CN103471474B - A kind of miniaturized radar fuze structure - Google Patents
A kind of miniaturized radar fuze structure Download PDFInfo
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- CN103471474B CN103471474B CN201310416115.4A CN201310416115A CN103471474B CN 103471474 B CN103471474 B CN 103471474B CN 201310416115 A CN201310416115 A CN 201310416115A CN 103471474 B CN103471474 B CN 103471474B
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- millimeter wave
- wave transceiving
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- video amplifier
- transceiving assembly
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Abstract
The invention discloses a kind of miniaturized radar fuze structure, comprise transmitting antenna, millimeter wave transceiving assembly, the video amplifier, number of signals WP, reception antenna; Described millimeter wave transceiving assembly, the video amplifier, number of signals WP are cylindrical, and millimeter wave transceiving assembly, video amplifier number of signals WP connect fastening in circumferencial direction symmetry successively between any two; Described transmitting antenna, reception antenna are fastened on the outer surface of millimeter wave transceiving assembly, the video amplifier, number of signals WP; Transmitting antenna and reception antenna adopt cruciform symmetry configuration.The present invention can ensure the aerodynamic configuration of cabin body, and greatly can improve space availability ratio again, compact overall structure, space availability ratio is high, achieves the miniaturization of fuse structure, lightweight, modularization, meets the developing direction of Modern weapon system.
Description
Technical field
The present invention relates to a kind of miniaturized radar fuze structure.
Background technology
Fuse is the important component part in guided missile, is the final actuating unit that guided missile plays end effect, and its effect success or failure directly determine the success or failure of guided missile system and Target Countermeasure.Each part of fuse is mainly firmly connected into an entirety by fuse structure design, it is made to form a good aerodynamic configuration, and there is enough intensity, rigidity and stability, can bear and be delivered in the various load that may run in the whole life cycle of guided missile.Each part of fuse is fastened on framework by main employing of current fuse structure design, is then fastened in the body of cabin by frame installation.
Although can meet its function according to the method for designing of current fuse structure, under same aerodynamic configuration constraint, its space availability ratio is not high yet; Otherwise, under the condition meeting said function, will certainly large volume be added, thus cause quality to increase.This version can not adapt to Modern weapon system miniaturization, lightweight, high-performance, modular developing direction.
Summary of the invention
For solving the defect existed in prior art, the invention provides a kind of miniaturized radar fuze structure, this miniaturized radar fuze structure can improve space availability ratio under the aerodynamic configuration condition of regulation, realizes the miniaturization of fuse structure, lightweight, high-performance, modularization.
The present invention is achieved by the following technical programs:
A kind of miniaturized radar fuze structure, comprises transmitting antenna, millimeter wave transceiving assembly, the video amplifier, number of signals WP, reception antenna; Described millimeter wave transceiving assembly, the video amplifier, number of signals WP are cylindrical, and millimeter wave transceiving assembly, video amplifier number of signals WP connect fastening in circumferencial direction symmetry successively between any two; Described transmitting antenna, reception antenna are fastened on the outer surface of millimeter wave transceiving assembly, the video amplifier, number of signals WP; Transmitting antenna and reception antenna adopt cruciform symmetry configuration.
The feed mouth of the transmitting and receiving port of described millimeter wave transceiving assembly, transmitting antenna and reception antenna is waveguiding structure.
The signal of described reception antenna, transmitting antenna and millimeter wave transceiving assembly is fed to and adopts waveguide direct-connected.
The waveguide mouth front-back staggered of described transmitting antenna and reception antenna is installed.
Also comprise nose cone, nose cone is anchored on the outer surface of millimeter wave transceiving assembly at circumferencial direction.
Described nose cone adopts the heat proof material that can bear the stationary point high temperature of 700 DEG C.
Also comprise the case on the outer surface being enclosed within millimeter wave transceiving assembly, the video amplifier and number of signals WP, case is fastened on circumference symmetry direction.
Described fastening mode is for be undertaken fastening by screw.
Beneficial effect of the present invention is: the aerodynamic configuration that can ensure cabin body, greatly can improve space availability ratio again, compact overall structure, space availability ratio is high, achieve the miniaturization of fuse structure, lightweight, modularization, meet the developing direction of Modern weapon system.
Accompanying drawing explanation
Fig. 1 is top view of the present invention;
Fig. 2 is the A-A face sectional view of Fig. 1;
In figure: 1-nose cone, 3-transmitting antenna, 4-case, 5-millimeter wave transceiving assembly, the 6-video amplifier, 7-reception antenna, 9-digital processing unit.
