CN209814288U - External airborne control system for combat aircraft - Google Patents
External airborne control system for combat aircraft Download PDFInfo
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- CN209814288U CN209814288U CN201822015428.XU CN201822015428U CN209814288U CN 209814288 U CN209814288 U CN 209814288U CN 201822015428 U CN201822015428 U CN 201822015428U CN 209814288 U CN209814288 U CN 209814288U
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Abstract
The application discloses combat aircraft is with external machine carries control system, including control management subsystem, this control management subsystem detachably fixes treating the adaptation aircraft outside, and control management subsystem configures into and receives the control instruction to treat the external weapon of carrying of adaptation aircraft organism and put in according to controlling the instruction. The application provides an aircraft of fighting uses external machine to carry control system is one set of external independent machine to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different aircraft of fighting can effectual promotion aircraft fighting ability to the additional installation and the user demand of suspended object after installing additional.
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 for a combat aircraft.
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 restricted by the design of the initial system architecture of the operational aircraft, the addition of new weapon attack capability usually requires refitting, upgrading, integrating and verifying the original complex system (especially the control management subsystem) on the original aircraft, the development and verification process needs to be repeated once every weapon addition, and the design refitting person needs 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.
SUMMERY OF THE UTILITY MODEL
The present application is directed to an external airborne control system for a combat aircraft to address at least one of the above-mentioned problems
The application discloses combat aircraft is with external machine carries control system includes:
the control management subsystem is detachably fixed outside the airplane to be adapted and configured to receive a control instruction and release a weapon mounted outside the airplane body to be adapted according to the control instruction.
According to at least one embodiment of the present application, the control management subsystem includes:
a communication device;
the control management device receives a control instruction through the communication device and controls the weapon to be thrown according to the control instruction;
and the power supply equipment is used for supplying power to the control management equipment and the communication equipment.
According to at least one embodiment of the present application, the control management subsystem includes:
the navigation equipment is connected with the control management equipment;
the satellite signal receiving antenna is respectively connected with the control management equipment and the navigation equipment; wherein
The control management device is configured to control the navigation device to enter an alignment state or a navigation operation according to the received alignment instruction or navigation instruction;
the power supply equipment is connected with the navigation equipment and used for supplying power to the navigation equipment.
According to at least one embodiment of the present application, the navigation device is an inertial satellite integrated navigation device.
According to at least one embodiment of the present application, the control management apparatus includes:
the weapon control unit receives a control instruction through the communication equipment and controls and operates the weapon according to the control instruction.
According to at least one embodiment of the present application, the weapon control unit comprises:
and the power-on unit receives a power-on instruction through the communication equipment and controls the power supply equipment to power on the weapon according to the power-on instruction.
According to at least one embodiment of the present application, the weapon control unit comprises:
the preparation unit receives a preparation instruction through the communication equipment and controls the weapon to carry out preparation operation before emission according to the preparation instruction;
the parameter binding unit receives a weapon use scheme and a target data binding instruction sent by the control device through the communication device, and performs target data binding operation on the weapon according to the target data binding instruction;
and the launching calculation unit is used for finishing weapon attack envelope calculation and launching condition calculation, reporting a calculation result to the control equipment through the communication equipment, receiving a launching instruction sent by the control equipment, and controlling the suspension device to finish the launching operation of the weapon according to the launching instruction.
According to at least one embodiment of the present application, the control management apparatus includes:
and the state reporting unit is used for reporting the state information of the control management equipment through the communication equipment.
The application has at least the following beneficial technical effects:
the application discloses combat aircraft is with external machine carries control system for one set of external independent machine carries control system to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different combat aircraft do not influence the normal work and the operational capability performance of original quick-witted system after installing additional to installing additional and user demand of novel weapon.
Drawings
FIG. 1 is a system block diagram of an external airborne control system for a combat aircraft according to the present application.
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 onboard control system for the combat aircraft according to the present application is described in further detail below with reference to fig. 1.
The application discloses combat aircraft is with external machine carries control system can include control management subsystem 3.
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 suspended object (including a weapon 2) mounted outside the aircraft body to be adapted according to control information included in the control command, for example, control the launching and launching of the weapon 2, and control the pod launching and other operations.
The application discloses combat aircraft is with external machine carries control system for one set of external independent machine carries control system to can with the original weapon fire control system concurrent operation of aircraft, can realize fast that different combat aircraft do not influence the normal work and the operational capability performance of original quick-witted system after installing additional to installing additional and the user demand of novel weapon.
In some alternative embodiments, the external onboard control system for a combat aircraft of the present application may also suspend the device 1 and the steering apparatus 4.
In some alternative embodiments, the suspension device 1 is removably fixed to the outside of the aircraft to be fitted, for example to the bottom of the aircraft fuselage; meanwhile, the suspension device 1 is used to suspend a suspension to be carried, which may be, for example, a weapon 2, a pod, or the like.
In some alternative embodiments, the suspension device 1 is detachably fixed at the point of attachment of the aircraft to be fitted. Further, the suspension device 1 is detachably fixed at the lower part of the primary suspension rack 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 suspension rack of the airplane to be adapted, so as to be fixedly suspended at the lower part of the primary suspension rack.
In some alternative embodiments, control device 4 is configured to send control commands to control management subsystem 3 in a controlled manner (e.g., manual control by a driver).
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 frequency band used by the wireless communication device is a UHF band, and the frequency band used by the wireless communication device is selected to be between 300 mhz and 850 mhz.
Preferably, the control device 4 is a wireless controller, such as a tablet, a mobile phone, etc. in the portable wireless smart display control 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 display control 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 suspended object 2 according to the manipulation instruction.
In the external airborne control system for a combat aircraft of the present application, the control management device 32 may be a weapon fire control computer device; 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 weapon suspension interface 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 enter the alignment state or the navigation state 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, the control management apparatus 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 performs control operation on the weapon 2 according to the control command.
Specifically, the weapon control unit may further include a power-on unit, a preparation unit, a parameter binding unit, a transmission resolving 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 status reporting unit may be configured to report the status of the control management device 32 responding 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 for a combat aircraft of the present application, the control management device 32 (i.e., a weapon fire control computer) is a control core, and has the satellite navigation information receiving and processing capabilities of GPS, beidou, etc., and is respectively linked with the storage battery power supply, the inertial navigation/satellite integrated navigation device, the control device 4 (i.e., a portable wireless controller), etc., and performs information interaction with the portable wireless controller, thereby completing logic control such as power supply, alignment, resolving, launching, weapon switching, hanging point switching, etc., and status display and report of weapons.
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 for the combat aircraft can further 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 for the combat aircraft is an external independent airborne control system, can work in parallel with the original weapon fire control system of the aircraft, and can quickly meet the requirements of different combat aircraft on the installation and use of suspenders (novel weapons/other suspenders); 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, the airplane is not required to be changed in software and hardware, 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 quickly formed.
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 (8)
1. The utility model provides a combat aircraft is with external machine carries control system which characterized in that includes:
the aircraft comprises a control management subsystem (3), wherein the control management subsystem (3) is detachably fixed outside an aircraft to be adapted, and the control management subsystem (3) is configured to receive a control instruction and release a weapon (2) mounted outside an aircraft body to be adapted according to the control instruction.
2. The outboard airborne control system of claim 1, wherein said control management subsystem (3) includes:
a communication device (31);
the control management device (32) receives a control instruction through the communication device (31), and controls the weapon (2) to be released according to the control instruction;
a power supply device (33), the power supply device (33) being configured to supply power to the control management device (32) and the communication device (31).
3. The external airborne control system for combat aircraft according to claim 2, characterized in that said control management subsystem (3) comprises:
a navigation device (34), the navigation device (34) being connected with the control management device (32);
a satellite signal receiving antenna (35), wherein the satellite signal receiving antenna (35) is respectively connected with the control management device (32) and the navigation device (34); wherein
The control management device (32) is configured to control the navigation device (34) to enter an alignment state or a navigation state according to the received alignment instruction or navigation instruction;
the power supply device (33) is connected with the navigation device (34) and is used for supplying power to the navigation device (34).
4. The external airborne control system of claim 3, wherein said navigational device (34) is an inertial satellite integrated navigational device.
5. The external airborne control system for combat aircraft according to claim 2, characterized in that said control and management device (32) comprises:
the weapon control unit receives a control command through the communication device (31) and controls and operates the weapon (2) according to the control command.
6. The external airborne control system of claim 5, wherein said weapon control unit comprises:
the power-on unit receives a power-on instruction through the communication equipment (31) and controls the power supply equipment (33) to power on the weapon according to the power-on instruction.
7. The external airborne control system of claim 6, wherein said weapon control unit comprises:
a preparation unit which receives a preparation instruction through the communication device (31) and controls the weapon (2) to perform a preparation before firing operation according to the preparation instruction;
the parameter binding unit receives a weapon use scheme and a target data binding instruction through the communication equipment (31), and performs target data binding operation on the weapon (2) according to the target data binding instruction;
and the launching resolving unit is used for completing weapon attack envelope and launching condition resolving, reporting a resolving result through the communication equipment (31), receiving a launching instruction at the same time, and completing launching operation on the weapon (2) according to the launching instruction.
8. The external airborne control system for combat aircraft according to claim 2, characterized in that said control and management device (32) comprises:
and the state reporting unit is used for reporting the state information of the control management equipment (32) through the communication equipment (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822015428.XU CN209814288U (en) | 2018-12-03 | 2018-12-03 | External airborne control system for combat aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822015428.XU CN209814288U (en) | 2018-12-03 | 2018-12-03 | External airborne control system for combat aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN209814288U true CN209814288U (en) | 2019-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822015428.XU Active CN209814288U (en) | 2018-12-03 | 2018-12-03 | External airborne control system for combat aircraft |
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| CN (1) | CN209814288U (en) |
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- 2018-12-03 CN CN201822015428.XU patent/CN209814288U/en active Active
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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 for combat aircraft Granted publication date: 20191220 License type: Common License Record date: 20220222 |