CN114963888B - Integrated missile controller and installation and use method thereof - Google Patents
Integrated missile controller and installation and use method thereof Download PDFInfo
- Publication number
- CN114963888B CN114963888B CN202210410804.3A CN202210410804A CN114963888B CN 114963888 B CN114963888 B CN 114963888B CN 202210410804 A CN202210410804 A CN 202210410804A CN 114963888 B CN114963888 B CN 114963888B
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- 238000009434 installation Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000004891 communication Methods 0.000 claims abstract description 38
- 238000012545 processing Methods 0.000 claims abstract description 19
- 230000003321 amplification Effects 0.000 claims abstract description 9
- 238000003199 nucleic acid amplification method Methods 0.000 claims abstract description 9
- 238000005192 partition Methods 0.000 claims abstract description 7
- 238000012360 testing method Methods 0.000 claims description 6
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 238000005474 detonation Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 11
- 238000005259 measurement Methods 0.000 description 6
- 230000006872 improvement Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Abstract
The invention relates to an integrated missile controller and an installation and use method thereof. The integrated missile controller is characterized in that a controller shell is of an annular structure, an outer ring is in common type with an inner cavity of a control cabin shell, and a warhead jet channel is arranged in the middle of the inner ring; the controller shell is provided with a concave structure for arranging an external communication connector along the axial middle part of the bullet. The integrated control unit comprises a computer board, a signal processing board, a power amplification board, an external and internal communication connector; the computer board and the signal processing board are fixed on the controller shell, are arranged on two sides of the partition board in the shell, and the power amplification board is arranged on the signal processing board; the external communication connector is arranged in the middle of the controller shell; the intra-pair communication connector is disposed on the back cover. The front cover plate and the rear cover plate are respectively arranged at the front end and the rear end of the controller shell. The invention has the advantages of simple hardware structure, convenient connection, high space utilization rate, good electromagnetic shielding effect and the like, and can improve the effective load or range of the missile, so that the overall performance of the missile is obviously improved.
Description
Technical Field
The invention belongs to the technical field of missile structural design, and particularly relates to an integrated missile controller. In addition, the invention also relates to a mounting and using method of the integrated missile controller.
Background
The control cabin is a control center of the whole bullet and has the functions of navigation, guidance, whole bullet logic time sequence control, test and the like. The controller is a single machine formed by combining and designing the on-board comprehensive control unit and the structure, and is core electronic equipment in the control cabin. The quality of the design can directly influence the overall performance, manufacturing cost and production period of the control cabin and even the missile, and various factors such as the overall performance, the process, the use and the cost must be considered in the structural design.
In the prior art, in order not to influence the jet forming and damage power of the energy-collecting and nail-breaking warhead, a jet channel of the warhead needs to be reserved in the middle of the control cabin. In the structural design, the scheme is that after a plurality of layers of rectangular hardware circuit boards of the integrated control unit are stacked, the rectangular hardware circuit boards are arranged at the side of the control cabin in a scattered state along the spring axis direction. The other units with different functions, equipment installation and communication cable laying and connection between the units cause the problems of large volume, heavy weight, disordered structural layout and low space utilization rate of the control cabin. The increase of the negative space and the mass further reduces the effective load or the range of the missile, and seriously influences the overall performance of the missile. In summary, how to solve the problems of miniaturization and integration of the controller is a technical problem to be solved by those skilled in the art.
Disclosure of Invention
Aiming at the defects or improvement demands of the prior art, the invention provides an integrated missile controller, thereby solving the technical problems of large size, heavy weight, disordered structural layout and low space utilization rate of a control system component in the prior art. Another object of the present invention is to provide a method of installation and use comprising the above integrated missile controller.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the integrated missile controller is mainly characterized by comprising a controller shell, a front cover plate, a rear cover plate, studs, support columns, a comprehensive control unit and the like.
