Multifunctional aircraft command vehicle
Through the power supply solution integrating mains, vehicle-mounted power supply and UPS system, the problem of insufficient power supply during the movement of the aircraft command vehicle is solved, equipment redundancy and efficient booting are achieved, and control seats are added to meet the operation needs of multiple people.
Patent Information
- Application Number
- CN202422487212.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-15
- Publication Date
- 2025-07-04
- Estimated Expiration
- 2034-10-15
AI Technical Summary
Traditional aircraft command vehicles cannot supply power at the same time during movement, and the computer terminal equipment is insufficient redundant, resulting in equipment being unable to be redundant, insufficient seats, and low equipment booting efficiency.
The integrated power supply solution of the main power supply, vehicle-mounted power supply system and UPS system is adopted, and power is supplied to the main, secondary industrial control machine and display screen through inverters and UPS systems to realize uninterrupted power supply, and control seats are added to realize data interconnection and independent operation.
Ensure that the command vehicle is continuously powered during the movement, achieve equipment redundancy and efficient start-up, and add control seats to meet the needs of multiple people.
Smart Images
Figure CN223058888U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aircraft control vehicles, in particular to a multifunctional aircraft command vehicle. Background Art
[0002] Aircraft have become increasingly common in various industries. Currently, aircraft command vehicles mainly rely on mains power supply. With the continuous change of application scenarios, when the command vehicle is moving continuously, the traditional command vehicle cannot achieve the simultaneous power supply of all devices during the vehicle movement; and when a failure occurs in the computer terminal device of the traditional command vehicle, the aircraft will be out of control and the device cannot be redundant; moreover, the traditional command vehicle faces the problem of insufficient seats due to a large number of personnel.
[0003] The purpose of the aircraft command vehicle provided by the utility model is to solve the problems that all devices cannot be powered simultaneously during the movement of the command vehicle, the computer terminal device cannot be redundant, the startup efficiency of the command vehicle device is slow, and the seats are insufficient. Content of the Utility Model
[0004] The utility model provides a multifunctional aircraft command vehicle, including: a command vehicle body, the command vehicle body includes a cab (1), a command cabin (2) and an equipment cabin (3), and the command cabin (2) is isolated from the equipment cabin (3); an antenna for communicating with the aircraft is arranged outside the top of the command vehicle body, and the antenna is connected to a control system inside the command vehicle; the control system includes multiple display screens arranged in the command cabin (2), the multiple display screens are controlled by an industrial control computer, and a corresponding control seat (203) is arranged in front of each display screen, and each control seat (203) can control the industrial control computer; the industrial control computer includes a main industrial control computer (302) and a secondary industrial control computer (214), and the display screens include multiple main display screens (205) and multiple secondary display screens (206);
[0005] The power supply and distribution system of the command vehicle is integrated by mains power, vehicle-mounted power supply and distribution system and UPS system. The mains power and the vehicle-mounted power supply and distribution system are connected to an in-vehicle inverter, and the mains power or the vehicle-mounted power supply and distribution system supplies power to the inverter. The inverter directly supplies power to the secondary industrial control computer (214) and the secondary display screen (206). The inverter is connected to the UPS system, and the UPS system is connected to the main industrial control computer (302) and the main display screen (205). The inverter transmits power to the UPS and then the UPS system supplies power to the main industrial control computer (302) and the main display screen (205), or the UPS battery in the UPS system directly supplies power to the main industrial control computer (302) and the main display screen (205).
[0006] A multifunctional aircraft command vehicle as described above, wherein the command cabin includes a first workbench (201) and a second workbench (202). A plurality of control seats (203) are arranged in front of the first workbench (201) and the second workbench (202). Two auxiliary display screens (206) are fixed on the storage cabinet above the first workbench (201), and two main display screens (205) are embedded at the partition board (207) above the second workbench (202).
