CN105758270A - Test system and method for barreled-missile radio fuse - Google Patents
Test system and method for barreled-missile radio fuse Download PDFInfo
- Publication number
- CN105758270A CN105758270A CN201610188738.4A CN201610188738A CN105758270A CN 105758270 A CN105758270 A CN 105758270A CN 201610188738 A CN201610188738 A CN 201610188738A CN 105758270 A CN105758270 A CN 105758270A
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- test
- processing circuit
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- 238000012360 testing method Methods 0.000 title claims abstract description 66
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000012545 processing Methods 0.000 claims abstract description 31
- 239000002131 composite material Substances 0.000 claims abstract description 15
- 230000005284 excitation Effects 0.000 claims abstract description 9
- 238000004891 communication Methods 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 6
- 230000003044 adaptive effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 abstract 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000009666 routine test Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C21/00—Checking fuzes; Testing fuzes
Abstract
The invention discloses a test system and method for a barreled-missile radio fuse.The system comprises a dynamic excitation device, an additional antenna additionally installed at the front end of a storage and transportation launching barrel, a main control computer, a command module, a microwave video composite module, a VXI bus computer case, a comprehensive adaptive composite module, a remote control cover, a signal processing circuit and a fuse excitation composite module.The signal processing circuit is connected with the signal end of the additional antenna.The method includes the steps of installing the additional antenna, connecting the additional antenna and the test system, installing a test cable, automatically testing the radio fuse and dismantling a feeder and the test cable.According to the system, the signal processing circuit is connected with the additional antenna through the feeder, a closed-loop link is formed, a front cover of the storage and transportation launching barrel does not need to be disassembled, it is avoided that the original storage environment of a guided missile is damaged, and efficiency is improved; by means of the method, the signal processing circuit, the feeder and the additional antenna are used for forming the signal link, response signals are transmitted to the main control computer to evaluate the performance of the radio fuse, and safe and efficient effects are achieved.
Description
Technical field
The present invention relates to Radio Fuze of Missile technical field of performance test, particularly relate to a kind of wound packages Radio Fuze of Missile test system and method for testing.
Background technology
Certain type guided missile adopts wound packages form, is placed at ordinary times in accumulating launching tube.Accumulating launching tube adopts metal material, makes the external wireless signal of telecommunication cannot be introduced in cylinder, thus protecting guided missile in cylinder to avoid being subject to the impact of external electromagnetic environment；Launching tube seals, and fills drying nitrogen, and air pressure is maintained at about 125kPa, provides good storage condition for guided missile.The electronic fuse that this guided missile adopts is positioned at guided missile front portion.For guaranteeing that electronic fuse is functional, it is necessary to it is carried out routine test.
Accumulating launching tube structure is divided into protecgulum, cylinder, bonnet；Electronic fuse is positioned at guided missile front portion, corresponding with accumulating launching tube protecgulum.Electronic fuse surface is provided with upper left, upper right, three antennas of going to the bottom, substantially according to about 120 ° be spaced centered by the guided missile longitudinal axis, each antenna beam centrage and guided missile longitudinal axis forward angle about 70 °, half-power beam width about 15 ° in the longitudinally asymmetric plane of guided missile, three antenna beams are being perpendicular in longitudinal axis plane and cover 360 °.
At present, the test of this wound packages Radio Fuze of Missile is based on special test system and realizes.This test system is the Auto-Test System of " vxi bus technology+virtual instrument technique ", also comprise the equipment such as main control computer, microwave video combination, fuse incentive combination, dynamic excitation device, antenna feeder cover, remote control cover, during test, system makes electronic fuse startup work, fuse to emission microwave pulse signal, antenna feeder cover inputs fuse incentive combination by 3 antennas after receiving；Fuse incentive combination, on the basis that microwave pulse signal is analyzed, produces corresponding analog echo signal, and output radiates to antenna feeder cover and to fuze antenna on bullet；Electronic fuse receives analog echo signal by antenna, and the response signal output produced after processing by analysis is to vxi bus instrument, by its performance according to the feature analysis judgement electronic fuse to response signal.
