CN204188081U - Command & control integrated apparatus housing and air defence missile command & control device - Google Patents
Command & control integrated apparatus housing and air defence missile command & control device Download PDFInfo
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- CN204188081U CN204188081U CN201420603708.1U CN201420603708U CN204188081U CN 204188081 U CN204188081 U CN 204188081U CN 201420603708 U CN201420603708 U CN 201420603708U CN 204188081 U CN204188081 U CN 204188081U
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- command
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- installing port
- mounting box
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- 238000012545 processing Methods 0.000 claims abstract description 21
- 230000010365 information processing Effects 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 abstract description 3
- 238000004891 communication Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000007123 defense Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- HCOLPNRPCMFHOH-UHFFFAOYSA-N Prodigiosin Natural products CCCCCC1C=C(C=C/2N=C(C=C2OC)c3ccc[nH]3)N=C1C HCOLPNRPCMFHOH-UHFFFAOYSA-N 0.000 description 1
- XHCLAFWTIXFWPH-UHFFFAOYSA-N [O-2].[O-2].[O-2].[O-2].[O-2].[V+5].[V+5] Chemical compound [O-2].[O-2].[O-2].[O-2].[O-2].[V+5].[V+5] XHCLAFWTIXFWPH-UHFFFAOYSA-N 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- DMBHHRLKUKUOEG-UHFFFAOYSA-N diphenylamine Chemical compound C=1C=CC=CC=1NC1=CC=CC=C1 DMBHHRLKUKUOEG-UHFFFAOYSA-N 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000004973 liquid crystal related substance Substances 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- TWFGRJUTAULJPZ-USZBIXTISA-N prodigiosin Chemical compound N1=C(C)C(CCCCC)=C\C1=C/C1=NC(C=2[N]C=CC=2)=C[C]1OC TWFGRJUTAULJPZ-USZBIXTISA-N 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 229910001935 vanadium oxide Inorganic materials 0.000 description 1
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Abstract
The utility model relates to a kind of command & control integrated apparatus housing and air defence missile command & control device, comprises shell, and the front end of shell is provided with photoelectric subassembly installing port, and the upper surface of sheath top plate is provided with location time service assembly installing port; Sheath top plate has linking arm by the first chain connection, and shell is connected with fixed station, and the stage casing of shell side is provided with the button mounting box for installing button by the 3rd hinge, and button mounting box can fold or launch; Enclosure is provided with interface processing circuitry plate erecting bed and information-processing circuit plate erecting bed.Linking arm, fixed station all can fold or launch; Housing compact of the present utility model, volume are little, lightweight, and installation is removed debit and just, by a relatively large margin reduced time in wartime, improves air defence missile fighting efficiency.
Description
Technical field
The utility model relates to air defence missile command & control field, is specifically related to a kind of command & control integrated apparatus housing and air defence missile command & control device.
Background technology
At present, portable air defense missile Command automation system individual equipment is generally made up of parts such as operating grip, processor, Helmet Mounted Display, gunsight, missile orientation devices, although this individual equipment system solve portable air defense missile under battle conditions in be difficult to find target, target homing guidance, cooperative air-defense, in problems such as night and poor visibility situation cannot use, but the structure disperses of this system components, volume are comparatively large, installation is removed between the time receiving long, cause its battlefield bad adaptability.Therefore, study a kind of command & control integrated apparatus housing and air defence missile command & control device, it is very important for being little, the portable system of volume for making the system integration thus improving its battlefield adaptability.
Summary of the invention
For the defect existed in above-mentioned prior art or deficiency, the purpose of this utility model is, provides a kind of command & control integrated apparatus housing.
In order to realize above-mentioned task, the utility model adopts following technical scheme to be solved.
A kind of command & control integrated apparatus housing, comprise shell, the front end of described shell is provided with photoelectric subassembly installing port; The upper surface of sheath top plate is provided with location time service assembly installing port; The rear edge of sheath top plate has linking arm by the first chain connection, and linking arm can launch above the upper surface of shell or with the direction away from case nose along with turning folding of the first hinge; There is the fixed station for fixing display the rear end of shell side by the second chain connection, and fixed station can be launched in the groove in shell side face or with the direction away from groove by turning folding of the second hinge; The stage casing of shell side is provided with the button mounting box for installing button by the 3rd hinge, and button mounting box triple hingedly can turn folding in shell side face or launch with the direction away from housing along with; Button mounting box hollow, its lateral surface has multiple button installing port; Enclosure is provided with interface processing circuitry plate erecting bed and information-processing circuit plate erecting bed;
Further, described shell side is provided with opening, this opening is coated with dismountable opening cover plate.
Further, described outer casing bottom is provided with dovetail groove or other mechanical interfaces.
Further, described shell is provided with 2 air plugs.
Further, described shell is provided with power switch installing port.
Another object of the present utility model is, a kind of air defence missile command & control device is provided, comprises integrated command device housing, photoelectric subassembly, location time service assembly, interface processing circuitry plate, information-processing circuit plate, electronic compass, display, button and guidance panel; Wherein, photoelectric subassembly is arranged on photoelectric subassembly installing port; Time service assembly in location is arranged on location time service assembly installing port; Interface processing circuitry plate and information-processing circuit plate are installed on interface processing circuitry plate erecting bed in the enclosure and information-processing circuit plate erecting bed respectively; Electronic compass is arranged on the end of linking arm; Display is arranged on the rear end of fixed station; Button to be arranged in button mounting box and from button installing port; Guidance panel is arranged on button mounting box medial surface.Photoelectric subassembly, display link information treatment circuit plate; Location time service assembly, electronic compass, button and guidance panel connecting interface treatment circuit plate, information-processing circuit plate is connected by serial ports with interface processing circuitry plate.
The utility model has the advantage of:
Command & control integrated shell of the present utility model by arranging the parts such as mounting interface, linking arm, erecting bed and installing plate on shell, can realize each component integration of air defence missile command & control device on a shell, make becoming one of device whole height structure, can be portable, improve the battlefield adaptability of device.In addition, them are enable to be folded to the outer surface of shell by the hinge on linking arm, erecting bed and installing plate.To sum up, housing compact of the present utility model, volume are little, lightweight, and installation is removed debit and just, by a relatively large margin reduced time in wartime, improves air defence missile fighting efficiency.
Accompanying drawing explanation
The structural representation of the deployed condition of the integrated command device housing of Fig. 1.
The structural representation of the folded position of the integrated command device housing of Fig. 2.
Fig. 3 is the structural representation of the deployed condition of air defence missile command & control integrated apparatus.
Fig. 4 is the structural representation of the folded position of air defence missile command & control integrated apparatus.
Fig. 5 is the connection block diagram of air defence missile command & control integrated apparatus.
Fig. 6 is the inner buttons guidance panel layout of air defence missile command & control integrated apparatus.
Each label implication in figure: 1-photoelectric subassembly installing port, 2-locates time service assembly installing port, 3-shell, 4-first hinge, 5-linking arm, 6-fixed station, 7, button mounting box, 8-first hinge, 9-photoelectric subassembly, 10-locates time service assembly, 11-electronic compass, 12-display, 13-button, 31-opening cover plate, 71-button installing port.
Detailed description of the invention
Embodiment 1
Follow the technical solution of the utility model, the structure of the command & control integrated apparatus housing of the present embodiment as shown in Figure 1 and Figure 2, comprise shell 3, the front end of shell 3 is provided with photoelectric subassembly installing port 1, be provided with multiple bolt hole around photoelectric subassembly installing port 1, bolt hole is used for, by bolt, photoelectric subassembly is fixed on photoelectric subassembly installing port 1.
The upper surface of shell 3 top board is provided with location time service assembly installing port 2, for installing location time service assembly.
The rear edge of shell 3 top board is connected with the linking arm 5 for installing electronic compass by the first hinge 4, and linking arm 5 can launch above the upper surface of shell 3 or with the direction away from shell 3 front end along with turning folding of the first hinge 8; During work, the housing of the present embodiment is connected on guided missile, linking arm 5 launches with the direction away from shell 3 front end, such structural design can make to be arranged on the guided missile head of electronic compass away from shell 3 front of linking arm 5 end, thus the magnetic reducing guided missile head is on the impact of electronic compass orientation.
The rear end of shell 3 side is connected with the fixed station 6 for fixing display by the second hinge 8, and fixed station 6 can be launched in the groove of shell 3 side or with the direction away from groove by turning folding of the second hinge 8.When the setting of fixed station 6 is to meet in working order, operating personnel are convenient to observation display.
The stage casing of shell 3 side is provided with the button mounting box 7 for installing button by the 3rd hinge, and button mounting box 7 triple hingedly can turn folding in shell 3 side or launch with the direction away from housing along with; Button mounting box 7 hollow, its lateral surface has multiple button installing port 71, its quantity is identical with the key number of employing.
Shell 3 inside is provided with interface processing circuitry plate erecting bed and information-processing circuit plate erecting bed, and they are for mounting interface treatment circuit plate and information-processing circuit plate.Meanwhile, shell 3 side is provided with opening, this opening is coated with dismountable opening cover plate 31, can be installed and arrange the interface processing circuitry plate and information-processing circuit plate that are arranged on shell 3 inside by opening.
