CN109436373B - High-ultrasonic rapid force and heat combined test cabin - Google Patents

High-ultrasonic rapid force and heat combined test cabin Download PDF

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CN109436373B
CN109436373B CN201811445899.2A CN201811445899A CN109436373B CN 109436373 B CN109436373 B CN 109436373B CN 201811445899 A CN201811445899 A CN 201811445899A CN 109436373 B CN109436373 B CN 109436373B
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CN109436373A (en
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张智
欧东斌
高贺
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China Academy of Aerospace Aerodynamics CAAA
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60Testing or inspecting aircraft components or systems
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Manufacturing & Machinery (AREA)
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  • Aviation & Aerospace Engineering (AREA)
  • Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)

Abstract

A high-ultrasonic-speed force-heat combined test cabin body is formed by taking a double-layer cylindrical sleeve as a structural main body of the test cabin body, wherein a test environment is provided for force-heat combined test in the cylindrical sleeve, a cooling water circulation channel is formed in an interlayer of the double-layer cylindrical sleeve and is used for circularly cooling the test cabin body, a cabin door is positioned at the front end of the cabin body, a tensile force model carrying frame of the high-ultrasonic-speed force-heat combined test is conveniently placed, a test model is conveniently installed and removed, and external equipment on the upper portion and the lower portion of the cabin body can effectively isolate vibration conduction of the test model in a test process. The invention ensures the smooth development of the high ultrasonic speed force heat combined test, runs stably for a long time, and has the advantages of reasonable structure, easy processing, convenient installation, convenient test operation and the like.

Description

一种高超声速力热联合试验舱体A hypersonic combined force and heat test chamber

技术领域Technical Field

本发明属于高超声速试验技术,涉及一种适用于高超声速力热联合试验的舱体。The invention belongs to hypersonic test technology and relates to a cabin suitable for hypersonic force and heat combined test.

背景技术Background technique

高超声速试验,通过利用加热器和喷管加热、加速气流,在试验舱体内模拟高超声速飞行器当地局部热环境,来研究高超声速飞行器的防热材料和结构在气动条件下的防热性能。事实上,高超声速飞行器在飞行过程中还同时承受着气动力载荷、飞行器表面氧化等多种恶劣因素,高超声速力热联合试验是研究新型高超声速飞行器的头锥、翼前缘等部位在长时间高速飞行时高温、应力、氧化等问题的重要地面试验手段之一,对飞行器防热系统设计起到重要的推进作用。试验舱体是电弧风洞试验设备的重要组成部件之一,是拆装试验模型、开展考核试验的重要场地,承担着维持试验环境低压长时间稳定运行的重要使命。Hypersonic tests use heaters and nozzles to heat and accelerate the airflow, simulating the local thermal environment of the hypersonic aircraft in the test chamber to study the thermal performance of the hypersonic aircraft's thermal protection materials and structures under aerodynamic conditions. In fact, hypersonic aircraft are also subject to a variety of harsh factors such as aerodynamic loads and surface oxidation during flight. Hypersonic combined force and heat tests are one of the important ground test methods for studying the high temperature, stress, oxidation and other problems of the nose cone, wing leading edge and other parts of new hypersonic aircraft during long-term high-speed flight. It plays an important role in promoting the design of aircraft thermal protection systems. The test chamber is one of the important components of the arc wind tunnel test equipment. It is an important site for disassembling test models and conducting assessment tests. It has the important mission of maintaining the low-pressure and long-term stable operation of the test environment.

