CN105022042A - Terminal grating for RCS test of aeroengine exhausting system and method of terminal grating - Google Patents
Terminal grating for RCS test of aeroengine exhausting system and method of terminal grating Download PDFInfo
- Publication number
- CN105022042A CN105022042A CN201510378478.2A CN201510378478A CN105022042A CN 105022042 A CN105022042 A CN 105022042A CN 201510378478 A CN201510378478 A CN 201510378478A CN 105022042 A CN105022042 A CN 105022042A
- Authority
- CN
- China
- Prior art keywords
- test
- plate
- exhaust system
- radial
- terminal
- 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.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/41—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using analysis of echo signal for target characterisation; Target signature; Target cross-section
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a terminal grating for RCS test of an aeroengine exhausting system and a method of the terminal grating. The terminal grating is used to simulate influence of a turbine blade structure on the engine exhausting system, and carry out RCS test on the exhausting system. The terminal grating is composed of radial insertion plates, circumferential insertion plates and a positioning and supporting circular ring. The terminal grating is placed in the front portion of a support plate, and tightly cooperates with the surface of an annular mixing chamber. The terminal grating for RCS test of the exhausting system is simple in structure and convenient to install, is stably mounted at the terminal of an object to be tested, reduces the turbine level of the object to be tested, and can more effectively simulate the influence of the internal turbine blade structure of the exhausting system on test; the engine exhausting system with the terminal grating serves as a test piece and mounted in a weak-scattering casing, the weak-scattering casing is placed on a rotary table of a darkroom, and test is carried out by testing the darkroom; and thus, a result of RCS test of the exhausting system is closer to that of test for the exhausting system when the engine is in an installing state.
Description
Technical field
The present invention relates to Radar Target Scatter technical field of measurement and test, specifically, relate to terminal grid and the method for a kind of aeromotor exhaust system RCS test.
Background technology
The Stealth Fighter of target depends primarily on the size of its RCS, RCS is a very complicated physical quantity, it is relevant with physical parameter with the geometric parameter of target, again with the relating to parameters of incident radar wave, simultaneously also relevant relative to radar attitude angle with target.
Cavity body structure is typical strong scattering source, and this structure is very common on operational aircraft.As the structure such as jet pipe of the passenger cabin of aircraft, air intake duct, exhaust system, the RCS of these structures to aircraft has very large contribution.How accurately to obtain the RCS of these cavity body structures, have direct impact to the RCS test of aircraft and the employing of stealthy measure.The research method of target radar scattering cross-section mainly comprises theoretical analysis and measuring technology.Although electromagnetic theory has its integrality, can analyze typical scattering mechanism, for the target with complex appearance, utilize existing technological means to be difficult to calculate its RCS, therefore measuring technology is means effectively, fast and accurately.
Aeromotor exhaust system has extremely complicated inner structure, as the flame holder of after-burner, injection loop, support plate and lobed mixer etc., adopts the method for numerical simulation to be difficult to obtain the RCS with the exhaust system of above-mentioned labyrinth.Therefore, the RCS for accurately obtaining exhaust system is necessary to adopt experimental test procedures.From the viewpoint of experiment, it is extremely difficult for adopting current technology to carry out system test to aeromotor.On the one hand, domestic rarely have laboratory can carry out RCS test to large-sized cavity.On the other hand, system test there is no need for the impact of analysis component RCS." Radar Cross-sectionMeasurements of a Full-Scale Aircraft Duct/Engine Structure " (IEEETransactions on Antennas and Propagation, VoL.54, NO.8, Page2437,2066) during the RCS of airplane intake tests, describe a kind of end device for the test of outfield RCS cavity, this device is that a circular metal is dull and stereotyped, this metal plate structure is simple, easy to assembly.But test data can be caused bigger than normal than True Data.At " Electromagnetic Scattering Characteristics of Serpentine Inlet " (aviation journal, Vol.28, No.6, page1296-13012007) in, describe a kind of end device of simulating air intake port compressor blade, this device can the installation state of more real simulated engine than the end device of metal plate, and test result is truer.But because the structure containing this kind of complexity of compressor blade in this device can cause difficulty of processing and cost to increase, and applicability reduces.Some experiment is that the inner structure of capsule components has been done a large amount of simplify processes, as reduced the blade progression of test terminal.Above-mentioned end device and method of testing are all the RCS test experiments for aeromotor air intake duct.Although exhaust system and gas handling system all belong to typical cavity body structure, it is more complicated that exhaust system compares gas handling system inner structure, and comparatively how a lot of fan blade is for the turbo blade quantity of inflow point.Be difficult to adopt above-mentioned two kinds of typical end devices in reality test.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes terminal grid and the method for a kind of aeromotor exhaust system RCS test.
