CN113687323A - Low-scattering shell for binary vector engine and application thereof - Google Patents
Low-scattering shell for binary vector engine and application thereof Download PDFInfo
- Publication number
- CN113687323A CN113687323A CN202111244335.4A CN202111244335A CN113687323A CN 113687323 A CN113687323 A CN 113687323A CN 202111244335 A CN202111244335 A CN 202111244335A CN 113687323 A CN113687323 A CN 113687323A
- Authority
- CN
- China
- Prior art keywords
- scattering
- low
- binary vector
- vector engine
- shell
- 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
- 238000012360 testing method Methods 0.000 claims abstract description 24
- 238000009434 installation Methods 0.000 claims abstract description 11
- 230000009193 crawling Effects 0.000 claims abstract description 7
- 239000007921 spray Substances 0.000 claims abstract description 4
- 238000011156 evaluation Methods 0.000 claims description 3
- 238000004088 simulation Methods 0.000 claims description 3
- 230000006978 adaptation Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 description 6
- 239000006260 foam Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 230000005764 inhibitory process Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000011358 absorbing material Substances 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002592 echocardiography Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000023886 lateral inhibition Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Images
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
- G01S7/40—Means for monitoring or calibrating
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention provides a low-scattering shell for a binary vector engine and application thereof, wherein the low-scattering shell comprises a flat mouse-shaped structure surrounded by a plane bottom, a conical side wall and an arc-shaped top, and comprises a front section and a rear section, the tail part of the rear section is provided with a notch part, and the size of the notch part is matched with that of a test installation part of a binary vector engine spray pipe to be tested. The method can independently obtain the radar scattering cross section of the inner area of the back cavity of the aircraft engine, and can also obtain the influence of crawling waves and diffraction waves of the outer adjusting piece of the aircraft engine on the forward radar scattering of the aircraft.
Description
Technical Field
The disclosure relates to the technical field of aircraft engine stealth design, in particular to a low-scattering shell for a binary vector engine and application thereof.
Background
In the stealth design of an aircraft engine, electromagnetic testing is a direct means for obtaining a radar scattering cross section. In a conventional electromagnetic test, in order to obtain a radar scattering cross section of an internal area of a cavity of an aircraft engine, the external part of the cavity is generally wrapped by a low-scattering shell, so that radar scattering signals generated by external wall surfaces, pipelines, installation edges and the like are effectively inhibited, and the device is one of necessary devices for improving backward electromagnetic test precision of the aircraft engine.
Through the accumulation of the hidden design basis of the early-stage aircraft engine, the design method of the low-scattering shell is completely mastered at present, the radar scattering cross section of the low-scattering shell reaches-20 dBsm, and the electromagnetic test requirement of the current aircraft engine is met. At present, the low-scattering shell can only have good inhibition effect within +/-50 degrees of backward direction, and has poor forward and lateral inhibition effects. Besides strong scattering of the aircraft engine towards the cavity, weak signals such as creeping waves, diffracted waves and the like generated by exposed components such as an external adjusting sheet and the like have strong contribution to a radar scattering section of the aircraft in the forward direction. In particular, for a flat airplane with a binary thrust vectoring nozzle, the influence of a weak signal generated by the external adjusting sheet on the forward radar scattering is more serious. The low-scattering shell for the electromagnetic test of the aircraft engine designed at the present stage has poor forward and lateral suppression effects, the magnitude of electromagnetic signals generated by creeping waves and diffraction is low, the possibility of being covered by the low-scattering shell forward electromagnetic scattering signals exists, and forward weak signal data generated by exposed components such as an external adjusting sheet cannot be accurately and effectively acquired.
At present, an electromagnetic test of the aero-engine can only acquire the radar scattering characteristic in a backward azimuth angle, the contribution to the forward radar scattering of the airplane is covered by a signal of a low-scattering shell, and the phenomena of creeping waves and diffraction waves of an outer adjusting sheet of the aero-engine cannot be effectively analyzed. Therefore, a low-scattering shell which can be used for testing weak signals such as creeping waves at the edge of an outer adjusting sheet and the like and can independently obtain strong signals of a backward cavity inner domain is needed to be provided so as to more reasonably and comprehensively evaluate the forward and backward radar scattering characteristics of the binary vector engine.
Disclosure of Invention
In view of this, the embodiment of the present disclosure provides a low-scattering shell for a binary vector engine, which can be used for weak diffraction and strong scattering electromagnetic tests of the engine, and can independently obtain a radar scattering cross section in an inner domain of a backward cavity of an aircraft engine, and simultaneously obtain the influence of crawling waves and diffraction waves of an external adjustment sheet of the aircraft engine on forward radar scattering of an aircraft.
