CN114363391A - Unmanned aerial vehicle ground command control system - Google Patents
Unmanned aerial vehicle ground command control system Download PDFInfo
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- CN114363391A CN114363391A CN202210080051.4A CN202210080051A CN114363391A CN 114363391 A CN114363391 A CN 114363391A CN 202210080051 A CN202210080051 A CN 202210080051A CN 114363391 A CN114363391 A CN 114363391A
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Abstract
The invention discloses a ground command control system of an unmanned aerial vehicle, which comprises a cabin body, a display and control console subsystem, a communication subsystem, a data chain subsystem, a power supply and distribution subsystem and an environmental control subsystem, wherein the display and control console subsystem is connected with the cabin body; the front part in the cabin body is a working cabin, the storage cabin and the link cabin which are arranged on the left and the right are arranged above the rear part of the cabin body, and the oil engine cabin is arranged below the rear part; the display and control console subsystem comprises a first flight control seat, a second flight control seat, a comprehensive display seat, a task load seat and a link monitoring seat; the communication subsystem is used for providing monitoring inside and outside the cabin body, meteorology outside the cabin body and wireless communication outside the cabin body; the data chain subsystem is used for providing wireless data communication for the system and the unmanned aerial vehicle; the power supply and distribution subsystem is used for providing power for all electric equipment of the system; the environmental control subsystem is used for providing environmental conditions for the cabin. The invention integrates the ground command control station, the differential station, the line-of-sight link communication station and the satellite communication station into a whole, and the design greatly reduces the design cost and improves the integration level of the ground control system of the unmanned aerial vehicle.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle ground command control, and particularly relates to an unmanned aerial vehicle ground command control system.
Background
With the rapid development of unmanned aerial vehicles and other related neighborhood disciplines in recent years, unmanned aerial vehicles have developed powerful weapons integrating reconnaissance and attack, in the future, the unmanned aerial vehicle has the attacking capability of fully autonomously completing remote striking and even air-air combat missions, particularly the fixed wing unmanned aerial vehicle can be applied to the fields of surveying and mapping, geology, petroleum, agriculture and forestry and the like initially due to the excellent function and modular integration of the unmanned aerial vehicle, along with the rapid development of the technology of the unmanned aerial vehicle, the application of the fixed wing unmanned aerial vehicle is expanded more widely, at present, the fixed wing unmanned aerial vehicle can be widely applied to border cruising, tactical reconnaissance, public security monitoring, anti-terrorism, smuggling, anti-drug, disaster monitoring, forest fire prevention, communication relay, meteorological monitoring, geographic information reconnaissance and the like, meanwhile, the system can complete the task execution of special scenes suitable for the fields of battlefield reconnaissance and monitoring, positioning and calibration, damage assessment, electronic warfare and the like. Meanwhile, a Ground Control Station (GCS) matched with the development of large and medium-sized fixed wing unmanned aerial vehicles has comprehensive capabilities of integrating control, aiming, communication and processing, including mission planning, digital maps, satellite data chains and image processing capabilities, and the Ground Station has more powerful functions in the future, can control not only the unmanned aerial vehicle cluster of the same model, but also the united cluster of unmanned aerial vehicles of different models. The ground station system has openness and compatibility, the function expansion can be realized by adding new functional modules without redesigning and replacing the existing system, and the same hardware and software modules can be used for different ground stations.
The main functions of the unmanned aerial vehicle ground station include: (1) the method comprises the steps that control information of an unmanned aerial vehicle, an onboard task load and communication link equipment is collected through input equipment, and the control information is combined into a standard control instruction to be sent to the unmanned aerial vehicle and the link equipment; (2) receiving telemetering data of the unmanned aerial vehicle, the onboard task load and the communication link equipment in real time, analyzing the data and reflecting the data to an unmanned aerial vehicle operator in the forms of charts and the like; (3) and editing and planning the flight mission air route of the unmanned aerial vehicle. The unmanned aerial vehicle ground station is synthesized in same software and is realized above function, can not integrate each item function according to the actual application needs.
At present, the common unmanned aerial vehicle ground command control station in China is designed separately from a command control station, a differential station, a line-of-sight link communication station and a satellite communication station, and each station forms an independent movable ground station. From the economic benefits aspect, this kind of design greatly increased unmanned aerial vehicle system's design cost, from the technical aspect consideration, this kind of design technique degree of difficulty also will greatly increased.