The technical solution adopted for the present invention to solve the technical problems is: comprise radial plate, circumference plate, positioning supports annulus, engine exhaust system, engine exhaust system is by restraining expanding nozzle, thermoscreen, support plate, flame holder, ring-like mixing chamber, center cone forms, it is characterized in that: described circumferential plate comprises all lower portion plates, circumference middle part plate, circumference top plate, radial plate, all lower portion plates, circumference middle part plate, circumference top plate and positioning supports annulus compositing terminal grid, terminal grid is positioned at a prelaminar part, and contact with center cone, formed with ring-like mixing chamber surface and closely cooperate, terminal grid Center-to-Center is bored, ring-like mixing chamber, convergence expanding nozzle is coaxially installed, the both ends of described radial plate and the centre of radial plate have narrow slit, and slit width is 2mm, the degree of depth of cracking is 0.8 ~ 0.9 times of himself width, adjacent radial plate distance d< λ
min/ 4, wherein λ
minfor minimal wave length, the radial distance centered by the length of radial plate between poppet surface and ring-like mixing chamber inside surface, the thickness of radial plate, circumferential plate is respectively 2mm.
The terminal grid utilizing described aeromotor exhaust system RCS to test carries out a method of testing, and it is characterized in that comprising the following steps:
Step 1. calculates the length of radial plate, according to the radial plate required for this group data creating according to the inside radius of the ring-like mixing chamber of tested exhaust system, the radiuscope of center cone;
Step 2. calculates the minimum wavelength λ in test according to test radar wave frequency meter
min, the minimum wavelength λ in test
minfor 30mm, calculate the quantity of maximum radial plate required in this test according to minimum wavelength;
Step 3. makes circumferential plate according to the physical dimension of radial plate;
Radial plate coordinates with circumferential plate fixing compact by step 4., increase according to actual test wavelength or reduce the quantity of radial plate, adjust radial plate, make the interval of two adjacent radial plates be less than 1/4th of test wavelength, and carry out combination with positioning supports annulus and be mounted to terminal grid;
The terminal grid combined is arranged on prelaminar part, i.e. an exhaust system air inlet incoming flow position of test exhaust system by step 5., and terminal grid closely cooperates with surperficial formation of ring-like mixing chamber;
Engine exhaust system with terminal grid is installed as test block and is placed in weak scattering housing by step 6., and is placed in darkroom by weak scattering housing turntable is tested;
Step 7. proofreads analyzing test data.
Beneficial effect
The terminal grid that a kind of aeromotor exhaust system RCS that the present invention proposes tests and method, adopt terminal grid simulation turbine blade arrangement on the impact of engine exhaust system, and test for engine system RCS.Terminal grid is made up of radial plate, circumferential plate and positioning supports annulus, and terminal grid is positioned at prelaminar part of engine exhaust system, and contact with center cone, closely cooperates with surperficial formation of ring-like mixing chamber.The terminal cell structure that engine exhaust system RCS tests is simple, it is convenient to install, firmly can be arranged on the end of test object, greatly reduce the progression of the turbine of testee, compare use terminal metal flat board measurement model can better the structure such as simulated exhaust internal system turbo blade on the impact of test; Engine exhaust system with terminal grid is installed as test block and is placed in weak scattering housing, and weak scattering housing is placed in darkroom turntable is tested; Exhaust system RCS test is closer to exhaust system test result during engine installation state.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, the terminal grid of a kind of aeromotor exhaust system RCS test of the present invention and method are described in further detail.
Fig. 1 is terminal grid of the present invention and aeromotor exhaust system scheme of installation.
Fig. 2 is the terminal cell structure schematic diagram that engine exhaust system RCS of the present invention tests.
Fig. 3 is radial plate front view of the present invention.
