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Vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table

A technology of moment of inertia and test model, which is used in measurement devices, aerodynamic tests, aircraft component tests, etc., and can solve problems such as low accuracy and difficult positioning.

Inactive Publication Date: 2020-02-14
CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The present invention aims to provide a vertical wind tunnel spin test model rotational inertia measurement torsion table to solve the problems of difficult positioning and low precision of the existing wind tunnel test model rotational inertia measurement model

Method used

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  • Vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table
  • Vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table
  • Vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table

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Embodiment

[0053] Cooperate see Figure 1-Figure 8 , the test model 11 in the present embodiment is common aircraft model, and it comprises fuselage 12, the main wing 13 of fuselage 12 both sides, the vertical tail of the head 14 of fuselage 12 front portion, fuselage 12 rear upper surface 15, and the empennage 16 on fuselage 12 rear both sides. Wherein the head 14 of the test model 11 is roughly a columnar structure, the vertical tail 15 and the empennage 16 respectively protrude from the rear of the fuselage 12 for a certain distance, and the vertical tail 15 and the empennage 16 are spaced along the vertical direction of the test model 11 to form grooves Form 17.

[0054] This embodiment provides a vertical wind tunnel spin test model moment of inertia measurement torsion platform 18, which includes a base 19, the middle position of the lower end surface of the base 19 is provided with a connecting part 20 for connecting with the moment of inertia measurement equipment, In this embo...

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Abstract

The invention relates to the field of wind tunnel test model measurement, and in order to solve the problems of difficult positioning and low precision of an existing wind tunnel test model rotationalinertia measurement model, the invention provides a vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table. The table comprises a base, and a connectingpart used for being connected with rotational inertia measurement equipment is arranged in the middle of the lower end face of the base; scales in the length direction of the base are arranged on theside face of the base, and the zero position of the scales is located on the symmetrical face of the base; the base is provided with two sliding blocks capable of moving in the length direction of the base; the two sliding blocks are respectively connected with bracket components used for supporting and positioning a test model; and pointer interfaces are arranged on the sliding blocks and are used for matching and connecting pointers. The vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table can achieve clamping, supporting and measurement of three attitudes: yawing, pitching and rolling of a model; and a fixture interface can adapt to vertical wind tunnel tail rotation test model auxiliary fixtures with various shapes, and the vertical wind tunnel tail rotation test model rotational inertia measurement torsional pendulum table is rapid and convenient to install.

Description

technical field [0001] The invention relates to the field of wind tunnel test model measurement, in particular to a vertical wind tunnel spin test model moment of inertia measurement torsion table. Background technique [0002] When carrying out the vertical wind tunnel aircraft model spin test, the model used is usually required to be consistent with the mass distribution of the real aircraft, that is, to meet the requirements of the Froude number similarity criterion. Therefore, parameters such as the total mass, center of mass position, and moment of inertia must be strictly controlled during the model design and processing stages, and comprehensive measurement and debugging of the actual mass distribution parameters of the model is required before the test begins. [0003] The existing measuring device cannot conveniently and accurately clamp the test model and realize the measurement of various attitudes. Contents of the invention [0004] The invention aims to provi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M1/10G01M9/06B64F5/60
CPCB64F5/60G01M1/10G01M9/06
Inventor 吴海瀛伍钰璇李涵江鲲鹏颜来
Owner CHINA AERODYNAMICS RES & DEV CENT