[0007] A multifunctional aircraft command vehicle as described above, wherein a control lever (208) is installed in the middle of the second workbench (202) for controlling the aircraft. The control lever (208) includes a side lever and a remote controller.
[0008] A multifunctional aircraft command vehicle as described above, wherein the interior of the command cabin (2) further includes a lighting component. The lighting component includes a lighting lamp (209) and a lighting lamp switch (210). The lighting lamp (209) is installed on the inner side of the middle top of the command cabin (2), and the lighting lamp switch (210) is installed at the door opening of the command cabin (2). The lighting lamp switch (210) is installed side by side with the air conditioner switch. The air conditioner switch controls an air conditioner (211) installed above the partition board (207); the interior of the command cabin (2) further includes a monitoring camera (212), and the monitoring camera (212) is installed on the top of the command cabin (2).
[0009] A multifunctional aircraft command vehicle as described above, wherein the antennas arranged on the outer side of the top of the command vehicle body include a PCS antenna, a power radio antenna, and a weather station antenna. The antennas and the brackets are placed in an antenna cabinet (213) installed at the door opening of the command cabin (2) of the command vehicle when idle, and are taken out from the antenna cabinet (213) and magnetically adsorbed on the outer side of the top of the command vehicle body when in use.
[0010] A multifunctional aircraft command vehicle as described above, wherein an electrical cabinet (301), a main industrial control computer (302), and a vehicle-mounted power supply and distribution system (303) are arranged inside the equipment cabin (3). The electrical cabinet (301) and the vehicle-mounted power supply and distribution system (303) are placed side by side. A UPS device and an inverter are installed inside the electrical cabinet (301). A partition layer (3031) is installed above the vehicle-mounted power supply and distribution system (303) as a storage layer. The main industrial control computer (302) is installed at a position below the partition board (207) of the equipment cabin (3), and a fire extinguisher (304) is placed outside the electrical cabinet (301).
[0011] A multifunctional aircraft command vehicle as described above, wherein a secondary industrial control computer (214) is installed at a position below the partition board (207) inside the command cabin (2), and the main industrial control computer (302) is electrically connected to the secondary industrial control computer (214).
[0012] A multifunctional aircraft command vehicle as described above, wherein the inverter distributes multiple power supplies to in-vehicle devices, including a direct transmission circuit for powering basic vehicle-mounted devices, a step-down circuit, a circuit for powering the UPS main unit, and a circuit for powering the secondary industrial control computer (214) and the secondary display screen (206).
[0013] A multifunctional aircraft command vehicle as described above, wherein the in-vehicle energy battery in the vehicle-mounted power supply and distribution system provides direct current of 12V, the UPS battery in the UPS system provides direct current of 72V, and alternating current of 220V is provided by three methods: the in-vehicle energy battery through an inverter, the UPS system, and the commercial power.
[0014] The beneficial effects achieved by the present utility model are as follows:
[0015] (1) The present utility model improves the vehicle's power supply and distribution system by integrating commercial power, vehicle-mounted power supply and distribution, and UPS, enabling the command vehicle to ensure the power demand of the entire command cabin even when changing from a stopped state to a driving state, realizing an uninterrupted function.
[0016] (2) The present utility model adds control seats, and the data between each control seat is interconnected; they can also operate independently without interference. When one control seat fails and cannot be used, any one of the other control seats can take over the original control seat. Description of the Drawings
[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings described below are only some embodiments recorded in the present utility model. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings.
[0018] Figure 1 It is a schematic diagram of the cabin partition of a multifunctional aircraft command vehicle;
[0019] Figure 2 It is a distribution diagram of the equipment in the command cabin and the equipment cabin;
[0020] Figure 3 It is a schematic diagram of the connection of vehicle-mounted devices.
