CN114001964B - Flight table with large-span S-bend air inlet and exhaust system - Google Patents
Flight table with large-span S-bend air inlet and exhaust system Download PDFInfo
- Publication number
- CN114001964B CN114001964B CN202111289867.XA CN202111289867A CN114001964B CN 114001964 B CN114001964 B CN 114001964B CN 202111289867 A CN202111289867 A CN 202111289867A CN 114001964 B CN114001964 B CN 114001964B
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- test
- engine
- aero
- aircraft
- exhaust system
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- 238000012360 testing method Methods 0.000 claims abstract description 98
- 230000005540 biological transmission Effects 0.000 claims description 11
- 239000000446 fuel Substances 0.000 claims description 3
- 108010066278 cabin-4 Proteins 0.000 description 14
- 238000000034 method Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N15/00—Investigating characteristics of particles; Investigating permeability, pore-volume, or surface-area of porous materials
- G01N15/10—Investigating individual particles
- G01N15/14—Electro-optical investigation, e.g. flow cytometers
Abstract
The utility model relates to an aeroengine test field is a flight platform that contains curved air intake and exhaust system of large span S, through locating the top of aircraft organism with the test cabin to locate the middle part of test cabin with the aeroengine for the test, and set up the curved intake duct of S and the curved exhaust system of S that link to each other with the aeroengine for the test in the test cabin, can guarantee under the condition that the aircraft structure does not change, satisfy the running environment of the curved intake of large span S, exhaust system of aeroengine for the test, can test the aeroengine for the test effectively and accurately when carrying out flight test.
Description
Technical Field
The application belongs to the field of aeroengine tests, and particularly relates to a flight table with a large-span S-bend air inlet and exhaust system.
Background
Before the aeroengine which is newly developed is in service, various test works need to be carried out, and test equipment which accords with the operation environment of the aeroengine needs to be correspondingly constructed for the aeroengine test.
The existing method for testing the newly developed aero-engine is to take off an original aero-engine and assemble a newly developed aero-engine at the position to develop a flight test; the existing flying platform is not capable of constructing technical conditions of a large-span S-bend air inlet and exhaust system operation environment at the original aeroengine position no matter in a wing hanging type or embedded type, and is difficult to realize technically and not measurable in cost and efficiency.
Therefore, how to construct a large-span S-bend air inlet and exhaust system for a newly-developed aeroengine for flight test more effectively is a problem to be solved.
Disclosure of Invention
The purpose of the application is to provide a flight table containing a large-span S-bend air inlet and exhaust system, so as to solve the problem that the large-span S-bend air inlet and exhaust system is difficult to construct for a newly-developed aeroengine for flight test in the prior art.
The technical scheme of the application is as follows: the utility model provides a contain flight platform of curved air intake and exhaust system of large span S, includes aircraft organism, wing, former aeroengine, experimental aeroengine and test cabin, the top of aircraft organism is located in the test cabin, be equipped with bearing structure between test cabin and the aircraft organism, experimental aeroengine locates the middle part in test cabin for the experiment, experimental aeroengine can be with self power transmission to the aircraft organism in, the front end in test cabin be equipped with experimental aeroengine ' S the curved intake duct of S of entry intercommunication, the rear end be equipped with experimental aeroengine ' S the curved exhaust system of S of export intercommunication, experimental aeroengine is connected in the curved intake duct of S and the curved exhaust system ' S of S lower extreme.
Preferably, the support structure comprises a front support and a rear support, both of which are connected between the aircraft body and the test chamber, the front support and the rear support being arranged side by side along the length direction of the aircraft body.
Preferably, the front support is arranged below the S-bend air inlet channel, the rear support is arranged below the test aero-engine, the rear support is of a hollow structure and is internally communicated with the interior of the aircraft body and the test aero-engine, and the rear support is internally provided with a thrust transmission mechanism, a fuel transmission mechanism and a test cable assembly of the aero-engine.
Preferably, the thrust transmission mechanism is used for transmitting power into the aircraft body and driving the aircraft to fly in cooperation with the original aeroengine.
Preferably, the wings comprise a left wing and a right wing, and the original aeroengine comprises a left original aeroengine arranged on the left wing and a right original aeroengine arranged on the right wing.
Preferably, the wing comprises a left tail wing and a right tail wing, and the S-bend exhaust system is positioned at the middle position of the left tail wing and the rear tail wing.
