CN109436373A - A kind of hypersonic power heat integration test cabin - Google Patents
A kind of hypersonic power heat integration test cabin Download PDFInfo
- Publication number
- CN109436373A CN109436373A CN201811445899.2A CN201811445899A CN109436373A CN 109436373 A CN109436373 A CN 109436373A CN 201811445899 A CN201811445899 A CN 201811445899A CN 109436373 A CN109436373 A CN 109436373A
- Authority
- CN
- China
- Prior art keywords
- cabin
- power heat
- heat integration
- tested
- hypersonic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 230000010354 integration Effects 0.000 title claims abstract description 25
- 238000012360 testing method Methods 0.000 title abstract description 37
- 238000001816 cooling Methods 0.000 claims abstract description 23
- 239000000498 cooling water Substances 0.000 claims abstract description 4
- 238000003032 molecular docking Methods 0.000 claims description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract 1
- 238000002474 experimental method Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000010339 dilation Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000010301 surface-oxidation reaction Methods 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND 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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- Y—GENERAL 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
A kind of hypersonic power heat integration test cabin, it is test cabin main structure body by the double-deck tubular interplanting, experimental enviroment is provided inside cylindrical sleeve for power heat integration test, the double-deck tubular jacket layer is cooling water circulation passage, cabin is tested for circulating cooling, hatch door is located at cabin front end, the pulling force model machine heavy frame of hypersonic power heat integration test is facilitated to put, the installation and dismounting of convenient test model, the bellows above and below cabin effectively obstruct during test external equipment to the conduct vibrations of test model.Use of the invention ensure that the smooth development of hypersonic power heat integration test, long-time steady operation, and have many advantages, such as that structurally reasonable, handling ease, install convenient, test operation are convenient.
Description
Technical field
The invention belongs to hypersonic experimental techniques, are related to a kind of cabin suitable for hypersonic power heat integration test.
Background technique
Hypersonic test, by simulating high ultrasound in experimental cabin body using heater and jet pipe heating, acceleration air-flow
The local local thermal environment of fast aircraft, to study the solar heat protection of the heat insulation material and structure of hypersonic aircraft under aerodynamic conditions
Performance.In fact, aerodynamic load, aircraft surface oxidation etc. are gone back in flight course while being subject to hypersonic aircraft
A variety of severe factors, hypersonic power heat integration test is the positions such as nose cone, the nose of wing for studying novel hypersonic aircraft
One of important ground experiment means in long-time high-speed flight the problems such as high temperature, stress, oxidation, to aircraft heat-protection system
Design plays important progradation.Testing cabin is one of important composition component of arc tunnel testing equipment, is dismounting examination
The important place tested model, carry out certification test carries the important mission for maintaining experimental enviroment low pressure long-time steady operation.
Since power heat integration test needs to simulate model mechanics load, for a long time hypersonic Aerodynamic Ablation and oxygen to be measured
Environment is divided, the design for testing cabin needs to meet the Various Complexes such as vacuum, high temperature, long Shi Yunhang and the collaboration of each subsystem and wants
Ask, while also to take into account model dismounting, test process observation, Test Data Collecting etc., with the reliable and stable fortune of guarantee test equipment
Row, obtains authentic and valid test data.Traditional hypersonic test cabin be cube structure, each two hatch doors in left and right,
A round observation window is respectively distributed on hatch door, since the rear and front end of test cabin is all connected with arc tunnel equipment, tradition is high
When supersonic speed tests cabin applied to power heat integration test, the heavy frame for realizing the pulling force model machine of pulling force load would interfere with cabin
Door folding influences model dismounting, and the pulling force loading mechanism of model machine also results in traditional cabin and vacuum leak occurs.
Summary of the invention
Technology of the invention solves the problems, such as: the hypersonic test cabin of tradition being overcome to carry out when power heat integration is tested not
Foot provides a set of model and dismounts the test that convenient, data acquisition acquisition is convenient, carries out suitable for hypersonic power heat integration test
Cabin.