Be provided with dovetail groove or other mechanical interfaces bottom shell 3, fixedly mount on guided missile time easy to use.
Shell 3 is provided with 2 air plugs, is respectively used to connect battery, communication equipment or external monitor.
Shell 3 is provided with power switch installing port.
As shown in Figure 1, wherein, linking arm 5, fixed station 6 and button mounting box 7 are all in deployed condition by the rotation of self hinge to the integrated command device housing of the present embodiment state in the course of the work.After end-of-job, be carried status of processes as shown in Figure 2, linking arm 5, fixed station 6 and button mounting box 7 are all folded in the outer surface of shell 3, are easy to carry.
Embodiment 2
Follow the technical solution of the utility model, the structure of the air defence missile command & control device of the present embodiment as shown in Figure 3 and Figure 4, comprises integrated command device housing, photoelectric subassembly 9, location time service assembly 10, interface processing circuitry plate, information-processing circuit plate, electronic compass 11, display 12, button 13 and guidance panel; Wherein, photoelectric subassembly 9 is arranged on photoelectric subassembly installing port 1; Location time service assembly 10 is arranged on location time service assembly installing port 2; Interface processing circuitry plate and information-processing circuit plate are arranged on interface processing circuitry plate erecting bed in shell 3 and information-processing circuit plate erecting bed respectively; Electronic compass 11 is arranged on the end of linking arm 5; Display 12 is arranged on the rear end of fixed station 6; Button to be arranged in button mounting box 7 and from button installing port 71; Guidance panel is arranged on button mounting box 7 medial surface.Shell 3 is provided with power supply instruction, indicating fault, communication indicates 3 indicator lamps, for corresponding display power supply, fault and communication instruction situation.Power switch is arranged on power switch installing port, and power switch adopts light touch type button.
Photoelectric subassembly 9, display 12 link information treatment circuit plate; Location time service assembly 10, electronic compass 11, button 13 and guidance panel connecting interface treatment circuit plate.
In air defence missile command & control integrated apparatus, the selection of each parts is as follows:
Photoelectric subassembly 9 is made up of opticator and movement.Opticator is focal length is 50mm, and F-number is the infrared lens of 0.8; Movement is array is 384 × 288, and pixel dimension is 25 μm × 25 μm, the vanadium oxide infrared image sensor of response wave band 8 ~ 14 μm, and photoelectric subassembly exports the PAL/NTSC infrared image that frame frequency is 50Hz.The outer rear of photoelectric subassembly arranges 4 buttons: Menu key, upturning key, downturning key, check key, regulate for photoelectric subassembly.
The location time service assembly 10BDM610 Big Dipper/GPS dual system four frequency circuit plate and OSAn10854B position receiver antenna are formed.Adopt BDS B1/GPS L1 frequency, can civil signal be received when not installing sector card, after sector card is installed, military frequency can be received.The positional information of location time service assembly 10 for providing precision to be less than 20m, precision is less than 1us time service information.
Interface processing circuitry plate is made up of 2 pieces of HY-STM32F4 ×× core144 circuit boards, and as shown in Figure 5, HY-STM32F4 ×× core144 circuit board has 2 SPI interfaces, 3 serial line interfaces, 1 external signal interface and power interfaces.The 2nd SPI interface on 2 pieces of circuit boards is connected by cross cable, and power interface connects external cell by power line.A SPI interface on first circuit board is connected by cable with the button of message processing module, and the first serial line interface is connected by RS232 cable with location time service assembly.The first serial line interface on second circuit board is connected by RS232 cable with missile orientation assembly, second serial line interface is connected by RS232 cable with the liquid crystal display assembly on key-press module, and external signal interface is connected with external interface by the button of cable with key-press module.Interface processing module achieve radio station parameter configuration and receive with the communication of higher level's command system, missile orientation device data receiver, locator data, button data process, Campaign Process data record, simulated training data genaration and power management function.
Information-processing circuit plate adopts IECTEK-DM6437 circuit board, circuit board there are USB interface, PAL interface, SPI interface and power interface, USB interface connects display module by vision cable, PAL interface connects photoelectric subassembly by coaxial cable, SPI interface is connected to the first circuit board of interface processing circuitry plate by cable, and power interface connects external cell by power line.Information-processing circuit plate realizes superposing and output display function of data-signal and photosignal.