Disclosure of Invention
In order to improve the integration level of the ground command control system of the unmanned aerial vehicle and reduce the design cost of the ground command control system of the unmanned aerial vehicle, the invention aims to provide the ground command control system of the unmanned aerial vehicle.
The invention adopts the following technical scheme to achieve the aim that:
an unmanned aerial vehicle ground command control system comprises a cabin body, a display and control console subsystem, a communication subsystem, a data chain subsystem, a power supply and distribution subsystem and an environmental control subsystem; wherein:
the front part in the cabin body is a working cabin, the storage cabin and the link cabin which are arranged on the left and right are arranged above the rear part of the cabin body, and the oil engine cabin is arranged below the rear part;
the display control console subsystem comprises a first flight control seat, a second flight control seat, a comprehensive display seat, a task load seat and a link monitoring seat; the first flight control seat and the second flight control seat are used for operating the unmanned aerial vehicle and monitoring various parameters of the unmanned aerial vehicle; the comprehensive display mat is connected with interactive display equipment arranged on the outer wall of the cabin body and used for displaying display pictures of other seats; the task load seat is used for monitoring parameters and instructions of the mounted load equipment and operating when the unmanned aerial vehicle carries out a task; the link monitoring agent is used for monitoring the communication link;
the communication subsystem is used for providing internal and external monitoring of the cabin body, external weather of the cabin body and external wireless communication of the cabin body;
the data chain subsystem is used for providing wireless data communication for the system and the unmanned aerial vehicle;
the power supply and distribution subsystem is used for providing power for all electric equipment of the system;
and the environmental control subsystem is used for providing environmental conditions for the cabin.
Furthermore, a first lighting window, a power supply hole door, an air outlet, an oil engine heat dissipation window and a storage bin door are formed in the left side wall of the cabin body; the right side wall of the cabin body is provided with an air inlet, an access door, a second lighting window and a link cabin door, and a remote control panel is arranged inside the right side wall of the cabin body; the outer wall of the rear end of the cabin body is provided with an oil engine mounting door; a link access is arranged on the top plate above the link cabin.
Furthermore, the first flight control seat and the second flight control seat of the display and control console subsystem are arranged at the front end in the working cabin in parallel, and the comprehensive display seat, the task load seat and the link monitoring seat are arranged at the rear end in the working cabin in parallel.
Further, the ground command control system of unmanned aerial vehicle as claimed in claim 1, wherein the communication subsystem comprises a voice recording device, a 4G/5G communication module, a weather meter lodging mechanism and a GNSS differential station; the 4G/5G communication module comprises a 4G/5G antenna, the GNSS differential station comprises a receiver and a GPS antenna, and the 4G/5G antenna and the GPS antenna are arranged at the top of the cabin; the meteorological instrument is arranged at the top of the cabin body through a meteorological instrument lodging mechanism.
Further, the data chain divides the system to include lifter, the U wave band antenna and the U wave band equipment that are connected to and the L wave band antenna and the L wave band equipment that are connected, wherein, the U wave band antenna passes through the lifter and installs on the outer wall of cabin body one side, set up electronic top cap on the link access & exit at link cabin top, be equipped with the electronic lifter that is used for installing L wave band antenna in the link cabin.
Furthermore, the environment control subsystem comprises an integrated air conditioner, a lighting lamp and a fan, the integrated air conditioner is installed at the front end of the cabin body, and an air duct connected with the integrated air conditioner 2 is formed in the top of the working cabin; and a temperature and humidity clock is arranged on the inner wall of the working cabin.
Furthermore, the first flight control seat and the second flight control seat are arranged the same, and comprise a flight operating platform, wherein a flight control computer and a keyboard, a mouse, an accelerator lever, a rocker and a pedal which are matched with the flight control computer are arranged on the flight operating platform; the flight control computer is provided with a plurality of displays; and the operation platforms of the comprehensive display seat, the task load seat and the link monitoring seat are all provided with a keyboard, a mouse and a plurality of displays.
Further, supply and distribute the power subsystem and include UPS power, distribution control box, diesel generator, first mains input and second mains input, wherein, the distribution control box includes box and installs dual supply automatic switch-over controller in it, first mains input and second mains input are installed in the power wall box, and first mains input, second mains input are used for connecting the input of first city electricity and second city electricity respectively, dual supply automatic switch-over controller is connected respectively to the output of diesel generator and power wall box.