Technical solution of the invention: a kind of hypersonic power heat integration test cabin, including the double-deck cylindrical sleeve, cooling
Ring, forward flange, rear flange, rectangular viewing windows, pulling force load window, bellows, front door, jet pipe interface, round observation window
Mouthful；Two cooling rings are docked with the housing both ends of the double-deck cylindrical sleeve respectively, forward flange and the double-deck cylindrical sleeve inner sleeve and a cooling
Ring docking, rear flange are docked with the double-deck cylindrical sleeve inner sleeve and a cooling ring；Two rectangular viewing windows are separately mounted to bilayer
Cylindrical sleeve arranged on left and right sides, two pulling force load windows are separately mounted to the upper and lower two sides of cylindrical sleeve, and bellows and pulling force load window
Mouth docking；Front door is docked with forward flange, and the unlatching and closure of front door are realized by hinge and door lock.
The double-deck cylindrical sleeve is used with cooling ring, forward flange, rear flange, rectangular viewing windows, pulling force load window
Argon arc welding is welded.
It is provided with seal groove on the pulling force load window, seal with elastometic washer is used when docking with bellows.
It is provided with seal groove on the rectangular viewing windows and round watch window, is made after covering quartz glass on seal groove
Use seal with elastometic washer.
It is coupled between the front door and forward flange in snap fastener, sticking rubber sealing ring in front door sub-buckle.
The inner sleeve long 520mm, internal diameter 490mm, wall thickness 6mm, housing long 406mm, internal diameter 508mm of the bilayer cylindrical sleeve,
Wall thickness 6mm.
The cooling ring maximum inner diameter 570mm, wall thickness 6mm.
The cooling ring is uniformly distributed 4 cooling water connectors.
Front door is the disk of diameter 680mm, and wall thickness 15mm, center is provided with jet pipe interface.
The jet pipe interface internal diameter 140mm, left and right distance 400mm are uniformly distributed two diameter 150mm circle observation windows
Mouthful.
The long 280mm of rectangular viewing windows, width 80mm, to 50mm is stretched out out of my cabin, the round and smooth processing of corner discharges stress.
Pulling force loads window internal diameter 100mm.
Ripple pipe range 200mm, internal diameter 100mm, maximal dilation amount is ± 30mm.
The advantages of present invention is compared with traditional experiment cabin is:
(1) delicate structure of the invention, entire cabin can be cooling by former and later two cooling ring water flowings, when guarantee test is long
Between run, the structure type of inner sealing ensure that vacuum test environment required for power heat integration is tested.
(2) structure type of front door of the invention provides abundant locational space for pulling force model machine, and model is facilitated to tear open
Dress.
(3) vibration of equipment is transmitted to mould by tensile machine during bellows of the invention can effectively obstruct test
Type, bellows upper cover provide interface for partial pressure of oxygen system, test macro.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention.
Specific embodiment
As shown in Figure 1, power heat integration test cabin include the double-deck cylindrical sleeve 1, it is cooling ring 2, forward flange 3, rear flange 4, preceding
Hatch door 5, rectangular viewing windows 6, pulling force load window 7, bellows 8, jet pipe interface 9, round watch window 10, the double-deck cylindrical sleeve
1 housing both ends are docked with two cooling rings 2, and forward flange 3 dock with double-deck 1 inner sleeve of cylindrical sleeve and cooling ring 2, rear flange with pair
Layer 1 inner sleeve of cylindrical sleeve and cooling ring 2 are docked；Two rectangular viewing windows 6 are located at double-deck 1 left and right sides of cylindrical sleeve, two pulling force
Load window 7 is located at cylindrical sleeve two sides up and down, and bellows 8 is docked with pulling force load window 7, and front door 5 is docked with forward flange 3,
The unlatching and closure of hatch door can be realized by hinge and door lock.
