CN114485268B - Fire control system of unmanned helicopter integrating observation and striking - Google Patents
Fire control system of unmanned helicopter integrating observation and striking Download PDFInfo
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- CN114485268B CN114485268B CN202111661731.7A CN202111661731A CN114485268B CN 114485268 B CN114485268 B CN 114485268B CN 202111661731 A CN202111661731 A CN 202111661731A CN 114485268 B CN114485268 B CN 114485268B
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- 230000005693 optoelectronics Effects 0.000 claims abstract description 17
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 10
- 210000001015 abdomen Anatomy 0.000 claims abstract description 9
- 230000003993 interaction Effects 0.000 claims abstract description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 16
- 238000004458 analytical method Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 5
- 238000012546 transfer Methods 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 3
- 230000000875 corresponding effect Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims description 2
- 238000001514 detection method Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 claims description 2
- 230000001681 protective effect Effects 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000011835 investigation Methods 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G3/00—Aiming or laying means
- F41G3/22—Aiming or laying means for vehicle-borne armament, e.g. on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
Abstract
The invention discloses a fire control system of an unmanned helicopter integrating observation and striking, which comprises the following components: the system comprises an optoelectronic pod, a missile distributor, a missile anchor ear, a bidirectional data link and a ground control station; two cylindrical missiles are fixed on two lateral sides of a missile launching frame of the unmanned helicopter through missile anchor ear, and an optoelectronic pod is arranged on the belly of the unmanned helicopter and is used for tracking a target and measuring target information; the missile distributor is fixed at the lower end of the missile launcher and is used for receiving an optoelectronic pod, a cylindrical missile control instruction and a cylindrical missile launching ignition instruction sent by a ground control station, and sending out real-time working states of the optoelectronic pod and the cylindrical missile and transmitting alignment position and attitude information; the unmanned helicopter and the ground control station perform information interaction through a two-way data link, and the missile launcher is fixed on the abdomen of the unmanned helicopter.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle reconnaissance, striking and control, in particular to a reconnaissance and striking integrated unmanned helicopter fire control system.
Background
With the rapid development of the domestic and foreign reconnaissance and striking integrated unmanned aerial vehicle weapon system, the small unmanned helicopter has small volume, low cost, vertical take-off and landing capability and low requirements on take-off and landing sites, is favored by more and more users, and can be widely used for the tasks of aerial investigation, accurate striking, battlefield monitoring and the like. The traditional fixed wing unmanned system carries ammunition, has large volume, heavy weight and high cost for detecting load, and the fire control launching process has complex time sequence, so a fire control system which has low cost, light weight and simplified control and is suitable for a reconnaissance and striking integrated unmanned helicopter weapon is required to be designed to meet the requirement of the use of accompanying defense occasions during front line reconnaissance and battlefield transfer of the unmanned helicopter.
Disclosure of Invention
In view of the above, the invention provides a fire control system of an unmanned helicopter with integrated reconnaissance and striking, which has the advantages of low cost, light weight, simplified control and the like, and can accurately reconnaissance, accurately aim and continuously strike.
The technical scheme of the invention is as follows: a fire control system for an unmanned helicopter for surveillance and control, comprising: the system comprises an optoelectronic pod, a missile distributor, a missile anchor ear, a bidirectional data link and a ground control station;
Two cylindrical missiles are fixed on two lateral sides of a missile launching frame of the unmanned helicopter through missile anchor ear, and an optoelectronic pod is arranged on the belly of the unmanned helicopter and is used for tracking a target and measuring target information; the missile distributor is fixed at the lower end of the missile launcher and is used for receiving an optoelectronic pod, a cylindrical missile control instruction and a cylindrical missile launching ignition instruction sent by a ground control station, and sending out real-time working states of the optoelectronic pod and the cylindrical missile and transmitting alignment position and attitude information; the unmanned helicopter and the ground control station perform information interaction through a two-way data link, and the missile launcher is fixed on the abdomen of the unmanned helicopter.
Preferably, the cartridge-based missile comprises: launch canister and multipurpose missile installed in the launch canister.
Preferably, the bidirectional data chain comprises: an airborne data link antenna, an airborne data link terminal, a ground data link terminal and a ground data link antenna; the unmanned helicopter receives a photoelectric pod, a cylindrical missile control instruction and a cylindrical missile launching ignition instruction sent by a ground control station through an airborne data link antenna, and forwards the instruction received by the airborne data link antenna to a missile distributor through an airborne data link terminal; the unmanned helicopter comprises an unmanned helicopter, an airborne data chain antenna, an airborne data chain terminal, a missile launcher and a control system, wherein the airborne data chain antenna is arranged at the tail of the unmanned helicopter;
The ground data link terminal receives downlink data sent by the airborne data link terminal through a ground data link antenna, and acquires telemetry data and a striking load image through analysis; wherein the telemetry data comprises: the photoelectric pod infrared/visible light/laser working state, tracking speed, sight line pointing angle information, attitude information of a barrel-mounted missile, guide head working state and tracking data and transmitting alignment data.
Preferably, the ground control station comprises: the control shelter and the cross-country chassis are arranged at the bottom of the control shelter, the ground data link antenna and the GPS antenna are arranged outside the control shelter, and a fire control operator seat, a flight control operator seat and a power distribution cabinet are arranged in the control shelter; the GPS antenna is used for positioning the ground control station, the fire control operator seat and the flight control operator seat are respectively used for operators to perform fire control and flight control operation, and the power distribution cabinet is used for supplying power to the ground control station.
Preferably, the fire control operation seat is provided with a fire control computer, a control handle, a keyboard and mouse component and a ground data link terminal, the fire control computer collects control instructions of missile selection, engine ignition, guide head sight rotation, target tracking, photoelectric pod sight deflection, target tracking and distance measurement generated by the operation actions of the control handle and the keyboard and mouse component through a serial port and a USB port, and meanwhile, the ground data link terminal sends telemetry data and a hitting load image to the fire control computer, and the fire control computer completes analysis, display and recording of the hitting load image and telemetry data; the ground data link terminal transmits a control instruction generated by the fire control computer to the airborne data link terminal through the ground data link antenna and the airborne data link antenna in sequence; after receiving the control instruction, the airborne data link terminal respectively transmits the control instruction to a flight control system, a photoelectric pod and a missile distributor of the unmanned helicopter, and the striking load receiving instruction analyzes and executes corresponding actions of the control instruction to realize the control of the unmanned helicopter and the striking load; wherein the striking load is an optoelectronic pod, a missile distributor and a multipurpose missile.
Preferably, the fire control operator seat is further provided with a monitoring monitor, and the monitoring monitor is used for displaying the impact load image and the remote measurement data by the fire control computer.
The beneficial effects are that:
1. According to the fire control system, communication between the ground control station and the unmanned helicopter is realized through the bidirectional data link, so that photoelectric reconnaissance information sharing and control instruction sending by the ground control station are facilitated; an operator of the ground control station can control the photoelectric pod to finish searching and confirming the hitting target and measuring parameters; the missile launcher is used, a cylindrical missile can be mounted on the left side and the right side of the belly of the unmanned helicopter through missile anchor ear, and the cylindrical missile is convenient to assemble and disassemble; the missile distributor is convenient for realizing selection of fire-hit missiles, reporting the current missile loading state to the ground control station, responding to a command sent by the ground control station, and forwarding and sending a control command sent by the ground control station to the barreled missiles; therefore, the fire control system has the advantages of low cost, light weight, simplified control and the like, and can accurately detect, accurately aim and continuously strike.
2. According to the invention, the fire control computer arranged on the fire control operation seat can complete emission transfer alignment by combining the emission working time sequence of the multipurpose missile and the data fed back to the ground control station by the unmanned helicopter, so that the emission envelope of the multipurpose missile is calculated in real time, and the multipurpose missile is conveniently emitted by one key; the integrated photoelectric nacelle, the carrier (unmanned helicopter) and the information and missile trajectory characteristics of the multipurpose missile can realize fire control operation with low cost and simple operation, and can finish the tasks of aerial investigation, precision striking and the like of a weapon system.
Drawings
Fig. 1 is a schematic diagram of an on-board implementation of a fire control system of an unmanned helicopter with integrated fire control.
Fig. 2 is a schematic diagram of the layout of the ground control station of the fire control system of the unmanned helicopter with integrated fire control.
Fig. 3 is a schematic layout of the operating seat of the present invention.
The unmanned helicopter comprises a 1-unmanned helicopter, a 2-photoelectric pod, a 3-missile distributor, a 4-cylindrical missile, a 5-missile hoop, a 6-airborne data link antenna, a 7-airborne data link terminal, an 8-ground control station, a 201-control shelter, a 202-ground data link antenna, a 203-GPS antenna, a 301-fire control operator seat, a 302-flight control operator seat, a 303-monitoring monitor, a 304-fire control computer, a 305-control handle, a 306-keyboard mouse component, a 307-power distribution cabinet and a 308-ground data link terminal.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The embodiment provides a fire control system of an unmanned helicopter integrating reconnaissance and striking, which has the advantages of low cost, light weight, simplified control and the like, and can accurately reconnaissance, accurately aim and continuously strike.
As shown in fig. 1 and 2, the fire control system includes: the device comprises an optoelectronic pod 2, a missile distributor 3, a missile anchor ear 5, a bidirectional data link and a ground control station 8;
Two barrel-mounted missiles 4 (comprising a launching barrel and a multipurpose missile loaded in the launching barrel) are fixed on two lateral sides of a missile launching frame (fixed on the belly of the unmanned helicopter 1) of the unmanned helicopter 1 through missile hoops 5, and an optoelectronic pod 2 is arranged on the belly of the unmanned helicopter 1 and is used for tracking targets and measuring target information; the missile distributor 3 (missile launching control component) is fixed at the lower end of the missile launching frame and is used for receiving the photoelectric pod 2, the multipurpose missile control instruction and the multipurpose missile launching ignition instruction sent by the ground control station 8, and sending out the real-time working state of the luminous electric pod 2 and the multipurpose missile and transmitting the alignment position and gesture information; wherein, the unmanned helicopter 1 and the ground control station 8 are in information interaction through a two-way data link.
In the embodiment, the photoelectric pod 2 is a main load of a fire control system of the unmanned helicopter, and is integrated with a visible light camera, a long-wave uncooled infrared thermal imager and a laser range finder, and mainly has the functions of searching, observing, tracking, positioning, ranging and the like of the unmanned helicopter on a ground target.
In this embodiment, the bidirectional data link includes: an on-board data link antenna 6, an on-board data link terminal 7, a ground data link terminal 308, and a ground data link antenna 202; the unmanned helicopter 1 receives a photoelectric pod 2, a multipurpose missile manipulation instruction and a multipurpose missile launching ignition instruction sent by a ground control station 8 through an airborne data link antenna 6 (arranged at the tail of the unmanned helicopter 1), and forwards the instruction received by the airborne data link antenna 6 to a missile distributor 3 through an airborne data link terminal 7 (arranged on a missile launching frame);
The ground data link terminal 308 can receive the downlink data sent by the airborne data link terminal 7 through the ground data link antenna 202, and obtain telemetry data (the infrared/visible light/laser working state, tracking rate, line-of-sight pointing angle information of the optoelectronic pod 2, the attitude information of the cylindrical missile 4, the seeker working state and tracking data, and transmission alignment data) and the impact load image through analysis.
In this embodiment, the ground control station 8 adopts a mobile scheme, which includes: the control shelter 201 and an off-road chassis arranged at the bottom of the control shelter 201, a ground data chain antenna 202 and a GPS antenna 203 (used for positioning a ground control station 8) are externally arranged on the control shelter 201, and a fire control operator 301, a flight control operator 302, a power distribution cabinet 307 and the like are arranged in the control shelter 201;
As shown in fig. 3, a fire control operator seat 301 is provided with a monitor 303, a fire control computer 304, a control handle 305, a keyboard mouse component 306 and a ground data link terminal 308, the fire control computer 304 collects control instructions such as missile selection, engine ignition, seeker sight rotation, target tracking, photoelectric pod 2 sight deflection, target tracking, distance measurement and the like generated by the operation actions of the control handle 305 and the keyboard mouse component 306 through a serial port and a USB port, meanwhile, the ground data link terminal 308 sends telemetry data and a strike load image to the fire control computer 304 in the fire control operator seat 301, and the fire control computer 304 completes analysis, display and recording of the strike load image and telemetry data; the ground data link terminal 308 transmits the control instruction generated by the fire control computer 304 to the airborne data link terminal 7 through the ground data link antenna 202 and the airborne data link antenna 6 in sequence; after receiving the control instruction, the airborne data link terminal 7 respectively transmits the control instruction to a flight control system of the unmanned helicopter 1 (the unmanned helicopter 1 is carried by the unmanned helicopter and is controlled by a flight control operator 302), the photoelectric pod 2 and the missile distributor 3, and the striking load (the photoelectric pod 2, the missile distributor 3 and the multipurpose missile) receives the instruction for analysis and executes corresponding actions of the control instruction to realize the control of the unmanned helicopter 1 and the striking load; wherein the monitor 303 is used to perform the display of the impact load image and telemetry data by the fire control computer 304.
