CN111811823A - Rack construction suitable for ramjet engine free jet test - Google Patents
Rack construction suitable for ramjet engine free jet test Download PDFInfo
- Publication number
- CN111811823A CN111811823A CN202010504651.XA CN202010504651A CN111811823A CN 111811823 A CN111811823 A CN 111811823A CN 202010504651 A CN202010504651 A CN 202010504651A CN 111811823 A CN111811823 A CN 111811823A
- Authority
- CN
- China
- Prior art keywords
- rack
- tail
- pipeline
- engine
- test piece
- 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.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a bench structure suitable for a ramjet engine free jet test, which comprises: the system comprises a rack assembly, a resistance reducing and pressure reducing plate, a resistance reducing protection plate, an oil supply pipeline, a measuring pipeline, a turbulent flow resistance reducing plate and a base; the rack assembly consists of more than one rack; more than one rack is linearly distributed and fixed on the base; the rack positioned at the foremost end is a first rack, and the rack positioned at the rearmost end is a tail rack; the front end of the first rack is processed into a wedge structure, and the tip of the wedge structure faces the incoming flow direction of the airflow; an engine test piece to be tested is supported on the rack assembly; an oil supply pipeline and a measuring pipeline are arranged in the tail rack, and more than one anti-drag protection plate is arranged at the front end of the top of the tail rack; the tail end of the tail rack is provided with a turbulent flow resistance reducing plate; the invention can be suitable for free jet tests of various types of ramjet engines, and the strength and the rigidity of the rack structure meet the free jet test of all flight speeds within Ma6.0.
Description
Technical Field
The invention belongs to the technical field, and particularly relates to a rack structure suitable for a ramjet engine free jet test.
Background
Free jet testing, a form of testing that has become increasingly popular as testing techniques have evolved. In the free jet test, the entire test product (i.e., the engine test piece) was exposed to a high velocity air stream. The free stand plays a role in supporting and protecting a test product in a test. The Mach number of the current test simulation is higher and higher, and the test bench suitable for low Mach number in the past can not meet the use requirements in the aspects of strength, rigidity and resistance. The high mach number test uses a low mach number test bed, which can result in test bed nozzle deactivation (test failure) and bed overrun load limit causing product fly-out (test bed failure). The test fails, the time period delay is about 1 week, and the asset loss is 10-30 ten thousand. The test bench is damaged, the time period delay is about 2 months, and the asset loss is 100-1000 ten thousand. Both cycle delays and asset losses are a heavy cost to the trial.
Disclosure of Invention
In view of the above, the invention provides a rack structure suitable for a ramjet engine free jet test, which is reliable in installation, simple in structure, convenient to disassemble and assemble, and suitable for free jet tests of various types of ramjets, and the strength and rigidity of the rack structure meet all flight speeds within Ma6.0.
The invention is realized by the following technical scheme:
a bench structure suitable for ramjet free jet testing, comprising: the system comprises a rack assembly, a resistance reducing and pressure reducing plate, a resistance reducing protection plate, an oil supply pipeline, a measuring pipeline, a turbulent flow resistance reducing plate and a base;
the rack assembly consists of more than one rack; more than one rack is linearly distributed and fixed on the base, and a resistance-reducing pressure-reducing plate is respectively connected between two adjacent racks; the rack positioned at the foremost end is a first rack, and the rack positioned at the rearmost end is a tail rack; the front end of the first rack is processed into a wedge structure, and the tip of the wedge structure faces the incoming flow direction of the airflow;
an engine test piece to be tested is supported on the rack assembly;
an oil supply pipeline and a measuring pipeline are arranged in the tail rack, and an oil inlet of the oil supply pipeline is positioned at the bottom of the tail rack and is connected with an oil source of the test bed; an oil outlet of the oil supply pipeline is positioned at the top of the tail stand and is connected with an oil inlet pipeline of the engine test piece; the inlet of the measuring pipeline is positioned at the top of the tail stand and is connected with a pressure measuring nozzle of the shell of the engine test piece; the outlet of the measuring pipeline is positioned at the bottom of the tail rack and is connected with a measuring system of the test bed;
the oil supply pipeline and the measuring pipeline are both flexible pipelines;
more than one drag reduction protection plate is arranged at the front end of the top of the tail rack; the tail end of the tail rack is provided with a turbulent flow resistance reducing plate; the resistance-reducing protection plate is a wedge-shaped block, the tip end of the wedge-shaped block faces the incoming flow direction of the airflow and is used for reducing the airflow resistance, and meanwhile, an oil supply pipeline, a measuring pipeline and an ignition device positioned at the bottom of an engine test piece are protected and isolated from the airflow; the turbulence drag reduction plate is a wedge-shaped block, and the tip of the wedge-shaped block is back to the incoming flow direction of the air flow and is used for performing turbulence drag reduction on the air flow passing through the rack assembly and the engine test piece.
