CN209814289U - External airborne control system arranged inside missile hanging frame - Google Patents
External airborne control system arranged inside missile hanging frame Download PDFInfo
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- CN209814289U CN209814289U CN201822015432.6U CN201822015432U CN209814289U CN 209814289 U CN209814289 U CN 209814289U CN 201822015432 U CN201822015432 U CN 201822015432U CN 209814289 U CN209814289 U CN 209814289U
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Abstract
The application discloses set up at inside external machine of hanging bullet frame and carry control system includes: the suspension device is detachably fixed outside the airplane to be adapted, a containing cavity is formed in the suspension device, and meanwhile, the suspension device is used for suspending a weapon and controllably throwing the weapon; and the control management subsystem is arranged in the accommodating cavity of the suspension device and comprises navigation equipment and a satellite signal receiving antenna which are connected and used for aligning or navigating the weapon. The application sets up at the inside external machine of hanging bullet frame and carries control system for the independent machine of one set of external to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different operation aircraft do not influence the normal work of original quick-witted system after installing additional to installing additional and user demand of novel weapon, and can effectual promotion aircraft operation ability.
Description
Technical Field
The application belongs to the field of design and development of combat aircraft weapon fire control systems and aircraft and weapon refitting, and particularly relates to an external airborne control system arranged inside a missile hanging frame.
Background
The weapon attack capability of the battle airplane is mainly realized by the mutual and cooperative work of various airborne equipment (airborne weapon fire control system) arranged on the airplane, and the weapon attack capability is mostly required to be designed, developed and verified together with the airplane at the beginning of the development of the airplane or to be developed and realized by specially modifying the airborne system.
At present, the service life of a first-type combat aircraft is about 30 years or more, and with the continuous development and updating of airborne weapons, the timely increase of new weapon attack capability of an active aircraft becomes a conventional requirement; however, limited and constrained by the design of the initial system architecture of the operational aircraft, the addition of new weapon attack capability usually requires refitting, upgrading, designing, integrating and verifying the original complex system (especially the navigation equipment, the satellite signal receiving antenna and other equipment in the control management subsystem) on the original aircraft, the development and verification process needs to be repeated once when weapons are added, and the design refitting personnel need to be familiar with and master the original design state of the aircraft, and therefore the aircraft has the advantages of high cost, large workload, long time period, high implementation difficulty, high technical risk and small application range.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The present application is directed to an external airborne control system disposed inside a missile suspending frame to solve at least one of the above problems
The application discloses set up at inside external machine of hanging bullet frame and carry control system includes:
the suspension device is detachably fixed outside the airplane to be adapted, a containing cavity is formed in the suspension device, and meanwhile, the suspension device is used for suspending a weapon and controllably throwing the weapon; and
disposed within the receiving cavity of the suspension device:
and the navigation equipment and the satellite signal receiving antenna are connected for the alignment operation or the navigation operation of the weapon.
According to at least one embodiment of the application, the suspension device is detachably fixed at a hanging point location of the aircraft to be fitted.
According to at least one embodiment of the application, the top structure of the suspension device is configured to be adapted to a suspension interface of a primary pylon of a lower part of the aircraft to be adapted, and is fixedly suspended from the lower part of the primary pylon.
According to at least one embodiment of the application, the suspension device is a missile hanging rack or a launching rack, and the bottom of the suspension device is provided with a missile hanging hook matched with a suspension interface of the weapon.
According to at least one embodiment of the present application, the navigation device is a combined inertial/satellite navigation device.
The application has at least the following beneficial technical effects:
the application sets up at the inside external machine of hanging bullet frame and carries control system for the independent machine of one set of external to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different operation aircraft do not influence the normal work of original quick-witted system after installing additional to installing additional and user demand of novel weapon, and can effectual promotion aircraft operation ability.
Drawings
FIG. 1 is a block diagram of the system components of the external airborne control system of the present application disposed within a missile hanger.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The external airborne control system arranged inside the missile hooking bracket of the present application is further described in detail with reference to fig. 1.
The application discloses set up at inside external machine of hanging bullet frame and carry control system can include linkage 1, control management subsystem 3 and control device 4.