Furthermore, the outer wall of the front end of the cabin body is provided with a boarding ladder, and the outer wall of the rear end of the cabin body is provided with a boarding ladder.
Further, still include the chassis car, the chassis car passes through the sub vehicle frame and installs in cabin body below.
Compared with the prior art, the invention has the following technical effects:
1. the invention integrates the ground command control station, the differential station, the line-of-sight link communication station and the satellite communication station into a whole, and the design greatly reduces the design cost and improves the integration level of the ground control system of the unmanned aerial vehicle.
2. The system of the invention designs a first flight control seat, a second flight control seat, a comprehensive display seat, a task load seat, a link monitoring seat and interactive display equipment, wherein the hardware of each seat adopts a universal design, various types of software can be floatingly installed, and the functions are flexibly distributed; the reliability of the ground control unmanned aerial vehicle can be effectively improved by arranging the cabin control layout for multi-seat monitoring and control; the ground command control system carries out data communication in the local area network through the network switch, and hot backup can be carried out on communication among the control seats, the seats and the stations.
3. The invention is provided with the 4G/5G communication module, and can adopt a 4G/5G network for communication; the software can acquire specific data of wind speed and wind direction of a pilot on a seat to monitor a flight field visually by arranging the weather meter, so that the safety of a flight task is ensured; meanwhile, through designing the dual-redundancy line-of-sight link communication, the reliability of the ground control unmanned aerial vehicle can be effectively improved, and the safety of a flight task is guaranteed.
4. Supply the distribution subsystem to be equipped with the commercial power, the two redundant power supplies of oil machine, through adopting the distribution control box to control the first commercial power input in city, second commercial power input and diesel generator's automatic switch-over, simultaneously for each system provides two redundant power supplies, make the seamless switching of power supply, meanwhile, supply power for system key part as emergency power source through UPS host computer and supporting UPS battery, the power supply and distribution reliability of unmanned aerial vehicle ground command control system has effectively been improved, thereby unmanned aerial vehicle flight control's reliability has been improved, reduce its risk of doing things, the security has been improved greatly. The reliability of the ground control unmanned aerial vehicle is effectively improved, and the safety of flight tasks is guaranteed.
5. The chassis vehicle is designed at the bottom of the cabin body, so that the overall maneuverability of the system is strong.
6. The link antenna is convenient and safe to use by designing the link cabin and installing the link antenna, designing the electric sliding top cover on the top of the link cabin for protecting the link antenna and arranging the automatic lifting mechanism for installing and controlling the lifting action of the link antenna.
7. The cloud platform camera installed on the cabin roof through the cloud platform lodging device is convenient to install and control the posture of the cloud platform camera, and is convenient for workers to monitor the environment outside the cabin.
8. The integration and the arrangement of a plurality of seats can flexibly configure various ground station common software, so that the system can support the unmanned aerial vehicle simulation training function and the multi-machine monitoring function, has the intelligent control capability, can predict and analyze system faults and give alarm prompts, and provides a disposal method; the intelligent planning capability is provided, and automatic online task re-planning can be performed.
Drawings
Fig. 1 is a system block diagram of the ground command control system of the unmanned aerial vehicle of the present invention;
FIG. 2 is a schematic view of a display console subsystem;
FIG. 3 is a schematic diagram of a communication subsystem;
FIG. 4 is a schematic diagram of a data chain subsystem;
FIG. 5 is a schematic diagram of a power supply and distribution subsystem;
FIG. 6 is a schematic diagram of an environmental control subsystem;
fig. 7 is a system cross-linked diagram of the ground command and control system of the unmanned aerial vehicle of the present invention;
FIG. 8 is a schematic view of the exterior left side of the enclosure;
FIG. 9 is an external right side schematic view of the nacelle;
FIG. 10 is a schematic view of the exterior rear side of the nacelle;
FIG. 11 is a top schematic view of the nacelle;
FIG. 12 is a schematic view of the interior layout of the cabin;
FIG. 13 is a schematic view of the layout of the control seats;
FIG. 14 is a schematic layout diagram of a composite display agent, task load agent, and link monitor agent.