The utility model provides a flight platform that contains curved air intake and exhaust system of large span S through locating the test cabin in the top of aircraft organism to locate the middle part in test cabin with the aeroengine for the test, and set up the curved intake duct of S and the curved exhaust system of S that link to each other with the aeroengine for the test in the test cabin, can guarantee under the condition that the aircraft structure does not change, satisfy the running environment of the curved intake of large span S, exhaust system of aeroengine for the test, can test the aeroengine for the test effectively accurately when carrying out flight test.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a schematic side view of the overall structure of the present application;
fig. 2 is a schematic front view of the overall structure of the present application.
1. An aircraft body; 2. a right side wing; 3. the right side is provided with an original aeroengine; 4. a test cabin; 5. a front support; 6. a rear support; 7. s bending an air inlet channel; 8. an aeroengine for test; 9. s-bend exhaust system, 10, left tail fin; 11. a right tail; 12. a left side wing; 13. the left side is provided with an original aeroengine.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
A flying platform with a large-span S-bend air inlet and exhaust system comprises an airplane body 1, wings, an original aeroengine, a test cabin 4 and an aeroengine 8 for test. The aircraft body 1 is a main body mechanism of an aircraft, the wings comprise a main wing and an empennage, and the original aeroengine is arranged on the main wing. Because the test aero-engine 8 needs special large-span S-bend air inlet and exhaust system operation environment, the test cabin 4 is arranged above the aero-engine, a supporting structure is arranged between the test cabin 4 and the aircraft body 1, the test aero-engine 8 is arranged in the middle of the test cabin 4, the test aero-engine 8 can transmit self power into the aircraft body 1, a data detection system for detecting test data is arranged in the test cabin 4, the front end of the test cabin 4 is provided with an S-bend air inlet channel 7 communicated with an inlet of the test aero-engine 8, the rear end of the test cabin is provided with an S-bend exhaust system 9 communicated with an outlet of the test aero-engine 8, and the test aero-engine 8 is connected to the lower ends of the S-bend air inlet channel 7 and the S-bend exhaust system 9.
When the test aero-engine 8 is matched with an aircraft for flight test, the test cabin 4 is arranged above the aircraft body 1 in order to prevent the test cabin 4 from influencing the airflow field when the aircraft is in flight, the test cabin 4 has a relatively large weight, so that the position with enough assembly space is relatively small, and an S-bend air inlet and outlet system of the test aero-engine 8 is required to be arranged. Air at the upper part of the aircraft body 1 enters an inlet of the test aeroengine 8 from the S-bend air inlet channel 7, enters the test aeroengine 8 and then works, and is discharged into the S-bend exhaust system 9 through an exhaust outlet of the test aeroengine 8, and when the test aeroengine 8 works, power is transmitted into the aircraft body 1 to drive the aircraft body 1 to fly, and the driving force can be measured. Because the upper part of the aircraft body 1 has enough space for the test aero-engine 8 to arrange the large-span S-bend air inlet channel 7 and the S-bend exhaust system 9, the aircraft can be driven to perform various test works in a flight state, and the structure of the aircraft is not changed, so that the performance test of the test aero-engine 8, namely, the brand-new developed aero-engine can be effectively performed. The tested data are transmitted to the interior of the aircraft body 1 for monitoring and processing by the relevant personnel.
Preferably, the support structure comprises a front support 5 and a rear support 6, both the front support 5 and the rear support 6 being connected between the aircraft body 1 and the test chamber 4, the front support 5 and the rear support 6 being arranged side by side along the length of the aircraft body 1. The front support 5 and the rear support 6 are used for supporting the test cabin 4, and the aircraft is stably connected with the test cabin 4, so that the aircraft and the test cabin 4 can be stably matched when a flight test is carried out.
Preferably, the front support 5 is arranged below the S-bend air inlet channel 7, the rear support 6 is arranged below the test aero-engine 8, the rear support 6 is of a hollow structure, the inside of the rear support 6 is communicated with the inside of the aircraft body 1 and the inside of the test aero-engine 8, and a thrust transmission mechanism, a fuel transmission mechanism and a test cable assembly of the aero-engine are arranged in the rear support 6.
The front support 5 and the rear support 6 are arranged front and back to ensure the stability of the support of the test cabin 4, the fuel oil transfer mechanism supplies oil to the test aero-engine 8 and ensures the stable work of the test aero-engine 8, the test aero-engine 8 data acquired by the test cabin 4 in the test process are transferred into the aircraft body 1 through the thrust transfer mechanism in the rear support 6, and the acquisition and the inspection of the data are completed.
Preferably, the thrust transmission mechanism is of a pipeline structure and is used for transmitting the power of the test aero-engine 8 into the aircraft body 1, and the thrust transmission mechanism is matched with the original aero-engine to drive the aircraft to fly. When the pilot aeroengine 8 is in operation, the power of the left-hand original aeroengine 13 or the right-hand original aeroengine 3 can be appropriately reduced to ensure normal flight of the aircraft.
