CN105021899A - Device and method for testing electromagnetic scattering of jet pipe cavity of aeroengine - Google Patents
Device and method for testing electromagnetic scattering of jet pipe cavity of aeroengine Download PDFInfo
- Publication number
- CN105021899A CN105021899A CN201510378479.7A CN201510378479A CN105021899A CN 105021899 A CN105021899 A CN 105021899A CN 201510378479 A CN201510378479 A CN 201510378479A CN 105021899 A CN105021899 A CN 105021899A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- test
- scattering
- proving installation
- support frame
- 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
Landscapes
- Testing Of Engines (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention discloses a device and method for testing electromagnetic scattering of a jet pipe cavity of an aeroengine. A device body is wrapped in a pointed-cone-shaped absorbing material to carry out electromagnetic scattering test on the jet pipe cavity, the pointed-cone-shaped absorbing material at the outer wall can absorb most radar waves, electromagnetic wave reflection at the outer wall of a jet pipe model can be effectively shielded during electromagnetic test, electromagnetic reflection at the metal outer wall of the jet pipe model is eliminated, reliable electromagnetic scattering data of the jet pipe cavity is obtained, and the test data can accurately reflect the electromagnetic scattering characteristic of the jet pipe cavity. The test device is simple in structure, low in processing difficulty, low in cost and convenient to operate, can be used repeatedly, and greatly reduces the cost of electromagnetic scattering test of the jet pipe cavity; the test method can be used to obtain accurate and reliable test data; and the test method and device have great significance in researches on electromagnetic scattering of the jet pipe cavity.
Description
Technical field
The present invention relates to aeromotor electromagnetism stealth technology field, specifically, relate to a kind of aeromotor jet pipe EM scattering of cavities proving installation and method of testing.
Background technology
5th generation fighter plane a key character exactly there is stealth capabilities, and aeromotor jet pipe is the backward stronger radar scattering source of aircraft as TV university cavity body structure, the aeromotor jet pipe of low radar scattering is adopted to have vital role to the stealth capabilities improving aircraft.The Electromagnetic Scattering Characteristics research of aeromotor jet pipe mainly adopts experimental technique, and its experimental result can instruct design and the improvement of aeromotor jet pipe.
From the documents and materials published both at home and abroad, also do not find about aeromotor jet pipe EM scattering of cavities proving installation and method, but have the electromagnetic scattering testing research data about air intake duct, air intake duct and jet pipe are TV university cavity body structure, identical on proving installation with method of testing." Radar Corss SectionModeling and Measurements of inlet and Cylinders with Skew Blades " (IEEE, 2006,54th volume the 10th phase, 2930-2939 page) in, adopt the method at the outside coated plane absorbing material of air intake duct test model supporting construction, reduce model external electromagnetic wave reflection; This method needs coated absorbing material again when each test, and the plane absorbing material adopted is limited to outside electromagnetic shielding effect." straight tube inclined cutout side turns the Electromagnetic Scattering Characteristics of round air intake duct and the experimental study of suppression technology " (aviation journal, 1999,20th volume the 3rd phase, 205 to 210 pages) in, adopt the reflection of electromagnetic wave slackening outside wall surface in the method for test air intake duct model outside surface stickup absorbing material, the same defect that there is shielding outside wall surface electromagnetic wave weak effect.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of aeromotor jet pipe EM scattering of cavities proving installation and method of testing, proving installation adopts coated pointed cone absorbing material in device body outside wall surface to carry out the electromagnetic scattering test of jet pipe cavity, effectively can shield the reflection of electromagnetic wave of jet pipe outside wall surface in electromagnetism test, obtain reliable jet pipe EM scattering of cavities data; Proving installation structure is simple, easy to operate, cost of manufacture is low.
The technical solution adopted for the present invention to solve the technical problems is: comprise support frame, upper frame, inhale ripple pointed cone, seamed edge inhales ripple pointed cone, corner angle inhale ripple pointed cone, ripple pointed cone is inhaled in spout face, device body, flat base, jet pipe model, support frame is fixed on flat base, upper frame is positioned at above support frame, upper frame is by some suction ripple pointed cones of inner frame and surface mount, seamed edge inhales ripple pointed cone, it is into a single integrated structure that corner angle inhale ripple sharp cone distal, support frame is into a single integrated structure by some suction ripple sharp cone distal of inner frame and surface mount, upper frame and support frame fasten the device body forming rectangular trapezium structure, device body leading section has spout, periphery is pasted some spout faces and is inhaled ripple pointed cone, plane absorbing material is pasted in flat base bottom surface, jet pipe model is positioned at device body, fix on the support frame.