FIG. 15 is a schematic diagram of a power supply and distribution subsystem;
FIG. 16 is a diagram of power supply and distribution lines of the power supply and distribution subsystem.
The reference numerals in the drawings mean:
1. a storage box; 2. an integrated air conditioner; 3. a second lighting window; 4. a power supply hole door; 5. a sunshade; 6. an air outlet; 7. an oil engine heat dissipation window; 8. a storage compartment door; 9. an interactive display device; 10. a link bay door; 11. a first lighting window; 12. an entrance and exit door; 13. an air inlet; 14. a first flight control agent; 15. a second flight control agent; 16. a comprehensive display mat; 17. a task load mat; 18. a link monitor agent; 19. an air duct; 20. a link access port; 21. a remote control panel; 22. a storage bin; 23. an oil engine compartment; 24. a link bay; 25. an air outlet; 26. a temperature and humidity clock; 27. a coat hook; 28. 4G/5G antenna; 29. a weather instrument; 30. a U-band antenna; 31. a lifting rod; 32. climbing a ladder; 33. an oil engine mounting door; 34. boarding a cabin ladder; 35. a GPS antenna; 36. a meteorological instrument lodging mechanism; 37. a motorized top cover; 38. an L-band antenna; 39. a cradle head lodging device; 40. cloud deck camera.
The invention is further explained below with reference to the drawings and the detailed description.
Detailed Description
The ground command control system of the unmanned aerial vehicle comprises a cabin body, a display and control console subsystem, a communication subsystem, a data chain subsystem, a power supply and distribution subsystem and an environmental control subsystem. Wherein:
as shown in fig. 8-12, the front part of the cabin is a working cabin, the storage cabin 22 and the link cabin 24 are arranged on the left and right sides above the rear part of the cabin, the oil engine cabin 23 is arranged below the rear part, an oil engine is installed in the oil engine cabin 23 and used for emergency power supply of the command and control system, the link cabin 24 is internally provided with a link antenna, and the storage cabin 22 is used for storing accessories of articles. Preferably, the left side wall of the cabin body is provided with a first lighting window 11, a power supply hole door 4, an air outlet 25, an oil engine heat dissipation window 7 and a storage bin door 8; the right side wall of the cabin body is provided with an air inlet 13, an access door 12, a second lighting window 3 and a link cabin door 10, and a remote control panel 21 is arranged inside the right side wall of the cabin body. The outer wall of the rear end of the cabin body is provided with an oil engine mounting door 33; the top plate above the link cabin 24 is provided with a link access opening 20.
The first lighting window 11 and the second lighting window 3 are used for providing light rays for the working cabin; the power supply hole door is used for conveniently providing power distribution for all electric equipment in the square cabin, and the air outlet 25 and the air inlet are used for keeping air in the square cabin smooth; the oil engine heat dissipation window 7 is used for quickly dissipating heat generated in the working process of the oil engine, and the link cabin door 10 and the access door 12 are respectively used for facilitating the opening of the link cabin 24 and the operation cabin for operation; the link access port 20 is used for data interaction between link equipment in the cabin body and a link cabin 24; the remote control panel 21 is used for facilitating the control of the power supply of each power supply device in the cabin body by the working personnel.
The display and control console subsystem comprises a first flight control console 14, a second flight control console 15, a comprehensive display console 16, a task load console 17 and a link monitoring console 18; each seat forms a local area network through a network switch to carry out data interaction, and the seat communicates with the unmanned aerial vehicle through radio waves; the first flight control seat 14 and the second flight control seat 15 are used for operating the unmanned aerial vehicle and monitoring various parameters of the unmanned aerial vehicle, and one is active and the other is standby; the comprehensive display seat 16 is used for comprehensively displaying the display pictures of all other seats, and particularly displays the display pictures through the interactive display equipment 9 arranged on the outer wall of the cabin; the task load seat 17 is used for monitoring and operating parameters and instructions of load equipment mounted on the aircraft platform when the unmanned aerial vehicle carries out a task, and is a seat for controlling the load; the link monitor agent 18 is used to monitor the communication quality of the link. In the scheme, the hardware of each seat adopts a universal design, various kinds of software can be floatingly installed, and the functions are flexibly distributed; under the design, the reliability of the ground control unmanned aerial vehicle can be effectively improved through the control layout in the cabin monitored and controlled by the multiple seats; through the design of the network switch, the ground command control system carries out data communication in the local area network, and controls seats, and the communication among the seats and in the stations can carry out hot backup. Preferably, the first flight control agent 14 and the second flight control agent 15 are arranged in parallel at the front end in the working cabin, and the integrated display agent 16, the mission load agent 17, and the link monitor agent 18 are arranged in parallel at the rear end in the working cabin.
And the communication subsystem is used for providing the inside and outside monitoring of the cabin, the outside weather of the cabin and the outside wireless communication of the cabin for the whole ground command control system. The communication subsystem has an aviation plug cable connection. Specifically, the communication subsystem includes voice recording equipment (can design according to concrete needs, and this embodiment includes 5 monaural headset, 4 adapters, 4 under-deck cameras, cloud platform camera, hard disk recorder and lodging elevating system), 4G/5G communication module, weather instrument 28, weather instrument lodging mechanism 36 and GNSS difference ground station. The cameras in the cabin are used for observing the conditions of all positions in the cabin, and the tripod head camera 40 is convenient for workers in the cabin to observe the conditions of the runway of the unmanned aerial vehicle outside; the 4G/5G communication module comprises a 4G/5G antenna 29, and the GNSS differential station comprises a receiver and a GPS antenna 35; the 4G/5G antenna 2929 and the GPS antenna 35 are installed at the top of the cabin, the 4G/5G antenna 29 is used for the communication between the ground command control system and the 4G/5G wireless network of the external environment, and the GPS antenna 35 is used for the communication between differential equipment (namely a GNSS differential receiver) and a satellite; the meteorological instrument 28 is arranged on the top of the cabin body through a meteorological instrument lodging mechanism 36; the safety of the flight task is ensured by arranging the meteorological instrument 28 to ensure that software collects specific data of wind speed and wind direction of a pilot on a seat to visually monitor the flight field.
And the data chain subsystem is used for providing wireless data communication for the whole ground command control system and the unmanned aerial vehicle. The data chain subsystem has an aviation plug cable connection. Specifically, the data chain subsystem includes a lifting rod 31 (in this embodiment, a manual lifting rod), a U-band antenna and a U-band device connected to each other, and an L-band antenna 38 (i.e., a link antenna) and an L-band device connected to each other, wherein the U-band antenna 30 is installed on the outer wall of one side of the cabin body through the lifting rod 31, and the U-band antenna is controlled to lift. In the above-mentioned scheme, through designing two redundancy stadia link communication, can effectively improve ground control unmanned aerial vehicle's reliability, guarantee the safety of flight task. Preferably, an electric top cover 37 is arranged on the link access 20 at the top of the link cabin 24, and an electric lifting rod for installing an L-band antenna 38 (i.e. a link antenna) is arranged in the link cabin 24. In this mode, the electric top cover 37 is opened, and the L-band antenna 38 is lifted and lowered by the electric lifting mechanism.
The power supply and distribution subsystem is used for supplying power to all electric equipment of the whole system. As shown in fig. 5, the power supply and distribution subsystem includes a UPS power source (including a UPS host and its associated UPS battery), a distribution control box, and a diesel generator. The power supply and distribution subsystem is provided with an aviation plug cable connection and is arranged in a cabinet below the link monitoring seat 16.
The environmental control subsystem is used for providing environmental conditions for the cabin and comprises an integrated air conditioner 2, an illuminating lamp and a fan. The integrated air conditioner 2 is arranged at the front end of the cabin body, and an air duct 19 connected with the integrated air conditioner 2 is arranged at the top of the working cabin; preferably, a temperature and humidity clock 26 is arranged on the inner wall of the working cabin.
The invention also comprises vehicle-mounted accessories comprising related maintenance tools, specifically comprising a grounding wire, a wiring terminal, a power supply cable, a cable reel, a commercial power transfer cable, a military folding chair, a civil tool box and an electric tool box, which are arranged in the accessory box.