Furthermore, the bottom of more than one rack of the rack assembly is provided with more than two triangular reinforcing ribs.
Furthermore, the first rack is made of stainless steel materials, and the rest racks are made of Q235 carbon steel.
Further, the angle of the wedge structure of the first rack is 30-35 degrees.
Furthermore, two half clamping rings are fixed at the top of the first rack, and more than two radial holes which are uniformly distributed are formed in each half clamping ring;
the tops of the other racks are fixed with lower half snap rings;
an engine test piece to be tested is supported in the two half snap rings of the first rack and the lower half snap rings of the other racks;
connecting the engine test piece with the half clamping ring through a radial countersunk head screw to realize the connection of the engine test piece and the head rack; and the upper half clamping rings which correspond to the lower half clamping rings one by one are respectively sleeved on the engine test piece, each upper half clamping ring is in butt joint with the corresponding lower half clamping ring and is connected into a clamping ring through a bolt, and the connection of other racks and the engine test piece is realized.
Furthermore, the snap ring is made of stainless steel.
Has the advantages that: (1) when the free jet test simulates Ma6.0, the airflow from the test bed nozzle has the characteristics of high temperature, high speed and strong disturbance, and the rack structure has the characteristics of high strength, high rigidity and large heat capacity, can meet the use requirement of a long-time examination test in a state within Ma6.0 for more than 500s, and can stably work under a wide Mach number range.
(2) The platform I adopts a wedge structure, adopts a mode of connecting the engine test piece with the semi-snap ring by adopting a radial countersunk head screw, and adopts a resistance reduction protection plate and a turbulence resistance reduction plate, so that the front end, the middle part and the tail end of the platform structure are all provided with the resistance reduction structures, the incoming flow resistance of airflow can be reduced, and the airflow resistance of the platform structure is smaller than the maximum allowable resistance value of the test bed; the engine test piece is connected with the half clamping ring through the radial countersunk head screws, the whole clamping ring is converted into a half ring structure, a bolt connecting structure formed by butting an upper half clamping ring and an upper half clamping ring with a lower half clamping ring is omitted, and the windward area is only 35% of that of the clamping ring.
(3) The oil supply pipeline and the measuring pipeline are flexible pipelines, and the flexible pipelines are damaged when exposed in high-temperature, high-speed and strong-disturbance airflow, so that a test bench is in fire and measurement data are lost, and finally, the test fails; the oil supply pipeline and the measuring pipeline adopt a built-in assembly scheme, so that the total length of the flexible pipeline exposed in the air flow is 20%, and the safety and the reliability of the test are greatly improved.
(4) The anti-drag protection plate disclosed by the invention can be used for protecting the flexible pipeline which is exposed to 20% of airflow and the ignition device which is positioned at the bottom of the engine test piece while reducing drag, so that the pipeline damage and the early spontaneous combustion of the ignition device can be avoided, and the anti-drag protection plate is an important protection measure for ensuring the success of a test.
(5) The rack assembly is designed in a split mode, namely, the rack assembly consists of more than one rack, the more than one rack are mutually independent and can be independently hoisted into the test bed and installed in place, the integral type test bed is more convenient and faster to install than the integral type test bed, the field operation is convenient, and the labor cost is saved; the supporting position for supporting the engine test piece is adjusted by adjusting the distance between more than one stand, and the supporting position of the engine test piece is changed only by adjusting the distance between more than one stand, so that the stand remanufacturing cost and the test time cost are reduced; and the number of the racks is increased or decreased, so that the engine test device can adapt to engine test pieces of different models, and the adaptability to engine tests of different models is improved.