Adopt described proving installation to carry out a method of testing for test engine jet pipe EM scattering of cavities, it is characterized in that comprising the following steps:
Engine jet pipe EM scattering of cavities proving installation is fixed on test table by step 1., and proving installation spout is facing to Radar Measurement System direction;
Step 2. opens Radar Measurement System, completes background radar scattering test;
Step 3. closes Radar Measurement System, engine jet pipe EM scattering of cavities proving installation is unloaded from test table, remove upper frame, ripple pointed cone inhaled in spout face, by fixing for the jet pipe model of test on the support frame, and upper frame and support frame fastened install;
The proving installation being provided with jet pipe model is steadily fixed on test table by step 4., and jet pipe model spout is consistent with device body spout, towards Radar Measurement System direction;
Step 5. opens Radar Measurement System, completes the test of jet pipe model radar scattering;
Step 6. closes Radar Measurement System, unloads proving installation from test table, Treatment Analysis test data.
Beneficial effect
The aeromotor jet pipe EM scattering of cavities proving installation that the present invention proposes and method of testing, electromagnetic scattering proving installation adopts coated sharp cone distal absorbing material in device body outside wall surface to carry out the electromagnetic scattering test of jet pipe cavity, the radar wave of the sharp cone distal absorbing material Absorbable rod overwhelming majority of outside wall surface, the reflection of electromagnetic wave of jet pipe model outside wall surface is effectively shielded in electromagnetism test, eliminate the ELECTROMAGNETIC REFLECTION of jet pipe model metal outside wall surface, obtain reliable jet pipe EM scattering of cavities data, test data reliably can reflect the Electromagnetic Scattering Characteristics of jet pipe cavity.Proving installation structure is simple, difficulty of processing is little, cost is low, simple operation, and reusable, greatly reduces jet pipe EM scattering of cavities testing cost; Method of testing can obtain accurately, reliable test data; Electromagnetic scattering proving installation and method of testing are studied significant to the electromagnetic scattering of jet pipe cavity.
Compared to metal material, the present invention adopts absorbing material to have low-down Electromagnetic Scattering Characteristics, when jet pipe model is placed in electromagnetic scattering proving installation, proving installation is except the nozzle position of device body leading section, all the other outside wall surface are all wrapped by sharp cone distal suction ripple material and block, radar wave is injected from nozzle position, tests the Electromagnetic Scattering Characteristics that the data obtained are approximately jet pipe cavity.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of aeromotor jet pipe EM scattering of cavities proving installation of the present invention and method of testing are described in further detail.
Fig. 1 is engine jet pipe EM scattering of cavities proving installation schematic diagram of the present invention.
Fig. 2 places jet pipe model position schematic diagram in proving installation of the present invention.
In figure:
1. support frame 2. upper frame 3. is inhaled ripple pointed cone 4. seamed edge and is inhaled ripple pointed cone 5. corner angle suction ripple pointed cone 6. spout face suction ripple pointed cone 7. device body 8. flat base 9. jet pipe model
Embodiment
The present embodiment is a kind of aeromotor jet pipe EM scattering of cavities proving installation and method of testing.
Consult Fig. 1, Fig. 2, engine jet pipe EM scattering of cavities proving installation, adopt and cover at proving installation body outer wall bread the electromagnetic scattering test that sharp cone distal absorbing material carries out jet pipe cavity, the radar wave of the sharp cone distal absorbing material Absorbable rod overwhelming majority of outside wall surface, the reflection of electromagnetic wave of jet pipe outside wall surface is effectively shielded in electromagnetism test, eliminate the ELECTROMAGNETIC REFLECTION in jet pipe metal outer wall face, obtain reliable jet pipe EM scattering of cavities data, test data reliably can reflect the Electromagnetic Scattering Characteristics of jet pipe cavity.