In existing test process, need first to unload accumulating launching tube protecgulum, by the antenna feeder enclosure in test system on fuse, by fuse incentive combination through antenna feeder cover to fuze antenna radiated radio frequency (RF) analog echo signal, received, by antenna feeder cover, the RF pulse signal that electronic fuse is sent by its antenna, it is achieved the test to electronic fuse simultaneously.After being completed, also need to reinstall accumulating launching tube protecgulum, drying nitrogen is filled to about 125kPa in accumulating launching tube, carry out airtight test, cause that test implementation process is loaded down with trivial details, required time is long, and in test process, guided missile departs from original storage condition, is likely to face the outstanding problem such as impact of complex electromagnetic environment.
Summary of the invention
The technical problem to be solved is to provide a kind of wound packages Radio Fuze of Missile test system, signal processing circuit is connected additional antenna by feeder line, form closed loop link, without disassembling accumulating launching tube protecgulum, avoid damage to the original storage condition of guided missile, improve efficiency, it is to avoid disassemble the impact by external electromagnetic environment of the rear electronic fuse.
The technical problem to be solved is to also provide for a kind of wound packages Radio Fuze of Missile method of testing, signal processing circuit is utilized to form signal link with feeder line and additional antenna, it is done directly the signal between test system and electronic fuse receive and launch, and response signal can be passed to main control computer to assess the performance of electronic fuse, safety, efficiently.
nullFor solving above-mentioned technical problem，The technical solution used in the present invention is: a kind of wound packages Radio Fuze of Missile test system，Including dynamic excitation device、It is installed at the additional antenna of accumulating launching tube front end、Main control computer、Command module、Microwave video composite module、Vxi bus cabinet、Comprehensive adapter combination module、Remote control cover、Signal processing circuit and fuse incentive combination module，Described signal processing circuit is connected with additional antenna signal end，Described main control computer and microwave video composite module are by means of GPIB two-way communication，Described command module is by means of IEEE1394 bus and main control computer two-way communication，Described command module and vxi bus cabinet two-way communication，Vxi bus cabinet and comprehensive adapter combination module two-way communication，Described comprehensive adapter combination module also supporting installation function composite module and and his like power supply，Described signal processing circuit and fuse incentive combination module two-way communication，Described fuse incentive combination module and comprehensive adapter combination module two-way communication，Described dynamic excitation device and comprehensive adapter combination are bi-directionally connected，Microwave video composite module and remote control cover are bi-directionally connected，Remote control cover controls end communication with accumulating launching tube，Described accumulating launching tube controls end and connects comprehensive adapter combination module by means of test cable.
Described signal processing circuit includes the first wave filter, the first amplifier, the first adjustable attenuator, circulator, the second wave filter, the second amplifier and the second adjustable attenuator that are sequentially connected in series, described circulator connects additional antenna by feeder line, first wave filter receives the signal of fuse incentive combination module, and the second adjustable attenuator signal output part connects fuse incentive combination module by signal input.
Described additional antenna is microstrip antenna array, installation SMA interface supporting with microstrip antenna array.
For solving above-mentioned technical problem, the present invention also adopts the technical scheme that: the method for a kind of wound packages Radio Fuze of Missile test, comprises the steps:
The first step: install additional antenna, installs microstrip antenna array in accumulating launching tube front end；
Second step: connect additional antenna and test system, use feeder line to connect the circulator of additional antenna and signal processing circuit；
3rd step: install test cable, uses test cable to connect accumulating launching tube and controls end and comprehensive adapter combination module；
4th step: electronic fuse is tested automatically；
5th step: remove feeder line and test cable, completes test.
Described 4th step includes:
1) system drive electronic fuse so that it is in running order；
2) signal processing circuit receives the microwave pulse signal that accumulating launching tube antenna is launched, and passes it to fuse incentive combination module；
3) fuse incentive combination module produces echo, and the echo of generation is passed to additional antenna, and electronic fuse forms response signal, and response signal passes to vxi bus and main control computer；
4) main control computer judges the performance of electronic fuse by the response signal received.
Adopt and have the beneficial effects that produced by technique scheme: signal processing circuit is connected additional antenna by feeder line by this system, form closed loop link, without disassembling accumulating launching tube protecgulum, avoid damage to the original storage condition of guided missile, improve efficiency, it is to avoid disassemble the impact by external electromagnetic environment of the rear electronic fuse.
