CN108454874B - Unmanned aerial vehicle emitter - Google Patents
Unmanned aerial vehicle emitter Download PDFInfo
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- CN108454874B CN108454874B CN201810535872.6A CN201810535872A CN108454874B CN 108454874 B CN108454874 B CN 108454874B CN 201810535872 A CN201810535872 A CN 201810535872A CN 108454874 B CN108454874 B CN 108454874B
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- unmanned aerial
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- launching
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- 239000007789 gas Substances 0.000 claims description 77
- 230000001681 protective effect Effects 0.000 claims description 13
- 239000011261 inert gas Substances 0.000 claims description 7
- 238000004378 air conditioning Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 3
- 238000011835 investigation Methods 0.000 abstract description 3
- 238000010304 firing Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Toys (AREA)
Abstract
The invention discloses an unmanned aerial vehicle transmitting device which comprises a bracket, at least one transmitting unit positioned on the bracket and a pressure control system. Each emission unit comprises an inflation device, a gas storage device, a plurality of emission cylinders, an inflation control device and a plurality of control valves. The gas storage device is connected with the gas filling device, each emission cylinder is connected with the gas storage device, the gas filling control device is connected between the gas filling device and the gas storage device, and each control valve is respectively connected between one emission cylinder and the gas storage device. The pressure control system is positioned on the bracket and is connected with each gas storage device. The unmanned aerial vehicle transmitting device provided by the invention can complete the transmission of a plurality of unmanned aerial vehicles in a short time, achieves the requirement of space layout, covers a certain area in the shortest time, completes various tasks such as investigation in the coverage area, and can meet the use requirement of future intelligent war on the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle transmitting device.
Background
Unmanned aerial vehicle has advantages such as mobility height, use cost are low, maintenance use are simple as modern technological achievement, consequently, unmanned aerial vehicle all has extensive application in fields such as take photo by plane, agriculture, plant protection, express delivery transportation, observe wild animal, survey and drawing, relief of disaster etc. now to play important effect.
With the technological change, more warfare among countries in the future is unmanned intelligent warfare, and unmanned aerial vehicles play an important role in the intelligent warfare, and the space-to-day layout of unmanned aerial vehicles is particularly important in the process of the intelligent warfare. How to design a launch device of unmanned aerial vehicle, can launch many unmanned aerial vehicles in the short time, accomplish unmanned aerial vehicle's sky overall arrangement fast, be an important subject that the person of the field faced.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle transmitting device which can transmit a plurality of unmanned aerial vehicles in a short time so as to complete the space-to-day layout of the unmanned aerial vehicles and meet the use requirement of future intelligent wars on the unmanned aerial vehicles.
The unmanned aerial vehicle transmitting device provided by the embodiment of the invention comprises a bracket, at least one transmitting unit positioned on the bracket and a pressure control system. Each emission unit comprises an inflation device, a gas storage device, a plurality of emission cylinders, an inflation control device and a plurality of control valves. The gas storage device is connected with the gas filling device, each emission cylinder is connected with the gas storage device, the gas filling control device is connected between the gas filling device and the gas storage device, the control valves are respectively in one-to-one correspondence with the emission cylinders, and each control valve is respectively connected between the emission cylinder and the gas storage device. A pressure control system is positioned at the bracket and is connected to each of the gas storage devices.
Preferably, the control valve is a solenoid valve.
Preferably, the unmanned aerial vehicle transmitting device comprises two transmitting units, the bracket comprises a bottom frame and a protective frame arranged on the bottom frame, the inflating device is positioned on the bottom frame, and the gas storage devices and the transmitting cylinders of the two transmitting units are respectively positioned in the protective frame.
Preferably, the protection frame includes two support spaces arranged in a stacked manner, and each support space is used for accommodating the gas storage device of one emission unit and a plurality of emission cylinders.
Preferably, the gas storage device and the plurality of emission cylinders of each emission unit are arranged in the corresponding supporting space in parallel.
Preferably, the unmanned aerial vehicle launching device further comprises a plurality of supporting wheels, and the supporting wheels are respectively arranged at the bottom of the bracket and fixedly connected with the bracket.
Preferably, the unmanned aerial vehicle launching device further comprises at least one angle adjusting device, wherein the angle adjusting device is connected between the underframe and the protective frame and used for adjusting the angle between the protective frame and the underframe.
Preferably, the unmanned aerial vehicle flies to launch device still includes at least one bracing piece, the bracing piece is located the bracket is kept away from one side of transmitting end, and bracing piece one end is fixed with the bracket, and the other end supports and holds ground.
Preferably, each emission unit further comprises a gas channel communicating the inflation device and the gas storage device, the gas channel is arranged in the bracket, and the inflation control device is arranged in the gas channel.
Preferably, the inflator is filled with an inert gas.
According to the unmanned aerial vehicle launching device, the plurality of launching units are arranged, the gas storage device and the plurality of launching cylinders are arranged in each launching unit, the inflation time and the inflation speed of the inflation device to the gas storage device are controlled by the inflation control device, so that after gas in the gas storage device is released, a preset pressure value can be quickly reached, meanwhile, the on-off between the gas storage device and the launching cylinders is controlled by the control valve, and the launching time interval between every two unmanned aerial vehicles which are launched adjacently can be 8-10 seconds.
Therefore, according to the unmanned aerial vehicle transmitting device provided by the invention, the transmitting cylinders among the plurality of transmitting units alternately transmit the unmanned aerial vehicle, so that the transmission of a plurality of unmanned aerial vehicles can be completed in a short time, the requirement of space layout is met, a certain area is covered in the shortest time, various tasks such as investigation in the covered area are completed, and the use requirement of future intelligent war on the unmanned aerial vehicle can be met.
Drawings
Fig. 1 is a schematic diagram of an unmanned aerial vehicle transmitting device according to an embodiment of the present invention;
fig. 2 is a front view of the drone launcher of fig. 1;
fig. 3 is a rear view of the drone launching device of fig. 1;
fig. 4 is a side view of the drone launching device of fig. 1; a kind of electronic device with high-pressure air-conditioning system
Fig. 5 is a schematic view of the internal structure of the cradle in the unmanned aerial vehicle launching device of fig. 1.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, based on the embodiments of the invention, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the invention. Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, based on the embodiments of the invention, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
The unmanned aerial vehicle provided by the invention is further described in detail below with reference to the accompanying drawings and the embodiments.
Referring to fig. 1 to 5, an unmanned aerial vehicle launching device 100 according to an embodiment of the present invention includes a bracket 10, at least one launching unit 20 positioned on the bracket 10, and a pressure control system 30.
Each of the emitting units 20 includes an inflator 21, a gas storage device 22, a plurality of emitting cylinders 23, an inflation control device 25 (the inflation control device 25 is not shown in fig. 1, please refer to the inflation control device shown in fig. 4), and a plurality of control valves 24.
The gas storage device 22 is connected with the air charging device 21, and an air charging control device 25 is arranged between the gas storage device 22 and the air charging device 21. The inflation control device 25 is used for controlling the connection and the disconnection between the inflation device 21 and the gas storage device 22, and controlling the inflation speed and the inflation time of the inflation device 21 to the gas storage device 22.
Each emission cylinder 23 is respectively connected with the air storage device 22, a plurality of control valves 24 are respectively corresponding to the emission cylinders 23 one by one, and each control valve 24 is connected between the corresponding emission cylinder 23 and the air storage device 22 and is used for controlling the conduction and the closing between the air storage cylinder 221 and the emission cylinder 23. That is, a control valve 24 is provided between each of the launching cylinders 23 and the gas storage device 22 for controlling the conduction and closing between the gas storage device 22 and the launching cylinders 23.
The pressure control system 30 is positioned at the bracket 10 and connected to each of the air storage devices 22, for detecting and controlling the pressure value in each of the air storage devices 22. The pressure control system 30 detects a pressure value in the air cylinder 221, and controls and adjusts the pressure in the air cylinder 221 according to the detected pressure value.
