CN-121977781-A - Continuous cross-supersonic wind tunnel system based on heavy gas medium and application method thereof

CN121977781ACN 121977781 ACN121977781 ACN 121977781ACN-121977781-A

Abstract

The invention relates to the field of wind tunnel equipment, and discloses a continuous cross supersonic wind tunnel system based on a heavy gas medium and a use method thereof. The injection module sequentially comprises a heavy gas storage tank, a delivery pump, a vaporizer and a pressure regulating and gas distributing unit, and the recovery module sequentially comprises a vacuum pump set, a compressor, condensing equipment, a mixed gas storage tank, cold box freezing equipment and adsorption equipment. According to the invention, heavy gas is adopted to replace traditional air as a test medium, so that the structural dynamics characteristic of the aeroelastic model of the aircraft can be accurately simulated, the test safety is obviously improved, the energy consumption is reduced, and the requirements of the future high-composite-material-ratio large-scale civil aircraft all-aircraft aeroelastic ground simulation test are met.

Inventors

CHEN JIMING
WU SHENGHAO
CHEN ZHENHUA
PEI HAITAO
SUN YUNQIANG
YANG GAOQIANG
LONG BINGXIANG
GAO XINYU
Cong Chenghua

Assignees

中国空气动力研究与发展中心设备设计与测试技术研究所

Dates

Publication Date: 20260505
Application Date: 20260409

Claims (8)

1. The continuous transultrasonic wind tunnel system based on the heavy gas medium comprises a wind tunnel main body and is characterized in that a heavy gas injection module is arranged at the air inlet end of the wind tunnel main body, and heavy gas for a test piece to perform a pneumatic elasticity test is introduced into the wind tunnel main body by the heavy gas injection module; The exhaust end of the wind tunnel main body is provided with a heavy gas recovery module for recovering heavy gas; the heavy gas injection module sequentially comprises a heavy gas storage tank, a delivery pump, a vaporizer and a pressure-regulating and gas-distributing unit, wherein liquid heavy gas stored in the heavy gas storage tank is delivered to the vaporizer through the delivery pump to be vaporized and then enters the wind tunnel main body through the pressure-regulating and gas-distributing unit; The heavy gas recovery module sequentially comprises a vacuum pump module, a compressor, condensing equipment, a mixed gas storage tank, cold box freezing equipment and adsorption equipment, wherein the vacuum pump module sequentially conveys mixed gas at an exhaust end to the compressor and the condensing equipment for condensation treatment, liquid heavy gas after the condensation treatment enters the heavy gas storage tank, mixed gas exhausted from the condensing equipment enters the mixed gas storage tank, gas conveyed from the mixed gas storage tank sequentially passes through the cold box freezing equipment and the adsorption equipment for cryogenic liquefaction, liquid heavy gas obtained by cryogenic liquefaction enters the heavy gas storage tank, and the gas obtained by cryogenic liquefaction is exhausted as tail gas after the purification effect of the adsorption equipment.
2. The continuous transonic wind tunnel system based on heavy gas media of claim 1, wherein a first isolation door and a second isolation door are sequentially arranged at the upstream and downstream positions of a test section residence chamber of a main loop in the wind tunnel main body.
3. The continuous transonic wind tunnel system based on heavy gas media of claim 1, wherein the pressure-regulating air distribution unit is connected with a medium-pressure air source.
4. The continuous transonic wind tunnel system based on heavy gas medium according to claim 1, wherein the heavy gas has a gas molecular weight larger than the air molecular weight.
5. The continuous transonic wind tunnel system based on heavy gas medium according to claim 4, wherein the heavy gas has a gas molecular weight three or more times that of air.
6. The continuous transsupersonic wind tunnel system based on heavy gas medium according to claim 1, wherein the heavy gas is SF6 or R134a.
7. The method of using a heavy gas media based continuous transsupersonic wind tunnel system according to any of claims 1-6, comprising: placing the test piece into the wind tunnel main body to wait for the aeroelastic test; Introducing dry air in a medium-pressure air source into the wind tunnel main body through a pressure-regulating air-distributing unit, and then regulating the dryness and the vacuum degree of the wind tunnel main body by using a vacuum pump module through exhausting the air of the wind tunnel main body; Liquid heavy gas in a heavy gas storage tank is conveyed to a vaporizer for vaporization through a conveying pump, and heavy gas with specified pressure and flow is introduced into the wind tunnel main body through a pressure regulating and gas distributing unit; The aeroelastic test of the test piece was started.
8. The method for using the continuous cross-supersonic wind tunnel system based on the heavy gas medium according to claim 7, wherein after the pneumatic elasticity test of the test piece is completed, the gas in the wind tunnel main body is sequentially conveyed to a compressor and a condensing device under the action of a vacuum pump module, the liquid heavy gas condensed by the compressor and the condensing device enters the heavy gas storage tank, and the mixed gas discharged from the condensing device enters the mixed gas storage tank; The gas exhausted from the mixed gas storage tank sequentially passes through the cold box freezing equipment and the adsorption equipment, and is exhausted as tail gas after the gas exhausted from the cold box freezing equipment passes through the purification function of the adsorption equipment.

