CN107525975A - Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment - Google Patents
Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment Download PDFInfo
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- CN107525975A CN107525975A CN201710583215.4A CN201710583215A CN107525975A CN 107525975 A CN107525975 A CN 107525975A CN 201710583215 A CN201710583215 A CN 201710583215A CN 107525975 A CN107525975 A CN 107525975A
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- Prior art keywords
- missile
- borne antenna
- electric performance
- heating
- performance test
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/10—Radiation diagrams of antennas
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/003—Environmental or reliability tests
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Environmental & Geological Engineering (AREA)
- Electromagnetism (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses one kind to simulate Missile-borne Antenna electric performance test system under Aerodynamic Heating environment, including：Mobile device (guide rail, slide rail and the boxcar that can be moved on guide rail along guide rail), simulate Aerodynamic Heating system (firing equipment and heating control system), signal transmitting system (signal source, radio-frequency cable, launch loudspeaker and whistle control system), signal receives system and (receives loudspeaker, radio-frequency cable, frequency spectrograph and reception Data Management Analysis system), Missile-borne Antenna testpieces (bay section simulating piece, Missile-borne Antenna), test fixture, the present invention can effectively solve the electrical property measurement problem under the Aerodynamic Heating environment of Missile-borne Antenna, examine the reliability of Missile-borne Antenna heat protection design.
Description
Technical field
The invention belongs to aircraft thermal protection technology field, and in particular to Missile-borne Antenna under one kind simulation Aerodynamic Heating environment
Electric performance test system.
Background technology
Hypersonic long endurance class aircraft (refers generally to flying speed more than 5 Mach, the flight time is more than more than 400s's
Aircraft), in endoatmosphere, sustained maneuver is flown, and air-flow carries out continuing Aerodynamic Heating to aircraft, and stationary point hot-fluid peak value reaches
To 5MW/m2, total heating amount is 2 × 104MJ/m2, the flight time is up to more than 400s, Missile-borne Antenna face it is serious pneumatic plus
Heat, total heating amount is larger, and Missile-borne Antenna temperature is higher.
To ensure hypersonic aircraft by the normal work of Aerodynamic Heating Missile-borne Antenna, it is necessary to carry out heat to Missile-borne Antenna
Protection Design, different thermal protection schemes have considerable influence to Missile-borne Antenna electrical property, and the research of Missile-borne Antenna relies primarily on ground
Experiment.Therefore, seek reasonable, economical and efficient Missile-borne Antenna by the electrical performance test method of Aerodynamic Heating, be Missile-borne Antenna
Heat protection design studies more problem.
The content of the invention
The present invention provides Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment, for Missile-borne Antenna
By Aerodynamic Heating electric performance test, can check flight device Missile-borne Antenna thermal protective performance, instruct the heat of aircraft Missile-borne Antenna to prevent
Shield design.
Concrete technical scheme of the present invention is as follows：
Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment, including：Mobile device, simulation pneumatically add
Hot systems, signal transmitting system, signal receive system, Missile-borne Antenna testpieces, test fixture；Wherein：
Mobile device includes：Guide rail, slide rail and the boxcar that can be moved on guide rail along guide rail；Guide rail is fixed on ground
On, slide rail is located at guide rail overhead and guide rail parallel, and slide rail runs through boxcar；
Simulation Aerodynamic Heating system includes：Firing equipment and heating control system；Firing equipment includes quartz lamp heating system
System and graphite heating system, quartz lamp heating system and graphite heating system are interchangeable, and quartz lamp heating system exists for temperature
Less than 1200 DEG C of Aerodynamic Heating environment, graphite heating system are used for Aerodynamic Heating environment of the temperature below 1600 DEG C；
Signal transmitting system includes：Signal source, radio-frequency cable, transmitting loudspeaker and whistle control system；
Signal receives system：Receive loudspeaker, radio-frequency cable, frequency spectrograph and receive Data Management Analysis system；
Missile-borne Antenna test block：Bay section simulating piece, Missile-borne Antenna, bay section simulating piece is consistent with the thermal protection scheme of bay section,
Missile-borne Antenna is arranged on bay section simulating piece.
Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment, is divided into experiment heating zone and electrical property is surveyed
Area is tried, firing equipment is arranged in experiment heating zone, and signal transmitting system and signal receive system and be arranged in electric performance test area, lead to
Heating zone and UNICOM of electric performance test area will be tested by crossing guide rail and slide rail；Missile-borne Antenna test block is placed in boxcar by test fixture
Interior, boxcar is moved to electric performance test area along track from experiment heating zone, Missile-borne Antenna test block along slide rail it is synchronous with boxcar from
Experiment heating zone is moved to electric performance test area.