The suspension device 1 is detachably fixed outside the aircraft to be fitted, for example at the bottom of the aircraft body; meanwhile, the suspension device 1 is used for suspending a suspension 2 to be carried, and the suspension 2 may be, for example, a weapon, a pod, or the like.
The control management subsystem 3 is detachably fixed outside the airplane to be adapted; the control management subsystem 3 is configured to receive a control command sent by the corresponding control device 4, and perform corresponding control on a suspension (e.g., weapon 2) according to control information included in the control command, for example, control the launching and launching of weapon 2, and control pod launching and other operations.
The control device 4 is used for controlled (e.g., manual control by the driver) transmission of a control command to the control management subsystem 3.
The application sets up at the inside external machine of hanging the bullet frame and carries control system for the independent machine of one set of external to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different operation aircraft do not influence the normal work and the operational capability performance of original quick-witted system to installing additional and the user demand of novel weapon after installing additional.
In some alternative embodiments, the suspension device 1 is detachably fixed at a suspension point location at the lower part of the aircraft to be fitted. Further, the suspension device 1 is detachably fixed at the lower part of the primary pylon of the airplane to be adapted, wherein the top structure of the suspension device 1 can be configured to be adapted to the suspension interface of the primary pylon of the lower part of the airplane to be adapted, so as to be fixedly suspended at the lower part of the primary pylon.
In some alternative embodiments, control management subsystem 3 may include communication device 31, control management device 32, and power supply device 33.
The communication device 31 may be used in cooperation with the above-described manipulation device 4 by using a known wired communication device or a wireless communication device, for example.
Preferably, the control device 4 is a wireless controller, such as a tablet, a mobile phone, etc. in a portable wireless smart terminal, and correspondingly, the communication device 31 is a wireless communication device, such as a wireless router, a wireless communication antenna. In some optional embodiments, the portable wireless intelligent terminal integrates a miniaturized board card and a wireless antenna, the working frequency band and the signal intensity can be set and adjusted, 24 wireless controllers can work simultaneously in the same area, and a single wireless controller can control and manage 10 wireless communication terminals simultaneously; the touch display screen is anti-strong light reflection, supports day and night modes, and is visible in strong sunlight; the rechargeable battery is small and efficient, and can work for a long time, and the working time is not less than 4 hours. The multifunctional electronic weapon has the functions of realizing power switch, screen locking, weapon launching, emergency releasing and the like through physical keys. The portable type four-limb chair can be reliably fixed on four limbs of a person or a cabin equipment mounting rack through the modes of a binding band and the like, and has the characteristics of small size, portability, clear images, strong processing capability and the like.
The control management device 32 is mainly used for receiving the manipulation instruction sent by the manipulation device 4 through the communication device 31 and manipulating the weapon 2 according to the manipulation instruction.
In the external airborne control system arranged inside the missile hooking frame, the control management equipment 32 can be weapon fire control computer equipment; the weapon fire control computer adopts a miniaturized high integration technology and mainly comprises a case, a computer module, a bus communication module, an acquisition and recording module, a radio frequency wireless module, a discrete interface module, a power supply and monitoring module, a bus bottom plate and the like, and software adopts an open architecture and a modular design and has strong expandability. The device functionality may be incorporated into the portable wireless controller and battery power supply as necessary.
The power supply device 33 may be connected with the control management device 32, the communication device 31 and the suspension apparatus 1 for supplying power to the control management device 32, the communication device 31 and the suspension apparatus 1. The power supply device 33 may employ any of a variety of suitable batteries or power supplies, preferably a battery power supply in this embodiment; the storage battery power supply mainly comprises a single battery pack, a shell structure, a jumper, an electric connector, a circuit breaker, a heat insulation layer, fasteners and the like, adopts a real-time monitoring and quick assembling and disassembling interface, and has the characteristics of long endurance time, wide temperature resistance, complex working environment, long maintenance period interval and the like.
In some alternative embodiments, the suspension device 1 is a missile hanger or a launcher; a hook adapted to the suspension interface of the weapon 2 is arranged at the bottom of the suspension device 1.
Correspondingly, control management subsystem 3 may further include navigation device 34, satellite signal receiving antenna 35 (e.g., GPS antenna).
The number of the navigation devices 34 is one, and is connected to the control management device 32. Further, the navigation device 34 is preferably an inertial satellite integrated navigation device, which mainly comprises a chassis, an inertial sensitive component and an electronic component, has a pure inertial and GPS, beidou and other satellite integrated navigation modes, and is used for providing high-precision position, speed and attitude information.
The number of the satellite signal receiving antennas 35 is one, and the satellite signal receiving antennas are respectively connected with the control management device 32 and the navigation device 34; the satellite signal receiving antenna 35 (satellite antenna) is used for receiving and forwarding satellite signals to the inertial/satellite combined navigation device and control management device 32, and has GPS and Beidou satellite signal receiving capabilities.
Wherein the control management device 32 is configured to control the navigation device 34 to perform the alignment operation or the navigation operation according to the received alignment instruction or the navigation instruction. Accordingly, the control device 4 is used to send control information containing alignment instructions or navigation instructions to the control management device 32 in a controlled manner. Further, the power supply device 33 described above may also be connected to the navigation device 34 so as to supply power to the navigation device 34.
Further, when the suspension 2 is a weapon, the control and management device 32 may further include a weapon control unit. The weapon control unit receives control information containing a control command sent by the control device 4 through the communication device 31, and controls and operates the weapon according to the control command.
Specifically, the weapon control unit may further include a power-on unit, a preparation unit, a target data binding unit, a transmitting unit, and a status reporting unit.
The power-on unit can receive a power-on instruction sent by the control device 4 through the communication device 31, and control the power supply device 33 to power on the weapon according to the power-on instruction; the control device 4 is further configured to send control information containing a power-on instruction to the control management device 32 in a controlled manner.
The preparation unit can receive the preparation instruction sent by the control device 4 through the communication device 31 and control the weapon to carry out the preparation operation before the emission according to the preparation instruction.
The parameter binding unit can receive the weapon use scheme and the target data binding instruction sent by the control device 4 through the communication device 31, and perform target data binding operation on the weapon according to the target data binding instruction.
The launching resolving unit completes weapon attack envelope and launching condition resolving, reports resolving results to the control device 4 through the communication device 31, receives launching instructions sent by the control device 4, and controls the suspension device 1 to complete weapon launching operation according to the launching instructions.
Further, the state reporting unit may be configured to report the state of the control management device 32 in response to the control information of the control device 4 to the control device 4 through the communication device 31.
In some alternative embodiments, the suspension device 1 is provided with an installation space inside (i.e. an accommodation cavity may be formed), and each device in the control management subsystem 3 is fixedly arranged in the accommodation cavity of the suspension device 1; wherein, the quantity, size, the structure of holding the chamber can carry out suitable setting according to specific equipment of holding in advance. Particularly, when the suspension is a weapon 2, the suspension device 1 (i.e. the cartridge suspension) is a mounting and carrying platform for the weapon/suspension and system equipment, is used for docking with an aircraft suspension point interface and carrying and launching the weapon/suspension, and is used for mounting and carrying system energy sources (storage batteries), control management equipment (weapon fire control computer), sensors (inertial navigation/satellite combined navigation equipment) and other equipment. At the moment, the hanger structure needs to have enough strength, rigidity and shape space so as to meet the requirements of installing and arranging the bullet hooks, system equipment and hanging and carrying the shooting weapons/suspenders, the interfaces on the hanger need to have the universal interface capacity for butting with the primary hanger interfaces of different types of airplanes, and the bullet hooks adopt a single-hanging distance or composite-hanging distance (the hanging distance and the structural form can be selected) form so as to meet the butting and hanging and throwing requirements of different interface weapons/suspenders.
In summary, in some optional embodiments of the external airborne control system arranged inside the missile hanging rack, the control management device 32 (i.e., the weapon fire control computer) is a control core, has the satellite navigation information receiving and processing capabilities of GPS, beidou and the like, is respectively linked with the storage battery power supply, the inertial navigation/satellite combined navigation device, the control device 4 (i.e., the portable wireless controller) and the like, and performs information interaction with the portable wireless controller to complete logic control and state display and report of power supply, alignment, resolving, launching, weapon switching, hanging point switching and the like of the weapon.
Further, the control device 4 (i.e., the portable wireless controller) has a long-term self-power supply capability, establishes wireless communication with the system weapon fire control computer through the antenna, provides important information display and solution such as a system state, a weapon state, an attack situation, an attack area and the like for a pilot/operator, and provides human-machine control interfaces such as weapon power supply, transfer alignment, weapon firing and emergency firing instructions.
Furthermore, the external airborne control system arranged inside the bullet hanging rack can also comprise ground task management equipment; the ground task management equipment mainly comprises a portable computer, a switching cable, task management software and the like, and is used for planning and generating target data, weapon binding parameters and working frequency point information. The ground task management equipment can also be used for generating a weapon use scheme, attack parameters, an attack route, a weapon plan attack area and the like on the ground according to a plan of operation, and binding the results into the portable wireless controller and the weapon fire control computer to serve as a reference basis for actual flight and attack calculation.
The external airborne control system arranged in the missile hanging frame is an external independent airborne control system, can work in parallel with the original weapon fire control system of the airplane, and can quickly meet the requirements of different combat airplanes on the installation and use of suspended objects (novel weapons/other suspended objects); in addition, the aircraft is only mechanically connected with the aircraft, and the normal work and the fighting capacity exertion of the original aircraft system are not influenced after the aircraft is additionally arranged; furthermore, the system provides working power and realizes power supply, control, display and information interaction of weapons/suspenders, and does not need an airplane to provide power and control signal crosslinking; furthermore, the system is hung and installed under the primary hanging rack of the airplane hanging point through a universal mechanical interface, software and hardware change is not needed to be carried out on the airplane, the system can be adapted to various combat airplane platforms, the additional installation and use requirements of different combat airplanes on suspended objects (novel weapons/other suspended objects) can be met, and the combat capability can be formed rapidly.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides a set up at the inside external machine of hanging bullet frame and carry control system which characterized in that includes:
the suspension device (1) is detachably fixed outside an airplane to be adapted, a containing cavity is arranged inside the suspension device (1), and meanwhile, the suspension device (1) is used for suspending a weapon (2) and controllably throwing the weapon (2); and
arranged in a housing cavity of the suspension device (1):
a navigation device (34) and a satellite signal receiving antenna (35) connected for alignment or navigation operation of the weapon (2).
2. The external airborne control system arranged inside a missile hooking bracket according to claim 1 is characterised in that the suspension unit (1) is removably fixed at the location of the point of attachment of the aircraft to be fitted.
3. The external airborne control system arranged inside a missile hooking bracket according to claim 2, characterized in that the top structure of the suspension device (1) is configured to be matched with the suspension interface of the primary suspension bracket of the airplane to be matched with the suspension point and fixedly suspended at the lower part of the primary suspension bracket.
4. The external airborne control system arranged inside a cartridge rack according to claim 3, characterized in that the suspension device (1) is a cartridge rack or a launcher, and the bottom of the suspension device (1) is provided with a cartridge hook adapted to the suspension interface of the weapon.
5. The external airborne control system disposed inside the cradle of claim 1, wherein the navigation device (34) is a combination inertial/satellite navigation device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822015432.6U CN209814289U (en) | 2018-12-03 | 2018-12-03 | External airborne control system arranged inside missile hanging frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822015432.6U CN209814289U (en) | 2018-12-03 | 2018-12-03 | External airborne control system arranged inside missile hanging frame |
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| Publication Number | Publication Date |
|---|---|
| CN209814289U true CN209814289U (en) | 2019-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822015432.6U Active CN209814289U (en) | 2018-12-03 | 2018-12-03 | External airborne control system arranged inside missile hanging frame |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113311735A (en) * | 2021-07-12 | 2021-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft mounted object bus control system |
-
2018
- 2018-12-03 CN CN201822015432.6U patent/CN209814289U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113311735A (en) * | 2021-07-12 | 2021-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft mounted object bus control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co.,Ltd. Assignor: AVIC SHENYANG AIRCRAFT DESIGN & Research Institute|CHINA NATIONAL AERO-TECHNOLOGY IMPORT & EXPORT Corp. Contract record no.: X2022990000101 Denomination of utility model: External airborne control system set inside the bullet rack Granted publication date: 20191220 License type: Common License Record date: 20220222 |
|
| EE01 | Entry into force of recordation of patent licensing contract |