CN112332069A - Patrol and fly guided missile front deck radar overall structure - Google Patents
Patrol and fly guided missile front deck radar overall structure Download PDFInfo
- Publication number
- CN112332069A CN112332069A CN202011199103.7A CN202011199103A CN112332069A CN 112332069 A CN112332069 A CN 112332069A CN 202011199103 A CN202011199103 A CN 202011199103A CN 112332069 A CN112332069 A CN 112332069A
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- radar
- missile
- servo
- antenna array
- module
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/1207—Supports; Mounting means for fastening a rigid aerial element
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- 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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/14—Supports; Mounting means for wire or other non-rigid radiating elements
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/281—Nose antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/36—Structural form of radiating elements, e.g. cone, spiral, umbrella; Particular materials used therewith
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/40—Engine management systems
Abstract
The invention relates to a general radar structure of a forecabin of a cruise missile, belonging to the technical field of miniaturization design of electronic equipment. Under the condition of meeting the electrical performance index, optimizing the shape and the size of an antenna mouth surface structure according to the corresponding section size enveloped by the missile hood and the pitching track of an antenna array surface, and overcoming the restriction of the missile hood envelope on the shape of a radar antenna array; the back of the antenna array surface is provided with a wire passing groove so that cables of the power distribution network and the T/R assembly can pass through and be fixed, and friction and interference of the cables to the antenna array surface during rotation are avoided; in order to facilitate the general butt joint assembly with the missile, an oblique angle is designed at one corner of the fan cover, so that the radar and the missile interface bolt can be conveniently detached. Each module in the host unit is 3U in size standard, and lockers are arranged on two sides of the module and fastened in the chassis in a plugging mode, so that the overall rigidity of the frame-type chassis is enhanced.
Description
Technical Field
The invention belongs to the technical field of miniaturization design of electronic equipment, and relates to a miniaturization overall structure design of a radar of a forecabin of a cruise missile.
Background
In recent years, with the advancement of technology and the rapid development of weapon systems, there has been an increasing demand for the missile-borne radar function. Missile carrying equipment has special requirements on structural design and mainly shows that: (1) due to the narrow space on the missile, the requirements on the space size and the weight of the radar are very strict, and the missile-borne radar needs to be designed in a small (micro) size and light weight mode. (2) The particularity of environmental conditions, particularly the severe conditions such as impact and vibration in the missile launching stage, so that the impact resistance and vibration resistance design of the missile-borne radar equipment is particularly important while the requirements on volume and weight are met;
disclosure of Invention
Technical problem to be solved
A certain radar is positioned in a nose cover of a front cabin of a cruise missile, the overall structural design can be carried out only in a limited space enveloped by the nose cover (the maximum section size: 230mm multiplied by 280mm), and the radar is required to have stronger vibration resistance. This severely restricts the overall layout, shape and weight of the radar apparatus, and the overall structure cannot be designed according to the usual structural form.
Technical scheme
A total structure of a radar of a nose cabin of a cruise missile is characterized by comprising a servo and antenna unit and a host unit, wherein the servo and antenna unit comprises a servo system and an antenna array surface, an active power component network (9), a T/R component, a wave control machine and a thermal control device are arranged on the back surface of the antenna array surface, the shape and the size of the structure of the antenna array surface are optimized according to the corresponding section size of an envelope space curve of the nose cabin hood and the pitching track of the antenna array surface, and the four corners of the antenna array surface are subjected to corner cut processing according to the envelope space curve; a wiring groove is designed on the back of the antenna array surface, so that cables of the power distribution network and the T/R assembly can pass through and be fixed; host unit use frame-type quick-witted case as the structure main part, its inside installation is frequently combined receiving module, signal processing module, data processing module, sampling timing module, and 3U modules are installed to its outside one side: the fan protection device comprises a power supply module I, a servo control module, a fan and a fan cover, wherein the shape of one corner of the fan cover is designed to be an oblique angle; the other side is provided with a power module II and a crystal oscillator, and the bottom of the case is provided with a motherboard; the 3U modules in the case are loaded into corresponding positions in a vertical plugging mode and are locked by the lockers on two sides of each module, so that the modules are electrically connected with a motherboard at the bottom of the case; two side surfaces of the case are respectively provided with a supporting structure extending towards two sides and used as a mounting seat of the servo and antenna unit; mounting holes are respectively arranged on two surfaces of the mounting seat and are used as mounting hole positions for connecting the servo unit and the antenna unit; the servo and antenna unit is connected with the main unit through a mounting screw on a rear servo bracket of the servo and antenna unit.
