod being connected with one end of the web supporting bent rod through a rotating assembly, and the rotating assembly being installed at the end, away from the stand column, of the supporting rod; and a belly supporting bend rod, the end, away from the rotating assembly, of the belly supporting bent rod being fixedly connected with the installation base, and the installation base being fixedly installed on the belly of the aircraft model. Free pitching / rolling motion of the airplane model under the action of aerodynamic force can be achieved, the structure is simple, mechanism rotation damping is small, interference is small, precision is high, and installation is easy, convenient and reliable.

Description

technical field [0001] The invention relates to the field of aircraft wind tunnel tests, in particular to a vertical wind tunnel model pitch-roll test device and a method of use. Background technique [0002] Aircraft pitch characteristics are important indicators for evaluating aircraft maneuverability and aerodynamic performance. The research on aircraft pitch characteristics through wind tunnel tests has the advantages of low cost, low risk, and high precision. [0003] Aircraft pitching test devices are classified according to the constraints, mainly including pitching forced oscillation test devices and free pitching test devices. There are mainly four types of model support methods, which are: belly support, tail support, wingtip support and back support. In the wind tunnel test, the support device supports or drives the pitching motion of the aircraft model, and is used for unsteady tests at large angles of attack and dynamic derivative tests. [0004] In the prior ...

AI Technical Summary

Problems solved by technology

[0004] In the prior art, the wind tunnel test system for researching aircraft pitching characteristics is mainly established in traditional horizontal wind tunnels for conventional layout aircraft. Although it can meet the routine tests such as dynamic derivative test and high angle of attack unsteady test, it still faces some problems. Problems: 1) There are inherent defects in the traditional horizontal wind tunnel for rotary flight tests. Since the gravity direction of the model is perpendicular to the axis of the wind tunnel test section, it is difficult to solve the balance problem in the model rotation and the weight of the rotary part; 2 ) The free pitch / roll wind tunnel test technology is still a blank in domestic research. Since the flying wing aircraft is prone to enter a dangerous out-of-control roll state during flight, it is necessary to conduct in-depth research on the mechanism and improvement measures of this phenomenon in the wind tunnel, resulting in The demand for testing the free pitch / roll characteristics of flying-wing aircraft has increased sharply, and the existing wind tunnel test system can no longer meet the test requirements of unconventional aircraft such as flying-wing aircraft; 3) The existing free pitch / roll The device usually adopts the wingtip support method that penetrates the fuselage. This support method not only greatly damages the aerodynamic shape of the flying-wing aircraft, but also seriously affects the accuracy and reliability of the test results, and even results in completely opposite tests. Results; 4) The wingtip support method makes it very difficult to adjust the position of the center of rotation of the model, and the installation of the vertical plate at the wingtip also seriously interferes with the development of the wingtip vortex, which affects the accuracy of the test results. Poor adaptability

Images