CN113985926A - Unmanned aerial vehicle guidance missile attack system - Google Patents
Unmanned aerial vehicle guidance missile attack system Download PDFInfo
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- CN113985926A CN113985926A CN202111230407.XA CN202111230407A CN113985926A CN 113985926 A CN113985926 A CN 113985926A CN 202111230407 A CN202111230407 A CN 202111230407A CN 113985926 A CN113985926 A CN 113985926A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/12—Target-seeking control
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Abstract
The invention discloses an unmanned aerial vehicle guided missile attacking system, which comprises an unmanned aerial vehicle and a ground control center; the unmanned aerial vehicle is provided with a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box; the fire control subsystem calculates attack attitude and opportunity according to target information acquired by the reconnaissance pod, carrier platform information of the unmanned aerial vehicle and command control information of a ground command control center, and controls launching of the guided missile; the guided missile is hung on the weapon hanging frame, and the information interaction between the fire control subsystem and the guided missile is realized; guiding the missile to realize target attack; the data chain realizes remote wireless information interaction between the unmanned aerial vehicle and the ground control center; the scout nacelle acquires target information in real time; the distribution box is used for power supply management; the ground control center is used for remote control. The invention can realize remote control and program launching, and when executing attack tasks, the invention does not need to pass through a helicopter, a bomber and a fighter, and has the characteristics of low cost, zero casualties, long distance, high precision and flexible launching.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles and guided missiles, and particularly relates to an unmanned aerial vehicle guided missile attack system.
Background
The unmanned aerial vehicle is mainly used for extreme motion, is gradually used for executing aerial patrol tasks, and has not been researched by utilizing the unmanned aerial vehicle to realize guided missile attack tasks.
At present, an air-guided missile attacking system mainly utilizes helicopters, bombers and fighters to realize the attacking tasks on a ground static target, a ground moving target and a low-altitude moving target, which have high requirements on expenses and technology. When the unmanned aerial vehicle executes an attack task, the attribute, the position and the state of a target need to be actively acquired, the flight attitude of the unmanned aerial vehicle needs to be combined, the fire control subsystem is used for resolving and controlling the aiming of the intelligent missile, and the target can be effectively attacked only by being launched under the control of a remote commander or a program, so that a guided missile attack system using the unmanned aerial vehicle is not available.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art, and provides an unmanned aerial vehicle guided missile attack system which actively acquires the attribute, position and state of a target, and launches a guided missile under the control of a remote commander so as to realize effective attack on the target with low cost, zero casualty, long distance and high precision.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
an unmanned aerial vehicle guided missile attack system comprising: unmanned aerial vehicle and ground control center;
the unmanned aerial vehicle is provided with a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box;
the unmanned aerial vehicle is used for providing a carrier platform of a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box;
the fire control subsystem is used for resolving attack postures and opportunities and controlling launching of guided missiles according to target information acquired by the reconnaissance pod, carrier platform information of the unmanned aerial vehicle (namely unmanned aerial vehicle attitude data acquired by the unmanned aerial vehicle flight control subsystem) and instruction control information of a ground instruction control center;
the weapon hanging frame is used for hanging a guided missile and realizing information interaction between the fire control subsystem and the guided missile;
the guided missile is used for realizing target attack;
the data chain is used for realizing remote wireless information interaction between the unmanned aerial vehicle and the ground control center;
the reconnaissance nacelle is used for acquiring the attribute, state and position information of the target in real time;
the power distribution box is used for power supply management of the unmanned aerial vehicle guided missile attack system;
and the ground control center is used for unmanned aerial vehicle control, fire control subsystem control and guided missile control.
In order to optimize the technical scheme, the specific measures adopted further comprise:
foretell unmanned aerial vehicle platform chooses for use fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, fixed wing rotor wing composite wing unmanned aerial vehicle, rotor unmanned aerial vehicle verts, tail sitting posture unmanned aerial vehicle or unmanned helicopter.
The power of the unmanned aerial vehicle is oil engine type, electric type, hydrogen power type, solar type or hybrid type.
The fire control subsystem or the data chain encrypts the interacted information in real time.
The data link described above includes a wireless transmission device.
The reconnaissance pod is a photoelectric pod.
The fire control subsystem is arranged at the rear row of the machine body.
The weapon hanging frame and the guided missile are respectively installed below and on the side of the unmanned aerial vehicle body and are assembled according to a certain elevation angle, so that mechanical interference with the rotor wing, the propeller and the unmanned aerial vehicle body is avoided.
The reconnaissance nacelle is mounted below the nose of the unmanned aerial vehicle.