The controller shell is a main body structure of the controller, and a loading space and a good working environment are provided for the integrated control unit. The hardware of the comprehensive control unit consists of a computer board, a signal processing board, a power amplification board, an external communication connector and an internal communication connector. The computer board and the signal processing board are respectively arranged at two sides of the middle partition board of the controller shell and are fixed on the controller shell through studs. The power amplification board is arranged on the upper side of the signal processing board through the support column. The external communication connector is arranged in the middle of the controller shell. The intra-pair communication connector is arranged on the back cover plate. The front cover plate and the rear cover plate are respectively arranged at the front end and the rear end of the controller shell.
Preferably, the controller shell is of an annular structure, the outer ring and the inner cavity of the control cabin shell are in the same type, and a warhead jet channel is reserved in the middle of the inner ring. The controller shell is provided with a plurality of concave structures along the axial middle part of the bullet for arranging the external communication connectors of the integrated control unit.
Preferably, the integrated control unit integrates functions of navigation, guidance, full-bullet logic time sequence control, test and the like. The computer board and the signal processing board hardware are of annular structures, and a plurality of mounting interfaces are arranged at the inner ring and the outer ring, so that the situation that any special-shaped avoidance structure is adopted by each hardware circuit board due to other mounting forms is avoided.
Preferably, the communication circuit between the computer board and the signal processing board is connected by an electric connector, so that the computer board is convenient to assemble and disassemble during maintenance. The communication circuit between the computer board and the power amplifier board is directly inserted by adopting a printed board type rectangular electric connector, and has the advantages of simple hardware circuit structure, no extra cable, convenient connection and the like.
Preferably, the studs and the support columns play a role in supporting up and down, are used for pressing the hardware circuit board of the integrated control unit on one hand, and provide mounting interfaces for the front cover plate and the rear cover plate on the other hand.
Preferably, the controller is of a closed structure, has a good electromagnetic shielding effect, and prevents the external environment and equipment from interfering signals of the integrated control unit.
Preferably, the controller is arranged along the radial direction of the controller, and after the controller is mounted on the control cabin shell, an operation window is reserved at a corresponding position on the control cabin shell, so that the plugging or replacement operation of the connector is facilitated.
Preferably, the controller and the control cabin shell adopt a radial connection installation mode, the shape of the controller is the same as the inner cavity of the control cabin shell, the space utilization rate is highest, any protruding structure is avoided in the control cabin, and the structural member processing manufacturability is good.
The invention also provides a method for installing and using the integrated missile controller, which comprises the controller, a front-stage warhead, an inertial measurement unit, a clamp and the like.
The front combat unit is arranged on a front cover plate of the controller, the inertial unit is arranged on a rear cover plate of the controller, and the inertial unit and the communication cable of the controller are clamped through the clamp. The controller is connected with the front-stage warhead, the inertial unit and the like to form a whole, and the structural parts of the controller are designed to play the functions of the controller, and are used as other stand-alone or functional module mounting supporting pieces at the same time, so that the structure of the controller is comprehensively utilized.
The invention provides an installation and use method of an integrated missile controller, which comprises the following steps:
preferably, the front cover plate is made of titanium alloy, has the advantages of high strength and light weight, and plays a role in isolating detonation of the front-stage warhead together with the controller shell 1.
Preferably, the rear cover plate is thickened integrally in thickness, and threaded holes for installing the controller in the control cabin are formed in the side surfaces. The inertial unit is arranged on the rear cover plate, so that the installation rigidity of the inertial unit can be improved. And the rear cover plate is provided with a positioning pin hole for installing the inertial unit, and the positioning pin hole is used for ensuring the installation accuracy of the inertial unit relative to the full bullet.
The invention has the beneficial effects that:
1. the controller structural design fully considers modularization, miniaturization and combination design. By adopting the annular structural design scheme, the middle part is reserved with the warhead jet channel, and the integrated control unit and the communication cable thereof are integrally arranged in the main body structure of the controller shell, thereby solving the technical problems of large size, heavy weight, disordered structural layout and low space utilization rate of the control system component in the prior art. The electromagnetic shielding device has the advantages of simple structure, convenience in service treatment, good electromagnetic shielding performance, high reliability and the like.
2. The adoption of a multipurpose structural design form, the sunken structure in the middle part 4 of the controller shell is used for setting up an external communication interface of the integrated control unit, so that repeated setting of connector brackets is avoided, and the number of structural members is reduced. The controller is connected with the front combat unit, the inertial unit and the like to form a whole, and can be integrally arranged in the control cabin and the like. The mutual osmosis is arranged between the devices, so that the controller structure is comprehensively utilized. Has the advantages of compact structure, small occupied space of the elastomer structure and the like. The effective load or range of the missile can be further improved, so that the overall performance of the missile is obviously improved.
Drawings
FIG. 1 (a) is a front view of a controller in an embodiment of the present invention;
FIG. 1 (b) is an A-A cross-sectional view of a front view of a controller in an embodiment of the present invention;
FIG. 1 (c) is a top view of a controller in an embodiment of the invention;
FIG. 2 (a) is a front view of a controller housing in an embodiment of the present invention;
FIG. 2 (B) is a B-B cross-sectional view of a front view of a controller housing in an embodiment of the present invention;
FIG. 2 (c) is a top view of a controller housing in an embodiment of the invention;
FIG. 3 (a) is a front view of a back cover plate in an embodiment of the invention;
FIG. 3 (b) is a C-C cross-sectional view of a front view of a back cover in an embodiment of the invention;
FIG. 3 (c) is a rear view of the back cover plate in an embodiment of the invention;
FIG. 4 is an isometric view of a method of installing and using a controller in an embodiment of the invention.
In the drawings, like reference numerals are used to designate like elements or structures, wherein:
the device comprises a 1-controller shell, a 1 a-warhead jet channel, a 1 b-middle partition plate, a 1 c-cable avoidance hole, a 1 d-cylindrical boss, a 1 e-concave structure, a 1 f-electric connector mounting interface, a 1 g-screw hole, a 2-front cover plate, a 3-rear cover plate, a 3 a-screw hole, a 3 b-positioning pin hole, a 3 c-pair internal communication connector mounting interface, a 3 d-cable clamp mounting interface, a 3 e-rear cover plate positioning pin hole, a 3 f-hollow structure, a 4-stud, a 5-support column, a 6-comprehensive control unit, a 6 a-computer board, a 6 b-signal processing board, a 6 c-power amplifier board, a 6 d-external communication connector, a 6 e-pair internal communication connector, a 7-controller, an 8-front-stage warhead, a 9-inertia unit and a 10-clamp.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
As shown in fig. 1 (a) to fig. 3 (c), an embodiment of the present invention is an integrated missile controller, which is disposed in a missile control cabin and requires as small a weight and volume as possible. The controller mainly comprises a controller shell 1, a front cover plate 2, a rear cover plate 3, studs 4, support columns 5, a comprehensive control unit 6 and the like.
The controller shell 1 adopts an annular structure, the outer ring and the inner cavity of the control cabin shell are in the same type, and a warhead jet channel 1a is reserved in the middle of the inner ring. The two groups of concentric ring structures are connected through a middle partition plate 1b, and 4 communication cable avoidance holes 1c are uniformly distributed on the two groups of concentric ring structures and are used for the communication cable passing through and connecting between the computer board 6a and the signal processing board 6 b. The two sides of the middle partition board 1b are respectively provided with 10 cylindrical bosses 1d, wherein 6 cylindrical bosses are uniformly distributed along the inner side of the outer ring of the controller shell 1, and the other 4 cylindrical bosses are uniformly distributed along the outer side of the inner ring of the controller shell 1 to provide mounting interfaces for the computer board 6a and the signal processing board 6b, and the height of the cylindrical bosses 1d is determined according to the heights of the raised components on the hardware circuit board. The controller housing 1 is circumferentially and uniformly provided with 4 concave structures 1e along the axial middle part of the bullet, (the concave structures 1e can be a plurality of positions, for example, one to six positions are circumferentially and uniformly distributed), and an electric connector mounting interface 1f is arranged on the controller housing and is used for arranging or arranging the external communication connector 6d of the integrated control unit 6. The layout skillfully utilizes the communication cable installation space of the integrated control unit 6 reserved in the middle of the controller shell 1 to arrange connectors, and no connector bracket is required to be additionally arranged. Meanwhile, the disordered communication cables among the hardware circuit boards are packaged in the controller shell 1, and the controller has the advantages of being neat and concise in structural arrangement and the like. Two rows of screw holes 1g are arranged in the middle of the outer ring of the controller shell 1 and are mechanical interfaces for connecting the controller with a control cabin.
The front cover plate 2 and the rear cover plate 3 are used for sealing the front end and the rear end of the controller, and can provide mounting interfaces for other functional modules, and the mounting interfaces are respectively fixedly connected to the middle thread of the stud 4 by penetrating screw hole mounting interfaces at the inner ring and the outer ring through screws. Wherein, the left side of back shroud 3 is provided with screw hole 3a and location pinhole 3b, through the locating pin location back when the inertial measurement unit installation, screws are screwed down again. The right side is provided with an integrated control unit to internal communication connector installation interface 3c, and adopts a local protruding structural design form. The middle part is provided with a plurality of cable clamp installation interfaces 3d, so that the cable is convenient to run and arrange. And a rear cover plate positioning pin hole 3e is arranged right above the control cabin shell, so that the installation accuracy of the inertial measurement unit is led to the control cabin shell, and the installation accuracy of the inertial measurement unit relative to the full bullet is further ensured. The middle part of the back is designed into an inner hollow structure 3f, so that interference with components on the computer board 6a is avoided, and the axial overall size of the controller is further reduced.
The lower ends of the stud 4 and the support column 5 are of external thread structures, the upper end is of a cylindrical support structure, the middle part of the stud is provided with internal threads, and a linear open slot is formed in the middle of the cylindrical end face, so that the mounting operation is facilitated.
The integrated control unit 6 is composed of a computer board 6a, a signal processing board 6b, a power amplification board 6c, an external communication connector 6d, an internal communication connector 6e and the like. The computer board 6a and the signal processing board 6b are annular structures, are conformal with the inner cavity of the controller shell 1, and release component arrangement space as much as possible in the circumferential direction. The power amplification board 6c is of a rectangular structure, is connected with the computer board 6a through the support column 5, adopts printed board type connectors to directly insert the power amplification board, and strictly controls the cylinder height at the upper part of the support column 5 according to the butt joint height of the connectors in the design process. The external communication connector 6d can be arranged everywhere, and three parts, namely a steering control interface, a test interface, an engine ignition interface and the like, are designed in the embodiment. The external communication connector 6d is arranged along the radial direction of the controller, and an operation window is reserved at a corresponding position after the control cabin shell is sleeved, so that the missile total package and test are facilitated.
As shown in fig. 4, the invention also provides a method for installing and using the integrated missile controller, which comprises a controller 7, a front-stage warhead 8, an inertial unit 9, a clamping hoop 10 and the like.
The controller 7 is used as a mounting main body structure, the front-stage warhead 8 is arranged on the front cover plate 2 of the controller 7, and the jet flow central axis of the front-stage warhead 8 coincides with the projectile body axis. The material of the front cover plate 2 is preferably titanium alloy, has the advantages of high strength and light weight, plays a role in isolating detonation of the front-stage warhead together with the controller shell 1, prevents the front-stage warhead from damaging the main-stage warhead, and the thickness of the front cover plate 2 can be repeatedly and iteratively determined according to simulation or test results. The inertial measurement unit 9 is arranged at the left side of the center of the rear cover plate 3 of the controller 7, so that a main-stage warhead jet channel is further avoided, and a communication cable between the inertial measurement unit 9 and the controller 7 is fixed through a clamp 10. In order to improve the installation rigidity and the support strength of the front combat unit 8 and the inertial unit 9, a plurality of threaded holes can be further formed in the lateral directions of the front cover plate 2 and the rear cover plate 3, and the front combat unit and the inertial unit are connected and reinforced with the control cabin shell through screws during installation. Therefore, the controller is not only a core single machine in the control cabin, but also can provide an installation interface for other single machines or devices, and the devices are mutually penetrated and installed, so that the internal space of the control cabin is fully utilized.