Fig. 4 is radial plate left view of the present invention.
In figure:
1. ring-like mixing chamber 11. center cone of expanding nozzle 7. thermoscreen 8. support plate 9. flame holder 10. restrained by positioning supports annulus 2. weeks radial plates 6. of lower portion plate 3. circumference middle part plate 4. circumferential top plate 5.
Embodiment
The present embodiment is terminal grid and the method for a kind of aeromotor exhaust system RCS test.
Consult Fig. 1 ~ Fig. 4, the terminal grid that in the present embodiment, engine exhaust system RCS tests is made up of radial plate, circumferential plate, positioning supports annulus and engine exhaust system; Wherein, circumferential plate comprises all lower portion plates 2, circumference middle part plate 3, circumferential top plate 4; Positioning supports annulus 1 and all lower portion plates 2, circumference middle part plate 3, circumferential top plate 4 closely cooperate compositing terminal grid.Engine exhaust system by restraining expanding nozzle 6, thermoscreen 7, support plate 8, flame holder 9, ring-like mixing chamber 10, center cone 11 form; It is anterior that terminal grid is arranged on support plate 8, and contact with center cone 11, formed closely cooperate with ring-like mixing chamber 10 surface.Terminal grid Center-to-Center cone 11, ring-like mixing chamber 10, convergence expanding nozzle 6 are coaxially installed.Positioning supports annulus 1, all lower portion plates 2, circumference middle part plate 3, circumferential top plate 4, radial plate 5 all adopt the metal material identical with test cavity.
In the present embodiment, the length W of radial plate 5 is calculated according to center cone 11 radius of engine exhaust system, ring-like mixing chamber 10 inside radius, be that to have the degree of depth be W1 at W2 place in radial plate two ends length distance, width is the narrow slit of H, the centre of radial plate has identical narrow slit, and the degree of depth of cracking is 0.8 ~ 0.9 times of himself width; Wherein, W is 140mm, W1 be 40mm, W2 be 5mm, W3 be 69mm, L1 be 50mm, H is 2mm; Positioning supports annulus 1 radius is 295mm, thickness is 2mm, length is 140mm.According to the structure of positioning supports annulus 1 and radial plate 5, the radius size of all lower portion plates 2, circumference middle part plate 3, circumferential top plate 4 can be determined, all lower portion plates are 300mm, circumference middle part plate is 365mm, circumferential top plate is 430mm, and the thickness of three circumferential plates is 2mm.Radial distance centered by the length of radial plate between poppet surface and ring-like mixing chamber inside surface, the thickness of radial plate, circumferential plate is respectively 2mm.According to incident radar wave wavelength, calculate assemblage gap, adjacent radial plate distance d< λ
min/ 4, wherein λ
minfor minimal wave length, the interval of two adjacent radial plates is no more than 1/4th of test wavelength.Getting incident wavelength in the present embodiment is 50mm, and the quantity calculating required radial plate 5 is as requested 240.
Engine exhaust system with terminal grid is installed as test block and is placed in weak scattering housing, and weak scattering housing is placed in darkroom turntable is tested.
Based on the terminal grid that aeromotor exhaust system RCS tests, the present embodiment also proposes a kind of method that terminal grid utilizing aeromotor exhaust system RCS to test carries out testing, and it comprises the following steps:
Step one, calculate the length of radial plate according to the inside radius of the ring-like mixing chamber of tested exhaust system and the radiuscope of center cone, the radial plate required for this group data creating and positioning supports annulus;
Step 2, the minimum wavelength λ calculated according to test radar wave frequency meter in test
min, the minimum wavelength λ in test
minfor 30mm, calculate the quantity of maximum radial plate required in this test according to minimum wavelength;
Step 3, make all lower portion plates, circumferential top plate and circumferential top plate according to the physical dimension of radial plate;
Step 4, radial plate and all lower portion plates, circumference middle part plate and circumferential top plate combined and installs, adjust radial plate, ensure that the interval between adjacent radial plate is less than 1/4th of test wavelength, radial plate, all lower portion plates, circumference middle part plate, circumferential top plate and positioning supports annulus are combined into terminal grid;
Step 5, the terminal grid combined is arranged on a prelaminar part of test exhaust system, is exhaust system air inlet incoming flow position, terminal grid contact with center cone, and surperficial formation of ring-like mixing chamber closely cooperate;
Step 6, the engine exhaust system with terminal grid installed as test block be placed in weak scattering housing, and weak scattering housing is placed in darkroom turntable is tested;
Step 7, check and correction analyzing test data.
Claims (2)
1. the terminal grid of an aeromotor exhaust system RCS test, comprise radial plate, circumference plate, positioning supports annulus, engine exhaust system, engine exhaust system is by restraining expanding nozzle, thermoscreen, support plate, flame holder, ring-like mixing chamber, center cone forms, it is characterized in that: described circumferential plate comprises all lower portion plates, circumference middle part plate, circumference top plate, radial plate, all lower portion plates, circumference middle part plate, circumference top plate and positioning supports annulus compositing terminal grid, terminal grid is positioned at a prelaminar part, and contact with center cone, formed with ring-like mixing chamber surface and closely cooperate, terminal grid Center-to-Center is bored, ring-like mixing chamber, convergence expanding nozzle is coaxially installed, the both ends of described radial plate and the centre of radial plate have narrow slit, and slit width is 2mm, the degree of depth of cracking is 0.8 ~ 0.9 times of himself width, adjacent radial plate distance d< λ
min/ 4, wherein λ
minfor minimal wave length, the radial distance centered by the length of radial plate between poppet surface and ring-like mixing chamber inside surface, the thickness of radial plate, circumferential plate is respectively 2mm.
2. the terminal grid utilizing the aeromotor exhaust system RCS described in claim 1 to test carries out a method of testing, and it is characterized in that comprising the following steps:
Step 1. calculates the length of radial plate, according to the radial plate required for this group data creating according to the inside radius of the ring-like mixing chamber of tested exhaust system, the radiuscope of center cone;
Step 2. calculates the minimum wavelength λ in test according to test radar wave frequency meter
min, the minimum wavelength λ in test
minfor 30mm, calculate the quantity of maximum radial plate required in this test according to minimum wavelength;
Step 3. makes circumferential plate according to the physical dimension of radial plate;
Radial plate coordinates with circumferential plate fixing compact by step 4., increase according to actual test wavelength or reduce the quantity of radial plate, adjust radial plate, make the interval of two adjacent radial plates be less than 1/4th of test wavelength, and carry out combination with positioning supports annulus and be mounted to terminal grid;
The terminal grid combined is arranged on prelaminar part, i.e. an exhaust system air inlet incoming flow position of test exhaust system by step 5., and terminal grid closely cooperates with surperficial formation of ring-like mixing chamber;
Engine exhaust system with terminal grid is installed as test block and is placed in weak scattering housing by step 6., and is placed in darkroom by weak scattering housing turntable is tested;
Step 7. proofreads analyzing test data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510378478.2A CN105022042B (en) | 2015-07-01 | 2015-07-01 | A kind of the terminal grid and method of aero-engine gas extraction system RCS tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510378478.2A CN105022042B (en) | 2015-07-01 | 2015-07-01 | A kind of the terminal grid and method of aero-engine gas extraction system RCS tests |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105022042A true CN105022042A (en) | 2015-11-04 |
| CN105022042B CN105022042B (en) | 2018-01-26 |
Family
ID=54412146
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510378478.2A Expired - Fee Related CN105022042B (en) | 2015-07-01 | 2015-07-01 | A kind of the terminal grid and method of aero-engine gas extraction system RCS tests |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105022042B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109613502A (en) * | 2018-12-10 | 2019-04-12 | 中国航发四川燃气涡轮研究院 | It is a kind of for assembling the low scattering shell of two-dimensional nozzle engine |
| CN113418938A (en) * | 2021-06-19 | 2021-09-21 | 西北工业大学 | Device and method for comparison test of radar absorbing material of aircraft engine fan support plate |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6252541B1 (en) * | 1994-07-11 | 2001-06-26 | Mcdonnell Douglas Corporation | Low RCS test mounts |
| CN101306725A (en) * | 2008-07-12 | 2008-11-19 | 张周卫 | Spacing stealth flight process |