In this embodiment, the control valve 24 is an electromagnetic valve, so as to realize automatic control of conduction and closing between the gas storage device 22 and the emission tube 23. In other embodiments, the control valve 24 may be another mechanical valve, and the communication and closing between the gas storage device 22 and the canister 23 may be achieved manually.
For convenience of description, in the present embodiment, the unmanned aerial vehicle transmitting apparatus 100 includes two transmitting units 20. The bracket 10 comprises a bottom frame 11 and a protective frame 12 arranged on the bottom frame 11, wherein the air charging devices 21 of the two emission units 20 are respectively positioned in the bottom frame 11, and the air storage devices 22 and the emission cylinders 23 of the two emission units 20 are respectively positioned in the protective frame 12.
Specifically, the protective frame 12 includes two support spaces 121 disposed in a stacked manner, and each of the support spaces 121 is configured to accommodate the gas storage device 22 and the plurality of the emission cylinders 23 of one emission unit 20. The gas storage device 22 and the plurality of the launching cylinders 23 of each launching unit 20 are arranged in the corresponding supporting space 121 in parallel.
In the present embodiment, the gas storage device 22 of each of the firing units 20 includes two gas cylinders 221, and each of the firing units 20 includes 3 firing cylinders 23. The two air cylinders 221 and the 3 air cylinders 23 of each emission unit 20 are arranged in parallel in the corresponding supporting space 121. That is, the unmanned aerial vehicle transmitting device 100 provided in the present embodiment can transmit 6 unmanned aerial vehicles in a short time.
For convenience of explanation, 3 emission cartridges 23 in the first emission unit 20 in this embodiment are respectively identified as emission cartridge A1, emission cartridge A2, emission cartridge A3, and 3 emission cartridges 23 in the second emission unit 20 are respectively identified as emission cartridge B1, emission cartridge B2, emission cartridge B3. The process of launching the unmanned aerial vehicle of the unmanned aerial vehicle launching device 100 in the present embodiment will be specifically described below.
When the unmanned aerial vehicle needs to be launched, the launching barrel A1, the launching barrel A2, the launching barrel A3, the launching barrel B1, the launching barrel B2 and the launching barrel B3 are respectively filled with the unmanned aerial vehicle. The inflator 21 of each of the emitting units 20 is filled with an inert gas.
The inflation control device 25 of each of the transmitting units 20 controls the inflation device 21 to be in communication with the gas storage device 22, and the gas in the inflation control device 25 is released into the corresponding gas storage device 22. The inflation control device 25 controls the inflation time to be within 10 to 12 seconds, so that the pressure in the gas storage device 22 can be increased to a predetermined pressure value. When the pressure in the gas storage device 22 reaches the prescribed pressure value, the inflation control device 25 controls the gas storage device 22 to be disconnected from the corresponding inflation device 21 to stop inflation.
And opening a control valve 24 between the launching tube A1 and the corresponding gas storage device 22, and launching the unmanned aerial vehicle in the launching tube A1. After the unmanned aerial vehicle of the launching tube A1 is launched, the unmanned aerial vehicle stays for 1 to 2 seconds, and the air charging control device 25 of the first launching unit 20 controls the air storage device 22 to be communicated with the corresponding air charging device 21 so as to charge the corresponding air storage device 22. The inflation control device 25 controls the inflation time to be within 10 to 12 seconds, so that the pressure in the gas storage device 22 can be brought to a predetermined pressure value. When the pressure in the gas storage device 22 reaches the prescribed pressure value, the inflation control device 25 controls the gas storage device 22 to be disconnected from the corresponding inflation device 21 to stop inflation.
Meanwhile, after the unmanned aerial vehicle in the launching tube A1 is launched, the unmanned aerial vehicle stays for 8-10 seconds, a control valve 24 between the launching tube B1 and a corresponding gas storage device 22 is opened, and the unmanned aerial vehicle in the launching tube B1 launches. After the unmanned aerial vehicle of the launching tube B1 is launched, the unmanned aerial vehicle stays for 1 to 2 seconds, and the air inflation control device 25 of the second launching unit 20 controls the air storage device 22 to be communicated with the corresponding air inflation device 21 so as to inflate the corresponding air storage device 22. The inflation control device 25 controls the inflation time to be within 10 to 12 seconds, so that the pressure in the gas storage device 22 can be brought to a predetermined pressure value. When the pressure in the gas storage device 22 reaches the prescribed pressure value, the inflation control device 25 controls the gas storage device 22 to be disconnected from the corresponding inflation device 21 to stop inflation.