由于力热联合试验需要模拟待测模型力学加载、长时间高超声速气动烧蚀以及氧分压环境,试验舱体的设计需要满足真空、高温、长时运行以及各分系统协同等多种复杂要求,同时还要兼顾模型拆装、试验过程观测、试验数据采集等,以保证试验设备可靠稳定运行,获取真实有效的试验数据。传统的高超声速试验舱体为立方体结构,左右各两个舱门,舱门上各分布一个圆形观察窗,由于试验舱体的前后两端都连接有电弧风洞设备,传统高超声速试验舱体应用于力热联合试验时,用于实现拉力加载的拉力样机的承力架将妨碍舱门开合、影响模型拆装,样机的拉力加载机构也会导致传统舱体发生真空泄露。Since the combined force and heat test needs to simulate the mechanical loading of the model to be tested, long-term hypersonic aerodynamic ablation and oxygen partial pressure environment, the design of the test cabin needs to meet multiple complex requirements such as vacuum, high temperature, long-term operation and coordination of various subsystems. At the same time, it is also necessary to take into account the disassembly and assembly of the model, observation of the test process, and test data collection, so as to ensure the reliable and stable operation of the test equipment and obtain real and effective test data. The traditional hypersonic test cabin is a cubic structure with two doors on the left and right, and a circular observation window on each door. Since the front and rear ends of the test cabin are connected to arc wind tunnel equipment, when the traditional hypersonic test cabin is used in the combined force and heat test, the load-bearing frame of the tensile prototype used to achieve tensile loading will hinder the opening and closing of the door and affect the disassembly and assembly of the model. The tensile loading mechanism of the prototype will also cause vacuum leakage in the traditional cabin.

发明内容Summary of the invention

本发明的技术解决问题:克服传统高超声速试验舱体开展力热联合试验时的不足,提供一套模型拆装便捷、数据采集获取方便、适用于高超声速力热联合试验进行的试验舱体。The technology of the present invention solves the problem of overcoming the shortcomings of traditional hypersonic test chambers in conducting combined force and heat tests, and providing a test chamber that is convenient for model assembly and disassembly, convenient for data collection and acquisition, and suitable for conducting combined force and heat tests of hypersonic speed.

本发明的技术解决方案:一种高超声速力热联合试验舱体,包括双层筒形套、冷却环,前法兰,后法兰,矩形观察窗口、拉力加载窗口、波纹管、前舱门,喷管接口、圆形观察窗口;两个冷却环分别与双层筒形套的外套两端对接,前法兰与双层筒形套内套和一个冷却环对接,后法兰与双层筒形套内套和一个冷却环对接;两个矩形观察窗口分别安装在双层筒形套左、右两侧,两个拉力加载窗口分别安装在筒形套上、下两侧,波纹管与拉力加载窗口对接;前舱门与前法兰对接,通过铰链和门锁实现前舱门的开启和闭合。The technical solution of the present invention is as follows: a hypersonic combined force and heat test cabin, comprising a double-layer cylindrical sleeve, a cooling ring, a front flange, a rear flange, a rectangular observation window, a tension loading window, a bellows, a front cabin door, a nozzle interface, and a circular observation window; two cooling rings are respectively butted with the two ends of the outer sleeve of the double-layer cylindrical sleeve, the front flange is butted with the inner sleeve of the double-layer cylindrical sleeve and a cooling ring, and the rear flange is butted with the inner sleeve of the double-layer cylindrical sleeve and a cooling ring; two rectangular observation windows are respectively installed on the left and right sides of the double-layer cylindrical sleeve, two tension loading windows are respectively installed on the upper and lower sides of the cylindrical sleeve, and the bellows is butted with the tension loading window; the front cabin door is butted with the front flange, and the opening and closing of the front cabin door are realized by hinges and door locks.

所述的双层筒形套与冷却环、前法兰、后法兰、矩形观察窗口、拉力加载窗口使用氩弧焊进行焊接。The double-layer cylindrical sleeve is welded with the cooling ring, the front flange, the rear flange, the rectangular observation window and the tension loading window by using argon arc welding.

所述拉力加载窗口上开有密封槽,与波纹管对接时使用橡胶圈密封。A sealing groove is provided on the tension loading window, and a rubber ring is used for sealing when the window is butted against the corrugated pipe.

所述的矩形观察窗口和圆形观察窗口上开有密封槽,密封槽上覆盖石英玻璃后使用橡胶圈密封。The rectangular observation window and the circular observation window are provided with sealing grooves, which are covered with quartz glass and sealed with rubber rings.

所述的前舱门与前法兰间呈子母扣配合安装,前舱门子扣上粘结橡胶密封圈。The front door and the front flange are installed in a snap-fit manner, and a rubber sealing ring is bonded to the snap of the front door.

所述双层筒形套的内套长520mm,内径490mm,壁厚6mm,外套长406mm,内径508mm,壁厚6mm。The inner sleeve of the double-layer cylindrical sleeve is 520 mm long, 490 mm in inner diameter and 6 mm in wall thickness, while the outer sleeve is 406 mm long, 508 mm in inner diameter and 6 mm in wall thickness.

所述冷却环最大内径570mm,壁厚6mm。The cooling ring has a maximum inner diameter of 570 mm and a wall thickness of 6 mm.

所述冷却环均匀分布4个冷却水接口。The cooling ring has four cooling water interfaces evenly distributed thereon.

前舱门为直径680mm的圆盘,壁厚15mm,中心位置开有喷管接口。The front door is a disc with a diameter of 680mm, a wall thickness of 15mm, and a nozzle interface in the center.

所述喷管接口内径140mm,左、右距离400mm均匀分布两个直径150mm圆形观察窗口。The nozzle interface has an inner diameter of 140 mm, and two circular observation windows with a diameter of 150 mm are evenly distributed at a distance of 400 mm on the left and right.

矩形观察窗口长280mm、宽80mm、向舱外伸出50mm,拐角处圆滑处理释放应力。The rectangular observation window is 280mm long, 80mm wide, and extends 50mm outside the cabin. The corners are rounded to relieve stress.

拉力加载窗口内径100mm。The inner diameter of the tension loading window is 100mm.

波纹管长200mm,内径100mm,最大伸缩量为±30mm。The bellows is 200mm long, 100mm inside diameter, and has a maximum expansion and contraction range of ±30mm.

本发明与传统试验舱体相比的优点在于:Compared with the traditional test chamber, the advantages of the present invention are:

(1)本发明的结构精巧,整个舱体可通过前后两个冷却环通水冷却,保证试验长时间运行,内封闭的结构形式保证了力热联合试验所需要的真空试验环境。(1) The structure of the present invention is sophisticated. The entire cabin can be cooled by water through two front and rear cooling loops to ensure long-term operation of the test. The internally enclosed structure ensures the vacuum test environment required for the combined force and heat test.

(2)本发明的前舱门的结构形式为拉力样机提供了充裕的位置空间,方便模型拆装。(2) The structural form of the front door of the present invention provides ample space for the tensile prototype, making it convenient for the model to be disassembled and assembled.

(3)本发明的波纹管可有效阻隔试验过程中设备的振动通过拉力机构传导到模型,波纹管上盖为氧分压系统、测试系统提供了接口。(3) The bellows of the present invention can effectively prevent the vibration of the equipment from being transmitted to the model through the tension mechanism during the test, and the upper cover of the bellows provides an interface for the oxygen partial pressure system and the test system.

附图说明BRIEF DESCRIPTION OF THE DRAWINGS

图1为本发明的结构示意图。FIG1 is a schematic structural diagram of the present invention.

具体实施方式Detailed ways

如图1所示,力热联合试验舱体包括双层筒形套1、冷却环2、前法兰3、后法兰4、前舱门5、矩形观察窗口6、拉力加载窗口7、波纹管8、喷管接口9、圆形观察窗口10,双层筒形套1的外套两端与两个冷却环2对接,前法兰3与双层筒形套1内套和冷却环2对接,后法兰与双层筒形套1内套和冷却环2对接;两个矩形观察窗口6位于双层筒形套1左右两侧,两个拉力加载窗口7位于筒形套上下两侧,波纹管8与拉力加载窗口7对接,前舱门5与前法兰3对接,通过铰链和门锁可实现舱门的开启和闭合。As shown in Figure 1, the combined force and heat test chamber includes a double-layer cylindrical sleeve 1, a cooling ring 2, a front flange 3, a rear flange 4, a front cabin door 5, a rectangular observation window 6, a tension loading window 7, a bellows 8, a nozzle interface 9, and a circular observation window 10. The two ends of the outer sleeve of the double-layer cylindrical sleeve 1 are connected to the two cooling rings 2, the front flange 3 is connected to the inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2, and the rear flange is connected to the inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2; the two rectangular observation windows 6 are located on the left and right sides of the double-layer cylindrical sleeve 1, the two tension loading windows 7 are located on the upper and lower sides of the cylindrical sleeve, the bellows 8 is connected to the tension loading window 7, and the front cabin door 5 is connected to the front flange 3. The hatch door can be opened and closed by hinges and door locks.

双层筒形套1的内套长520mm,内径490mm,壁厚6mm,外套长406mm,内径508mm,壁厚6mm,冷却环2最大内径570mm,壁厚6mm,均匀分布4个冷却水接口,前后冷却环四进四出。前舱门为直径680mm的圆盘,壁厚15mm,中心位置为喷管接口9,喷管接口9内径140mm,左右距离400mm均匀分布两个圆形观察窗口10,圆形观察窗口10内径150mm,矩形观察窗口6长280mm、宽80mm、向舱外伸出50mm可有效避免长时间试验时窗口上的石英玻璃被烤坏,拐角处圆滑处理释放应力。拉力加载窗口7内径100mm,波纹管8长200mm,内径100mm,最大伸缩量为±30mm。The inner sleeve of the double-layer cylindrical sleeve 1 is 520mm long, 490mm in diameter, and 6mm thick. The outer sleeve is 406mm long, 508mm in diameter, and 6mm thick. The maximum inner diameter of the cooling ring 2 is 570mm, and the wall thickness is 6mm. There are 4 evenly distributed cooling water interfaces, and the front and rear cooling rings have four inlets and four outlets. The front door is a disc with a diameter of 680mm and a wall thickness of 15mm. The center position is the nozzle interface 9, and the nozzle interface 9 has an inner diameter of 140mm. Two circular observation windows 10 are evenly distributed at a distance of 400mm from left to right. The circular observation window 10 has an inner diameter of 150mm. The rectangular observation window 6 is 280mm long, 80mm wide, and extends 50mm outside the cabin to effectively prevent the quartz glass on the window from being burned during long-term testing. The corners are rounded to release stress. The inner diameter of the tensile loading window 7 is 100mm, and the bellows 8 is 200mm long, 100mm in diameter, and the maximum telescopic amount is ±30mm.

Claims (8)

1.一种高超声速力热联合试验舱体,其特征在于:包括双层筒形套(1)、冷却环(2),前法兰(3),后法兰(4),矩形观察窗口(6)、拉力加载窗口(7)、波纹管(8)、前舱门(5),喷管接口(9)、圆形观察窗口(10);两个冷却环(2)分别与双层筒形套(1)的外套两端对接,前法兰(3)与双层筒形套(1)内套和一个冷却环(2)对接,后法兰(4)与双层筒形套(1)内套和一个冷却环(2)对接;两个矩形观察窗口(6)分别安装在双层筒形套(1)左、右两侧,两个拉力加载窗口(7)分别安装在筒形套(1)上、下两侧,波纹管(8)与拉力加载窗口(7)对接;前舱门(5)与前法兰(3)对接,通过铰链和门锁实现前舱门(5)的开启和闭合;1. A hypersonic thermal combined test cabin, characterized in that it comprises a double-layer cylindrical sleeve (1), a cooling ring (2), a front flange (3), a rear flange (4), a rectangular observation window (6), a tension loading window (7), a bellows (8), a front cabin door (5), a nozzle interface (9), and a circular observation window (10); two cooling rings (2) are respectively connected to the two ends of the outer sleeve of the double-layer cylindrical sleeve (1); the front flange (3) is connected to the inner sleeve of the double-layer cylindrical sleeve (1) and a cooling ring (2); the rear flange (4) is connected to the inner sleeve of the double-layer cylindrical sleeve (1) and a cooling ring (2); two rectangular observation windows (6) are respectively installed on the left and right sides of the double-layer cylindrical sleeve (1); two tension loading windows (7) are respectively installed on the upper and lower sides of the cylindrical sleeve (1); the bellows (8) is connected to the tension loading window (7); the front cabin door (5) is connected to the front flange (3), and the front cabin door (5) is opened and closed by hinges and door locks; 所述拉力加载窗口(7)上开有密封槽,与波纹管(8)对接时使用橡胶圈密封;The tensile loading window (7) is provided with a sealing groove, and a rubber ring is used to seal when it is connected to the bellows (8); 所述的矩形观察窗口(6)和圆形观察窗口(10)上开有密封槽,密封槽上覆盖石英玻璃后使用橡胶圈密封。The rectangular observation window (6) and the circular observation window (10) are provided with sealing grooves, which are covered with quartz glass and sealed with rubber rings. 2.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述的双层筒形套(1)与冷却环(2)、前法兰(3)、后法兰(4)、矩形观察窗口(6)、拉力加载窗口(7)使用氩弧焊进行焊接。2. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that the double-layer cylindrical sleeve (1) and the cooling ring (2), the front flange (3), the rear flange (4), the rectangular observation window (6), and the tensile loading window (7) are welded using argon arc welding. 3.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述的前舱门(5)与前法兰(3)间呈子母扣配合安装,前舱门(5)子扣上粘结橡胶密封圈。3. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the front door (5) and the front flange (3) are installed in a snap-fit manner, and a rubber sealing ring is bonded to the snap of the front door (5). 4.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述双层筒形套(1)的内套长520mm,内径490mm,壁厚6mm,外套长406mm,内径508mm,壁厚6mm。4. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that the inner sleeve of the double-layer cylindrical sleeve (1) is 520 mm long, 490 mm inner diameter, and 6 mm thick, while the outer sleeve is 406 mm long, 508 mm inner diameter, and 6 mm thick. 5.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述冷却环(2)最大内径570mm,壁厚6mm;所述冷却环(2)均匀分布4个冷却水接口。5. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the maximum inner diameter of the cooling ring (2) is 570 mm and the wall thickness is 6 mm; the cooling ring (2) has 4 cooling water interfaces evenly distributed. 6.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述前舱门(3)为直径680mm的圆盘,壁厚15mm,中心位置开有喷管接口(9)。6. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the front door (3) is a disc with a diameter of 680 mm, a wall thickness of 15 mm, and a nozzle interface (9) is opened at the center. 7.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述矩形观察窗口(6)长280mm、宽80mm、向舱外伸出50mm,拐角处圆滑处理释放应力。7. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the rectangular observation window (6) is 280 mm long, 80 mm wide, and extends 50 mm outside the chamber, and the corners are rounded to release stress. 8.根据权利要求1所述的一种高超声速力热联合试验舱体,其特征在于:所述喷管接口(9)内径140mm,左、右距离400mm均匀分布两个直径150mm的圆形观察窗口(10)。8. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the nozzle interface (9) has an inner diameter of 140 mm, and two circular observation windows (10) with a diameter of 150 mm are evenly distributed at a distance of 400 mm on the left and right.
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CN112747890B (en) * 2020-12-29 2023-03-14 中国航天空气动力技术研究院 Pneumatic and thermal combined test system and test method