[0021] Reference Signs:
[0022] 1. Cockpit; 2. Command cabin; 3. Equipment cabin; 201. Desk 1; 202. Desk 2; 203. Control seat; 204. Seat lever; 205. Main display screen; 206. Sub-display screen; 207. Partition; 208. Control lever; 209. Lighting lamp; 210. Lighting switch; 211. Air conditioner; 212. Monitoring camera; 213. Antenna cabinet; 302. Main industrial control computer; 303. Vehicle-mounted power supply and distribution system; 304. Fire extinguisher; 2031. Seat 1; 2032. Seat 2; 2033. Seat 3; 2034. Seat 4; 3031. Storage compartment. Detailed implementation manner
[0023] The following combines the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work belong to the protection scope of the present invention.
[0024] Embodiment
[0025] See Figures 1 to 3 , the present invention provides a multifunctional aircraft command vehicle, including: a command vehicle body, the command vehicle body includes a cockpit 1, a command cabin 2 and an equipment cabin 3, the cockpit 1 is located at the front of the vehicle, the command cabin 2 is located in the middle of the vehicle, the equipment cabin 3 is located at the rear of the vehicle, and the command cabin 2 is isolated from the equipment cabin 3. An antenna for communicating with the aircraft is provided outside the top of the command vehicle body, and the antenna is connected to the control system in the command vehicle; the control system includes multiple display screens arranged in the command cabin 2, the multiple display screens are controlled by multiple industrial control computers, and corresponding control seats 203 are arranged in front of each display screen, and each control seat 203 can control multiple industrial control computers; the industrial control computers include a main industrial control computer 302 and a sub-industrial control computer 214, and the display screens include multiple main display screens 205 and multiple sub-display screens 206. The power supply and distribution system of the command vehicle is integrated by the commercial power, the vehicle-mounted power supply and distribution system 303 and the UPS (uninterruptible power supply) system. The commercial power and the vehicle-mounted power supply and distribution system 303 are connected to the in-vehicle inverter, and the commercial power or the vehicle-mounted power supply and distribution system 303 supplies power to the inverter. The inverter supplies power to the sub-industrial control computer 214 and the sub-display screen 206. The inverter is connected to the UPS system, and the UPS system is connected to the main industrial control computer 302 and the main display screen 205. The inverter transmits power to the UPS and the UPS system supplies power to the main industrial control computer 302 and the main display screen 205, or the UPS battery in the UPS system directly supplies power to the main industrial control computer 302 and the main display screen 205.
[0026] The interior of the command module 2 includes a variety of on-vehicle devices, including multiple workstations. For example, in the command module 2 as shown in the figure, there are two workstations. Workstation 1 201 is set near the middle window, and workstation 2 202 is set near the partition 207. Multiple control seats 203 are arranged in front of each workstation. For example, in the command module 2 as shown in the figure, two control seats 203 are arranged in front of both workstation 1 201 and workstation 2 202. That is, the command vehicle of the present utility model can accommodate four operators. A seat lever 204 is installed on the side of the control seat 203, and the angle of the seat back can be adjusted through the seat lever 204. Optionally, the four control seats 203 include seat 1 2031, seat 2 2032, seat 3 2033, and seat 4 2034. Among them, seat 2 2032 cannot slide back and forth, and only the angle of the seat back can be adjusted through the side seat lever 204; the lower bases of seat 1 2031, seat 3 2033, and seat 4 2034 are connected to the vehicle body through a front-back sliding device for front-back movement, and at the same time, the angle of the seat back can be adjusted through the side seat lever 204. The control seats are interconnected with each other and can also operate independently without interference. When one control seat fails and cannot be used, any one of the other control seats can replace the original control seat.
[0027] Above each workstation inside the command module 2, multiple display screens are fixed. For example, in the command module 2 as shown in the figure, there are four display screens, two main display screens 205 and two secondary display screens 206. Among them, the two secondary display screens 206 are fixed on the storage cabinet above workstation 1 201 and can be used for meteorological information, etc., to observe the meteorological data of the flight test environment in real time. Two storage cabinets for storing flight test materials and office supplies are also arranged adjacent to each other; the two main display screens 205 are embedded in the partition 207 above workstation 2 202, and a control lever 208 is installed in the middle of workstation 2 202 for controlling the aircraft.
[0028] In addition, the interior of the command module 2 also includes a lighting component. The lighting component includes a lighting lamp 209 and a lighting switch 210. The lighting lamp 209 is installed on the inner side of the middle top of the command module 2, and the lighting switch 210 is installed at the door of the command module 2. The lighting switch 210 is installed side by side with the air conditioner switch, and the air conditioner switch controls the air conditioner 211 installed above the partition 207. The interior of the command module 2 also includes a monitoring camera 212, and the monitoring camera 212 is installed on the top of the command module 2.
[0029] The antennas installed on the outer side of the top of the command vehicle body include, but are not limited to, PCS antennas, power radio antennas, and weather station antennas. These antennas and their brackets are placed in the antenna cabinet 213 installed at the door opening of the command cabin 2 of the command vehicle when not in use, and are taken out from the antenna cabinet 213 and magnetically adsorbed on the outer side of the top of the command vehicle body when in use. The PCS antenna is connected to the PCS device (energy storage converter) in the electrical cabinet 301 of the equipment compartment 3. There are 2 PCS antennas. One of the PCS antennas is used by the PCS device to receive satellite data and transmit it to the aircraft, and the PCS device is connected to the control lever 208 (including side lever, remote control) to obtain control signals and send them to the aircraft through the other PCS antenna for flight control, and receive the flight data of the aircraft.
[0030] Inside the equipment compartment 3, an electrical cabinet 301, a main industrial control computer 302, and a vehicle-mounted power supply and distribution system 303 are arranged. The electrical cabinet 301 and the vehicle-mounted power supply and distribution system 303 are placed side by side. The electrical cabinet 301 is internally installed with a UPS device and an inverter. A storage compartment 3031 is installed above the vehicle-mounted power supply and distribution system 303. The main industrial control computer 302 is installed at a position below the partition 207 of the equipment compartment 3, and a fire extinguisher 304 is placed outside the electrical cabinet 301. A secondary industrial control computer 214 is installed at a position below the partition 207 in the command cabin 2, and the main industrial control computer 302 is electrically connected to the secondary industrial control computer 214. The vehicle-mounted power supply and distribution system 303 includes vehicle-mounted power supply and distribution equipment and vehicle-mounted energy batteries. The vehicle-mounted power supply and distribution equipment includes, for example, engines, vehicle-mounted circuits, etc. The vehicle-mounted energy batteries can be connected to the mains, and the mains powers and stores energy for the vehicle-mounted energy batteries. The following gives some parameter examples of the vehicle-mounted energy batteries. The vehicle-mounted energy batteries are composed of 4 groups of series-connected battery cells, with a usable power of 7.2 degrees of electricity, a maximum voltage of 3.65V for a single battery cell, a storage voltage of 3.2V, and a storage SOC of about 45%; the battery weight is about 30kg, the service life is 3 years, the battery SOC (system-on-chip) is charged to 90% before use, and when the battery SOC is used up to 40%, use should be stopped. When the vehicle needs to be stored for a long time, the battery should be discharged to about 45%; the battery should be avoided from direct sunlight to prevent the battery life from being reduced due to excessive temperature.
[0031] In the present utility model, the power supply connection relationship between the various vehicle-mounted devices in the aircraft command vehicle is as Figure 3 shown. The inverter is connected to the mains or the vehicle-mounted battery, and the mains or the vehicle-mounted battery directly powers the inverter. The inverter distributes multiple power supplies to the in-vehicle devices (taking 7 routes as an example in the figure), including a direct transmission circuit for powering the basic vehicle-mounted devices, a buck circuit, a circuit for powering the UPS host, and a circuit for powering the secondary industrial control computer 214 and the secondary display screen 206.
[0032] Figure 3There are 4 direct current circuits for powering the basic in-vehicle equipment. The first socket strip can be connected to standby equipment, the second socket strip is connected to a laptop and a display monitor, the fourth socket strip is connected to a small weather station and an in-vehicle monitor. (The small weather station consists of a secondary display screen 206 and a weather station antenna. When in use, place the weather station antenna on the roof of the vehicle and turn on the power of the command cabin 2, and the weather station will start automatically. The small weather station can collect parameters such as wind speed, wind direction, temperature, air pressure, humidity and noise in real time and display them on the secondary display screen 206 in real time), and the circuit connected to the ceiling light. The step-down circuit is one of the inverters, and is connected to the air conditioner and the radio through a step-down module. The inverter powers the UPS host through a 16A fifth socket strip. The UPS host is connected to a UPS battery (the UPS host and the UPS battery form a UPS system), the main industrial control computer 302 and two main display screens. The power-on of the industrial control computer and the display screen is set unidirectionally, that is, just press the button once and it can remain on all the time. The power supply method between the main industrial control computer 302 and the two main display screens is direct transmission by the UPS. The inverter powers the secondary industrial control computer 214 and two secondary display screens 206 through the third socket strip. The power supply method between the secondary industrial control computer 214 and the secondary display screen 206 monitor is direct transmission by the inverter. The UPS host powers the PCS device, the switch, the power radio, etc. through the sixth socket strip.
[0033] The power supply system in the command vehicle is divided into direct current 12V, 72V and alternating current 2020V. The direct current 12V is directly provided by the in-vehicle energy battery. When using the in-vehicle energy battery, it is necessary to press the battery power-on button briefly to make the battery output current, and it is necessary to press the inverter power-on button briefly to turn on the inverter. The direct current 72V is provided by the UPS battery. When using the UPS battery, long press the power-on button of the UPS host to turn on the UPS host and convert the direct current 72V into alternating current 220V for use. The alternating current 220V is provided by the in-vehicle energy battery through three methods: inverter, UPS output and commercial power, with commercial power being preferred and the inverter and UPS automatically switching. Long press the power-on / off button of the UPS host to complete the power-on and power-off of the UPS host. It is possible to judge whether the UPS host is turned on by the current output situation on the UPS host panel. The temperature of the UPS host during use shall not exceed 50°C, otherwise the UPS host will automatically cut off the power. The output power of the inverter is 3KW, which can convert the direct current 12V of the in-vehicle energy battery into alternating current 220V, and at the same time connect to the commercial power and grid with the 220V power converted from the in-vehicle energy battery. Under the condition that commercial power is preferred, when one of the power sources of commercial power or the energy battery is disconnected, the inverter can still output the 220V alternating current that has not been disconnected for the load to use.
[0034] For those skilled in the art, it is obvious that the present utility model is not limited to the details of the above-described exemplary embodiments, and the present utility model can be implemented in other specific forms without departing from the spirit or basic characteristics of the present utility model. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present utility model is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present utility model. Any reference signs in the claims should not be construed as limiting the claimed elements involved.
[0035] In the description of the present utility model, unless otherwise specified, the meaning of "a plurality of" is two or more; the orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation on the present utility model. In addition, terms such as "first", "second", "third", etc. are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.
[0036] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "connected" and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
Claims
1. A multi-functional aircraft command vehicle, characterized in that, Including: The command vehicle body, which includes a cockpit (1), a command cabin (2) and an equipment cabin (3). There is a separation between the command cabin (2) and the equipment cabin (3). An antenna for communicating with the aircraft is arranged on the outer side of the top of the command vehicle body, and the antenna is connected to the control system inside the command vehicle. The control system includes multiple display screens arranged in the command cabin (2), and the multiple display screens are controlled by an industrial control computer. A corresponding control seat (203) is arranged in front of each display screen, and each control seat (203) can operate the industrial control computer. The industrial control computer includes a main industrial control computer (302) and a secondary industrial control computer (214), and the display screens include multiple main display screens (205) and multiple secondary display screens (206). The power supply and distribution system of the command vehicle is integrated by the commercial power, the vehicle-mounted power supply and distribution system and the UPS system. The commercial power and the vehicle-mounted power supply and distribution system are connected to the in-vehicle inverter, and the inverter is powered by the commercial power or the vehicle-mounted power supply and distribution system. The inverter directly powers the secondary industrial control computer (214) and the secondary display screens (206). The inverter is connected to the UPS system, and the UPS system is connected to the main industrial control computer (302) and the main display screens (205). The inverter transmits power to the UPS and then the UPS system powers the main industrial control computer (302) and the main display screens (205), or the UPS battery in the UPS system directly powers the main industrial control computer (302) and the main display screens (205).
2. The multifunctional aircraft command vehicle according to claim 1, characterized in that, Inside the command cabin, there are a first workbench (201) and a second workbench (202). Multiple control seats (203) are arranged in front of the first workbench (201) and the second workbench (202). Two secondary display screens (206) are fixed on the storage cabinet above the first workbench (201), and two main display screens (205) are embedded at the partition (207) above the second workbench (202).
3. The multifunctional aircraft command vehicle according to claim 2, wherein, A joystick (208) is installed in the middle of the second workbench (202) for controlling the aircraft. The joystick (208) includes a side stick and a remote controller.
4. The multifunctional aircraft command vehicle according to claim 1, wherein The interior of the command cabin (2) also includes a lighting component, which includes a lighting lamp (209) and a lighting lamp switch (210). The lighting lamp (209) is installed on the inner side of the middle top of the command cabin (2), and the lighting lamp switch (210) is installed at the door opening of the command cabin (2). The lighting lamp switch (210) is installed side by side with the air conditioner switch, and the air conditioner switch controls the air conditioner (211) installed above the partition (207). The interior of the command cabin (2) also includes a monitoring camera (212), and the monitoring camera (212) is installed on the top of the command cabin (2).
5. The multifunctional aircraft command vehicle according to claim 1, characterized in that, The antennas arranged on the outer side of the top of the command vehicle body include a PCS antenna, a power radio antenna and a weather station antenna. The antennas and the brackets are placed in the antenna cabinet (213) installed at the door opening of the command cabin (2) of the command vehicle when not in use, and are taken out from the antenna cabinet (213) and magnetically adsorbed on the outer side of the top of the command vehicle body when in use.
6. The multifunctional aircraft command vehicle according to claim 1, characterized in that, Inside the equipment cabin (3), an electrical cabinet (301), a main industrial control computer (302) and a vehicle-mounted power supply and distribution system (303) are arranged. The electrical cabinet (301) and the vehicle-mounted power supply and distribution system (303) are placed side by side. An UPS device and an inverter are installed inside the electrical cabinet (301). A storage compartment (3031) is installed above the vehicle-mounted power supply and distribution system (303). The main industrial control computer (302) is installed below the partition board (207) of the equipment cabin (3). A fire extinguisher (304) is placed outside the electrical cabinet (301).
7. The multifunctional aircraft command vehicle according to claim 6, wherein, A secondary industrial control computer (214) is installed at the position below the partition board (207) inside the command cabin (2). The main industrial control computer (302) is electrically connected to the secondary industrial control computer (214).
8. A multifunctional aircraft command vehicle according to claim 1, characterized in that, The inverter distributes multiple power supplies to in-vehicle devices, including a direct transmission circuit for powering basic vehicle-mounted devices, a step-down circuit, a circuit for powering the UPS main unit, and a circuit for powering the secondary industrial control computer (214) and the secondary display screen (206).
9. The multifunctional aircraft command vehicle according to claim 8, characterized in that, The vehicle-mounted energy battery in the vehicle-mounted power supply and distribution system provides direct current of 12V. The UPS battery in the UPS system provides direct current of 72V. Alternating current of 220V is provided by three methods: through the vehicle-mounted energy battery via the inverter, the UPS system, and the commercial power.