| CN102926888A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Stealth exhaust system |
| CN102991669A (en) * | 2012-12-12 | 2013-03-27 | 北京理工大学 | Aircraft fluidic thrust vector control system |
-
2015
- 2015-07-01 CN CN201510378478.2A patent/CN105022042B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6252541B1 (en) * | 1994-07-11 | 2001-06-26 | Mcdonnell Douglas Corporation | Low RCS test mounts |
| CN101306725A (en) * | 2008-07-12 | 2008-11-19 | 张周卫 | Spacing stealth flight process |
| CN102926888A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Stealth exhaust system |
| CN102991669A (en) * | 2012-12-12 | 2013-03-27 | 北京理工大学 | Aircraft fluidic thrust vector control system |
Non-Patent Citations (2)
| Title |
|---|
| 李岳锋 等: "不同出口形状S形喷管的RSC特性", 《航空动力学报》 * |
| 高翔 等: "出口形式对双S弯排气系统红外特性影响研究", 《红外与激光工程》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109613502A (en) * | 2018-12-10 | 2019-04-12 | 中国航发四川燃气涡轮研究院 | It is a kind of for assembling the low scattering shell of two-dimensional nozzle engine |
| CN109613502B (en) * | 2018-12-10 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Low-scattering shell for assembling binary nozzle engine |
| CN113418938A (en) * | 2021-06-19 | 2021-09-21 | 西北工业大学 | Device and method for comparison test of radar absorbing material of aircraft engine fan support plate |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105022042B (en) | 2018-01-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10093436B2 (en) | Wireless aircraft engine communication system | |
| CN105424369B (en) | A kind of aero-engine aerodynamic model exerciser | |
| CN111792061A (en) | Pneumatic thermal test device and method utilizing shock wave boundary layer interference | |
| CN105022042A (en) | Terminal grating for RCS test of aeroengine exhausting system and method of terminal grating | |
| CN105181317A (en) | Rudderpost heat sealing test device | |
| CN112268708A (en) | Axial flow turbine refined acoustic experimental device and experimental method | |
| Papamoschou et al. | Experiments on shielding of jet noise by airframe surfaces | |
| CN112577703A (en) | Arc wind tunnel variable angle flat plate narrow gap heat flow measurement test device | |
| CN110319999B (en) | System and method for developing turbulence screen honeycomb PIV optical test based on cascade wind tunnel | |
| CN112964448B (en) | Airflow mixer for plane blade grid high-altitude flow simulation device | |
| CN215115096U (en) | Arc wind tunnel variable angle flat plate narrow gap heat flow measurement test device | |
| McKinley et al. | Measurement of near-field and far-field noise from full scale high performance jet engines | |
| CN104916191B (en) | A kind of infrared measurement of temperature simulation device | |
| CN203519411U (en) | Multi-station rotary plate | |
| Hervy et al. | Improvement of an altitude test facility capability in glaciated icing conditions at DGA Aero-engine Testing | |
| Ricouard et al. | ROSAS wind tunnel test campaign dedicated to unconventional aircraft concepts study | |
| CN205749371U (en) | A kind of absorbing material row ripple rejection test device | |
| Boyle et al. | DGEN aeropropulsion research turbofan core/combustor-noise measurements: Experiment and modal structure at core-nozzle exit | |
| Plumblee et al. | Near Field Noise Analyses of Aircraft Propulsion Systems with Emphasis on Prediction Techniques for Jets | |
| RU158308U1 (en) | SIMULATOR OF NATURAL CONDITIONS OF OPERATION OF A GAS TURBINE ENGINE IN TESTS FOR ABSENCE OF AUTO OSCILLATIONS OF WORKING BLADES OF THE COMPRESSOR | |
| Kempaiah et al. | High-resolution turbofan intake flow characterization by automated stereoscopic-PIV in an industrial wind tunnel environment | |
| CN114295643B (en) | System and method for testing dynamic wave absorbing performance of interference material | |
| Zachos et al. | Flowfield Investigation of a Compressor Cascade at High Incidence—Part 1: Pneumatic Probe Measurements | |
| CN114076674B (en) | Acoustic measurement device and method suitable for blade grid rectangular pipeline outlet | |
| KR102419316B1 (en) | Member for simulating angle of attack, and direct connecting type test apparatus for supersonic engine using the member |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180126 Termination date: 20180701 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |