Small-range high lift-drag ratio force-measuring balance applied to low-density wind tunnel

Abstract

The invention discloses a small-range high lift-drag ratio force-measuring balance applied to a low-density wind tunnel. The small-range high lift-drag ratio force-measuring balance comprises a main balance body; and a model connection end, a first combined measuring component, an axial force measuring component, a rolling moment measuring component, a second combined measuring component and a fulcrum bar are arranged at the main balance body successively. According to the invention, the axial force measuring component and the rolling moment measuring component are arranged in the middle of the balance measuring component and the combined measuring components are arranged at the two ends symmetrically so as to reduce the interference on the axial component and rolling torque component by the large normal and pitching torque loads, thereby measuring the rest of four components except the axial force and the rolling torque. On the basis of the designed load and appearance dimension of the small-range high lift-drag ratio force-measuring balance, the force measuring testing requirement of the low-density wind tunnel with the large lift force and complex appearance model is met and thetesting capacity of the low-density wind tunnel is improved effectively. Meanwhile, the anti-interference capability of the axial force measurement precision is enhanced; and the rolling torque sensitivity and measurement accuracy are improved.

Description

technical field [0001] The invention belongs to the technical field of aerospace force-measuring tests, and in particular relates to a force-measuring balance with a small range and high lift-to-drag ratio, which is applied to the aerodynamic force measurement of a complex lift body shape model in a low-density wind tunnel. Background technique [0002] The low-density wind tunnel is an important test equipment for studying rarefied aerodynamic characteristics. It is used to simulate the high-altitude and high-speed flight status of spacecraft, carry out experimental research on the aerodynamic characteristics of spacecraft models in the slip flow region and transition flow region, and problems related to rarefied gas dynamics. experimental research. [0003] With the rapid development of hypersonic aircraft with complex shapes, the flight time of the aircraft in the thin transition flow region and slip flow region has increased significantly, and the strong viscous interfer...

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Problems solved by technology

[0006] The purpose of the present invention is to provide a force-measuring balance with a small range and high lift-drag ratio, which solves the shortcomings of conventional force-measuring balances, such as insufficient measurement accuracy of axial load and rolling moment, and the difficult problem that anti-heat insulation measures for small-sized models are difficult to achieve, and satisfies complex lift forces. Measurement requirements for low-density wind tunnel aerodynamic tests of body-shaped spacecraft

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