In this embodiment, the fire control software used by the fire control computer 304 is developed by QT Creator, which is a piece of cross-platform (Linux, mac OS, windows) software developed by an Integrated Development Environment (IDE) including project generation wizards and advanced c++ editors, and the software can be combined with the workflow and principle before the multi-purpose missile is launched to develop the fire control software matched with the use flow of the multi-purpose missile and the optoelectronic pod 2, so that the fire control software has a good man-machine interaction interface, is simple and convenient to operate, and has good system portability; the fire control operator uses the fire control software to generate instructions and display the system operating status and load images.
In this embodiment, the flight control operator station 302 completes data analysis, display and recording of the platform state, the link device state and the like of the unmanned helicopter 1 through flight control software.
Before the fire control system works, a ground control station 8 flight control operator plans a flight path of the unmanned helicopter 1 through a flight control operator seat 302, the unmanned helicopter 1 patrols and flies according to the planned flight path and carries out two-way communication with the ground control station 8 through a two-way data link, the fire control operator of the ground control station 8 is remotely connected with a control handle 305 of a fire control computer 304 to control the sight rotation of the photoelectric pod 2, so that a target area is searched, when a suspected target is found, the photoelectric pod 2 is used for locking and tracking the target, target position information and azimuth information are acquired in real time, and the sight of the photoelectric pod 2 continuously tracks the target; after a tracking target is confirmed, measuring the distance between the unmanned helicopter 1 and the target through a laser range finder of the photoelectric pod 2, receiving sight angle information of the photoelectric pod 2 by a fire control operator 301, sending a striking instruction to a missile distributor 3 through a bidirectional data link, controlling and selecting any one barrel-mounted missile 4 or all two barrel-mounted missiles 4 by the missile distributor 3 to electrify, carrying out electrifying self-checking on the barrel-mounted missiles 4, unfolding protective covers at the front end and the rear end of the launching barrel, feeding back a self-checking result to the fire control computer 304 after the self-checking of the barrel-mounted missiles 4 is finished, starting inertial group transfer alignment by the fire control computer 304, and carrying out sub-inertial transfer alignment by a 'speed+position' matching method by the moving base alignment for ensuring that the launching moment of the barrel-mounted missiles 4 has correct navigation resolving initial conditions;
The fire control system controls the guide head sight line of the cylindrical guided missile 4 to automatically face the target area, and an operator switches to a guide head view field picture to adjust the tracking wave door to lock the target; the fire control computer 304 on the fire control operator seat 301 in the ground control station 8 calculates and displays whether the multi-purpose missile attack is allowed, an operator fires a missile launching button through a control handle 305, the fire control computer 304 automatically completes the ascending instruction and data transmission such as a target hitting parameter, an engine ignition instruction and the like through a ground data link terminal 308 after acquiring a launching instruction, the missile distributor 3 receives the ground instruction and the target parameter received by the airborne data link terminal 7 and forwards the ground instruction and the target parameter to the barreled missile 4, and after the feedback of the barreled missile 4 completes the parameter binding, the missile distributor 3 completes the ignition of a solid rocket engine through a relay of the self-contained missile distributor; after the solid rocket engine is ignited, the multipurpose missile is pushed to fly to a target off track; after the fire control computer 304 of the ground control station 8 finishes missile launching, a picture can be displayed and switched to a detection picture of the photoelectric pod 2, so that the target is continuously observed, and the multipurpose missile striking effect is evaluated; the method can also switch to the view field picture of the guide head of another multipurpose missile, execute missile launching according to the steps, and implement continuous striking of the target.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. An unmanned helicopter fire control system integrating fire and fire observation, comprising: the device comprises an optoelectronic pod (2), a missile distributor (3), a missile anchor ear (5), a bidirectional data link and a ground control station (8);
Two cylindrical missiles (4) are fixed on two lateral sides of a missile launching frame of the unmanned helicopter (1) through missile hoops (5), and photoelectric pods (2) are arranged on the belly of the unmanned helicopter (1) and are used for tracking targets and measuring target information; the missile distributor (3) is fixed at the lower end of the missile launching frame and is used for receiving an optoelectronic pod (2) and a cylindrical missile (4) control instruction sent by a ground control station (8) and a cylindrical missile (4) launching ignition instruction, and emitting the optoelectronic pod (2) and the cylindrical missile (4) in real-time working state and transmitting alignment position and attitude information; the unmanned helicopter (1) and the ground control station (8) perform information interaction through a bidirectional data link, and the missile launcher is fixed on the abdomen of the unmanned helicopter (1); the barrel-mounted missile (4) comprises: the launching tube and the multipurpose missile installed in the launching tube;
The ground control station (8) comprises: the control shelter (201), wherein a fire control operation seat (301), a flight control operation seat (302) and a power distribution cabinet (307) are arranged in the control shelter (201); a fire control computer (304) is arranged on the fire control operation seat (301); the ground control station (8) further comprises: the off-road chassis arranged at the bottom of the control shelter (201), the ground data chain antenna (202) and the GPS antenna (203) are externally arranged on the control shelter (201),
The bi-directional data chain comprises: an airborne datalink antenna (6), an airborne datalink terminal (7), a ground datalink terminal (308) and a ground datalink antenna (202);
The fire control operation seat (301) is also provided with a control handle (305), a keyboard and mouse component (306) and a ground data link terminal (308), the fire control computer (304) collects control instructions of missile selection, engine ignition, guide head sight rotation, target tracking, photoelectric pod (2) sight deflection, target tracking and distance measurement generated by the operation actions of the control handle (305) and the keyboard and mouse component (306) through a serial port and a USB port, meanwhile, the ground data link terminal (308) sends telemetry data and a hitting load image to the fire control computer (304), and the fire control computer (304) analyzes, displays and records the hitting load image and the telemetry data; the ground data link terminal (308) transmits a control instruction generated by the fire control computer (304) to the airborne data link terminal (7) sequentially through the ground data link antenna (202) and the airborne data link antenna (6); after receiving the control instruction, the airborne data link terminal (7) respectively transmits the control instruction to the flight control system, the photoelectric pod (2) and the missile distributor (3) of the unmanned helicopter (1), and the striking load receiving instruction analyzes and executes the corresponding action of the control instruction to realize the control of the unmanned helicopter (1) and the striking load; wherein the striking load is an optoelectronic pod (2), a missile distributor (3) and a multipurpose missile;
Before the fire control system works, a ground control station (8) flight control operator plans a flight path of an unmanned helicopter (1) through a flight control operator seat (302), the unmanned helicopter (1) patrols and flies according to the planned flight path and carries out two-way communication with the ground control station (8) through a two-way data link, the fire control operator of the ground control station (8) is remotely connected with a control handle (305) of a fire control computer (304) to control the sight rotation of a photoelectric pod (2), so that a target area is searched, and when a suspected target is found, the photoelectric pod (2) is used for locking and tracking the target, the position information and the azimuth information of the target are acquired in real time, and the sight of the photoelectric pod (2) continuously tracks the target; after a tracking target is confirmed, measuring the distance between the unmanned helicopter (1) and the target through a laser range finder of the photoelectric pod (2), receiving sight angle information of the photoelectric pod (2) by a fire control operator (301), sending a striking instruction to a missile distributor (3) through a bidirectional data link, controlling and selecting any one cylindrical missile (4) or all two cylindrical missiles (4) by the missile distributor (3), powering on the cylindrical missile (4) for self-checking, unfolding protective covers at the front end and the rear end of a launching cylinder, feeding back a self-checking result to a fire control computer (304) after the self-checking of the cylindrical missile (4) is finished, starting inertial group transmission alignment by the fire control computer (304), and carrying out sub-guide transmission alignment by a 'speed+position' matching method for ensuring that the cylindrical missile (4) has correct navigation resolving initial conditions at the moment;
the fire control system controls the guide head sight line of the barrel-mounted missile (4) to automatically face the target area, an operator switches to a guide head view field picture, and a tracking wave door is adjusted to lock the target; a fire control computer (304) on a fire control operation seat (301) in a ground control station (8) calculates and displays whether a multipurpose missile attack is allowed or not, an operator fires a missile launching button through a control handle (305), after the fire control computer (304) collects a launching instruction, a hitting target parameter, an engine ignition instruction and data transmission are automatically completed through a ground data link terminal (308), a missile distributor (3) receives the ground instruction and the target parameter received by an airborne data link terminal (7), the ground instruction and the target parameter are forwarded to a cylindrical missile (4), and after the cylindrical missile (4) feeds back the completion parameter binding, the missile distributor (3) completes the ignition of a solid rocket engine through a relay of the self-contained missile distributor; after the solid rocket engine is ignited, the multipurpose missile is pushed to fly to a target off track; after the fire control computer (304) of the ground control station (8) finishes missile launching, a picture can be displayed and switched to a detection picture of the photoelectric pod (2), so that the target is continuously observed, and the multipurpose missile striking effect is evaluated; the method can also switch to the view field picture of the guide head of another multipurpose missile, execute missile launching according to the steps, and implement continuous striking of the target.
2. The fire control system of the unmanned helicopter with the integrated observation and striking function according to claim 1, wherein the unmanned helicopter (1) receives a photoelectric pod (2), a control instruction of a barrel-mounted missile (4) and an ignition instruction transmitted by the barrel-mounted missile (4) which are sent out by a ground control station (8) through an airborne data link antenna (6), and forwards the instruction received by the airborne data link antenna (6) to a missile distributor (3) through an airborne data link terminal (7); the unmanned helicopter comprises an unmanned helicopter body, an airborne data chain antenna (6), an airborne data chain terminal (7) and a missile launcher, wherein the airborne data chain antenna (6) is arranged at the tail part of the unmanned helicopter body (1);
The ground data link terminal (308) receives downlink data sent by the airborne data link terminal (7) through the ground data link antenna (202), and acquires telemetry data and a striking load image through analysis; wherein the telemetry data comprises: the photoelectric pod (2) is used for tracking the infrared, visible light and laser working states, the tracking speed and the sight line pointing angle information; attitude information, guide head working state and tracking data of the barrel-mounted missile (4) and transfer alignment data.
3. The fire control system of the unmanned helicopter integrated with the observation and the striking as claimed in claim 2, wherein the GPS antenna (203) is used for positioning the ground control station (8), the fire control operator seat (301) and the flight control operator seat (302) are respectively used for the fire control and the flight control operation of operators, and the power distribution cabinet (307) is used for supplying power to the ground control station (8).
4. A fire control system of an unmanned helicopter with integrated fire control as claimed in claim 3, wherein the fire control operator seat (301) is further provided with a monitor (303), and the monitor (303) is used for executing the display of the fire control computer (304) on the impact load image and the telemetry data.
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| CN202111661731.7A CN114485268B (en) | 2021-12-31 | 2021-12-31 | Fire control system of unmanned helicopter integrating observation and striking |
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| CN202111661731.7A CN114485268B (en) | 2021-12-31 | 2021-12-31 | Fire control system of unmanned helicopter integrating observation and striking |
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| CN114485268B true CN114485268B (en) | 2024-05-03 |
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| CN107883817A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | Depopulated helicopter control system and control method with integrated guidance weapon |
| CN212332970U (en) * | 2019-10-12 | 2021-01-12 | 普宙飞行器科技（深圳）有限公司 | Unmanned aerial vehicle machine carries fire extinguishing bomb device, fire control unmanned aerial vehicle |
| CN111924103A (en) * | 2020-08-19 | 2020-11-13 | 航天科工通信技术研究院有限责任公司 | Intelligent bomb striking system of autorotation gyroplane |
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