Preferably, the main wing comprises a left wing 12 and a right wing 2, and the original aero-engine comprises a left original aero-engine 13 arranged on the left wing 12, and a right original aero-engine 3 arranged on the right wing 2. The aircraft engine 8 for test is arranged on the aircraft, so that the original aircraft engines can be assembled on the main wings of the two aircraft, and the design of the aircraft does not need to be changed at all, thereby effectively meeting the test requirements of the newly-developed aircraft engines.
Preferably, the tail comprises a left tail 10 and a right tail 11, and the S-bend exhaust system 9 is located at the middle position of the left tail 10 and the rear tail. By adopting a double-tail wing layout and arranging the S-bend exhaust system 9 between the two tail wings, the experimental aero-engine 8 and the tail wings can be mutually noninterfered.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. The utility model provides a flight platform that contains curved air intake and exhaust system of large span S, includes aircraft organism (1), wing, original aeroengine, experimental aeroengine (8) and test cabin (4), its characterized in that: the test cabin (4) is arranged above the aircraft body (1), a supporting structure is arranged between the test cabin (4) and the aircraft body (1), the test aero-engine (8) is arranged in the middle of the test cabin (4), the test aero-engine (8) can transmit self power into the aircraft body (1), the front end of the test cabin (4) is provided with an S-bend air inlet channel (7) communicated with an inlet of the test aero-engine (8), the rear end of the test cabin is provided with an S-bend air exhaust system (9) communicated with an outlet of the test aero-engine (8), and the test aero-engine (8) is connected to the lower ends of the S-bend air inlet channel (7) and the S-bend air exhaust system (9);
the support structure comprises a front support (5) and a rear support (6), wherein the front support (5) and the rear support (6) are connected between the aircraft body (1) and the test cabin (4), and the front support (5) and the rear support (6) are arranged side by side along the length direction of the aircraft body (1);
the front support (5) is arranged below the S-shaped air inlet channel (7), the rear support (6) is arranged below the test aero-engine (8), the rear support (6) is of a hollow structure and is internally communicated with the interior of the aircraft body (1) and the test aero-engine (8), and a thrust transmission mechanism, a fuel transmission mechanism and a test cable assembly of the aero-engine are arranged in the rear support (6).
2. The flying platform with a large span S-curve intake and exhaust system of claim 1, wherein: the thrust transmission mechanism is of a pipeline structure and is used for transmitting power of the experimental aero-engine (8) into the aircraft body (1) and driving the aircraft to fly in cooperation with the original aero-engine.
3. The flying platform with a large span S-curve intake and exhaust system of claim 1, wherein: the aircraft wing comprises a left side wing (12) and a right side wing (2), and the original aircraft engine comprises a left original aircraft engine (13) arranged on the left side wing (12) and a right original aircraft engine (3) arranged on the right side wing (2).
4. The flying platform with a large span S-curve intake and exhaust system of claim 1, wherein: the wing comprises a left tail wing (10) and a right tail wing (11), and the S-bend exhaust system (9) is positioned at the middle position of the left tail wing (10) and the rear tail wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111289867.XA CN114001964B (en) | 2021-11-02 | 2021-11-02 | Flight table with large-span S-bend air inlet and exhaust system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111289867.XA CN114001964B (en) | 2021-11-02 | 2021-11-02 | Flight table with large-span S-bend air inlet and exhaust system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114001964A CN114001964A (en) | 2022-02-01 |
| CN114001964B true CN114001964B (en) | 2024-02-02 |
Family
ID=79926589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111289867.XA Active CN114001964B (en) | 2021-11-02 | 2021-11-02 | Flight table with large-span S-bend air inlet and exhaust system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114001964B (en) |
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| JPH11152095A (en) * | 1997-11-20 | 1999-06-08 | Mitsubishi Heavy Ind Ltd | Aircraft testing plant |
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| CN105424369A (en) * | 2015-12-15 | 2016-03-23 | 中国燃气涡轮研究院 | Pneumatic model tester for aircraft engine |
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| US5396793A (en) * | 1993-09-17 | 1995-03-14 | United Technologies Corporation | Altitude gas turbine engine test cell |
| JPH11152095A (en) * | 1997-11-20 | 1999-06-08 | Mitsubishi Heavy Ind Ltd | Aircraft testing plant |
| JP2000313399A (en) * | 1999-04-30 | 2000-11-14 | Kawasaki Heavy Ind Ltd | Aircraft engine test facility |
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| Publication number | Publication date |
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| CN114001964A (en) | 2022-02-01 |
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