In order to achieve the above purpose, the invention provides the following technical scheme:
the utility model provides a low scattering casing for binary vector engine, low scattering casing includes and encloses the flat mouse column structure that is that establishes by plane bottom, taper lateral wall and cambered surface top to including anterior segment and back end, the notch portion is seted up to the afterbody of back end, the size of notch portion and the binary vector engine spray tube test installation department size looks adaptation that awaits measuring.
Further, the taper angle of the tapered side walls on both sides of the front section is 60 ° ± 5 °.
Furthermore, the angle of the sharp corner of the head of the front section is 20-30 degrees, the sharp point is subjected to rounding treatment, and the rounding radius is less than 2 mm.
Further, the low-scattering shell comprises a closing plug cone matched with the shape and the size of the notch part, the closing plug cone is detachably connected to the notch part, the closing body is integrally formed on the low-scattering shell, and the length ratio of the central line of the front section to the central line of the rear section is 1.618 after the closing body is formed.
Further, the angle range of the tail sharp corner of the closed plug cone is 60 degrees +/-5 degrees, and the sharp point is subjected to rounding treatment, and the rounding radius is smaller than 2 mm.
Furthermore, the junction of the front section and the rear section is rounded, and the radius of the rounding is 2-10 mm.
The invention also provides an application of the low-scattering shell for the binary vector engine, which can be used for diagnosing the influence of the crawling wave of the external adjusting piece of the binary vector engine on the forward radar scattering performance of the airplane under the real installed environment.
The invention also provides application of the low-scattering shell for the binary vector engine, which can be used for electromagnetic scattering test or simulation evaluation of the backward binary vector engine.
The invention provides a low-scattering shell for a binary vector engine, which has the beneficial effects that:
1. the contribution of the external adjusting piece creeping wave to the aircraft forward radar scattering cross section during the real installation of the binary vector engine can be obtained.
2. The radar scattering cross section of the backward cavity inner domain of the binary vector engine can be obtained.
3. When the front section and the rear section of the low-scattering shell are closed, the radar scattering cross section of the low-scattering shell in the omnidirectional angular domain range can be independently obtained.
4. The low-scattering shell is trial-manufactured by all metal, and expensive materials such as wave transmission or wave absorption are not adopted.
5. The scattering cross section of the low scattering shell forward radar is less than-30 dBsm.
6. When the rear section of the low-scattering shell is closed, the scattering cross section of the backward radar is smaller than-25 dBsm.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic top view of the low scattering housing of the present invention;
FIG. 2 is a schematic view of the cross-sectional structure A-A of FIG. 1;
FIG. 3 is a schematic cross-sectional view taken along line B-B of FIG. 1;
in the figure: 1-the preceding paragraph; 2-rear section; 3-binary vector engine external regulating sheet; 4-binary vector engine; 5-closing the plug cone.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present disclosure, and the drawings only show the components related to the present disclosure rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the disclosure provides a low-scattering shell for a binary vector engine, which can be used for analyzing and judging the influence of diffraction on the edge of an external adjusting sheet of the binary vector engine on the scattering of a forward radar of an airplane, and can also be used for electromagnetic testing of the internal domain of a backward cavity structure of the binary vector engine.
The low scattering shell comprises a flat mouse-shaped structure surrounded by a plane bottom, a conical side wall and an arc surface top, and comprises a front section and a rear section, wherein a notch part is formed in the tail part of the rear section, and the size of the notch part is matched with the size of a test installation part of the binary vector engine spray pipe to be tested. Specifically, the shell comprises a front section, a rear section, a binary vector engine, an outer adjusting sheet lap joint edge, a closing plug cone and the like. The front section of the shell is a closed body and mainly is a carrier for crawling incident waves and echoes; the rear section and a binary vector engine are subjected to fusion design; the binary vector engine is a full-size test piece; the lap joint of the outer adjusting sheet is a sawtooth-shaped edge. The molded surface of the shell is symmetrical left and right, is asymmetrical up and down, is made of metal and does not contain materials such as wave-transmitting materials or wave-absorbing materials. The shell can be used for diagnosing the influence of the crawling wave of the external adjusting piece of the binary vector engine on the stealth performance of the airplane forward radar in a real installation environment, and can also be used for electromagnetic scattering test or simulation evaluation of the backward binary vector engine.
