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A landing gear hatch control mechanism for model airplanes

A technology for landing gear doors and aircraft models, which is used in the testing of machines/structural components, measuring devices, instruments, etc., can solve the problems of insufficient structural strength and high cost

Inactive Publication Date: 2018-04-10
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, during the whole machine wind tunnel experiment, it is impossible to put a real plane in the wind tunnel
In the usual full-aircraft wind tunnel experiments, the aircraft model is very small, and it is impossible to scale down the real control mechanism of the hatch and install it in the aircraft model. The cost is too high and the structural strength is not enough. Therefore, it is urgent to provide a A door operating mechanism for opening and closing a steerable door of an airplane model

Method used

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  • A landing gear hatch control mechanism for model airplanes
  • A landing gear hatch control mechanism for model airplanes
  • A landing gear hatch control mechanism for model airplanes

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Embodiment Construction

[0012] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.

[0013] figure 1 Shown is a structural schematic diagram of a cabin door 1 used for a full-machine wind tunnel experiment according to a specific embodiment of the present invention. What is shown in the figure is a partial structural schematic diagram of an aircraft model, which shows that an opening is provided on the fuselage 2, and a hatch 1 is covered at the opening position, and the hatch 1 can be a landing gear hatch or can be It is any hatch structure that can be opened and closed during real aircraft flight, that is to say, the hatch 1 on the aircraft model is a structure that can be opened and closed by a manipulation mechanism.

[0014] The cabin door 1 is rot...

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Abstract

The invention provides an undercarriage door operating mechanism for an airplane model. The undercarriage door operating mechanism for an airplane model is characterized in that the undercarriage door is rotatably hinged to the body of the airplane model through a rotating shaft; the operating mechanism is provided with an operating shaft which is fixedly connected with the rotating shaft of the undercarriage door, and a motor which drives the operating shaft to rotate; and at least one reduction gear is arranged between the motor and the operating shaft. The undercarriage door operating mechanism for an airplane model provides a door operating mechanism which can operate on / off of an undercarriage door, for a full-aircraft wind tunnel experiment.

Description

technical field [0001] The invention relates to an aviation aerodynamic test equipment, in particular to a mechanism which can be used to open and close a landing gear hatch of an aircraft model during a wind tunnel test of the whole machine. Background technique [0002] The whole aircraft wind tunnel test is based on the principle of aerodynamics. The entire aircraft model is fixed in the wind tunnel, and artificial airflow is applied to flow through the aircraft model to simulate various complex flight states in the air and obtain test data. The main purpose of the full-aircraft wind tunnel test is to obtain the variation law of various aerodynamic parameters of the aircraft model and to simulate the handling performance of the aircraft under different flow fields and flow velocities. [0003] Under normal circumstances, the size of the wind tunnel will impose certain restrictions on the size of the aircraft model, that is to say, in order to adapt to the size of the wind...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08
CPCG01M9/08
Inventor 宗宁黎军李晨韩江旭赵卓林乔晓冬陈同银
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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