Detailed description of the invention
Technical scheme of the present invention is further described below in conjunction with accompanying drawing, but described in claimed scope is not limited to.
Miniaturized radar fuze structure as a kind of in Fig. 1 to Fig. 2, comprises transmitting antenna 3, millimeter wave transceiving assembly 5, the video amplifier 6, number of signals WP 9, reception antenna 7; Described millimeter wave transceiving assembly 5, the video amplifier 6, number of signals WP 9 are cylindrical, and millimeter wave transceiving assembly 5, the video amplifier 6 number of signals WP 9 connect fastening in circumferencial direction symmetry successively between any two; Described transmitting antenna 3, reception antenna 7 are fastened on the outer surface of millimeter wave transceiving assembly 5, the video amplifier 6, number of signals WP 9; Transmitting antenna 3 and reception antenna 7 adopt cruciform symmetry to configure.
Described millimeter wave transceiving assembly 5, the video amplifier 6, number of signals WP 9 are columniform design and farthest can utilize radial space; Transmitting antenna 3 and reception antenna 7 adopt cruciform symmetry configuration to be then conducive to wave cover 360 ° of spaces, antenna E face.
The feed mouth of the transmitting and receiving port of described millimeter wave transceiving assembly 5, transmitting antenna 3 and reception antenna 7 is waveguiding structure.
Described reception antenna 7, transmitting antenna 3 are fed to the signal of millimeter wave transceiving assembly 5 and adopt waveguide direct-connected.
Antenna adopts waveguide to connect, and waveguide mouth directly docks with transmitting-receiving subassembly, saves high frequency transmitting-receiving cable and connector.
The waveguide mouth front-back staggered of described transmitting antenna 3 and reception antenna 7 is installed.The transmitting and receiving partial design space that transmitting-receiving subassembly is convenient in the design of waveguide mouth front-back staggered is relatively independent, is conducive to ensureing receive-transmit isolation.
Also comprise nose cone 1, nose cone 1 is anchored on the outer surface of millimeter wave transceiving assembly 5 at circumferencial direction.This setting can ensure the aerodynamic configuration of guided missile.
Described nose cone 1 adopts the heat proof material that can bear the stationary point high temperature of 700 DEG C.
Also comprise the case 4 on the outer surface being enclosed within millimeter wave transceiving assembly 5, the video amplifier 6 and number of signals WP 9, case 4 is fastened on circumference symmetry direction.
The setting be enclosed within outside assembly of nose cone, case can ensure physical protection and the electromagnetic shielding of cabin body aerodynamic configuration and internal signal
Described fastening mode is for be undertaken fastening by screw.
The present invention has broken the conventional design method of framework fixed Combination, adopt interconnective mode between combination, power line between combination and holding wire are from the cabling of wall grooving out of my cabin, connect between line without connector, with switching soldering of printed boards, both the space that general connector takies had been eliminated, and the detection to M signal during convenient debugging.
Claims (8)
1. a miniaturized radar fuze structure, comprise transmitting antenna (3), millimeter wave transceiving assembly (5), the video amplifier (6), number of signals WP (9), reception antenna (7), it is characterized in that: described millimeter wave transceiving assembly (5), the video amplifier (6), number of signals WP (9) are cylindrical, and millimeter wave transceiving assembly (5), the video amplifier (6), number of signals WP (9) connect fastening in circumferencial direction symmetry successively between any two; Described transmitting antenna (3), reception antenna (7) are fastened on the outer surface of millimeter wave transceiving assembly (5), the video amplifier (6), number of signals WP (9); Transmitting antenna (3) and reception antenna (7) adopt cruciform symmetry configuration.
2. a kind of miniaturized radar fuze structure as claimed in claim 1, is characterized in that: the feed mouth of the transmitting and receiving port of described millimeter wave transceiving assembly (5), transmitting antenna (3) and reception antenna (7) is waveguiding structure.
3. a kind of miniaturized radar fuze structure as claimed in claim 2, is characterized in that: described reception antenna (7), transmitting antenna (3) are fed to the signal of millimeter wave transceiving assembly (5) and adopt waveguide direct-connected.
4. a kind of miniaturized radar fuze structure as claimed in claim 1, is characterized in that: the waveguide mouth front-back staggered of described transmitting antenna (3) and reception antenna (7) is installed.
5. a kind of miniaturized radar fuze structure as claimed in claim 1, it is characterized in that: also comprise nose cone (1), nose cone (1) is anchored on the outer surface of millimeter wave transceiving assembly (5) at circumferencial direction.
6. a kind of miniaturized radar fuze structure as claimed in claim 5, is characterized in that: described nose cone (1) adopts the heat proof material that can bear the stationary point high temperature of 700 DEG C.
7. a kind of miniaturized radar fuze structure as claimed in claim 1, it is characterized in that: also comprise the case (4) on the outer surface being enclosed within millimeter wave transceiving assembly (5), the video amplifier (6) and number of signals WP (9), case (4) is fastened on circumference symmetry direction.
8. the miniaturized radar fuze structure of the one as described in claim 1,5 or 7, is characterized in that: described fastening mode is for be undertaken fastening by screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310416115.4A CN103471474B (en) | 2013-09-12 | 2013-09-12 | A kind of miniaturized radar fuze structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310416115.4A CN103471474B (en) | 2013-09-12 | 2013-09-12 | A kind of miniaturized radar fuze structure |
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| Publication Number | Publication Date |
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| CN103471474A CN103471474A (en) | 2013-12-25 |
| CN103471474B true CN103471474B (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310416115.4A Active CN103471474B (en) | 2013-09-12 | 2013-09-12 | A kind of miniaturized radar fuze structure |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105004228B (en) * | 2015-08-11 | 2016-07-06 | 成都天奥测控技术有限公司 | Millimeter wave influence fuse detector front end method of testing and tester |
| CN105716480B (en) * | 2016-02-04 | 2017-12-22 | 西安电子科技大学 | Radar fuze and its design method based on radio frequency agile transceiver |
| CN107782206A (en) * | 2017-11-22 | 2018-03-09 | 中国工程物理研究院电子工程研究所 | A kind of aerial guided bomb fuse and its environmental information recognition methods based on mems accelerometer |
| CN109974543A (en) * | 2019-04-28 | 2019-07-05 | 芜湖博高光电科技股份有限公司 | A kind of novel millimeter wave closely feels fuse front end |
| CN112629345B (en) * | 2020-12-10 | 2023-08-01 | 中国人民解放军32181部队 | Millimeter wave fuze auxiliary integral manufacturing total system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4495851A (en) * | 1981-12-18 | 1985-01-29 | Brown, Boveri & Cie Ag | Apparatus for setting and/or monitoring the operation of a shell fuse or detonator |
| US5325784A (en) * | 1993-02-01 | 1994-07-05 | Motorola, Inc. | Electronic fuze package and method |
| DE102005039902A1 (en) * | 2005-02-04 | 2006-08-10 | Rheinmetall Waffe Munition Gmbh | Device for increasing the precision of tail-wing stabilized ammunition |
| US7417582B2 (en) * | 2004-10-22 | 2008-08-26 | Time Domain Corporation | System and method for triggering an explosive device |
| US8026465B1 (en) * | 2009-05-20 | 2011-09-27 | The United States Of America As Represented By The Secretary Of The Navy | Guided fuse with variable incidence panels |
| CN203501916U (en) * | 2013-09-12 | 2014-03-26 | 贵州航天电子科技有限公司 | Radar fuse structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6834591B2 (en) * | 1998-12-23 | 2004-12-28 | Bae Systems Plc | Proximity fuze |
| US7121210B2 (en) * | 2003-02-18 | 2006-10-17 | Kdi Precision Products, Inc. | Accuracy fuze for airburst cargo delivery projectiles |
-
2013
- 2013-09-12 CN CN201310416115.4A patent/CN103471474B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4495851A (en) * | 1981-12-18 | 1985-01-29 | Brown, Boveri & Cie Ag | Apparatus for setting and/or monitoring the operation of a shell fuse or detonator |
| US5325784A (en) * | 1993-02-01 | 1994-07-05 | Motorola, Inc. | Electronic fuze package and method |
| US7417582B2 (en) * | 2004-10-22 | 2008-08-26 | Time Domain Corporation | System and method for triggering an explosive device |
| DE102005039902A1 (en) * | 2005-02-04 | 2006-08-10 | Rheinmetall Waffe Munition Gmbh | Device for increasing the precision of tail-wing stabilized ammunition |
| US8026465B1 (en) * | 2009-05-20 | 2011-09-27 | The United States Of America As Represented By The Secretary Of The Navy | Guided fuse with variable incidence panels |
| CN203501916U (en) * | 2013-09-12 | 2014-03-26 | 贵州航天电子科技有限公司 | Radar fuse structure |
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| Publication number | Publication date |
|---|---|
| CN103471474A (en) | 2013-12-25 |
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