Adopt and have the beneficial effects that produced by technique scheme: the method utilizes signal processing circuit to form signal link with feeder line and additional antenna, it is done directly the signal between test system and electronic fuse receive and launch, and response signal can be passed to main control computer to assess the performance of electronic fuse, safety, efficiently.
Accompanying drawing explanation
Fig. 1 is the systematic schematic diagram of the present invention；
Fig. 2 is signal processing circuit schematic diagram；
Fig. 3 is additional antenna mounting structure schematic diagram；
Fig. 4 is the left view of Fig. 3.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.
Elaborate a lot of detail in the following description so that fully understanding the present invention, but the present invention can also adopt other to be different from alternate manner described here to be implemented, those skilled in the art can do similar popularization when without prejudice to intension of the present invention, and therefore the present invention is not by the restriction of following public specific embodiment.
nullAs shown in Figure 1，The invention discloses a kind of wound packages Radio Fuze of Missile test system，Including dynamic excitation device、It is installed at the additional antenna of accumulating launching tube front end、Main control computer、Command module、Microwave video composite module、Vxi bus cabinet、Comprehensive adapter combination module、Remote control cover、Signal processing circuit (referring to accompanying drawing 2) and fuse incentive combination module，Described signal processing circuit is connected with additional antenna signal end，Described main control computer and microwave video composite module are by means of GPIB two-way communication，Described command module is by means of IEEE1394 bus and main control computer two-way communication，Described command module and vxi bus cabinet two-way communication，Vxi bus cabinet and comprehensive adapter combination module two-way communication，Described comprehensive adapter combination module also supporting installation function composite module and and his like power supply，Described signal processing circuit and fuse incentive combination module two-way communication，Described fuse incentive combination module and comprehensive adapter combination module two-way communication，Described dynamic excitation device and comprehensive adapter combination are bi-directionally connected，Microwave video composite module and remote control cover are bi-directionally connected，Remote control cover controls end communication with accumulating launching tube，Described accumulating launching tube controls end and connects comprehensive adapter combination module by means of test cable；Described signal processing circuit includes the first wave filter, the first amplifier, the first adjustable attenuator, circulator, the second wave filter, the second amplifier and the second adjustable attenuator that are sequentially connected in series, described circulator connects additional antenna by feeder line, first wave filter receives the signal of fuse incentive combination module, and the second adjustable attenuator signal output part connects fuse incentive combination module by signal input；Described additional antenna is microstrip antenna array, installation SMA interface supporting with microstrip antenna array.
In concrete application process, electronic fuse is launched signal and is received and be fed to process circuit through accumulating launching tube additional antenna (referring to accompanying drawing 3-4), through circulator input filter, filter the ambient interferences of other frequency, amplifier is amplified to suitable level, adjustable attenuator adjusts the entire gain of transmission channel so that the fuse transmitting signal entering test system is maintained at stable available horizontal；The pumping signal that fuse incentive combination produces through feeder line input processing circuit, after filtering, amplifications, the process such as Gain tuning, through circulator, feeder line to additional antenna so that the pumping signal that on bullet, fuze antenna receives is maintained at stable available horizontal.
After accumulating launching tube additional antenna, connecting test system and tested wound packages guided missile as follows is only needed: 1. utilize feeder line test system and process circuit to be coupled together during Radio Fuze of Missile test, also can keep being connected with test system (fuse incentive combination) by processing circuit, it is not necessary to all reconnect feeder line during test every time；2. 3 feeder lines are utilized to be connected processing circuit respectively with the SAM interface of 3 additional antenna on accumulating launching tube protecgulum.Compared to when former method, the equipment connection work in test is simplified.
The method that the invention also discloses the test of a kind of wound packages Radio Fuze of Missile, comprises the steps:
The first step: install additional antenna, installs microstrip antenna array in accumulating launching tube front end；
Second step: connect additional antenna and test system, use feeder line to connect the circulator of additional antenna and signal processing circuit；
3rd step: install test cable, uses test cable to connect accumulating launching tube and controls end and comprehensive adapter combination module；
4th step: electronic fuse is tested automatically；
5th step: remove feeder line and test cable, completes test.
Described 4th step includes:
1) system drive electronic fuse so that it is in running order；
2) signal processing circuit receives the microwave pulse signal that accumulating launching tube antenna is launched, and passes it to fuse incentive combination module；
3) fuse incentive combination module produces echo, and the echo of generation is passed to additional antenna, and electronic fuse forms response signal, and response signal passes to vxi bus and main control computer；
4) main control computer judges the performance of electronic fuse by the response signal received.
The method in concrete application process, first connecting test cable, then start test program and realize electronic fuse and automatically test, pull down test cable afterwards, namely complete test job.Compared to former testing process, eliminate the operation of the time and effort consuming such as gas charge and discharge, airtight test in the dismounting of accumulating launching tube protecgulum and cylinder, operating process is greatly simplified, operating time is greatly shortened, difficulty is decreased obviously, it is looser to require, the fixing only feeder line being connected with the SAM interface of additional antenna has special requirement, reduces the uncertainty in test process and insecurity to greatest extent.
Claims (5)
- null1. a wound packages Radio Fuze of Missile test system，It is characterized in that: include dynamic excitation device、It is installed at the additional antenna of accumulating launching tube front end、Main control computer、Command module、Microwave video composite module、Vxi bus cabinet、Comprehensive adapter combination module、Remote control cover、Signal processing circuit and fuse incentive combination module，Described signal processing circuit is connected with additional antenna signal end，Described main control computer and microwave video composite module are by means of GPIB two-way communication，Described command module is by means of IEEE1394 bus and main control computer two-way communication，Described command module and vxi bus cabinet two-way communication，Vxi bus cabinet and comprehensive adapter combination module two-way communication，Described comprehensive adapter combination module also supporting installation function composite module and and his like power supply，Described signal processing circuit and fuse incentive combination module two-way communication，Described fuse incentive combination module and comprehensive adapter combination module two-way communication，Described dynamic excitation device and comprehensive adapter combination are bi-directionally connected，Microwave video composite module and remote control cover are bi-directionally connected，Remote control cover controls end communication with accumulating launching tube，Described accumulating launching tube controls end and connects comprehensive adapter combination module by means of test cable.
- 2. wound packages Radio Fuze of Missile according to claim 1 test system, it is characterized in that: described signal processing circuit includes the first wave filter, the first amplifier, the first adjustable attenuator, circulator, the second wave filter, the second amplifier and the second adjustable attenuator that are sequentially connected in series, described circulator connects additional antenna by feeder line, first wave filter receives the signal of fuse incentive combination module, and the second adjustable attenuator signal output part connects fuse incentive combination module by signal input.
- 3. wound packages Radio Fuze of Missile according to claim 2 test system, it is characterised in that: described additional antenna is microstrip antenna array, installation SMA interface supporting with microstrip antenna array.
- 4. one kind adopts the method that test system as claimed in claim 1 carries out wound packages Radio Fuze of Missile test, it is characterised in that: comprise the steps:The first step: install additional antenna, installs microstrip antenna array in accumulating launching tube front end；Second step: connect additional antenna and test system, use feeder line to connect the circulator of additional antenna and signal processing circuit；3rd step: install test cable, uses test cable to connect accumulating launching tube and controls end and comprehensive adapter combination module；4th step: electronic fuse is tested automatically；5th step: remove feeder line and test cable, completes test.