Need to carry out Aerodynamic Heating theory analysis to Missile-borne Antenna actual working environment before carrying out electric performance test, draw heating
Equipment needs the thermal boundary condition (thermal boundary curve) controlled, selects suitable heating system.
When formulating testing scheme, it is necessary to set test window, Missile-borne Antenna test block is heated to survey in experiment heating zone
Window is tried, electric performance test area is quickly moved to by mobile device, carries out signal testing, the formulating rules of test window should
Catch the peak value of thermal boundary condition, cover thermal boundary condition again, every group by no less than 2 test windows and to no less than
2 Missile-borne Antenna test blocks are tested.
Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment of the present invention, can effectively solve missile-borne day
Line is measured problem by Aerodynamic Heating electrical property, examines the reliability of Missile-borne Antenna heat protection design.
Brief description of the drawings
Fig. 1 is the static heat electric performance test system layout figure according to the embodiment of the present invention；
Fig. 2 is the electric performance test area layout according to the embodiment of the present invention；
Fig. 3 is the example test window figure according to the embodiment of the present invention.
Embodiment
Below in conjunction with the accompanying drawings and embodiment the present invention is described in further detail.
Shown in all accompanying drawings 1 and Fig. 2, Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment, wrap
Include：Boxcar (1), Missile-borne Antenna (2), experiment heating zone (3), firing equipment (4), bay section simulating piece (5), electric performance test area
(6), guide rail (7), slide rail (8), frequency spectrograph (9), signal source (10), radio-frequency cable (11), transmitting loudspeaker (12), receive loudspeaker
(13)。
Wherein, firing equipment can be quartz burner heater, or graphite heating system, bay section simulating piece and bay section
Thermal protection scheme is consistent, and Missile-borne Antenna is arranged on bay section simulating piece, Missile-borne Antenna and the composition Missile-borne Antenna examination of bay section simulating piece
Test part.Signal source, radio-frequency cable and transmitting loudspeaker form signal transmitting system together, receive loudspeaker, radio-frequency cable and frequency spectrograph
Signal is formed together receives system.Missile-borne Antenna test block is installed on the mobile device.Test block is with mobile device on slide rail
Moved along guide rail.Test fixture and the size dimension of heating system can be according to Missile-borne Antenna test block exact shape and big subtotal
Calculate and determine, the frequency of signal transmitting system determines that the control condition of heating system is by missile-borne according to the frequency of use of Missile-borne Antenna
Pneumatic thermal environment residing for antenna determines.
Heating system includes quartz lamp heating system and graphite heating system.Quartz lamp heating system exists available for temperature
Less than 1200 DEG C of Aerodynamic Heating environment, graphite system can be used for Aerodynamic Heating environment of the temperature below 1600 DEG C.Carry out electricity
Need to carry out Aerodynamic Heating theory analysis before performance test, show that firing equipment needs the thermal boundary condition controlled, selection is suitably
Heating system.
The thermal boundary curve of theory analysis, when formulating testing scheme, it is necessary to set test window, Missile-borne Antenna test block
Test window is heated to, signal test system is quickly moved to by mobile device, carries out signal measurement.Therefore, test is formulated
Window is one of key of testing program, and the formulating rules of test window should catch the peak value of thermal boundary condition, cover again
To thermal boundary condition.
In the present embodiment, Missile-borne Antenna test block size is 200mm × 200mm flat boards, and thickness 10mm, material is glass
Steel；Experiment uses quartz lamp heating system.Test window is as shown in Figure 3.This example designs three test windows and tested altogether.
A) test block 1 is heated to test window 2, is moved quickly to electric performance test area, carries out Missile-borne Antenna electrical property survey
Examination；
B) when test block 2 is heated to test window 2, electric performance test area, Missile-borne Antenna electric performance test are moved quickly to；
C) when test block 3 is heated to test window 2, electric performance test area, Missile-borne Antenna electric performance test are moved quickly to.
One skilled in the art will appreciate that the above is only the preferred embodiments of the present invention, the present invention is not limited to above-mentioned reality
Example is applied, embodiment is merely illustrative, every not depart from skill of the present invention especially just in the explanation in terms of specific size
The modification or modification that art scheme substantive content is made, belong to protection scope of the present invention.
Claims (6)
1. Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment, including：Mobile device, simulation Aerodynamic Heating
System, signal transmitting system, signal receive system, Missile-borne Antenna testpieces, test fixture；Wherein：
Mobile device includes：Guide rail, slide rail and the boxcar that can be moved on guide rail along guide rail；Guide rail fixes on the ground, sliding
Rail is located at guide rail overhead and guide rail parallel, and slide rail runs through boxcar；
Simulation Aerodynamic Heating system includes：Firing equipment and heating control system；
Signal transmitting system includes：Signal source, radio-frequency cable, transmitting loudspeaker and whistle control system；
Signal, which receives system, to be included：Receive loudspeaker, radio-frequency cable, frequency spectrograph and receive Data Management Analysis system；
Missile-borne Antenna test block includes：Bay section simulating piece, Missile-borne Antenna；Missile-borne Antenna is arranged on bay section simulating piece.
2. Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment according to claim 1, is divided into examination
Heating zone and electric performance test area are tested, firing equipment is arranged in experiment heating zone, and signal transmitting system and signal receive system cloth
Put in electric performance test area, heating zone and UNICOM of electric performance test area will be tested by guide rail and slide rail；Missile-borne Antenna test block
It is placed in by test fixture in boxcar, boxcar is moved to electric performance test area, Missile-borne Antenna test along track from experiment heating zone
Part is moved to electric performance test area along slide rail is synchronous with boxcar from experiment heating zone.
3. Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment according to claim 1, heating are set
Standby to include quartz lamp heating system and graphite heating system, quartz lamp heating system and graphite heating system are interchangeable, quartz lamp
Heating system is used for Aerodynamic Heating environment of the temperature below 1200 DEG C, and graphite heating system is used for temperature below 1600 DEG C
Aerodynamic Heating environment.
4. Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment according to claim 1,3, carries out
Need to carry out Aerodynamic Heating theory analysis to Missile-borne Antenna actual working environment before electric performance test, show that firing equipment needs to control
Thermal boundary condition (thermal boundary curve), select suitable heating system.
5. Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment according to claim 1,2, is making
, it is necessary to set test window when determining testing scheme, Missile-borne Antenna test block is heated to test window in experiment heating zone, passes through shifting
Dynamic device is quickly moved to electric performance test area, carries out signal testing, and the formulating rules of test window should catch thermal boundary bar
The peak value of part, covers thermal boundary condition again.
6. Missile-borne Antenna electric performance test system under a kind of simulation Aerodynamic Heating environment according to claim 5, every group leads to
Cross no less than 2 test windows and no less than 2 Missile-borne Antenna test blocks are tested.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710583215.4A CN107525975A (en) | 2017-07-17 | 2017-07-17 | Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710583215.4A CN107525975A (en) | 2017-07-17 | 2017-07-17 | Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment |
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| Publication Number | Publication Date |
|---|---|
| CN107525975A true CN107525975A (en) | 2017-12-29 |
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| CN201710583215.4A Pending CN107525975A (en) | 2017-07-17 | 2017-07-17 | Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201229251Y (en) * | 2008-05-22 | 2009-04-29 | 北京航空航天大学 | Infrared thermal source water cooling device for high-temperature aerodynamic heat simulation test for missile aircraft |
| CN101907422A (en) * | 2010-06-02 | 2010-12-08 | 北京航空航天大学 | Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile |
| CN103344841A (en) * | 2013-05-09 | 2013-10-09 | 电子科技大学 | Free space terminal short-circuit system for temperature changing measurement of dielectric property of dielectric material |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
-
2017
- 2017-07-17 CN CN201710583215.4A patent/CN107525975A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201229251Y (en) * | 2008-05-22 | 2009-04-29 | 北京航空航天大学 | Infrared thermal source water cooling device for high-temperature aerodynamic heat simulation test for missile aircraft |
| CN101907422A (en) * | 2010-06-02 | 2010-12-08 | 北京航空航天大学 | Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile |
| CN103344841A (en) * | 2013-05-09 | 2013-10-09 | 电子科技大学 | Free space terminal short-circuit system for temperature changing measurement of dielectric property of dielectric material |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
Non-Patent Citations (2)
| Title |
|---|
| 宋银锁: "《气动加热条件下天线罩瞄准误差的测试技术》", 《航空兵器》 * |
| 寇彬彬: "《分层材料介电性能变温测试技术研究》", 《硕士学位论文》 * |
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Application publication date: 20171229 |
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