In the present embodiment, engine jet pipe EM scattering of cavities proving installation is made up of support frame 1, upper frame 2, suction ripple pointed cone 3, seamed edge suction ripple pointed cone 4, corner angle suction ripple pointed cone 5, spout face suction ripple pointed cone 6, device body 7, flat base 8, jet pipe model 9, support frame 1 is fixed on flat base 8, upper frame 2 is arranged on above support frame 1, upper frame 2 is by some suction ripple pointed cones 3 of inner frame and surface mount, seamed edge inhales ripple pointed cone 4, corner angle are inhaled ripple pointed cone 5 and are formed integrative-structure, support frame 1 forms integrative-structure with some suction ripple pointed cones 3 of surface mount, upper frame 2 and support frame 1 fasten the device body 7 forming rectangular trapezium structure, device body 7 leading section has spout, periphery is pasted some spout faces and is inhaled ripple pointed cone 6, plane absorbing material is pasted in flat base 8 bottom surface, jet pipe model 9 is positioned at device body 7, be fixed on support frame 1.Support frame 1 and upper frame 2 structure adopt wooden frame mortise-tenon joint to form.Sharp cone distal absorbing material has low-down Electromagnetic Scattering Characteristics, when jet pipe model 9 is placed in device body 7, except device body 7 leading section nozzle, remainder is all blocked by sharp cone distal absorbing material, radar wave is injected from spout, the data obtained in test are approximately the Electromagnetic Scattering Characteristics of jet pipe cavity, and test data accurately, reliably.
Based on above-mentioned engine jet pipe EM scattering of cavities proving installation, the present embodiment also proposes a kind of method of testing of carrying out test engine jet pipe EM scattering of cavities, and it comprises the following steps:
Step one, be fixedly mounted on test table by engine jet pipe EM scattering of cavities proving installation, proving installation spout faces Radar Measurement System direction;
Step 2, unlatching Radar Measurement System, complete background radar scattering test;
Step 3, closedown Radar Measurement System, engine jet pipe EM scattering of cavities proving installation is taken off from test table, remove upper frame 2, ripple pointed cone 6 is inhaled in spout face, the jet pipe model 9 of test is fixed on support frame 1, and upper frame 2 and support frame 1 are fastened installation;
Step 4, be steadily fixed on test table by the proving installation being provided with jet pipe model 9, jet pipe model spout is consistent with device body spout, towards Radar Measurement System direction;
Step 5, open Radar Measurement System, complete the radar scattering test of jet pipe model 9;
Step 6, closedown Radar Measurement System, unload proving installation from test table, Treatment Analysis test data.
Claims (2)
1. an aeromotor jet pipe EM scattering of cavities proving installation, it is characterized in that: comprise support frame, upper frame, inhale ripple pointed cone, seamed edge inhales ripple pointed cone, corner angle inhale ripple pointed cone, ripple pointed cone is inhaled in spout face, device body, flat base, jet pipe model, support frame is fixed on flat base, upper frame is positioned at above support frame, upper frame is by some suction ripple pointed cones of inner frame and surface mount, seamed edge inhales ripple pointed cone, it is into a single integrated structure that corner angle inhale ripple sharp cone distal, support frame is into a single integrated structure by some suction ripple sharp cone distal of inner frame and surface mount, upper frame and support frame fasten the device body forming rectangular trapezium structure, device body leading section has spout, periphery is pasted some spout faces and is inhaled ripple pointed cone, plane absorbing material is pasted in flat base bottom surface, jet pipe model is positioned at device body, fix on the support frame.
2. adopt proving installation described in claim 1 to carry out a method of testing for test engine jet pipe EM scattering of cavities, it is characterized in that comprising the following steps:
Engine jet pipe EM scattering of cavities proving installation is fixed on test table by step 1., and proving installation spout is facing to Radar Measurement System direction;
Step 2. opens Radar Measurement System, completes background radar scattering test;
Step 3. closes Radar Measurement System, engine jet pipe EM scattering of cavities proving installation is unloaded from test table, remove upper frame, ripple pointed cone inhaled in spout face, by fixing for the jet pipe model of test on the support frame, and upper frame and support frame fastened install;
The proving installation being provided with jet pipe model is steadily fixed on test table by step 4., and jet pipe model spout is consistent with device body spout, towards Radar Measurement System direction;
Step 5. opens Radar Measurement System, completes the test of jet pipe model radar scattering;
Step 6. closes Radar Measurement System, unloads proving installation from test table, Treatment Analysis test data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510378479.7A CN105021899B (en) | 2015-07-01 | 2015-07-01 | A kind of aero-engine jet pipe EM scattering of cavities test device and method of testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510378479.7A CN105021899B (en) | 2015-07-01 | 2015-07-01 | A kind of aero-engine jet pipe EM scattering of cavities test device and method of testing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105021899A true CN105021899A (en) | 2015-11-04 |
| CN105021899B CN105021899B (en) | 2018-01-09 |
Family
ID=54412013
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510378479.7A Expired - Fee Related CN105021899B (en) | 2015-07-01 | 2015-07-01 | A kind of aero-engine jet pipe EM scattering of cavities test device and method of testing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105021899B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950433A (en) * | 2017-02-24 | 2017-07-14 | 北京航天长征飞行器研究所 | A kind of low electromagnetic scattering background environment implementation method for adapting to condition of high vacuum degree |
| 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 |
| CN110954868A (en) * | 2019-12-05 | 2020-04-03 | 中国航发四川燃气涡轮研究院 | Low-scattering shell for engine suitable for electromagnetic test of external field wind environment |
| CN111272778A (en) * | 2020-03-09 | 2020-06-12 | 北京环境特性研究所 | Automatic switching type reflectivity test support and test method |
| CN113378488A (en) * | 2021-05-23 | 2021-09-10 | 中国航发沈阳发动机研究所 | Method for improving stealth performance of forward radar of aircraft 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 |
| CN113418937A (en) * | 2021-06-08 | 2021-09-21 | 西北工业大学 | Rear-body-replaceable ultra-compact low-scattering carrier of aircraft engine |
| CN115079112A (en) * | 2022-07-21 | 2022-09-20 | 中国航发四川燃气涡轮研究院 | Near-ground dynamic RCS test system and method for aircraft engine |
| CN115267687A (en) * | 2022-09-29 | 2022-11-01 | 中国航发四川燃气涡轮研究院 | Low-cost modularized multi-posture engine low-scattering carrier |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0436664A (en) * | 1990-06-01 | 1992-02-06 | Yokohama Rubber Co Ltd:The | Radio wave absorber |
| TWM246995U (en) * | 2003-10-27 | 2004-10-11 | Ya-Wen Wu | Improved storage case structure for optical disc |
| CN101216556A (en) * | 2007-12-27 | 2008-07-09 | 复旦大学 | Electrically Large complex target and rugged face background composite electromagnetic scattering numerical value emulation method |
| US20100201564A1 (en) * | 2009-02-11 | 2010-08-12 | Foster John D | Removing clutter from radar cross section measurements using spectral tagging |
| CN103198227A (en) * | 2013-04-18 | 2013-07-10 | 南京理工大学 | Electromagnetic scattering analyzing method for superspeed flight targets |
| CN203590678U (en) * | 2013-12-03 | 2014-05-07 | 上海卫星装备研究所 | Spacecraft product vacuum wave-absorbing module |
-
2015
- 2015-07-01 CN CN201510378479.7A patent/CN105021899B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0436664A (en) * | 1990-06-01 | 1992-02-06 | Yokohama Rubber Co Ltd:The | Radio wave absorber |
| TWM246995U (en) * | 2003-10-27 | 2004-10-11 | Ya-Wen Wu | Improved storage case structure for optical disc |
| CN101216556A (en) * | 2007-12-27 | 2008-07-09 | 复旦大学 | Electrically Large complex target and rugged face background composite electromagnetic scattering numerical value emulation method |
| US20100201564A1 (en) * | 2009-02-11 | 2010-08-12 | Foster John D | Removing clutter from radar cross section measurements using spectral tagging |
| CN103198227A (en) * | 2013-04-18 | 2013-07-10 | 南京理工大学 | Electromagnetic scattering analyzing method for superspeed flight targets |