Referring to fig. 1-3, the front section 1 is a closed body and mainly formed by designing a straight line and a circular arc, the selected range of the sharp angle of the front section 1 is 20-30 degrees, the two side edges are designed as edges, the wedge angle of the edge is 60 degrees plus or minus 5 degrees, preferably 60 degrees, the sharp point is rounded, and the radius of the rounding is less than 2 mm. The rear section 2 is an opening body and is mainly designed by a straight line and a spline curve, and the design parameters of the spline curve are determined by the profile of the outer adjusting sheet 3 of the binary vector engine and the profile of the front section 1. The two sides of the rear section 2 are designed into edges, and the wedge angle of the edges is 60 degrees +/-5 degrees, preferably 60 degrees; the closed plug cone 5 and the rear section 2 are assembled to form a closed body, the closed plug cone 5 is formed by designing a straight line and a spline curve, the parameters of the spline curve are determined by the profile of the rear section 2, the angle selection range of a sharp point is 60 degrees +/-5 degrees, the rounding of the sharp point is carried out, and the rounding radius is less than 2 mm.
After the front section 1, the rear section 2 and the closing plug cone 5 form a closing body, the length ratio of the central lines of the closing body of the front section 1 and the closing body of the rear section 2 is 1.618. And the junction of the front section 1 and the rear section 2 is subjected to rounding treatment, and the rounding radius is 2-10 mm.
When the radar antenna is placed in the forward direction of the low-scattering shell, the closed plug cone 5 is not installed at the moment, the low-scattering shell is horizontally placed on the foam rotary table, and the angle between the central line of the low-scattering shell and the installation axis of the radar antenna is set to be 60 degrees. When the radar antenna starts to work, the foam rotary table rotates from 60 degrees to 0 degree and rotates to-60 degrees. At the moment, the electromagnetic test of the creeping wave of the external adjusting sheet 3 of the binary vector engine is completed. When the incident direction of the radar wave is perpendicular to the edge of the front section 1, the test data at the test point is removed. When the radar antenna irradiates the front section of the shell, the contribution of the crawling wave of the external adjusting piece to the forward radar scattering of the airplane can be obtained.
When the radar antenna is placed behind the low scattering shell, the closed plug cone is not installed at the moment, the low scattering shell is horizontally placed on the foam rotary table, and the angle between the central line of the low scattering shell and the installation axis of the radar antenna is set to be 60 degrees. When the radar antenna starts to work, the foam rotary table rotates from 60 degrees to 0 degree and rotates to-60 degrees. At this time, the electromagnetic test of the backward cavity inner region of the binary vector engine 4 is completed. When the radar antenna irradiates the rear section of the shell, the radar scattering cross section of the inner domain of the backward cavity of the binary vector engine can be independently obtained.
When the radar antenna is placed in the forward direction of the low scattering shell, the closed plug cone is installed, the low scattering shell is horizontally placed on the foam rotary table, the center line of the low scattering shell coincides with the installation axis of the radar antenna, and the angle is set to be 0 degrees. When the radar antenna starts to work, the foam rotary table starts from 0 degree, and electromagnetic testing in a 360-degree angle domain is completed. At this point, the electromagnetic testing of the low-scattering housing in the closed state is completed.
After the rear section of the shell is assembled with the closed plug cone, the radar scattering cross section in the omnidirectional angle domain of the horizontal plane of the low scattering shell can be obtained and is used for judging the inhibition effect of the low scattering shell on the external domain scattering signals of the binary vector engine.
When the upper and lower platforms of the low-scattering shell and the radar antenna are replaced, the test background needs to be calibrated through the standard body.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure 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 disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides a low scattering casing for binary vector engine, its characterized in that, low scattering casing includes and encloses the flat mouse column structure that is that establishes by plane bottom, taper lateral wall and cambered surface top to including anterior segment and back end, the notch part is seted up to the afterbody of back end, the size of notch part and the binary vector engine spray tube test installation department size looks adaptation that awaits measuring.
2. The low scatter housing for a binary vector engine as set forth in claim 1, wherein: the taper angle of the tapered side walls on both sides of the front section is 60 degrees +/-5 degrees.
3. The low scatter housing for a binary vector engine as set forth in claim 1, wherein: the angle of the sharp corner of the head of the front section is 20-30 degrees, and the sharp point is rounded, and the radius of the rounding is less than 2 mm.
4. The low scatter housing for a binary vector engine as set forth in claim 1, wherein: and the closing plug cone is matched with the shape and the size of the notch part, is detachably connected to the notch part, so that the low-scattering shell integrally forms a closing body, and the length ratio of the central line of the front section to the central line of the rear section is 1.618 after the closing body is formed.
5. The low scatter housing for a binary vector engine of claim 4, wherein: the angle range of the tail sharp corner of the closed plug cone is 60 +/-5 degrees, the sharp point is subjected to rounding treatment, and the rounding radius is smaller than 2 mm.
6. The low scatter housing for a binary vector engine as set forth in claim 1, wherein: and the junction of the front section and the rear section is subjected to rounding treatment, and the rounding radius is 2-10 mm.
7. Use of a low-scattering housing for a binary vector engine according to claim 1, wherein: the low-scattering shell can be used for diagnosing the influence of the crawling wave of the external adjusting piece of the binary vector engine on the scattering performance of the forward radar of the airplane in the real installation environment.
8. Use of a low-scattering housing for a binary vector engine according to claim 1, wherein: the low-scattering shell can be used for electromagnetic scattering test or simulation evaluation of a backward binary vector engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111244335.4A CN113687323B (en) | 2021-10-26 | 2021-10-26 | Low-scattering shell for binary vector engine and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111244335.4A CN113687323B (en) | 2021-10-26 | 2021-10-26 | Low-scattering shell for binary vector engine and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113687323A true CN113687323A (en) | 2021-11-23 |
| CN113687323B CN113687323B (en) | 2022-03-08 |
Family
ID=78587934
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111244335.4A Active CN113687323B (en) | 2021-10-26 | 2021-10-26 | Low-scattering shell for binary vector engine and application thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113687323B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114355311A (en) * | 2022-03-10 | 2022-04-15 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier for RCS (Radar Cross section) test of airfoil leading edge wave-absorbing structure and test method |
| CN114858755A (en) * | 2022-07-05 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Aero-engine coating frequency conversion in-situ laser detection system |
| 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 (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT8867528A0 (en) * | 1987-06-26 | 1988-06-07 | Aerospatiale | BLADE WITH REDUCED RADAR SIGNATURE |
| CN104103898A (en) * | 2014-06-24 | 2014-10-15 | 中国电子科技集团公司第十研究所 | High wave permeability and low RCS (Radar Cross Section) radome |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN108535712A (en) * | 2018-03-29 | 2018-09-14 | 北京环境特性研究所 | A kind of polarimetric calibration device and radar scattering polarization measurement system |
| CN109212504A (en) * | 2018-10-09 | 2019-01-15 | 北京环境特性研究所 | To scattering carrier low with what is laterally designed before taking into account |
| 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 |
| CN111504952A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier with both horizontal polarization and vertical polarization and testing method thereof |
| CN112177796A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Lateral sealing device for middle adjusting plate of combined spray pipe |
| CN112834997A (en) * | 2021-01-07 | 2021-05-25 | 中国航发沈阳发动机研究所 | Low-scattering carrier shape design method with rectangular opening characteristic |
| CN113075626A (en) * | 2021-03-31 | 2021-07-06 | 北京环境特性研究所 | Low-scattering carrier for darkroom background level evaluation test |
| CN113419224A (en) * | 2021-06-07 | 2021-09-21 | 西北工业大学 | Axisymmetric double-emission low-scattering carrier for RCS test and application method thereof |
| CN113532865A (en) * | 2021-06-24 | 2021-10-22 | 中国航发沈阳发动机研究所 | Low-scattering carrier suitable for various engines |
-
2021
- 2021-10-26 CN CN202111244335.4A patent/CN113687323B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT8867528A0 (en) * | 1987-06-26 | 1988-06-07 | Aerospatiale | BLADE WITH REDUCED RADAR SIGNATURE |
| CN104103898A (en) * | 2014-06-24 | 2014-10-15 | 中国电子科技集团公司第十研究所 | High wave permeability and low RCS (Radar Cross Section) radome |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN108535712A (en) * | 2018-03-29 | 2018-09-14 | 北京环境特性研究所 | A kind of polarimetric calibration device and radar scattering polarization measurement system |
| CN109212504A (en) * | 2018-10-09 | 2019-01-15 | 北京环境特性研究所 | To scattering carrier low with what is laterally designed before taking into account |
| 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 |
| CN111504952A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier with both horizontal polarization and vertical polarization and testing method thereof |
| CN112177796A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Lateral sealing device for middle adjusting plate of combined spray pipe |
| CN112834997A (en) * | 2021-01-07 | 2021-05-25 | 中国航发沈阳发动机研究所 | Low-scattering carrier shape design method with rectangular opening characteristic |
| CN113075626A (en) * | 2021-03-31 | 2021-07-06 | 北京环境特性研究所 | Low-scattering carrier for darkroom background level evaluation test |
| CN113419224A (en) * | 2021-06-07 | 2021-09-21 | 西北工业大学 | Axisymmetric double-emission low-scattering carrier for RCS test and application method thereof |
| CN113532865A (en) * | 2021-06-24 | 2021-10-22 | 中国航发沈阳发动机研究所 | Low-scattering carrier suitable for various engines |
Non-Patent Citations (8)
| Title |
|---|
| GAO XU；等: "Improved test method based on vector cancellation for scattering characteristic of discontinuous target", 《JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS》 * |
| ODENDAAL J W ,等: "RCS measurements and results of an engine-inlet system design optimization", 《IEEE ANTENNAS & PROPAGATION MAGAZINE》 * |
| WANG, YF；等: "Analysis of target RCS measurement based on a low RCS carrier", 《2018 INTERNATIONAL CONFERENCE ON IDENTIFICATION, INFORMATION AND KNOWLEDGE IN THE INTERNET OF THINGS》 * |
| 刘晓春;等: "飞机部件RCS测试用载体设计技术研究", 《现代雷达》 * |
| 崔力,等: "一种埋入式腔体的低RCS载体外形设计", 《一种埋入式腔体的低RCS载体外形设计》 * |
| 徐伊达；等: "飞行器部件低散射载体的分析与设计", 《电讯技术》 * |
| 邵万仁；等: "军用蜗轮喷气发动机隐身设计初步探索", 《中国航空学会青年科技论坛文集》 * |
| 高翔: "飞行器/排气系统红外辐射及电磁散射特性数值研究", 《中国博士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114355311A (en) * | 2022-03-10 | 2022-04-15 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier for RCS (Radar Cross section) test of airfoil leading edge wave-absorbing structure and test method |
| CN114858755A (en) * | 2022-07-05 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Aero-engine coating frequency conversion in-situ laser detection system |
| 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 |
| CN115267687B (en) * | 2022-09-29 | 2023-02-21 | 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 |
|---|---|
| CN113687323B (en) | 2022-03-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113687323B (en) | Low-scattering shell for binary vector engine and application thereof | |
| Dobrzynski et al. | Full-scale noise testing on Airbus landing gears in the German Dutch wind tunnel | |
| Miley | Brightness and Polarization Distributions of Head-tail Galaxies at 1415 1~ 1iEIz | |
| US20120146861A1 (en) | Antenna characterization in a waveguide | |
| CN110954868A (en) | Low-scattering shell for engine suitable for electromagnetic test of external field wind environment | |
| CN216052163U (en) | Axisymmetric double-emission low-scattering carrier for RCS test | |
| CN113419224A (en) | Axisymmetric double-emission low-scattering carrier for RCS test and application method thereof | |
| CN112834997A (en) | Low-scattering carrier shape design method with rectangular opening characteristic | |
| Neilsen et al. | Spectral characterization in the near-and mid-field of military jet aircraft noise | |
| Emerson et al. | An improved design for indoor ranges | |
| US5053712A (en) | Method for comparing the quality of rf absorbers | |
| Liu et al. | Impact of chevrons on noise source characteristics in imperfectly expanded jet flows | |
| US5016185A (en) | Electromagnetic pyramidal cone absorber with improved low frequency design | |
| Malla et al. | Effects of extended expansion ramps on flow and acoustic field of low supersonic single expansion ramp nozzles | |
| Fiévet et al. | Acoustic waveforms produced by a laboratory scale supersonic jet | |
| Dougherty | Nacelle acoustic design by ray tracing in three dimensions | |
| CN113759195A (en) | Electromagnetic scattering auxiliary testing device for rotating blade | |
| Baier et al. | Near-field measurements of a low aspect ratio supersonic nozzle interacting with a surface | |
| CN114162347B (en) | P-band low-scattering carrier and application method thereof | |
| CN213876008U (en) | Microwave darkroom | |
| CN216783896U (en) | Carrier for designing and testing aircraft seeker | |
| US20220146463A1 (en) | Mixed-domain analysis of ultrasonic inspection data | |
| CN216958519U (en) | Pyramid wave absorber | |
| Ma et al. | Simulation and analysis of a shielding cavity used in on-site radiated emission measurement | |
| Swee Chia et al. | A comparison of bistatic scattering from two geologically distinct abyssal hills |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |