Double-end force measurement device and double-end measurement method

A force measuring device and double-ended technology, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., to achieve the effect of simple structure, easy processing and high rigidity

Inactive Publication Date: 2014-12-10
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Application Information

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Problems solved by technology

[0005] In order to solve the problem of six-component aerodynamic force measurement when the middle part of the segmented model is supported in the dynamometric test of the aerodynamic and kinematic coupling research, the present invention provides a double-ended dynamometer device and a measurement method

Method used

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Embodiment Construction

[0035] Such as figure 1 As shown, the double-end force-measuring device of the present invention mainly comprises a front section model connection end, a front section balance, a fixed end, a rear section balance and a rear section model connection end, and the front section balance and the back section balance are six components The strain balance adopts the "meter" beam and the "I" beam as the elastic sensitive elements respectively, and their specific sizes are different, and they are connected with the wind tunnel support device through the fixed end. The connecting end of the front model and the connecting end of the rear model are respectively connected with the front and rear parts of the test model through bearings and internal flexible shafts to realize the rolling motion of the model; the force measuring device is processed from a whole piece of steel The interior is a hollow structure, and bearings and flexible shafts are installed to support the front model and the...

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Abstract

The invention discloses a double-end force measurement device and a double-end measurement method and belongs to the technical field of aerodynamic force measurement of aerospace force test. The device and the method are used for measuring high-precision and high-accuracy six-component aerodynamic force of segmented test models during force test of wind tunnel aerodynamic/kinematic coupling research. The double-end force measurement device of a internal hollow structure is machined from a whole piece of high-elasticity steel and comprises a front-segment model connecting end, a front-segment balance, a fixing end, a rear-segment balance and a rear-segment model connecting end, and a *-beam and an I-beam different in specific size are respectively adopted as elastic sensitive elements of the front-segment balance and the rear-segment balance. The measurement method includes measuring aerodynamic resultant force and moment of force of the test model through the front-segment balance and the rear-segment balance. The problem about simultaneous six-component force measurement of the segmented models in special test is solved, and the device and the method can be widely applied to wind tunnel force test in model middle support modes such as hanger support, bracing wire support and web support modes.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel aerodynamic measuring devices, and in particular relates to a double-end force measuring device and a measuring method. Background technique [0002] At present, internal balances are commonly used in conventional wind tunnel dynamometric tests. They have various structures, series of sizes, and targeted ranges and application ranges. Different aircraft dynamometric tests require the development of different balances to measure aerodynamic forces. According to different structural forms, internal balances can be divided into rod balances, ring balances and chip balances. Among them, the rod balance is widely used in the full-mode force measurement test of aircraft or missiles, and the ring balance and chip balance are mainly used in some force measurement tests with special requirements: such as vector jet flow, component force measurement and hinge moment test Wait. In this type of test, th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
Inventor 向光伟谢斌赵忠良吴军强王超余立苗磊毛代勇
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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