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A low-speed wind tunnel aerial refueling hose-taper sleeve dynamic characteristics test device

An aerial refueling and refueling tube technology, which is applied in aerodynamic tests, measuring devices, transportation and packaging, etc., can solve problems such as low success rate, impact on flight safety, complex dynamic characteristics of refueling tube-drogue sleeve, etc., and achieve The effect of high precision and easy operation

Active Publication Date: 2021-01-22
中国航空工业集团公司哈尔滨空气动力研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the possible large influence of atmospheric turbulence in the soft refueling process, the influence of the refueling drogue by the atmospheric turbulence and the head wave effect of the refueling machine, the success rate of one refueling is very low; in addition, the refueling pipe- The drogue produces complex dynamic characteristics, which has a major impact on the control of the oil receiver and even the flight safety of the oil receiver and receiver
At this stage, although some dynamic modeling and simulation research work has been carried out on the dynamic characteristics of the aerial refueling hose-drogue sleeve, the dynamic aerodynamic characteristics of the refueling hose-drogue sleeve are not well understood

Method used

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  • A low-speed wind tunnel aerial refueling hose-taper sleeve dynamic characteristics test device
  • A low-speed wind tunnel aerial refueling hose-taper sleeve dynamic characteristics test device
  • A low-speed wind tunnel aerial refueling hose-taper sleeve dynamic characteristics test device

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0018] Such as Figure 1-5 As shown, a low-speed wind tunnel aerial refueling hose-drogue dynamic characteristic test device, including refueling pipe, refueling drogue, refueling pipe support mechanism, refueling pipe moving mechanism, refueling machine model, refueling conical pipe, two The high-speed camera and PIV equipment, the refueling drogue sleeve is connected with the refueling pipe, the refueling cone is installed on the model of the oil receiving machine, the model of the refueling machine is installed on the lower wall of the diffuser section of the wind tunnel, the supporting mechanism of the refueling pipe and the refueling pipe move The mechanism is located in front of the contraction section of the wind tunnel. The refueling pipe is installed on the refueling pipe support mechanism. Movement, the refueling pipe moving mechanism can realize the adjustable speed movement of the refueling drogue model at 0.01m / s~0.2m / s; the described refueling pipe moving mechani...

Embodiment 2

[0021] The concrete implementation process of this device is as follows:

[0022] 1. After confirming the position of the oil filling pipe moving mechanism, put down the suction cup. The suction cup is adsorbed on the bottom plate of the wind tunnel, so that the oil filling pipe moving mechanism is fixed in the lower wall of the wind tunnel, and then the turntable is leveled and fixed with the level adjustment and fixing parts of the turntable. fixed;

[0023] 2. Install the installed refueling support equipment on the turntable of the refueling pipe mobile device through its fixing plate; insert the bolt at the end of the refueling cone sleeve into the refueling pipe, and then bolt the refueling pipe to the fixed rope of the refueling pipe, and then put the refueling pipe The fixed rope is installed on the fueling pipe support mechanism through the fixed rope installation clip and the fixed rope tensioner, and the position of the fueling cone sleeve is roughly adjusted throug...

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Abstract

The invention provides a test device for the dynamic characteristics of a low-speed wind tunnel aerial refueling hose-taper sleeve. The device comprises a refueling pipe, a refueling taper sleeve, a refueling pipe supporting mechanism, a refueling pipe movement mechanism, a fuel receiver model, a fuel receiving taper pipe, two high-speed cameras and PIV (Particle Imaging Velocity) equipment, wherein the refueling pipe is installed on the refueling pipe supporting mechanism; the refueling pipe supporting mechanism is installed on the rotary table of the refueling pipe movement mechanism; refueling pipe movement equipment is controlled to move to drive the refueling taper sleeve to move; when the refueling taper sleeve is near the head of the fuel receiver model, the position of the refueling taper sleeve is regulated to enable the refueling taper sleeve to be connected with the oil receiving pipe; two high-speed cameras collect each piece of test data in a connection process; and the PIV equipment is started to collect bow wave effect data in the connection process of the refueling taper sleeve and the fuel receiving taper pipe. By use of the device, a refueling process can be moretruly simulated so as to be favorable for better researching the quality of the refueling taper sleeve and the length and the rigidity of the refueling pipe, and especially researching the influence effect of different connection speeds for the refueling process.

Description

technical field [0001] The invention belongs to the technical field of low-speed wind tunnel drop test, and relates to a low-speed wind tunnel aerial refueling hose-taper sleeve dynamic characteristic test device. Background technique [0002] Air refueling technology is mostly based on soft refueling. Soft refueling technology is more suitable for flight formation refueling and UAV refueling due to its one-to-many refueling capability, high refueling safety, low cost, and flexible use. In the future, it will still be a very important way of refueling. However, due to the large influence of atmospheric turbulence in the soft refueling process, the influence of the refueling drogue by the atmospheric turbulence, and the head wave effect of the refueling machine, the success rate of one refueling is very low; in addition, the refueling pipe- The drogue produces complex dynamic characteristics, which has a major impact on the control of the oil receiver, and even the flight sa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/02G01M99/00B64D39/04
CPCB64D39/04G01M9/02G01M99/00
Inventor 于金革曲明孙健侯良学王冬张戈杨希明郭承鹏于贤鹏刘南
Owner 中国航空工业集团公司哈尔滨空气动力研究所
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