| CN203590678U (en) * | 2013-12-03 | 2014-05-07 | 上海卫星装备研究所 | Spacecraft product vacuum wave-absorbing module |
Non-Patent Citations (3)
| Title |
|---|
| 邓洪伟等: "二元矢量喷管内外流场数值计算与隐身性分析", 《航空科学技术》 * |
| 郭静: "微波暗室目标RCS测试方法的研究与试验", 《中国优秀硕士学位论文全文数据库 信息科技辑》 * |
| 高翔等: "介质涂覆位置对双S弯排气系统电磁散射特性影响研究", 《物理学报》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950433A (en) * | 2017-02-24 | 2017-07-14 | 北京航天长征飞行器研究所 | A kind of low electromagnetic scattering background environment implementation method for adapting to condition of high vacuum degree |
| CN106950433B (en) * | 2017-02-24 | 2019-05-24 | 北京航天长征飞行器研究所 | A kind of low electromagnetic scattering background environment implementation method adapting to condition of high vacuum degree |
| 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 |
| CN110954868A (en) * | 2019-12-05 | 2020-04-03 | 中国航发四川燃气涡轮研究院 | Low-scattering shell for engine suitable for electromagnetic test of external field wind environment |
| CN110954868B (en) * | 2019-12-05 | 2024-04-02 | 中国航发四川燃气涡轮研究院 | Low scattering shell for engine suitable for electromagnetic test of external wind environment |
| CN111272778B (en) * | 2020-03-09 | 2022-10-21 | 北京环境特性研究所 | Automatic switching type reflectivity test support and test method |
| CN111272778A (en) * | 2020-03-09 | 2020-06-12 | 北京环境特性研究所 | Automatic switching type reflectivity test support and test method |
| CN113378488A (en) * | 2021-05-23 | 2021-09-10 | 中国航发沈阳发动机研究所 | Method for improving stealth performance of forward radar of aircraft engine |
| CN113378488B (en) * | 2021-05-23 | 2023-07-21 | 中国航发沈阳发动机研究所 | Method for improving stealth performance of forward radar of aeroengine |
| CN113418937A (en) * | 2021-06-08 | 2021-09-21 | 西北工业大学 | Rear-body-replaceable ultra-compact low-scattering carrier of aircraft engine |
| CN113418937B (en) * | 2021-06-08 | 2022-12-09 | 西北工业大学 | Rear-body-replaceable ultra-compact low-scattering carrier of aircraft 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 |
| CN115079112A (en) * | 2022-07-21 | 2022-09-20 | 中国航发四川燃气涡轮研究院 | Near-ground dynamic RCS test system and method for aircraft engine |
| CN115267687A (en) * | 2022-09-29 | 2022-11-01 | 中国航发四川燃气涡轮研究院 | Low-cost modularized multi-posture engine low-scattering carrier |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105021899B (en) | 2018-01-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105021899A (en) | Device and method for testing electromagnetic scattering of jet pipe cavity of aeroengine | |
| US10093436B2 (en) | Wireless aircraft engine communication system | |
| CN105653747B (en) | The emulation mode of the conformal sub- grid Electromagnetic Scattering of super speed vehicle | |
| EP1849974A3 (en) | Turbine engine tailcone resonator | |
| CN205161028U (en) | Wave absorption body , inhale mode piece and inhale ripples box | |
| CN106950433B (en) | A kind of low electromagnetic scattering background environment implementation method adapting to condition of high vacuum degree | |
| CN104470338A (en) | Shielding structure and electronic device having shielding structure | |
| CN202373696U (en) | Microwave/infrared composite antenna cover for airborne pod | |
| CN106649197A (en) | Calculation method of internal scattering characteristic of complicated cavity | |
| CN105161818B (en) | Airport radio antenna | |
| CN203732553U (en) | Medical capillary adapter, test card component and blood gas analyzer | |
| Verma et al. | Control of a Mach reflection-induced interaction using an array of vane-type vortex generators | |
| CN204205050U (en) | A kind of minimized wide-band logarithm periodic antenna | |
| CN212922013U (en) | Unmanned aerial vehicle wing vibration simulation model | |
| EP3158351B1 (en) | Air ventilation system with radio frequency shielding for use in magnetic resonance imaging systems | |
| CN207038163U (en) | A kind of set composite of resonant labyrinth noise reduction | |
| CN207870904U (en) | A kind of doppler transducer positioning fixture | |
| CN201039658Y (en) | Electromagnetism compatible shielding device | |
| Neri et al. | Experimental and numerical study of wheel bay cavity noise for full scale nose landing gear | |
| TWM344582U (en) | Wide-band, high precision GTEM transverse electromagnetic cell | |
| CN211784183U (en) | Composite material wing body fairing performance detection device | |
| CN104612970B (en) | Pump body structure and compressor | |
| Tinetti et al. | Scattering of high frequency duct noise by full scale hybrid wing body configurations | |
| CN203308802U (en) | Vertical baffling silencer | |
| Zhang et al. | Research of radio wave propagation in forest based on Non-uniform mesh Parabolic Equation |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180109 Termination date: 20180701 |