The inner sleeve long 520mm, internal diameter 490mm, wall thickness 6mm of the double-deck cylindrical sleeve 1, housing long 406mm, internal diameter 508mm, wall thickness
6mm, cooling ring 2 maximum inner diameter 570mm, wall thickness 6mm, is uniformly distributed 4 cooling water connectors, and front and back cooling ring four into four goes out.Before
Hatch door be diameter 680mm disk, wall thickness 15mm, center be jet pipe interface 9,9 internal diameter 140mm of jet pipe interface, left and right away from
Two round watch windows 10, round 10 internal diameter 150mm of watch window, the length of rectangular viewing windows 6 are uniformly distributed from 400mm
280mm, width 80mm, the quartz glass that can effectively avoid when testing for a long time on window to stretching 50mm out of my cabin are baked bad, turning
Locate round and smooth processing release stress.Pulling force loads 7 internal diameter 100mm of window, and bellows 8 is 200mm long, internal diameter 100mm, maximal dilation amount
For ± 30mm.
Claims (10)
1. cabin is tested in a kind of hypersonic power heat integration, it is characterised in that: preceding including the double-deck cylindrical sleeve (1), cooling ring (2)
Flange (3), rear flange (4), rectangular viewing windows (6), pulling force load window (7), bellows (8), front door (5), and jet pipe connects
Mouth (9), round watch window (10)；Two cooling rings (2) are docked with the housing both ends of the double-deck cylindrical sleeve (1) respectively, forward flange
(3) it is docked with double-deck cylindrical sleeve (1) inner sleeve and a cooling ring (2), rear flange (4) and double-deck cylindrical sleeve (1) inner sleeve and one
Cooling ring (2) docking；Two rectangular viewing windows (6) are separately mounted to the double-deck cylindrical sleeve (1) arranged on left and right sides, and two pulling force add
It carries window (7) and is separately mounted to cylindrical sleeve (1) upper and lower two sides, bellows (8) is docked with pulling force load window (7)；Front door
(5) it is docked with forward flange (3), the unlatching and closure of front door (5) is realized by hinge and door lock.
2. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the two layered cylinder
Shape set (1) and cooling ring (2), forward flange (3), rear flange (4), rectangular viewing windows (6), pulling force load window (7) use argon
Arc-welding is welded.
3. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the pulling force load
Window is provided with seal groove on (7), and seal with elastometic washer is used when docking with bellows (8).
4. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the rectangle is seen
It examines and is provided with seal groove on window (6) and round watch window (10), use seal with elastometic washer after quartz glass is covered on seal groove.
5. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the front door
(5) it is coupled between forward flange (3) in snap fastener, sticking rubber sealing ring in front door (5) sub-buckle.
6. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the bilayer tubular
Cover the inner sleeve long 520mm, internal diameter 490mm, wall thickness 6mm of (1), housing long 406mm, internal diameter 508mm, wall thickness 6mm.
7. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the cooling ring
(2) maximum inner diameter 570mm, wall thickness 6mm；The cooling ring (2) is uniformly distributed 4 cooling water connectors.
8. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the front door
(3) disk for being diameter 680mm, wall thickness 15mm, center is provided with jet pipe interface (9).
9. cabin is tested in a kind of hypersonic power heat integration according to claim 1, it is characterised in that: the rectangle observation
The long 280mm of window (6), width 80mm, to 50mm is stretched out out of my cabin, the round and smooth processing of corner discharges stress.
10. cabin is tested in a kind of hypersonic power heat integration according to claim 8, it is characterised in that: the jet pipe connects
Mouth (9) internal diameter 140mm, left and right distance 400mm are uniformly distributed the round watch window (10) of two diameter 150mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445899.2A CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445899.2A CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109436373A true CN109436373A (en) | 2019-03-08 |
| CN109436373B CN109436373B (en) | 2024-05-03 |
Family
ID=65556520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811445899.2A Active CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109436373B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112747890A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Pneumatic and thermal combined test system and test method |
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| Publication number | Publication date |
|---|---|
| CN109436373B (en) | 2024-05-03 |
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