Description

Continuous cross-supersonic wind tunnel system based on heavy gas medium and application method thereof Technical Field The invention relates to the field of wind tunnel equipment, in particular to a continuous cross-supersonic wind tunnel system based on a heavy gas medium and a use method thereof. Background With the continuous pursuit of advanced aircraft design for light weight and high performance, composite materials are widely applied to main bearing structures due to excellent mechanical properties such as high specific strength, high specific stiffness and the like. Compared with the traditional metal materials (such as aluminum alloy and titanium alloy), the composite material not only reduces the structural quality of the aircraft, but also has better aeroelastic cutting capability, thereby improving the critical speed of flutter and improving the flight stability and control performance. However, in the development process of such advanced aircrafts, higher requirements are put on accurate prediction and verification of aeroelastic characteristics (such as flutter, buffeting, static aeroelastic deformation and the like) of the advanced aircrafts, and high-fidelity aeroelastic tests are required to be carried out in a large wind tunnel. At present, air is generally adopted as a test medium in a large continuous cross-supersonic wind tunnel which is mainstream at home and abroad. However, the traditional wind tunnel taking air as a medium has a series of technical bottlenecks which are difficult to overcome when simulating the aeroelastic behavior of an advanced composite aircraft, namely, in the model scaling design, the model is often reinforced to meet the requirements of structural strength and rigidity, so that the model mass is increased, the air density is lower and is fixed, the ratio of the model mass to the air density is seriously deviated from a real flight state, namely, the model overweight problem, the mass scaling similarity is destroyed, and in the second, the model test is performed at a higher flow rate to meet the Mach number (Ma) similarity criterion due to the higher sound velocity of the air medium, so that the simultaneous meeting of the Fr similarity is almost impossible, particularly, in a low-speed or transonic section, the inertia-elastic coupling effect in the real flight cannot be accurately reproduced, and in the second, the model test is limited by the low air density, and the simulation accuracy of key flow phenomena such as high Reynolds number (Re) which influence the transition, separation and the like of the boundary layer is difficult to be achieved even at a high flow rate. In addition, when the air medium wind tunnel is subjected to a pneumatic elasticity test, the model vibration frequency is high, the rapid pressure is high, the risk of damage to the model structure is increased, higher requirements are put on a measurement and control system and safety protection, and meanwhile, in order to maintain high Mach number operation, the wind tunnel energy consumption is high, and the operation cost is high. More importantly, in key aeroelastic tests such as flutter boundary prediction and the like, stable simulation of an air medium under the condition of low speed and high density is difficult to realize, and accurate capture of the real flutter characteristics of the composite aircraft is limited. Disclosure of Invention Therefore, in order to solve the defects, the invention provides a continuous transonic wind tunnel system based on heavy gas medium and a use method thereof, compared with a conventional air medium wind tunnel, the invention adopts heavy gas medium to operate, the aeroelastic test model of the wind tunnel (particularly an aircraft made of composite materials) has the advantages of larger mass, lower frequency, lower rapid compression, more accurate test simulation, safer test and greatly improved aeroelastic test capability. On the one hand, the invention provides a continuous trans-supersonic wind tunnel system based on a heavy gas medium, which comprises a wind tunnel main body, wherein a heavy gas injection module is arranged at the air inlet end of the wind tunnel main body, and heavy gas for a test piece to perform a pneumatic elasticity test is introduced into the wind tunnel main body by the heavy gas injection module; The exhaust end of the wind tunnel main body is provided with a heavy gas recovery module for recovering heavy gas; the heavy gas injection module sequentially comprises a heavy gas storage tank, a delivery pump, a vaporizer and a pressure-regulating and gas-distributing unit, wherein liquid heavy gas stored in the heavy gas storage tank is delivered to the vaporizer through the delivery pump to be vaporized and then enters the wind tunnel main body through the pressure-regulating and gas-distributing unit; The heavy gas recovery module sequentially comprises a vacuum pump module, a compressor, condensing equipment, a m