(6) The engine test piece support device can adapt to the support of engine test pieces of different models by replacing the clamping rings matched with the engine test pieces of different models;
(7) according to the invention, the stand I and the clamping ring with higher temperature are made of stainless steel materials, the stand II and the stand III with lower temperature are made of Q235 carbon steel, and a dual-material design is adopted, so that the test requirements are met, and the cost is saved.
Drawings
FIG. 1 is a structural component diagram of the present invention;
FIG. 2 is a schematic diagram of a wedge structure of a rack I;
FIG. 3 is a schematic view of a radial countersunk head screw connecting an engine test piece with a half-snap ring
FIG. 4 is an assembly view of the oil supply line, the baffle plate and the snap ring;
FIG. 5 is a schematic structural view of a measurement pipeline and a resistance-reducing protection plate;
the device comprises a base, a power supply, a measuring pipeline, a turbulent flow resistance reducing plate, a clamping ring, an engine, an ignition device and a radial sunk screw, wherein the power supply comprises 1-a rack I1, 2-a rack II, 3-a rack III, 4-a resistance reducing plate, 5-a resistance reducing protection plate, 6-an oil supply pipeline, 7-a measuring pipeline, 8-a turbulent flow resistance reducing plate, 9-a clamping ring, 10-the engine, 11-the ignition device and 12-the radial sunk.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The present embodiment provides a bench structure suitable for ramjet free jet test, referring to fig. 1, comprising: the device comprises a rack assembly, a resistance reducing and pressure reducing plate 4, a resistance reducing and protecting plate 5, an oil supply pipeline 6, a measuring pipeline 7, a turbulent flow resistance reducing plate 8 and a base;
the rack assembly consists of more than one rack; namely, the rack assembly selects one or more racks according to the test requirements so as to improve the adaptability to engine test pieces 10 of different models; the composition scheme of rack subassembly has: gantry I1, gantry I1 and gantry II2, gantry I1 and gantry III3, gantry I1, gantry II2 and gantry III 3; in the embodiment, the scheme of a rack I1, a rack II2 and a rack III3 is selected;
the rack I1, the rack II2 and the rack III3 are all made of plates with the thickness of 60-80 mm by full welding with large grooves; the bottoms of the rack I1, the rack II2 and the rack III3 are respectively provided with more than two triangular reinforcing ribs so as to improve the strength, the rigidity and the heat capacity of the rack assembly; referring to the attached drawing 2, the front end (namely the windward end) of the rack I1 is processed into a wedge structure, the angle of the wedge structure is 30-35 degrees, the resistance reducing effect is poor when the angle is too large, and the safety factor is reduced when the angle is too small; in the embodiment, the angle of the wedge structure is selected to be 32 degrees; the rack II2 and the rack III3 both comprise two vertical frames which are connected into a whole by the resistance-reducing pressure-reducing plate 4;
the overall connection relationship is as follows: the rack I1, the rack II2 and the rack III3 are fixed on the base in a linear distribution manner, the tip of the wedge structure of the rack I1 faces the incoming flow direction of the airflow, and the rack II2 is positioned between the rack I1 and the rack III 3; the distance between the rack II2 and the racks I1 and III3 is set, and the distance between the rack II2 and the racks I1 and III3 can be adjusted to adapt to engine test pieces 10 of different models;
a resistance-reducing pressure-reducing plate 4 is respectively connected between the rack I1 and the rack II2 and between the rack II2 and the rack III 3;
the top of the rack I1 is fixed with two half clamping rings through bolts, and each half clamping ring is provided with more than two radial holes which are uniformly distributed;
the top of the rack II2 is fixed with a lower half snap ring through a bolt; the top of the rack III3 is fixedly provided with two lower half clamping rings through welding;
the engine test piece 10 to be tested is supported in the two half snap rings of the rack I1, one lower half snap ring of the rack II2 and the two lower half snap rings of the rack III 3; referring to fig. 3, the engine test piece 10 is connected with the semi-clamping ring through the radial countersunk head screw 12, so that the connection of the engine test piece 10 and the rack I1 is realized; the three upper half clamping rings are respectively sleeved on the engine test piece 10, are respectively butted with the three lower half clamping rings and are connected into a clamping ring 9 through bolts, so that the connection between the rack II2 and the rack III3 and the engine test piece 10 is realized; the support of the engine test pieces 10 of different models can be adapted by replacing the clamping rings 9 matched with the engine test pieces 10 of different models;
the rack I1 and the clamp ring 9 are made of stainless steel materials, and the rack II2 and the rack III3 are made of Q235 carbon steel;
referring to fig. 4-5, the 2-way oil supply pipeline 6 is arranged in the vertical frame at the front end of the rack III3, and the 2-way oil supply pipeline 6 is independent from each other, and can work independently or jointly; an oil inlet of the oil supply pipeline 6 is positioned at the bottom of the rack III3 and is connected with an oil source of the test bed; an oil outlet of the oil supply pipeline 6 is positioned at the top of the rack III3 and is connected with an oil inlet pipeline of the engine test piece 10;
20 measuring pipelines 7 are arranged in the vertical frame at the rear end of the rack III3, and the 20 measuring pipelines 7 are independent and do not influence each other; the inlet of the measuring pipeline 7 is positioned at the top of the rack III3 and is connected with a pressure measuring nozzle of the shell of the engine test piece 10; the outlet of the measuring pipeline 7 is positioned at the bottom of the rack III3 and is connected with a measuring system of the test bed; the 20 measuring pipelines 7 are all engraved with numbers, and the upper end and the lower end of the same measuring pipeline 7 are engraved with the same numbers, so that the measurement and the collection can be convenient;
the oil supply pipeline 6 and the measuring pipeline 7 are both flexible pipelines;
the front ends of the tops of the two vertical frames of the stand frame III3 are respectively provided with a resistance-reducing protection plate 5; the tail end of the rack III3 is provided with a turbulent flow resistance reducing plate 8; the resistance-reducing protection plate 5 is a wedge-shaped block, the tip end of the wedge-shaped block faces the incoming flow direction of airflow and is used for reducing the airflow resistance, and meanwhile, an oil supply pipeline 6, a measuring pipeline 7 and an ignition device 11 positioned at the bottom of an engine test piece 10 are protected and isolated from the airflow; the turbulence drag reduction plate 8 is a wedge-shaped block, and the tip of the wedge-shaped block faces back to the incoming flow direction of the air flow and is used for performing turbulence drag reduction on the air flow passing through the rack assembly and the engine test piece 10 and reducing the air flow resistance of the whole rack structure.
The design process of the bench structure is as follows:
the method comprises the following steps that 1, full estimation is carried out according to the structure and the test state of an engine test piece 10 for carrying out a free jet test, a design model of a rack structure is preliminarily given, namely, the composition scheme of a rack assembly is selected, and the sizes of a drag reduction plate 4, a drag reduction protection plate 5 and a turbulent flow drag reduction plate 8 are determined;
step 2, designing the rigidity and the strength of the composition scheme of the rack assembly selected in the step 1;
and 4, after diversified analysis and demonstration such as convenience, model adaptability, cost and the like are carried out on the composition scheme of the rack assembly selected in the step 1, the design of the rack structure is completed.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A bench structure suitable for ramjet free jet test, comprising: the device comprises a rack assembly, a resistance reducing and pressure reducing plate (4), a resistance reducing and protecting plate (5), an oil supply pipeline (6), a measuring pipeline (7), a turbulent flow resistance reducing plate (8) and a base;
the rack assembly consists of more than one rack; more than one rack is linearly distributed and fixed on the base, and a resistance-reducing pressure-reducing plate (4) is respectively connected between two adjacent racks; the rack positioned at the foremost end is a first rack, and the rack positioned at the rearmost end is a tail rack; the front end of the first rack is processed into a wedge structure, and the tip of the wedge structure faces the incoming flow direction of the airflow;
