A low-speed wind tunnel model powered flight test power system

A power system and flight experiment technology, applied in aerodynamic tests, measuring devices, instruments, etc., can solve the problems of aircraft model design difficulties, low engine power density, and inability to install aircraft models, etc., and achieve good engineering application prospects, Low frictional resistance and light weight
CN105588702BInactive Publication Date: 2017-09-29LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
Publication Date
2017-09-29
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses a power system of a flight test with power of a low-speed wind tunnel model. The power system comprises a wind tunnel test section, an aircraft model and a power system. The power system comprises a needle valve, a high pressure hose, a swivel joint, a plenum chamber and a nozzle. The needle valve is arranged outside the wind tunnel test section. One end of the high pressure hose is connected to the needle valve, and the other end of the high pressure hose is connected to the rotation end of the swivel joint. The fixed end of the swivel joint is fixed at the top of the aircraft model. The plenum chamber is arranged in the aircraft model and communicates with the swivel joint. The nozzle is arranged at the tail part of the aircraft model, and the inlet end of the nozzle communicates with the plenum chamber through a pipeline. According to the power system, the requirement of the flight test with power of the wind tunnel model can be satisfied, the power density provided by the power system is large, the response is fast, the occupied space is small, the power system can be installed in the aircraft model, the service life is long, and the aircraft model motion interference is small.
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Description

technical field

[0001] The invention belongs to the technical field of wind tunnel experiment devices, in particular to a low-speed wind tunnel model driving force flight experiment power system. Background technique

[0002] It is an effective way to solve the problems of control law design and high angle of attack flight control law design and verification in the wind tunnel, and the power system of the aircraft model is required to provide thrust similar to that of the prototype aircraft. .

[0003] In the prior art, there are generally the following three methods for providing similar power for aircraft models: (1) electric ducted fan motors. It is difficult; moreover, the power density of this kind of engine is small, and it needs a large engine to provide enough thrust, which cannot be installed in the aircraft model; in addition, this method also has the problem of short service life of the bearings. (2) Small turbojet engine, this kind of engine also needs to provi...

Claims

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