The technical parameters achieved are as follows: the maximum outer diameter phi of the controller is 130mm, the thickness of the main body is 55mm, and a jet channel with the diameter phi of 25mm is reserved in the middle part, so that the purposes of modularization and combination design of the controller are achieved. The structural design scheme of the controller provided by the invention shortens the overall length of the control cabin by 60mm, reduces the weight by about 500g and reduces the number of structural parts by 30%. The effective load of the missile is further improved, and the performance of the missile weapon system is obviously improved.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (9)
1. The integrated missile controller comprises a controller shell, a front cover plate, a rear cover plate, studs, support columns and a comprehensive control unit, and is characterized in that the controller shell is of a main body structure of the controller and is of an annular structure, an outer ring is in common type with an inner cavity of a control cabin shell, a warhead jet channel is reserved in the middle of the inner ring, and two groups of concentric ring structures are connected through a middle partition plate; the hardware of the comprehensive control unit consists of a computer board, a signal processing board, a power amplification board, an external communication connector and an internal communication connector; the computer board and the signal processing board are respectively arranged at two sides of a middle partition board of the controller shell and are fixed on the controller shell through studs; the power amplification board is arranged on the signal processing board through a support column; the external communication connector is arranged in the middle of the controller shell; the pair of internal communication connectors are arranged on the rear cover plate; the front cover plate and the rear cover plate are respectively arranged at the front end and the rear end of the controller shell.
2. The integrated missile controller of claim 1 wherein the integrated control unit integrates navigation, guidance, full missile logic timing control, testing, and the like; the computer board and the signal processing board hardware are of annular structures, and mounting interfaces are arranged at the inner ring and the outer ring.
3. The integrated missile controller according to claim 2 wherein the central part of the shell of the controller has a recess for the arrangement of the integrated control unit to the external communication connector; the controller is arranged with the external communication connectors along the radial direction of the controller.
4. An integrated missile controller according to claim 3 wherein the computer board is connected to the signal processing inter-board communication circuit by an electrical connector; the communication circuit between the computer board and the power amplifier board is directly plugged by adopting a printed board type rectangular electric connector.
5. An integrated missile controller according to claim 3 wherein the recess is circumferentially equispaced from one to six.
6. An integrated missile controller according to claim 2 wherein the studs and support columns function as support and release means for holding down the integrated control unit hardware circuit board and for providing mounting interfaces for the front and rear covers.
7. The integrated missile controller of claim 1 wherein the controller is in a closed configuration.
8. The method of installing and using an integrated missile controller of claim 1, including the controller, front combat section, inertial mass, and collar; the front combat unit is arranged on a front cover plate of the controller, the inertial unit is arranged on a rear cover plate of the controller, the inertial unit and the communication cable of the controller are clamped through a clamp, and the controller, the front combat unit and the inertial unit are connected to form a whole; the front cover plate is made of titanium alloy and plays a role in isolating detonation of the front-stage warhead together with the controller shell; the rear cover plate is thickened integrally in thickness and is provided with a positioning pin hole for installing the inertial unit, so that the installation rigidity and the accuracy of the inertial unit are improved.
9. The method of installing and using an integrated missile controller according to claim 8 wherein the structural components of the controller, in addition to functioning as the controller itself, are used as support members for other stand-alone or functional modules to provide comprehensive utilization of the controller structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210410804.3A CN114963888B (en) | 2022-04-19 | 2022-04-19 | Integrated missile controller and installation and use method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210410804.3A CN114963888B (en) | 2022-04-19 | 2022-04-19 | Integrated missile controller and installation and use method thereof |
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| CN114963888A CN114963888A (en) | 2022-08-30 |
| CN114963888B true CN114963888B (en) | 2023-11-03 |
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| CN114963888A (en) | 2022-08-30 |
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