Four-engine propeller aircraft wind tunnel test model based on air motors

A technology of wind tunnel test and air motor, applied in aerodynamic test, aircraft component test, machine/structural component test, etc., to achieve the effect of improving accuracy

Active Publication Date: 2018-06-01
中航通飞华南飞机工业有限公司
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AI Technical Summary

Problems solved by technology

This invention provides a design method for the test model of this type of aircraft, which solves the problem of simulating the drag coefficient and Mach number in the dynamic simulation test of the four-engine propeller aircraft, and improves its test technical ability and the accuracy of the slipstream influence data of the wind tunnel test Spend

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  • Four-engine propeller aircraft wind tunnel test model based on air motors
  • Four-engine propeller aircraft wind tunnel test model based on air motors
  • Four-engine propeller aircraft wind tunnel test model based on air motors

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Embodiment Construction

[0023] Below in conjunction with the embodiment of the present invention Figure 1-Figure 4 , clearly and completely describe the technical solutions in the embodiments of the present invention, obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0024] see figure 1 As shown, the embodiment of the present invention is: one end of the main strut 115 of the model oblique push-up is installed on the support platform of the wind tunnel, the other end is fixedly connected with the air bridge 15 through the strut connector 114, and the air bridge 15 is connected with the main balance One end of 112 is connected, and the other end of main balance 112 is installed on the connector 111, and connector 111 is fixedly conne...

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Abstract

The invention discloses a four-engine propeller aircraft wind tunnel test model based on air motors. One end of a supporting member is fixedly connected with a wind tunnel balance rack, and the otherend is connected to a main balance by means of a supporting rod connection member and an air bridge. Empennage and aerofoil assemblies are installed on an aircraft body, the middle section of the aircraft body is fixedly connected to balance connection members, the other end of each balance connection member is fixedly connected to the main balance, and a whole aircraft acting force is transmittedonto the main balance by means of the balance connection members. Flaps and ailerons are connected with an aerofoil stabilizing plane by means of respective angle changing pieces. A force and momentof a propeller are measured in real time by means of a rotating shaft balance during a wind tunnel test. A flow control device is installed in the aircraft body, and controls output power of the air motors by controlling gas flow. The invention provides a design method of the wind tunnel test model using the air motors for simulating power of the propellers, the flow field similarity degree in thepropeller power simulation tests is improved, and the data precision of wind tunnel tests is effectively improved.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic design, in particular to the field of wind tunnel tests on the influence of propeller aircraft model dynamics. Background technique [0002] With the development of aviation technology at home and abroad, high-power turboprop power systems are generally used in domestic new or planned new turboprop aircraft, and the impact of turboprop power is significantly increased; at the same time, limited by some special conditions of use, some The take-off speed of the propeller aircraft is relatively small, which further increases the amount of power influence; these factors have greatly increased the requirements for the simulation capability (that is, the driving power) of the propeller model power drive system in the wind tunnel test. The force test method cannot meet the requirements of the dynamic simulation test of the tensile coefficient and the test Mach number at the same time, and is restricte...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/08B64F5/60
CPCG01M9/08B64F5/60
Inventor 陈春鹏杨康智申蒸洋吴福章
Owner 中航通飞华南飞机工业有限公司
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