Display 12 adopts the OLED display of focal optical eyepiece and resolution ratio 800 × 600, for showing empty feelings early warning and shooting navigational figure.Display gunsight governor motion adopts 1 grade of ball head structure, and individual soldier can regulate the position of the relative eyes of display easily according to the actual conditions of oneself, the image of viewing display clearly.Display aims at prodigiosin adjustment diopter, and it with rubber eyeshade, can block extraneous light at rear side.
Guidance panel is used for the man-machine interaction between individual soldier and device.As shown in Figure 6, guidance panel is provided with 20 buttons, 4, outside, 16, inner side.4, outside button is used for attitude/shooting switching, missile attitude report, on-hook, handoff functionality operation; The button composition of inner side and layout are as shown in Figure 6.
Electronic compass 11 adopts HMR3500 electronic compass, for providing missile bearing and pitch information, and sends to interface processing circuitry plate.
As shown in Figure 3, wherein, linking arm 5, fixed station 6 and button mounting box 7 are all in deployed condition by the rotation of self hinge to the air defence missile command & control integrated apparatus of the present embodiment state in the course of the work.After end-of-job, be carried status of processes as shown in Figure 4, linking arm 5, fixed station 6 and button mounting box 7 are all folded in the outer surface of shell 3, are easy to carry.
Claims (6)
1. a command & control integrated apparatus housing, comprises shell, it is characterized in that, the front end of described shell is provided with photoelectric subassembly installing port; The upper surface of sheath top plate is provided with location time service assembly installing port; The rear edge of sheath top plate has linking arm by the first chain connection, and linking arm can launch above the upper surface of shell or with the direction away from case nose along with turning folding of the first hinge; There is the fixed station for fixing display the rear end of shell side by the second chain connection, and fixed station can be launched in the groove in shell side face or with the direction away from groove by turning folding of the second hinge; The stage casing of shell side is provided with the button mounting box for installing button by the 3rd hinge, and button mounting box triple hingedly can turn folding in shell side face or launch with the direction away from housing along with; Button mounting box hollow, its lateral surface has multiple button installing port; Enclosure is provided with interface processing circuitry plate erecting bed and information-processing circuit plate erecting bed.
2. command & control integrated apparatus housing as claimed in claim 1, it is characterized in that, described shell side is provided with opening, this opening is coated with dismountable opening cover plate.
3. command & control integrated apparatus housing as claimed in claim 1, it is characterized in that, described outer casing bottom is provided with dovetail groove.
4. command & control integrated apparatus housing as claimed in claim 1, is characterized in that, described shell is provided with 2 air plugs.
5. command & control integrated apparatus housing as claimed in claim 1, is characterized in that, described shell is provided with power switch installing port.
6. application rights requires the air defence missile command & control device of the arbitrary described housing of 1-5, comprises integrated command device housing, photoelectric subassembly, location time service assembly, interface processing circuitry plate, information-processing circuit plate, electronic compass, display, button and guidance panel; Photoelectric subassembly is arranged on photoelectric subassembly installing port; Time service assembly in location is arranged on location time service assembly installing port; Interface processing circuitry plate and information-processing circuit plate are installed on interface processing circuitry plate erecting bed in the enclosure and information-processing circuit plate erecting bed respectively; Electronic compass is arranged on the end of linking arm; Display is arranged on the rear end of fixed station; Button to be arranged in button mounting box and from button installing port; Guidance panel is arranged on button mounting box medial surface; Photoelectric subassembly, display link information treatment circuit plate; Location time service assembly, electronic compass, button and guidance panel connecting interface treatment circuit plate, information-processing circuit plate is connected by serial ports with interface processing circuitry plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420603708.1U CN204188081U (en) | 2014-10-17 | 2014-10-17 | Command & control integrated apparatus housing and air defence missile command & control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420603708.1U CN204188081U (en) | 2014-10-17 | 2014-10-17 | Command & control integrated apparatus housing and air defence missile command & control device |
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| Publication Number | Publication Date |
|---|---|
| CN204188081U true CN204188081U (en) | 2015-03-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420603708.1U Expired - Lifetime CN204188081U (en) | 2014-10-17 | 2014-10-17 | Command & control integrated apparatus housing and air defence missile command & control device |
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| CN (1) | CN204188081U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110671970A (en) * | 2019-10-09 | 2020-01-10 | 河南平原光电有限公司 | Straight sighting telescope with inclined plane parting |
-
2014
- 2014-10-17 CN CN201420603708.1U patent/CN204188081U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110671970A (en) * | 2019-10-09 | 2020-01-10 | 河南平原光电有限公司 | Straight sighting telescope with inclined plane parting |
| CN110671970B (en) * | 2019-10-09 | 2021-09-21 | 河南平原光电有限公司 | Straight sighting telescope with inclined plane parting |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |