CN114001964A - Flying platform with large-span S-shaped bent air inlet and exhaust system - Google Patents
Flying platform with large-span S-shaped bent air inlet and exhaust system Download PDFInfo
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- CN114001964A CN114001964A CN202111289867.XA CN202111289867A CN114001964A CN 114001964 A CN114001964 A CN 114001964A CN 202111289867 A CN202111289867 A CN 202111289867A CN 114001964 A CN114001964 A CN 114001964A
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- 238000012360 testing method Methods 0.000 claims abstract description 86
- 238000002474 experimental method Methods 0.000 claims description 10
- 238000012546 transfer Methods 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 7
- 239000000446 fuel Substances 0.000 claims description 5
- 108010066278 cabin-4 Proteins 0.000 description 6
- 238000005452 bending Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- 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
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- 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—Optical investigation techniques, e.g. flow cytometry
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- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Engines (AREA)
Abstract
The utility model relates to an aeroengine test field, for a flight platform that contains curved exhaust system that advances of big span S, through the top of locating the aircraft organism with the test chamber, and locate the middle part of test chamber with experimental aeroengine, and set up the curved intake duct of S and the curved exhaust system that links to each other with experimental aeroengine in the test chamber, can guarantee under the condition that the aircraft structure does not change, satisfy experimental aeroengine 'S the curved air admission of big span S, exhaust system' S operational environment, can effectively accurately test experimental aeroengine for when carrying out flight test.
Description
Technical Field
The application belongs to the field of aero-engine tests, and particularly relates to a flight platform with a large-span S-shaped curved air inlet and exhaust system.
Background
The invention relates to a test device which needs to carry out various test works before the newly developed aero-engine is in service, and correspondingly needs to construct test equipment which accords with the running environment of the aero-engine for the aero-engine test.
The existing method for testing a newly developed aero-engine is to take down an originally-installed aero-engine and equip a newly developed aero-engine at the position of the originally-installed aero-engine to carry out a flight test; the existing flying platform, no matter the aircraft engine is installed in a wing-hung or embedded mode, cannot establish the technical conditions of the operation environment of the large-span S-bend inlet and exhaust system at the position of the original aircraft engine, is difficult to technically realize, and has low cost and low efficiency which are not measurable.
Therefore, how to more effectively construct a large-span S bending inlet and exhaust system for a newly-researched aircraft engine for flight test is a problem to be solved.
Disclosure of Invention
The application aims to provide a flight platform with a large-span S-shaped curved inlet and exhaust system, and aims to solve the problem that the large-span S-shaped curved inlet and exhaust system is difficult to construct for a newly-researched aircraft engine for flight test in the prior art is needed to be solved.
The technical scheme of the application is as follows: the utility model provides a contain curved inlet exhaust system ' S of big span S flight platform, includes aircraft organism, wing, former dress aeroengine, experimental aeroengine and test chamber of using, the top of aircraft organism is located to the test chamber, be equipped with bearing structure between test chamber and the aircraft organism, experimental middle part of locating the test chamber with aeroengine, experimental aeroengine can be internal with self power transfer to aircraft organism, the front end of test chamber is equipped with the S curved intake duct that communicates with experimental aeroengine ' S entry, the rear end is equipped with the S curved exhaust system that communicates with experimental aeroengine ' S export, experimental aeroengine is connected in the lower extreme of the curved intake duct of S and the curved exhaust system of S.
Preferably, the support structure comprises a fore support and an aft support, both connected between the aircraft body and the test cabin, the fore support and the aft support being arranged side by side along the length of the aircraft body.
Preferably, the front support is arranged below the S-shaped air inlet, the rear support is arranged below the aircraft engine for test, the rear support is internally hollow and internally communicated with the interior of the aircraft body and the interior of the aircraft engine for test, and the rear support is internally provided with a thrust transfer mechanism, a fuel transfer mechanism and a test cable assembly of the aircraft engine.
Preferably, the thrust transmission mechanism is used for transmitting power into the aircraft body and is matched with an original aero-engine to drive the aircraft to fly.
Preferably, the wings comprise a left side wing and a right side wing, and the original aero-engine comprises a left original aero-engine arranged on the left side wing and a right original aero-engine arranged on the right side wing.
Preferably, the wing comprises a left empennage and a right empennage, and the S-bend exhaust system is positioned in the middle of the left empennage and the rear empennage.
The utility model provides a contain curved air intake and exhaust system 'S of big span S flight platform, through locating the top of aircraft organism with the test chamber, and locate the middle part of test chamber with aeroengine for the experiment, and set up the curved intake duct of S and the curved exhaust system of S that links to each other with aeroengine for the experiment in the test chamber, can guarantee under the condition that aircraft structure does not change, satisfy the curved air intake of big span S of aeroengine for the experiment, exhaust system' S operational environment, can effectively accurately test aeroengine for the experiment when carrying out flight test.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
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 wing; 3. the right original aeroengine; 4. a test chamber; 5. a front support; 6. rear support; 7. s bending an air inlet channel; 8. an aircraft engine for testing; 9. s-bend exhaust system, 10, left empennage; 11. a right empennage; 12. a left side wing; 13. the left side is originally installed the aeroengine.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A flight platform with a large-span S-bend air inlet and exhaust system comprises an aircraft body 1, wings, an original aircraft engine, a test cabin 4 and a test aircraft engine 8. The aircraft body 1 is a main body mechanism of an aircraft, the wings comprise a main wing and a tail wing, and an original aeroengine is arranged on the main wing. Because the aeroengine 8 for the test needs the special S-bend air intake of large span, exhaust system operational environment, consequently locate aeroengine' S top with test chamber 4, be equipped with bearing structure between test chamber 4 and the aircraft organism 1, aeroengine 8 for the test locates the middle part of test chamber 4, aeroengine 8 for the test can be with self power transmission to aircraft organism 1 in, be equipped with the data detection system who detects test data in the test chamber 4, the front end of test chamber 4 is equipped with the S-bend intake duct 7 with the entry intercommunication of aeroengine 8 for the test, the rear end is equipped with the S-bend exhaust system 9 with the export intercommunication of aeroengine 8 for the test, aeroengine 8 for the test connects in the lower extreme of S-bend intake duct 7 and S-bend exhaust system 9.
When the test aero-engine 8 is used in cooperation with an airplane for flight test, the test cabin 4 has a small number of positions having a sufficient assembly space due to the large weight of the test cabin 4, and an S-bend intake and exhaust system of the test aero-engine 8 needs to be provided, and the test cabin 4 is disposed above the airplane body 1 to prevent the test cabin 4 from affecting an airflow field during airplane flight. The air on the upper portion of the aircraft body 1 enters an inlet of the test aero-engine 8 from the S-shaped air inlet 7, enters the test aero-engine 8 and then is supplied to the test aero-engine 8 to work, the air is discharged into the S-shaped exhaust system 9 through an exhaust outlet of the test aero-engine 8, when the test aero-engine 8 works, power is transmitted into the aircraft body 1 to drive the aircraft body 1 to fly, and 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, and simultaneously, the aircraft can be driven to carry out various test works in a flying state, the structure of the aircraft is not changed, and the performance test can be effectively carried out on the test aero-engine 8, namely a newly developed aero-engine. The tested data are transmitted to the interior of the aircraft body 1 and monitored and processed by related workers.
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 cabin 4, the front support 5 and the rear support 6 being arranged side by side along the length of the aircraft body 1. Support test chamber 4 through fore-stock 5 and back support 6, it is stable to be connected between aircraft and the test chamber 4, guarantees that aircraft and test chamber 4 can stabilize the cooperation when carrying out flight test.
Preferably, the front support 5 is arranged below the S-shaped air inlet 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 inside of the aircraft body 1 and the inside of the test aero-engine 8, and the thrust transfer mechanism, the fuel transfer mechanism and the test cable assembly of the aero-engine are arranged in the rear support 6.