The wiring groove is 6mm multiplied by 3.5 mm.
The sizes of the mounting holes are 2 multiplied by phi 3.4 and 2 multiplied by phi 4.4.
The bevel angle is 35 degrees.
Advantageous effects
The invention adopts a method for designing the overall structure according to the envelope space of the head cover aiming at the restriction of the envelope space of the missile head cover on the structural layout design of the electronic equipment, overcomes the restriction of the envelope space of the front cabin head cover on the structural design, and has the advantages of space saving, convenient and reliable installation and weight reduction.
1. The radar complete machine is optimized into two large units, namely a servo and antenna unit and a host unit, has the design characteristics of high integration and light and small weight, and is more suitable for the characteristic requirement of light and small weight of the missile-borne radar;
2. independent radar antenna pedestal structures in the general structural design of the conventional radar are not adopted, but the supporting structures on two sides of the frame type case are used for replacing the antenna pedestal structures, so that the axial whole machine size of the radar is effectively reduced, and the total weight of the radar is reduced.
The invention has the following characteristics:
(1) the radar complete machine is optimized into two large units, namely a servo and antenna unit and a host unit, has the design characteristics of high integration and light and small weight, and is more suitable for the characteristic requirement of light and small weight of the missile-borne radar;
(2) independent radar antenna pedestal structures in the general structural design of the conventional radar are not adopted, but the supporting structures on two sides of the frame type case are used for replacing the antenna pedestal structures, so that the axial whole machine size of the radar is effectively reduced, and the total weight of the radar is reduced.
(3) Under the condition of meeting the electrical performance index, optimizing the shape and the size of an antenna mouth surface structure according to the corresponding section size enveloped by the missile hood and the pitching track of an antenna array surface, and overcoming the restriction of the missile hood envelope on the shape of a radar antenna array;
(4) each module in the host unit is 3U in size standard, and lockers are arranged on two sides of the module and fastened in the chassis in a plugging mode, so that the overall rigidity of the frame-type chassis is enhanced.
(5) A special 6mm multiplied by 3.5mm wire passing groove is designed at the back of the antenna array surface, so that a cable of the power distribution network and the T/R assembly can pass through and be fixed, and friction and interference of the cable to the antenna array surface during rotation are avoided.
(6) In order to facilitate the general butt assembly with the missile, the shape of the fan cover is designed to be an oblique angle of about 35 degrees, so that the radar and the missile interface bolt can be detached conveniently.
Drawings
FIG. 1 is a general layout diagram (partial section view) of a patrol missile forebay radar of the invention
FIG. 2 is a schematic diagram of the overall appearance of a patrol missile forebay radar of the invention
FIG. 3 is a schematic structural view (front side) of a servo and antenna unit of a patrol missile forebay radar of the invention
FIG. 4 is a schematic structural view (back side) of a servo and antenna unit of a patrol missile forebay radar of the invention
FIG. 5 is a schematic diagram of the back structure of an antenna array surface of a radar of a flight patrol missile forebay according to the invention
FIG. 6(a) schematic structural diagram of "radar for nose capsule of cruise missile" host unit of the invention
FIG. 6(b) a schematic diagram of a structure of a "radar for a nose capsule of a flying patrol missile" host unit according to the invention
FIG. 7A schematic structural view of a 3U module of a patrol missile forebay radar of the invention (A and B surfaces)
FIG. 8 is a schematic view of a mounting support structure of a radar of a forecabin of a cruise missile according to the invention
FIG. 9 is a schematic diagram of a radar assembly of a missile front cabin
1-radar, 2-front cabin hood, 3-mounting screw, 4-front cabin isolation frame, 5-servo and antenna unit, 6-host unit, 7-servo system, 8-antenna array, 9-power distribution network, 10-T/R component, 11-wave control machine, 12-thermal control device, 13-corner cut processing, 14-wiring groove, 15-chassis, 16-frequency comprehensive receiving module, 17-signal processing module, 18-data processing module, 19-sampling timing module, 20-power module I, 21-servo control module, 22-fan, 23-fan hood, 24-35 degree oblique angle, 25-power module II, 26-crystal oscillator, 27-mother board, 28-locker, 29-servo support, 30-mounting screws M3X12, 31-mounting screws M4X12, 32-mounting seat, 33-mounting hole phi 3.4 and 34-mounting hole phi 4.4.
Detailed Description
The invention will now be further described with reference to the following examples and drawings:
in order to solve the technical problems and ensure the realization of the technical indexes of the radar, a design method of adopting the overall structural form of the radar according to the curve envelope of the front cabin hood is determined according to theoretical calculation and model correction, and the limited space of the hood is utilized as far as possible.
The invention overcomes the restriction of missile hood envelope space on the structural layout design of electronic equipment, and adopts a method for carrying out overall structural design according to the hood envelope space.
The radar of a certain type is positioned in a nose cover (the maximum section size of the envelope of the nose cover: 230mm multiplied by 280mm) of a front cabin of a cruise missile, and the whole radar comprises a one-dimensional active phased antenna, a radio frequency front end, a signal processing system, a servo system, a secondary power supply and the like. In structural layout, the whole machine is divided into a host machine and an antenna unit by considering the space restriction of the envelope of the front cabin hood. The host unit takes a frame type case as a structural main body and comprises a radio frequency front end, a signal processing system, a servo system, a secondary power supply and other systems; the antenna unit comprises an antenna array surface, a power distribution network, a T/R component, a wave control machine, a thermal control device and the like. The main unit and the servo and antenna unit are connected through a servo bracket of the servo system to form a radar whole machine.
The layout of the overall structure is not easy because the space is very limited along the axis of the missile. Therefore, the invention does not adopt an independent antenna pedestal structure for supporting an antenna system in the general structure of the conventional radar, but designs the supporting structures extending outwards on the two sides of the frame type case, so that the frame type case replaces the antenna pedestal structure in the general structure of the conventional radar, thereby effectively reducing the size of the whole axial radar.
Under the condition of meeting the electrical performance index, the structural shape and size of the antenna opening surface are optimized according to the corresponding section size enveloped by the missile hood, and the four corners of the antenna array surface are subjected to corner cut processing according to an enveloping space curve.
In order to reduce the thickness of the antenna unit, a special 6mm × 3.5mm wire slot is designed on the antenna back plate, so that the cables of the power distribution network and the T/R assembly can pass through the wire slot and be fixed, and friction and interference of the cables to the rotation of the antenna array surface can be avoided.
A frame-type case of the host unit is internally provided with a frequency synthesis receiving module, a sampling timing module, a signal processing module and a data processing module, and both sides of the frame-type case are provided with a power supply module, a fan and the like. All modules in the frame-type case are designed to be 3U in size standard, and lockers are installed on two sides of the frame-type case and fastened in the case in a plugging mode, so that the overall rigidity of the frame-type case is enhanced.
The left side and the right side of the frame case of the main frame are respectively provided with an air inlet and an air outlet. In order to facilitate the butt joint assembly with the missile as a whole, the appearance of the air outlet cover is designed to be an oblique angle of about 35 degrees so as to facilitate the disassembly of the butt joint mounting bolt.
Referring to fig. 1, the invention is applied to a certain missile-borne product. A certain radar 1 is arranged in a front cabin hood (the maximum section size of the hood envelope: 230mm multiplied by 280mm)2 of a flying missile and is fixedly connected with a missile front cabin isolation frame 4 through 4M 5X16 mounting screws 3 at the entrance of the front cabin. The general layout of the present invention is shown in fig. 1.
The radar 1 is mainly divided into two parts, namely a servo and antenna unit 5 and a main unit 6, as shown in fig. 2.
The servo and antenna unit 5 mainly comprises a servo system 7 and an antenna array 8, as shown in fig. 3.
The back of the antenna array 8 is provided with an active sub-network 9, a T/R component 10, a wave control machine 11, a thermal control device 12 and the like, as shown in FIG. 4.
Optimizing the structural shape and size of the antenna array surface 8 according to the corresponding section size of the envelope space curve of the front cabin hood 2 and the pitching track of the antenna array surface 8, and performing corner cutting processing 13 on four corners of the antenna array surface 8 according to the envelope space curve; a special 6mm multiplied by 3.5mm wiring groove 14 is designed on the back of the antenna array surface 8, so that cables of the power distribution network 9 and the T/R assembly 10 can pass through and be fixed, and friction and interference of the cables to the antenna array surface 8 during rotation are avoided. The antenna array 8 back structure is outlined in fig. 5.