As shown in fig. 13 and 14, as a preferred implementation of the present invention, the first and second flight control agents 14 and 15 are provided in the same manner, specifically, as follows: the flight control device comprises a flight operation platform with the size of 1100mm multiplied by 825mm multiplied by 1689mm, wherein a flight control computer and a keyboard, a mouse, a rocker, an operating rod and pedals which are matched with the flight control computer are arranged on the flight operation platform; the flight control computer is provided with 2 24-inch displays and 3 21.5-inch displays; a first flight control computer of the first flight control seat 14 and a second flight control computer of the second flight control seat 15 form a rack-mounted server to form an internally closed data operation system; the sizes of the operation platforms of the comprehensive display platform 16, the task load platform 17 and the link monitoring platform 18 are 2100mm 850m 1758, a corresponding computer and a matched keyboard and mouse thereof are arranged on the operation platforms, and the computer is provided with 3 24-inch displays; the link monitor agent 16 is also equipped with a picture splitter; and the link computer of the comprehensive display position, the task load computer of the task load position and the link monitoring computer of the link monitoring position form a rack server to form an internally closed data operation system. Shock pad and channel-section steel are all installed to above-mentioned each operation panel below all around, conveniently dismantle and maintain, and such design makes the shelter install also can not influence its whole operating efficiency and performance on moving platform.
As shown in fig. 15 and 16, as a preferred implementation manner of the present invention, the power supply and distribution subsystem includes a UPS power supply, a distribution control box, a diesel generator, a first commercial power input end and a second commercial power input end, wherein the distribution control box includes a box body and a dual-power automatic switching controller installed therein, the first commercial power input end and the second commercial power input end are installed in a power wall box, the first commercial power input end and the second commercial power input end are respectively used for connecting the input of a first commercial power and a second commercial power, the output ends of the diesel generator and the power wall box are respectively connected to the dual-power automatic switching controller, the first output end of the dual-power automatic switching controller is connected to a picture splitter, a pan-tilt inverter 39, a down inverter 36 of a weather instrument, an exhaust fan, an integrated air conditioner 2 and an interactive display device 9, etc., the second output end of the dual-power automatic switching controller is connected to the UPS power supply, the UPS power supply is connected with a display console subsystem, link equipment (namely L-band equipment and U-band equipment), satellite communication equipment, a GPS antenna 35, an in-cabin camera, a tripod head camera 40, a lighting lamp, a weather instrument 28, a 4G/5G antenna 29 and other equipment.
In the above technical scheme, the distribution control box is used for controlling automatic switching of a first commercial power input end, a second commercial power input end and a diesel generator in a city. The first commercial power input end and the second commercial power input end are respectively connected to the input end of the power supply wall box through a power supply hole door 4 (adopting a connector) arranged on the cabin wall. The first commercial power input end and the second commercial power input end are both commercial power AC220V power supply input ends which respectively supply power for indoor and outdoor environment equipment and other equipment, and the diesel generator is an AC220V power supply input end.
Preferably, a coat hook 27 is arranged on the inner wall of the right side of the cabin body.
Preferably, the outer wall of the front end of the cabin body is provided with a cabin ascending ladder 34, and the outer wall of the rear end of the cabin body is provided with a top ascending ladder 32; the boarding ladder 34 is convenient for workers to enter the shelter, and the climbing ladder 32 is used for workers to conveniently climb the shelter roof for operation.
Preferably, the top of the cabin is provided with a sunshade for shielding all components on the top of the cabin.
Preferably, the invention further comprises a chassis truck, wherein the chassis truck is arranged below the cabin body through the auxiliary frame and used for realizing that the cabin body freely moves to a proper working place, and the maneuvering performance of the ground command control system is effectively improved. And a storage box is also arranged on the auxiliary frame.
The operation process of the large and medium-sized fixed wing unmanned aerial vehicle ground command control system is as follows:
opening a cable box arranged at the bottom of the vehicle to take out the commercial power cable; and inserting aerial plug interfaces of the cable tray into the commercial power 1 and the commercial power 2 on the power hole door 4, and connecting the other end of the commercial power cable into a distribution box of the flight site.
The air switch on the power supply hole door 4 is opened.
The access door of the working compartment is opened.
And opening the commercial power 1, the commercial power 2 and the UPS air switch on the distribution box.
And turning a knob switch on the distribution box to remote control.
And a knob switch on the distribution box is turned to the UPS on line.
And the UPS is turned on by long pressing a UPS switch button.
And pressing a power button on the remote control of the distribution box.
And pressing a first flight control seat button and a second flight control seat button on the remote control of the distribution box.
And pressing a task load seat button and a comprehensive monitoring seat display button on the remote control of the distribution box.
And pressing a link monitoring seat button on the distribution box remote control.
And pressing a control button of the interactive display equipment on the remote control of the distribution box.
And pressing a wall insertion button on the remote control of the distribution box.
And pressing a link cabin button on the distribution box remote control.
The lighting/air-exhausting button on the distribution box remote control is pressed.
And pressing a direct current equipment button on the remote control of the distribution box.
The lodging mechanism on the distribution box remote control is pressed.
The power switch on the meteorological instrument lodging mechanism 36 on the distribution box remote control is toggled on.
The control of the meteorological instrument lodging mechanism 36 on the remote control of the distribution box is switched to be lifted, after the meteorological instrument 28 is lifted to the right position, the red light is turned on, the control switch is switched to the middle position, and the power switch is switched to the off position.
And a power supply button of the tripod head lodging device 39 on the remote control of the distribution box is pressed.
And (3) shifting a lifting switch of the cradle head lodging device 39 on the remote control of the distribution box to a lifting position, shifting a control switch to a middle position after the cradle head is lifted to the proper position, and pressing a power supply button.
The link cabin 24 is opened, the electric top cover 37 is pressed down to be opened, after the electric top cover 37 is opened, the lifting button of the electric lifting rod is pressed down, and when the electric lifting rod is lifted to a proper position, the stopping button is pressed down.
The U-band antenna 30 is taken out, and the U-band antenna 30 is mounted on the lifting rod 31 and connected to the U-link connection line.
The accessory case was opened, and the 65 "display (i.e., interactive display device 9) was removed and hung from the outer wall of the cabin, and the power cord and HDIM video cord were connected.
And opening the computer of each seat, and operating the software on each seat after the computer is started.
The network switch 1, the network switch 2, and the screen splitter are turned on.
And opening power switches of the L-band equipment and the U-band equipment below the comprehensive seat cabinet.
And opening the display interfaces of the tripod head camera 40 outside the cabin and the camera inside the cabin through the webpage.
Waiting for command operation of a commander and a pilot.
In summary, the system of the present invention realizes the following main functions:
the main functions of the downlink data management program are as follows: receiving and distributing telemetry data, locally storing and reading telemetry data, receiving and distributing task load data, and locally storing and reading task load data.
The main functions of the flight control program are: the method comprises the steps of acquiring flight control instructions, transmitting and receiving remote control instructions, displaying remote-measuring information related to the flight of the unmanned aerial vehicle, locally storing and reading remote-control data, displaying remote-measuring and remote-controlling original data and the like.
The main functions of the link control program are: remote measurement and control of an unmanned aerial vehicle data link and control of a ground antenna.
The main functions of the flight path planning program are as follows: route planning, waypoint/route instruction collection, geographic location and track display.
The main functions of the task load control program are as follows: acquiring the instruction of the task load equipment and displaying the data of the task load equipment.
Claims (10)
1. An unmanned aerial vehicle ground command control system is characterized by comprising a cabin body, a display and control console subsystem, a communication subsystem, a data chain subsystem, a power supply and distribution subsystem and an environmental control subsystem; wherein:
the front part in the cabin body is a working cabin, the storage cabin (22) and the link cabin (24) which are arranged on the left and right are arranged above the rear part of the cabin body, and the oil cabin (23) is arranged below the rear part;
the display control console subsystem comprises a first flight control seat (14), a second flight control seat (15), a comprehensive display seat (16), a task load seat (17) and a link monitoring seat (18); wherein the first flight control seat (14) and the second flight control seat (15) are used for operating the unmanned aerial vehicle and monitoring various parameters of the unmanned aerial vehicle; the comprehensive display seat (16) is connected with an interactive display device (9) arranged on the outer wall of the cabin body and used for displaying display pictures of other seats; the task load seat (17) is used for monitoring parameters and instructions of the mounted load equipment and operating when the unmanned aerial vehicle carries out tasks; the link monitoring agent (18) is used for monitoring the communication link;
the communication subsystem is used for providing internal and external monitoring of the cabin body, external weather of the cabin body and external wireless communication of the cabin body;
the data chain subsystem is used for providing wireless data communication for the system and the unmanned aerial vehicle;
the power supply and distribution subsystem is used for providing power for all electric equipment of the system;
and the environmental control subsystem is used for providing environmental conditions for the cabin.
2. The unmanned aerial vehicle ground command and control system of claim 1, wherein the left side wall of the cabin body is provided with a first lighting window (11), a power supply hole door (4), an air outlet (25), an oil engine heat dissipation window (7) and a storage bin door (8); the right side wall of the cabin body is provided with an air inlet (13), an access door (12), a second lighting window (3) and a link cabin door (10), and a remote control panel (21) is arranged inside the right side wall of the cabin body; the outer wall of the rear end of the cabin body is provided with an oil engine mounting door (33); a link access (20) is arranged on the top plate above the link cabin (24).
3. The ground command control system of unmanned aerial vehicle according to claim 1, wherein the first flight control seat (14) and the second flight control seat (15) of the display and control console subsystem are arranged in parallel at the front end in the working cabin, and the integrated display seat (16), the task load seat (17) and the link monitor seat (18) are arranged in parallel at the rear end in the working cabin.
4. The ground command control system of unmanned aerial vehicle as claimed in claim 1, wherein the communication subsystem comprises a voice recording device, a 4G/5G communication module, a weather meter (28), a weather meter lodging mechanism (36) and a GNSS differential station; the 4G/5G communication module comprises a 4G/5G antenna (29), the GNSS differential station comprises a receiver and a GPS antenna (35), and the 4G/5G antenna (29) and the GPS antenna (35) are installed at the top of the cabin; the meteorological instrument (28) is arranged at the top of the cabin body through a meteorological instrument lodging mechanism (36).
5. The ground command control system of the unmanned aerial vehicle as claimed in claim 1, wherein the data chain subsystem comprises a lifting rod (31), a connected U-band antenna and U-band device, and a connected L-band antenna (38) and L-band device, wherein the U-band antenna (30) is installed on the outer wall of one side of the cabin body through the lifting rod (31), an electric top cover (37) is arranged on the link access (20) at the top of the link cabin (24), and an electric lifting rod for installing the L-band antenna (38) is arranged in the link cabin (24).
6. The ground command and control system of the unmanned aerial vehicle as claimed in claim 1, wherein the environmental control subsystem comprises an integrated air conditioner, a lighting lamp and a fan, the integrated air conditioner (2) is installed at the front end of the cabin, and an air duct (19) connected with the integrated air conditioner (2) is opened at the top of the working cabin; and a temperature and humidity clock (26) is arranged on the inner wall of the working cabin.
7. The ground command control system of the unmanned aerial vehicle according to claim 1, wherein the first flight control seat (14) and the second flight control seat (15) are arranged identically, and comprise a flight console on which a flight control computer and a keyboard, a mouse, a throttle lever, a rocker and a pedal matched with the flight control computer are arranged; the flight control computer is provided with a plurality of displays; and the operation platforms of the comprehensive display seat (16), the task load seat (17) and the link monitoring seat (18) are all provided with a keyboard, a mouse and a plurality of displays.
8. The ground command control system for unmanned aerial vehicle as claimed in claim 1, wherein the power supply and distribution subsystem comprises a UPS power supply, a distribution control box, a diesel generator, a first commercial power input terminal and a second commercial power input terminal, wherein the distribution control box comprises a box body and a dual-power automatic switching controller installed therein, the first commercial power input terminal and the second commercial power input terminal are installed in a power wall box, the first commercial power input terminal and the second commercial power input terminal are respectively used for connecting the input of a first commercial power and a second commercial power, and the output terminals of the diesel generator and the power wall box are respectively connected with the dual-power automatic switching controller.
9. The ground command and control system for unmanned aerial vehicles according to claim 1, wherein the outer wall of the front end of the cabin body is provided with a boarding ladder (34), and the outer wall of the rear end of the cabin body is provided with a boarding ladder (32).
10. The ground command control system for unmanned aerial vehicles according to claim 1, further comprising a chassis mounted below the cabin via a sub-frame.
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| CN202210080051.4A CN114363391A (en) | 2022-01-24 | 2022-01-24 | Unmanned aerial vehicle ground command control system |
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| CN202210080051.4A CN114363391A (en) | 2022-01-24 | 2022-01-24 | Unmanned aerial vehicle ground command control system |
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