an engine test piece (10) to be tested is supported on the bench component;
an oil supply pipeline (6) and a measuring pipeline (7) are arranged in the tail rack, and an oil inlet of the oil supply pipeline (6) is positioned at the bottom of the tail rack and is connected with an oil source of the test bed; an oil outlet of the oil supply pipeline (6) is positioned at the top of the tail stand and is connected with an oil inlet pipeline of the engine test piece (10); the inlet of the measuring pipeline (7) is positioned at the top of the tail stand and is connected with a pressure measuring nozzle of the shell of the engine test piece (10); the outlet of the measuring pipeline (7) is positioned at the bottom of the tail rack and is connected with a measuring system of the test bed;
the oil supply pipeline (6) and the measuring pipeline (7) are both flexible pipelines;
more than one drag reduction protection plate (5) is arranged at the front end of the top of the tail rack; the tail end of the tail rack is provided with a turbulent flow resistance reducing plate (8); the resistance-reducing protection plate (5) is a wedge-shaped block, the tip end of the wedge-shaped block faces the incoming flow direction of airflow and is used for reducing the airflow resistance, and meanwhile, an oil supply pipeline (6), a measuring pipeline (7) and an ignition device (11) located at the bottom of an engine test piece (10) are protected and isolated from the airflow; the turbulence drag reduction plate (8) is a wedge-shaped block, and the tip of the wedge-shaped block faces back to the incoming flow direction of the air flow and is used for performing turbulence drag reduction on the air flow passing through the rack assembly and the engine test piece (10).
2. The bench structure of claim 1, wherein the base of more than one bench of the bench assembly is provided with more than two triangular reinforcing ribs.
3. The rack structure suitable for the ramjet engine free jet test of claim 1, wherein the first rack is made of stainless steel and the rest of the racks are made of Q235 carbon steel.
4. The bench structure suitable for ramjet engine free jet test of claim 1, wherein the angle of the wedge structure of the primary bench is 30 ° to 35 °.
5. The rack structure suitable for the free jet test of the ramjet engine as claimed in claim 1, wherein two half snap rings are fixed on the top of the primary rack, and more than two radial holes are uniformly distributed on each half snap ring;
the tops of the other racks are fixed with lower half snap rings;
an engine test piece (10) to be tested is supported in the two half snap rings of the first rack and the lower half snap rings of the other racks;
an engine test piece (10) is connected with the semi-clamping ring through a radial sunk screw (12), so that the connection between the engine test piece (10) and the first rack is realized; and upper half clamping rings which correspond to the lower half clamping rings one by one are respectively sleeved on the engine test pieces (10), each upper half clamping ring is in butt joint with the corresponding lower half clamping ring and is connected into a clamping ring (9) through a bolt, and the connection of other racks and the engine test pieces (10) is realized.
6. A bench structure adapted for ramjet free jet testing according to claim 5, characterized in that said snap ring (9) is made of stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010504651.XA CN111811823A (en) | 2020-06-05 | 2020-06-05 | Rack construction suitable for ramjet engine free jet test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010504651.XA CN111811823A (en) | 2020-06-05 | 2020-06-05 | Rack construction suitable for ramjet engine free jet test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111811823A true CN111811823A (en) | 2020-10-23 |
Family
ID=72844646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010504651.XA Pending CN111811823A (en) | 2020-06-05 | 2020-06-05 | Rack construction suitable for ramjet engine free jet test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111811823A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0683385A1 (en) * | 1994-05-18 | 1995-11-22 | AEROSPATIALE Société Nationale Industrielle | Procedure and device for estimating the thrust of a ramjet |
| US6058846A (en) * | 1998-06-03 | 2000-05-09 | Lockhead Martin Corporation | Rocket and ramjet powered hypersonic stealth missile having alterable radar cross section |