The main unit 6 takes a frame type chassis 15 as a structural main body, 4 3U modules are installed in the main unit, the 3U modules are respectively a frequency synthesis receiving module 16, a signal processing module 17, a data processing module 18 and a sampling timing module 19, a power supply module I20, a servo control module 21, a fan 22, a fan cover 23 and the like are installed on one outer side of the main unit, and the shape of one corner of the fan cover is designed to be an oblique angle 24 of about 35 degrees. The other side is provided with a second power module 25 and a crystal oscillator 26, and the bottom of the chassis 15 is provided with a motherboard 27, as shown in fig. 6(a) and 6 (b).
The 3U module inside the chassis 15 is loaded into a corresponding position by a vertical plugging mode and locked by the lockers 28 at both sides of each module, thereby realizing the electrical connection with the motherboard 27 at the bottom of the chassis 15, and the structural shape of the 3U module is as shown in fig. 7.
The two side surfaces of the case 15 are respectively provided with a supporting structure extending towards the two sides and used as a mounting seat 32 of the servo and antenna unit 5. Mounting holes 2 × Φ 3.433 and 2 × Φ 4.434 are provided on both surfaces of the mounting base 32 as mounting holes for connecting the servo and antenna unit 5, respectively, as shown in fig. 8.
The servo and antenna unit 5 is connected with the main unit 6 by 4 mounting screws M3 × 1230 and 4 mounting screws M4 × 1231 on the rear servo bracket 29 thereof to form the radar 1, as shown in fig. 9.
Claims (4)
1. The general structure of the radar of the nose capsule of the cruise missile is characterized by comprising a servo and antenna unit (5) and a host unit (6), wherein the servo and antenna unit (5) comprises a servo system (7) and an antenna array surface (8), an active power sub-network (9), a T/R component (10), a wave control machine (11) and a thermal control device (12) are arranged on the back surface of the antenna array surface (8), the structural shape and the size of the antenna array surface (8) are optimized according to the corresponding section size of an envelope space curve of a nose cap (2) of the nose capsule and the pitching track of the antenna array surface (8), and four corners of the antenna array surface (8) are subjected to corner cut (13) processing according to the envelope space curve; a wiring groove (14) is designed on the back of the antenna array surface (8), so that cables of the power distribution network (9) and the T/R component (10) can pass through and be fixed; host computer unit (6) use frame-type quick-witted case (15) as the structure subject, its inside installation is frequently combined receiving module (16), signal processing module (17), data processing module (18), sampling timing module (19), 3U modules are installed to its outside one side: the fan protection device comprises a power supply module I (20), a servo control module (21), a fan (22) and a fan cover (23), wherein the shape of one corner of the fan cover is designed to be an oblique angle (24); the other side is provided with a power module II (25) and a crystal oscillator (26), and the bottom of the case (15) is provided with a motherboard (27); 3U modules in the case (15) are loaded into corresponding positions in a vertical plugging mode and are locked by lockers (28) on two sides of each module, so that the modules are electrically connected with a motherboard (27) at the bottom of the case (15); two side surfaces of the case (15) are respectively provided with a supporting structure extending towards two sides and used as a mounting seat (32) of the servo and antenna unit (5); mounting holes are respectively arranged on two surfaces of the mounting seat (32) and are used as mounting hole positions for connecting the servo and antenna unit (5); the servo and antenna unit (5) is connected with the main unit (6) through a mounting screw on a rear servo bracket (29) of the servo and antenna unit.
2. The general structure of the patrolling missile forecabin radar as claimed in claim 1, wherein the wiring groove (14) is 6mm x 3.5 mm.
3. The general structure of the patrolling missile forecabin radar as claimed in claim 1, wherein the sizes of the mounting holes are 2 x Φ 3.4 and 2 x Φ 4.4.
4. A boomerang missile forebay radar as a whole in claim 1 characterised by the fact that the angle of inclination (24) is 35 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011199103.7A CN112332069B (en) | 2020-11-01 | 2020-11-01 | Patrol and fly guided missile front deck radar overall structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011199103.7A CN112332069B (en) | 2020-11-01 | 2020-11-01 | Patrol and fly guided missile front deck radar overall structure |
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| Publication Number | Publication Date |
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| CN112332069A true CN112332069A (en) | 2021-02-05 |
| CN112332069B CN112332069B (en) | 2022-07-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970276A (en) * | 2021-11-16 | 2022-01-25 | 天津爱思达新材料科技有限公司 | High-strength connecting assembly for carbon fiber composite material |
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| CN113970276A (en) * | 2021-11-16 | 2022-01-25 | 天津爱思达新材料科技有限公司 | High-strength connecting assembly for carbon fiber composite material |
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| CN112332069B (en) | 2022-07-05 |
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