Preceding support 5 and back support 6 front and back set up to guarantee to support stably to test chamber 4, fuel transmission mechanism to experimental 8 fuel feeding of aeroengine and guarantee its steady operation, through the thrust transmission mechanism in the back support 6 to the aircraft organism 1 inside experimental, test cable assembly is with experimental 8 data transfer of aeroengine to the aircraft organism 1 for the experiment that test chamber 4 in the test process gathered, accomplish the collection and the inspection of data.
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 test aero-engine is matched with an original aero-engine to drive the aircraft to fly. When the test aero-engine 8 works, the power of the left original aero-engine 13 or the right original aero-engine 3 can be properly reduced, and the normal flight of the airplane can be guaranteed.
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. Because the aero-engine 8 for testing is arranged on the airplane, the original aero-engine can be assembled on the main wings of the two airplanes, and the design of the airplane does not need to be changed completely, so that the test requirement of the newly developed aero-engine can be effectively met.
Preferably, the tail wings include a left side tail wing 10 and a right side tail wing 11, and the S-bend exhaust system 9 is located at a middle position between the left side tail wing 10 and the rear side tail wing. By adopting a double-empennage layout and arranging the S-bend exhaust system 9 between the two empennages, the test aero-engine 8 and the empennages can be prevented from interfering with each other.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within 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 (6)
1. The utility model provides a contain curved air intake and exhaust system' S of big span S flight platform, includes aircraft organism (1), wing, former aeroengine, experimental aeroengine (8) and test chamber (4) of using, its characterized in that: the top of aircraft organism (1) is located in test cabin (4), be equipped with bearing structure between test cabin (4) and aircraft organism (1), the middle part of test cabin (4) is located with aeroengine (8) to the experiment, aeroengine (8) can be with self power transmission to aircraft organism (1) in the experiment, the front end of test cabin (4) is equipped with S curved intake duct (7) that communicates with the entry of aeroengine (8) for the experiment, the rear end is equipped with S curved exhaust system (9) with the export intercommunication of aeroengine (8) for the experiment, aeroengine (8) are connected in the lower extreme of S curved intake duct (7) and S curved exhaust system (9) for the experiment.
2. The flying platform comprising a large span S bend inlet and exhaust system according to claim 1, wherein: the supporting 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 airplane 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 airplane body (1).
3. The flying platform comprising a large span S bend inlet and outlet system according to claim 2, wherein: preceding support (5) are located the below of S curved intake duct (7), the below of experimental aeroengine (8) of using is located in back support (6), it is inside that back support (6) are inside hollow structure and its inside intercommunication in aircraft organism (1) and experimental aeroengine (8) of using, be equipped with aeroengine' S thrust transfer mechanism, fuel transfer mechanism, test cable assembly in back support (6).
4. The flying platform comprising a large span S bend inlet and outlet system according to claim 3, wherein: the thrust transmission mechanism is of a pipeline structure and is used for transmitting the power of the test aero-engine (8) to the plane body (1) and driving the plane to fly in cooperation with the original aero-engine.
5. The flying platform comprising a large span S bend inlet and exhaust system according to claim 1, wherein: the wing includes left side wing (12) and right side wing (2), former dress aeroengine is including locating left side former dress aeroengine (13) on left side wing (12), locating right side former dress aeroengine (3) on right side wing (2).
6. The flying platform comprising a large span S bend inlet and exhaust system according to claim 1, wherein: the wing comprises a left empennage (10) and a right empennage (11), and the S-shaped exhaust system (9) is positioned in the middle of the left empennage (10) and the rear empennage.
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 true CN114001964A (en) | 2022-02-01 |
| CN114001964B CN114001964B (en) | 2024-02-02 |
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| 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 |
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Citations (14)
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| GB1157478A (en) * | 1966-05-09 | 1969-07-09 | Gen Electric | Improvements in Simulated Jet Engine Model. |
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