| CN101941522A (en) * | 2010-09-13 | 2011-01-12 | 朱晓义 | Flying device |
| CN103940574A (en) * | 2013-09-30 | 2014-07-23 | 中国人民解放军国防科学技术大学 | Cooling device in free jet flow test cabin |
| CN105043625A (en) * | 2015-06-29 | 2015-11-11 | 西安航天动力测控技术研究所 | Thrust measuring device applied to solid propellant ramjet free-jet test |
| US20160057873A1 (en) * | 2014-08-22 | 2016-02-25 | Rolls-Royce Plc | Earthing arrangement for electrical panel |
| CN105752313A (en) * | 2016-05-10 | 2016-07-13 | 朱晓义 | Aircraft |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
| CN110044570A (en) * | 2019-04-16 | 2019-07-23 | 沈阳航空航天大学 | A kind of body of revolution fuselage surveys compacting and tests the error correcting method that pneumatically trembles |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
-
2020
- 2020-06-05 CN CN202010504651.XA patent/CN111811823A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0683385A1 (en) * | 1994-05-18 | 1995-11-22 | AEROSPATIALE Société Nationale Industrielle | Procedure and device for estimating the thrust of a ramjet |
| US6058846A (en) * | 1998-06-03 | 2000-05-09 | Lockhead Martin Corporation | Rocket and ramjet powered hypersonic stealth missile having alterable radar cross section |
| CN101941522A (en) * | 2010-09-13 | 2011-01-12 | 朱晓义 | Flying device |
| CN103940574A (en) * | 2013-09-30 | 2014-07-23 | 中国人民解放军国防科学技术大学 | Cooling device in free jet flow test cabin |
| US20160057873A1 (en) * | 2014-08-22 | 2016-02-25 | Rolls-Royce Plc | Earthing arrangement for electrical panel |
| CN105043625A (en) * | 2015-06-29 | 2015-11-11 | 西安航天动力测控技术研究所 | Thrust measuring device applied to solid propellant ramjet free-jet test |
| CN105752313A (en) * | 2016-05-10 | 2016-07-13 | 朱晓义 | Aircraft |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
| CN110044570A (en) * | 2019-04-16 | 2019-07-23 | 沈阳航空航天大学 | A kind of body of revolution fuselage surveys compacting and tests the error correcting method that pneumatically trembles |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
Non-Patent Citations (1)
| Title |
|---|
| 张京华 等: "一种内嵌火箭的冲压组合发动机性能分析", 《战术导弹技术》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8152094B2 (en) | Engine mounting apparatus | |
| Mee et al. | Three-component force balance for flows of millisecond duration | |
| CN111795828B (en) | Horizontal simulation launch test device and method | |
| CN109443788A (en) | A kind of Used For Turbojet Engine Test Bench system | |
| CN203011609U (en) | Flow-field pressure detecting device used for supersonic-velocity wind tunnel | |
| CN111811823A (en) | Rack construction suitable for ramjet engine free jet test | |
| CN103407579B (en) | A kind of major diameter airframe test loads fixture | |
| CN202330029U (en) | Multi-channel rigid axle suspension test bench | |
| CN106768800A (en) | A kind of model supporting device for multiple aircraft formation wind tunnel test | |
| CN210802752U (en) | Supersonic engine test bench air inlet thrust measuring device | |
| CN115560989B (en) | Integrated platform for high-altitude simulation test of aero-engine | |
| CN207797940U (en) | A kind of measuring device of monitoring coal mine tunnel top board displacement | |
| CN113945385B (en) | Model system for jet engine and air inlet channel ground bench combined test | |
| CN112903276A (en) | Open turbine blade test equipment | |
| CN112179668A (en) | Thermal state performance test protection device for gas turbine engine component | |
| CN205905758U (en) | Bracket component of engine | |
| CN215413430U (en) | Thrust transmission structure suitable for 10-ton supersonic rocket sledge interstage | |
| CN211235301U (en) | Positive internal pressure test tool for heat pipe | |
| Gkatzogiannis et al. | Simulation of Welding Residual Stresses in Large Structures–First Results of Thermal Analyses | |
| CN115855514B (en) | Double-bending special-shaped variable cross-section air inlet test device for vortex paddle power high-altitude bench test | |
| CN218765734U (en) | Helicopter aerogun ground recoil test bench and system | |
| CN115655024A (en) | Hyperstatic multipoint support combined static test system for multi-hanging missile | |
| CN111318847B (en) | Aeroengine experiment pulley and welding process | |
| Harrison | Active flow control of a boundary layer ingesting serpentine diffuser | |
| CN112834227A (en) | Exhaust system of single-cylinder diesel engine simulation complete machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20201023 |
|
| WD01 | Invention patent application deemed withdrawn after publication |