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103048110A (en) * 2012-12-14 2013-04-17 中国航空工业集团公司沈阳空气动力研究所 Experimental facility for realizing thrust deflexion and experimental technique thereof
CN103063398A (en) * 2012-12-28 2013-04-24 中国人民解放军国防科学技术大学 Hypersonic wind tunnel experiment module
CN103234804A (en) * 2013-04-25 2013-08-07 哈尔滨工业大学 High-power non-contact type rapid laser heating device
CN103344777A (en) * 2013-06-20 2013-10-09 哈尔滨工业大学 High-temperature and low-pressure oxygen dissociation environment test device for heat protection material
CN104132813A (en) * 2014-08-08 2014-11-05 中国航天科技集团公司第四研究院四0一所 Slidable double-cylinder type structure pressure stabilization bin for solid ramjet direct connection test
CN104458189A (en) * 2014-10-17 2015-03-25 北京航天益森风洞工程技术有限公司 Process layout method for conventional hypersonic speed wind tunnel
CN105181317A (en) * 2015-09-22 2015-12-23 中国航天空气动力技术研究院 Rudderpost heat sealing test device
CN205826262U (en) * 2016-07-07 2016-12-21 长沙市天映机械制造有限公司 A kind of air bubble clashes into the vacuum test cabin of detection testpieces performance parameter
CN106568568A (en) * 2016-10-19 2017-04-19 北京航天长征飞行器研究所 A supersonic wind tunnel test system for high temperature gas flow
CN108255207A (en) * 2018-01-02 2018-07-06 高砂建筑工程(北京)有限公司 Wind-tunnel idling and spout device and its control method
CN108534981A (en) * 2018-02-07 2018-09-14 北京航天长征飞行器研究所 A water spraying cooling device at the collection port for high temperature wind tunnel
CN209506126U (en) * 2018-11-29 2019-10-18 中国航天空气动力技术研究院 A kind of hypersonic power heat integration test cabin

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103048110A (en) * 2012-12-14 2013-04-17 中国航空工业集团公司沈阳空气动力研究所 Experimental facility for realizing thrust deflexion and experimental technique thereof
CN103063398A (en) * 2012-12-28 2013-04-24 中国人民解放军国防科学技术大学 Hypersonic wind tunnel experiment module
CN103234804A (en) * 2013-04-25 2013-08-07 哈尔滨工业大学 High-power non-contact type rapid laser heating device
CN103344777A (en) * 2013-06-20 2013-10-09 哈尔滨工业大学 High-temperature and low-pressure oxygen dissociation environment test device for heat protection material
CN104132813A (en) * 2014-08-08 2014-11-05 中国航天科技集团公司第四研究院四0一所 Slidable double-cylinder type structure pressure stabilization bin for solid ramjet direct connection test
CN104458189A (en) * 2014-10-17 2015-03-25 北京航天益森风洞工程技术有限公司 Process layout method for conventional hypersonic speed wind tunnel
CN105181317A (en) * 2015-09-22 2015-12-23 中国航天空气动力技术研究院 Rudderpost heat sealing test device
CN205826262U (en) * 2016-07-07 2016-12-21 长沙市天映机械制造有限公司 A kind of air bubble clashes into the vacuum test cabin of detection testpieces performance parameter
CN106568568A (en) * 2016-10-19 2017-04-19 北京航天长征飞行器研究所 A supersonic wind tunnel test system for high temperature gas flow
CN108255207A (en) * 2018-01-02 2018-07-06 高砂建筑工程(北京)有限公司 Wind-tunnel idling and spout device and its control method
CN108534981A (en) * 2018-02-07 2018-09-14 北京航天长征飞行器研究所 A water spraying cooling device at the collection port for high temperature wind tunnel
CN209506126U (en) * 2018-11-29 2019-10-18 中国航天空气动力技术研究院 A kind of hypersonic power heat integration test cabin

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