The invention has the following beneficial effects:
the invention can realize remote control and program launching, and when executing attack tasks, the invention does not need to pass through a helicopter, a bomber and a fighter, and has the characteristics of low cost, zero casualties, long distance, high precision and flexible launching.
The unmanned aerial vehicle guided missile attack system adapts to guided missiles such as self-guided mounting, homing guidance, remote control guidance and composite guidance.
Drawings
FIG. 1 is a system configuration diagram of the present invention.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the invention provides an unmanned aerial vehicle guided missile attacking system, comprising: unmanned aerial vehicle and ground control center;
the unmanned aerial vehicle is provided with a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance pod and a power distribution box, so that the determining, aiming and attacking efficiencies of a ground static target, a ground moving target and a low-altitude moving target are realized;
the unmanned aerial vehicle is used for providing a carrier platform of a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box;
the fire control subsystem is used for resolving attack postures and opportunities according to target information acquired by the reconnaissance pod, carrier platform information of the unmanned aerial vehicle and command control information of a ground command control center, providing display control and controlling launching of the guided missile;
the weapon hanging frame is used for hanging a guided missile and realizing information interaction between the fire control subsystem and the guided missile;
the guided missile is used for realizing target attack;
the data chain is used for realizing remote wireless information interaction between the unmanned aerial vehicle and the ground control center;
the unmanned aerial vehicle needs to realize the situation and information interaction with the commander in the ground command center through a data link.
Meanwhile, through the data chain, the unified controllability of the guided missile launching attack is realized, and the launching operation of the guided missile is directly controlled by a finger controller of the ground finger control center.
The reconnaissance nacelle is used for acquiring the attribute, state and position information of the target in real time;
the power distribution box is used for power supply management of the unmanned aerial vehicle guided missile attack system;
and the ground control center is used for unmanned aerial vehicle control, fire control subsystem control and guided missile control.
In an embodiment, the unmanned aerial vehicle platform chooses for use fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, fixed wing rotor wing composite wing unmanned aerial vehicle, rotor unmanned aerial vehicle verts, tail seat unmanned aerial vehicle or unmanned helicopter.
In an embodiment, the power of the unmanned aerial vehicle is oil engine type, electric type, hydrogen power type, solar type or hybrid type.
In an embodiment, the fire control subsystem or the data chain encrypts the interacted information in real time. AES 128, AES192, AES256 or Snow3G encryption may be employed.
Specifically, in consideration of transmission safety, when the unmanned aerial vehicle guided missile attack system sends control, state and data information to the ground control center, the fire control subsystem or the data chain can be used for partially or completely encrypting the sent control, state and data information. Accordingly, the ground control center needs to perform a decryption operation and then perform data processing, such as storage, processing, distribution, and the like.
In an embodiment, the data link comprises a wireless transmission device.
The reconnaissance pod is a photoelectric pod.
In an embodiment, the fire control subsystem is installed at the rear row of the fuselage to save installation space.
The weapon hanging frame and the guided missile are respectively installed below and on the side of the unmanned aerial vehicle body and are assembled according to a certain elevation angle, so that mechanical interference with the rotor wing, the propeller and the unmanned aerial vehicle body is avoided, and the unmanned aerial vehicle is convenient to install and utilize space;
the reconnaissance nacelle is arranged below the nose of the unmanned aerial vehicle, and target attribute, state and position information can be conveniently acquired.
The fire control subsystem is connected with the weapon hanging frame, the guided missile, the data chain, the reconnaissance nacelle and the unmanned aerial vehicle flight control subsystem through corresponding interfaces, and interconnection, intercommunication and interoperation of state information, control information and data are performed.
The unmanned aerial vehicle guided missile attacking system utilizes the reconnaissance pod to acquire the attribute, state and position information of a target in real time, combines unmanned aerial vehicle attitude data acquired by the unmanned aerial vehicle flight control subsystem, utilizes the fire control subsystem to calculate the attacking attitude and opportunity based on the target information, platform information and command information, and completes low-cost, zero-casualty, long-distance, high-precision and flexible launching attacking tasks of guided missiles under the control of a remote command controller or a program.
The unmanned aerial vehicle guided missile attack system adapts to guided missiles such as self-guided mounting, homing guidance, remote control guidance and composite guidance. The unmanned aerial vehicle guided missile attacking system can realize remote control center launching and program launching, and complete launching and attacking tasks of guided missiles. The unmanned aerial vehicle guided missile attacking system has the characteristics of low cost, zero casualties, long distance, high precision and flexible launching.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (9)
1. An unmanned aerial vehicle guided missile attack system, comprising: unmanned aerial vehicle and ground control center;
the unmanned aerial vehicle is provided with a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box;
the unmanned aerial vehicle is used for providing a carrier platform of a fire control subsystem, a weapon hanging frame, a guided missile, a data chain, a reconnaissance nacelle and a power distribution box;
the fire control subsystem is used for resolving attack postures and opportunities according to target information acquired by the reconnaissance pod, carrier platform information of the unmanned aerial vehicle and command control information of the ground command control center, and controlling launching of the guided missile;
the weapon hanging frame is used for hanging a guided missile and realizing information interaction between the fire control subsystem and the guided missile;
the guided missile is used for realizing target attack;
the data chain is used for realizing remote wireless information interaction between the unmanned aerial vehicle and the ground control center;
the reconnaissance nacelle is used for acquiring the attribute, state and position information of the target in real time;
the power distribution box is used for power supply management of the unmanned aerial vehicle guided missile attack system;
and the ground control center is used for unmanned aerial vehicle control, fire control subsystem control and guided missile control.
2. The system of claim 1, wherein the drone platform is selected from a fixed wing drone, a rotor drone, a fixed wing rotor compound wing drone, a tilt rotor drone, a tail-seated drone, or an unmanned helicopter.
3. The unmanned aerial vehicle guided missile attack system of claim 1, wherein the power of the unmanned aerial vehicle is oil-powered, electric, hydrogen-powered, solar, or hybrid.
4. The unmanned-aerial-vehicle-guided missile attack system of claim 1, wherein the fire control subsystem or the data chain encrypts the interacted information in real time.
5. An unmanned-aerial-vehicle-guided-missile attack system as recited in claim 1, wherein the data link comprises a wireless transmission device.
6. The unmanned-vehicle-guided missile attack system of claim 1, wherein the reconnaissance pod is a photovoltaic pod.
7. An unmanned-aerial-vehicle-guided missile attack system as claimed in claim 1, wherein the fire control subsystem is mounted in the rear row of the fuselage.
8. An unmanned aerial vehicle guided missile attack system as claimed in claim 1, wherein the weapon stores pylon and guided missile are mounted below and to the side of the unmanned aerial vehicle body respectively and are assembled at an elevation angle to avoid mechanical interference with the rotor, propeller and body.
9. An unmanned aerial vehicle guided missile attack system as defined in claim 1, wherein the reconnaissance pod is mounted below a nose of the unmanned aerial vehicle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111230407.XA CN113985926A (en) | 2021-10-22 | 2021-10-22 | Unmanned aerial vehicle guidance missile attack system |
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| CN202111230407.XA CN113985926A (en) | 2021-10-22 | 2021-10-22 | Unmanned aerial vehicle guidance missile attack system |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750101A (en) * | 2018-06-28 | 2018-11-06 | 彩虹无人机科技有限公司 | A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods |
| CN109774940A (en) * | 2019-01-23 | 2019-05-21 | 西安深瞳智控技术有限公司 | It is a kind of to examine the integrated synthesis avionics system for beating unmanned plane |
| CN109901626A (en) * | 2019-01-30 | 2019-06-18 | 北京理工大学 | A kind of scouting strike integration data processing system and method |
| CN110329515A (en) * | 2019-07-29 | 2019-10-15 | 陶文英 | It is a kind of to examine the design method and system for making integrated aircraft |
| CN111964538A (en) * | 2020-08-19 | 2020-11-20 | 航天科工通信技术研究院有限责任公司 | Guided missile attack system of autorotation rotor mechanism |
| CN112256053A (en) * | 2020-09-27 | 2021-01-22 | 中国航空工业集团公司洛阳电光设备研究所 | Fire control photoelectric system of small-sized scouting and fighting unmanned aerial vehicle |
-
2021
- 2021-10-22 CN CN202111230407.XA patent/CN113985926A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750101A (en) * | 2018-06-28 | 2018-11-06 | 彩虹无人机科技有限公司 | A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods |
| CN109774940A (en) * | 2019-01-23 | 2019-05-21 | 西安深瞳智控技术有限公司 | It is a kind of to examine the integrated synthesis avionics system for beating unmanned plane |
| CN109901626A (en) * | 2019-01-30 | 2019-06-18 | 北京理工大学 | A kind of scouting strike integration data processing system and method |
| CN110329515A (en) * | 2019-07-29 | 2019-10-15 | 陶文英 | It is a kind of to examine the design method and system for making integrated aircraft |
| CN111964538A (en) * | 2020-08-19 | 2020-11-20 | 航天科工通信技术研究院有限责任公司 | Guided missile attack system of autorotation rotor mechanism |
| CN112256053A (en) * | 2020-09-27 | 2021-01-22 | 中国航空工业集团公司洛阳电光设备研究所 | Fire control photoelectric system of small-sized scouting and fighting unmanned aerial vehicle |
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