- 5. the method for wound packages Radio Fuze of Missile according to claim 4 test, it is characterised in that: described 4th step includes:1) system drive electronic fuse so that it is in running order；2) signal processing circuit receives the microwave pulse signal that accumulating launching tube antenna is launched, and passes it to fuse incentive combination module；3) fuse incentive combination module produces echo, and the echo of generation is passed to additional antenna, and electronic fuse forms response signal, and response signal passes to vxi bus and main control computer；4) main control computer judges the performance of electronic fuse by the response signal received.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610188738.4A CN105758270B (en) | 2016-03-30 | 2016-03-30 | Wound packages Radio Fuze of Missile test system and method for testing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610188738.4A CN105758270B (en) | 2016-03-30 | 2016-03-30 | Wound packages Radio Fuze of Missile test system and method for testing |
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| CN105758270A true CN105758270A (en) | 2016-07-13 |
| CN105758270B CN105758270B (en) | 2017-06-16 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109104253A (en) * | 2018-09-28 | 2018-12-28 | 中国人民解放军陆军工程大学 | Missile Test System is remotely controlled cover calibrating installation |
| CN110855379A (en) * | 2019-10-30 | 2020-02-28 | 中国空空导弹研究院 | Passive forwarding system suitable for enclosed space |
| CN111664740A (en) * | 2020-05-28 | 2020-09-15 | 中国人民解放军32181部队 | Passive microwave communication adapter and system |
| CN111692930A (en) * | 2020-06-24 | 2020-09-22 | 北京宏动科技有限公司 | Universal radio fuse throwing test system |
| CN113377081A (en) * | 2021-06-08 | 2021-09-10 | 中国人民解放军陆军工程大学 | Simplified test module for missile equipment |
| CN113703010A (en) * | 2021-08-25 | 2021-11-26 | 上海机电工程研究所 | Pulse Doppler radar guided missile testing equipment and testing method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3942446A (en) * | 1974-09-06 | 1976-03-09 | The United States Of America As Represented By The Secretary Of The Army | Optical fuze and/or miss distance indicator |
| US5117230A (en) * | 1991-04-12 | 1992-05-26 | The United States Of America As Represented By The Secretary Of The Army | Electronic target radar simulator |
| CN101256230A (en) * | 2007-11-21 | 2008-09-03 | 北京理工大学 | Continuous wave chaos phase-modulation radio fuse detection system and demodulation method |
| CN103837868A (en) * | 2013-12-12 | 2014-06-04 | 江南机电设计研究所 | Side direction exploring antenna fuze signal processing device and method thereof |
| CN205482635U (en) * | 2016-03-30 | 2016-08-17 | 中国人民解放军军械工程学院 | Wound packages guided missile radio fuse test system |
-
2016
- 2016-03-30 CN CN201610188738.4A patent/CN105758270B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3942446A (en) * | 1974-09-06 | 1976-03-09 | The United States Of America As Represented By The Secretary Of The Army | Optical fuze and/or miss distance indicator |
| US5117230A (en) * | 1991-04-12 | 1992-05-26 | The United States Of America As Represented By The Secretary Of The Army | Electronic target radar simulator |
| CN101256230A (en) * | 2007-11-21 | 2008-09-03 | 北京理工大学 | Continuous wave chaos phase-modulation radio fuse detection system and demodulation method |
| CN103837868A (en) * | 2013-12-12 | 2014-06-04 | 江南机电设计研究所 | Side direction exploring antenna fuze signal processing device and method thereof |
| CN205482635U (en) * | 2016-03-30 | 2016-08-17 | 中国人民解放军军械工程学院 | Wound packages guided missile radio fuse test system |
Non-Patent Citations (1)
| Title |
|---|
| 孙宁等: "《某导弹引信自动化测试系统研制》", 《测试技术学报》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109104253A (en) * | 2018-09-28 | 2018-12-28 | 中国人民解放军陆军工程大学 | Missile Test System is remotely controlled cover calibrating installation |
| CN109104253B (en) * | 2018-09-28 | 2023-10-31 | 中国人民解放军陆军工程大学 | Remote control hood calibrating device of missile testing system |
| CN110855379A (en) * | 2019-10-30 | 2020-02-28 | 中国空空导弹研究院 | Passive forwarding system suitable for enclosed space |
| CN110855379B (en) * | 2019-10-30 | 2021-12-24 | 中国空空导弹研究院 | Passive forwarding system suitable for enclosed space |
| CN111664740A (en) * | 2020-05-28 | 2020-09-15 | 中国人民解放军32181部队 | Passive microwave communication adapter and system |
| CN111692930A (en) * | 2020-06-24 | 2020-09-22 | 北京宏动科技有限公司 | Universal radio fuse throwing test system |
| CN113377081A (en) * | 2021-06-08 | 2021-09-10 | 中国人民解放军陆军工程大学 | Simplified test module for missile equipment |
| CN113377081B (en) * | 2021-06-08 | 2022-11-04 | 中国人民解放军陆军工程大学 | Test system of guided missile control box |
| CN113703010A (en) * | 2021-08-25 | 2021-11-26 | 上海机电工程研究所 | Pulse Doppler radar guided missile testing equipment and testing method thereof |
| CN113703010B (en) * | 2021-08-25 | 2023-07-07 | 上海机电工程研究所 | Pulse Doppler radar guided missile testing equipment and testing method thereof |
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| CN105758270B (en) | 2017-06-16 |
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