Meanwhile, after the unmanned aerial vehicle in the launching tube B1 is launched, the unmanned aerial vehicle stays for 8-10 seconds, a control valve 24 between the launching tube A2 and a corresponding gas storage device 22 is opened, and the unmanned aerial vehicle in the launching tube A2 launches. When the unmanned aerial vehicle of the launching tube A2 is launched, the unmanned aerial vehicle stays for 1 to 2 seconds, and the air charging control device 25 of the first launching unit 20 controls the air storage device 22 to be communicated with the corresponding air charging device 21 so as to charge the corresponding air storage device 22. The inflation control device 25 controls the inflation time to be within 10 to 12 seconds, so that the pressure in the gas storage device 22 can be brought to a predetermined pressure value. When the pressure in the gas storage device 22 reaches the prescribed pressure value, the inflation control device 25 controls the gas storage device 22 to be disconnected from the corresponding inflation device 21 to stop inflation. And sequentially transmitting the transmitting cylinder B2, the transmitting cylinder A3 and the unmanned aerial vehicle in the transmitting cylinder B3 according to the circulation.
That is, in the unmanned aerial vehicle launching device provided by the embodiment of the invention, after the unmanned aerial vehicle in one of the launching cylinders 23 in one of the launching units 20 is launched, the unmanned aerial vehicle is stopped for 1-2 seconds to inflate the corresponding inflation device 21, so that the inflation of the air storage device 22 is completed within 10-12 seconds to reach a specified pressure value, and air storage preparation is made for the unmanned aerial vehicle launching in the other launching cylinder 23 in the launching unit 20. Meanwhile, after the unmanned aerial vehicle in the transmitting cylinder 23 is transmitted, the unmanned aerial vehicle stays for 8-10 seconds, and the unmanned aerial vehicle in one transmitting cylinder 23 in the other transmitting unit 20 is transmitted. In this way, the firing of the drones in all the firing cylinders 23 is completed.
In other words, according to the unmanned aerial vehicle launching device 100 provided by the invention, the plurality of launching units 20 are arranged, each launching unit 20 is provided with the gas storage device 22 and the plurality of launching cylinders 23, the inflation time and the inflation speed of the gas storage device 22 by the gas charging device 21 are controlled by the gas charging control device 25, so that after the gas in the gas storage device 22 is released, a preset pressure value can be quickly reached, meanwhile, the on-off between the gas storage device 22 and the launching cylinders 23 is controlled by the control valve 24, and the launching time interval between every two unmanned aerial vehicles which are launched adjacently can be completed by 8-10 seconds. According to the unmanned aerial vehicle launching device 100 provided by the embodiment of the invention, the first inflation time of the two gas storage devices 22 is 10-12 seconds, and the launching time interval between the two unmanned aerial vehicles is 8-10 seconds, so that the launching of 6 unmanned aerial vehicles can be completed within 40-50 seconds after the first inflation is completed.
Therefore, according to the unmanned aerial vehicle transmitting device 100 provided by the invention, the transmitting cylinders 23 among the plurality of transmitting units 20 alternately transmit unmanned aerial vehicles, so that the transmission of a plurality of unmanned aerial vehicles can be completed in a short time, the requirement of space layout is met, a certain area is covered in the shortest time, various tasks such as investigation in the covered area are completed, and the use requirement of future intelligent wars on the unmanned aerial vehicles can be met.
Meanwhile, the unmanned aerial vehicle transmitting device 100 provided by the invention can transmit a plurality of unmanned aerial vehicles in a short time, belongs to a cluster transmitting device, has a simple structure, is convenient to operate, belongs to a light transmitting mechanism, is convenient to carry and transport, can greatly reduce cost, and has strong operability.
In the present embodiment, the unmanned aerial vehicle transmitting device 100 is provided with two transmitting units 20, and each transmitting unit 20 includes 3 transmitting drums 23. In other embodiments, other numbers of the emitting units 20, such as 4, 5, etc., may be set according to specific space layout requirements, and each emitting unit 20 may also set other numbers of the emitting cylinders 23, such as 4, 5, etc., of the emitting cylinders 23 according to actual space layout requirements. Of course, the order of the emission of the plurality of emission tubes 23 of each emission unit 20 may be adjusted according to actual requirements, and is not limited to the order of A1, A2, A3 of the present embodiment.
In this embodiment, the inert gas is nitrogen. In other embodiments, other inert gases such as helium, argon, and the like may also be used. After unmanned aerial vehicle launches, inert gas's release can not produce the pollution to the air, and has the advantage of recycling.
In this embodiment, the unmanned aerial vehicle launching device 100 further includes a plurality of supporting wheels 40, and the supporting wheels 40 are respectively disposed at the bottom of the bracket 10 and fixedly connected with the bracket 10. The support wheels 40 are provided to facilitate transport of the unmanned aerial vehicle launching device 100.
Further, the unmanned aerial vehicle launching device 100 further comprises at least one angle adjusting device 50, and the angle adjusting device 50 is connected between the chassis 11 and the protective frame 12, and is used for adjusting the angle between the protective frame 12 and the chassis 11. When the angle between the protection frame 12 and the chassis 11 is set, the angle between the transmitting tube 23 and the chassis 11 is also set, so that the angle between the transmitting tube 23 and the chassis 11 can be adjusted by the angle adjusting device 50, thereby achieving the purpose of adjusting the transmitting angle of the unmanned aerial vehicle.
Further, the unmanned aerial vehicle launching device 100 further comprises at least one supporting rod 60, the supporting rod 60 is arranged on one side, far away from the launching end, of the bracket 10, one end of the supporting rod 60 is fixed with the bracket 10, and the other end of the supporting rod abuts against the ground. In this embodiment, the unmanned aerial vehicle launching device 100 is provided with a pair of support rods 60 for supporting the protective frame 12 to enhance the reliability and stability of the entire bracket 10.
Further, referring to fig. 5, each of the emitting units 20 further includes a gas channel 70 communicating the inflator 21 and the gas storage device 22, the gas channel 70 is disposed in the bracket 10, and the inflation control device 25 is disposed in the gas channel 70. The inert gas of the inflator 21 is supplied into the corresponding gas storage device 22 through the gas passage 70.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (9)
1. An unmanned aerial vehicle transmitting device, comprising:
a bracket;
two transmitting units positioned at the bracket, each of the transmitting units comprising:
an inflator;
the gas storage device is connected with the air charging device;
the emission cylinders are connected with the gas storage device and are parallel to each other;
the inflation control device is connected between the inflation device and the gas storage device; a kind of electronic device with high-pressure air-conditioning system
The control valves are respectively in one-to-one correspondence with the emission cylinders, and each control valve is respectively connected between the emission cylinder and the gas storage device; a kind of electronic device with high-pressure air-conditioning system
The pressure control system is positioned on the bracket and connected with each gas storage device;
the bracket comprises a bottom frame and a protective frame arranged on the bottom frame, the air charging device is positioned on the bottom frame, and the air storage devices and the transmitting cylinders of the two transmitting units are respectively positioned in the protective frame.
2. The unmanned aerial vehicle launching device of claim 1, wherein the control valve is a solenoid valve.
3. The unmanned aerial vehicle launching device of claim 1, wherein the protective frame comprises two support spaces arranged in a stacked manner, each of the support spaces being configured to accommodate the gas storage device of one launching unit and a plurality of launching cylinders.
4. The unmanned aerial vehicle launching device of claim 3, wherein the gas storage device and the plurality of launching drums of each launching unit are disposed side by side in the corresponding supporting space.
5. The unmanned aerial vehicle launching device of claim 1, further comprising a plurality of support wheels, wherein the support wheels are respectively disposed at the bottom of the bracket and fixedly connected to the bracket.
6. The unmanned aerial vehicle launching device of claim 1, further comprising at least one angle adjustment device connected between the chassis and the guard frame for adjusting an angle between the guard frame and the chassis.
7. The unmanned aerial vehicle launching device of claim 1, further comprising at least one support bar, wherein the support bar is disposed on a side of the bracket away from the launching end, one end of the support bar is fixed to the bracket, and the other end of the support bar abuts against the ground.
8. The unmanned aerial vehicle launching device of claim 1, wherein each launching unit further comprises a gas channel that communicates the inflation device with the gas storage device, the gas channel being disposed within the cradle, the inflation control device being disposed within the gas channel.
9. The unmanned aerial vehicle launching device of claim 1, wherein the inflator is filled with an inert gas.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535872.6A CN108454874B (en) | 2018-05-30 | 2018-05-30 | Unmanned aerial vehicle emitter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535872.6A CN108454874B (en) | 2018-05-30 | 2018-05-30 | Unmanned aerial vehicle emitter |
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| CN108454874A CN108454874A (en) | 2018-08-28 |
| CN108454874B true CN108454874B (en) | 2023-08-29 |
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| CN201810535872.6A Active CN108454874B (en) | 2018-05-30 | 2018-05-30 | Unmanned aerial vehicle emitter |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436364B (en) * | 2018-10-22 | 2021-10-15 | 南京航空航天大学 | Device and method for continuous launching of unmanned aerial vehicle |
| CN109229409B (en) * | 2018-10-23 | 2022-04-05 | 西北工业大学 | Cluster type unmanned aerial vehicle aerial rapid transmitting system |
| CN111056034B (en) * | 2019-11-21 | 2021-07-20 | 中国电子科技集团公司电子科学研究院 | Unmanned aerial vehicle cluster ejection system and working method |
| CN113998136B (en) * | 2021-12-02 | 2024-01-19 | 北京机电工程研究所 | Micro-aircraft transmitting device and method |
| CN117550123B (en) * | 2024-01-10 | 2024-04-09 | 成都航天万欣科技有限公司 | Pneumatic ejection system and control method |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5695153A (en) * | 1995-11-16 | 1997-12-09 | Northrop Grumman Corporation | Launcher system for an unmanned aerial vehicle |
| US6260797B1 (en) * | 1998-01-13 | 2001-07-17 | Science Applications International Corporation | Transformable gun launched aero vehicle |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| GB0312353D0 (en) * | 2003-05-30 | 2003-07-02 | Qinetiq Ltd | Launching aerial vehicles |
| AU2009200804A1 (en) * | 2006-07-31 | 2009-03-19 | Elbit Systems Ltd. | An unmanned aerial vehicle launching and landing system |
| CN103693207A (en) * | 2013-12-12 | 2014-04-02 | 桂林航龙科讯电子技术有限公司 | Small-sized unmanned aerial vehicle ejector |
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN107352041A (en) * | 2017-08-22 | 2017-11-17 | 成都戎创航空科技有限公司 | Unmanned plane Pneumatic catapult |
| CN206679277U (en) * | 2017-04-19 | 2017-11-28 | 桂艳春 | A kind of gas-powered catapult |
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN207346072U (en) * | 2017-09-01 | 2018-05-11 | 深圳市华讯方舟系统技术有限公司 | Unmanned plane protects structure and UAV system |
| CN208855884U (en) * | 2018-05-30 | 2019-05-14 | 深圳市华讯方舟系统技术有限公司 | Unmanned plane emitter |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7281682B2 (en) * | 2003-03-25 | 2007-10-16 | Dbi/Century Fuels & Aerospace Services | Spacecraft and launch system |
| US8662441B2 (en) * | 2011-02-16 | 2014-03-04 | Sparton Corporation | Unmanned aerial vehicle launch system |
| GB2531683B (en) * | 2016-02-12 | 2018-03-28 | Robonic Ltd Oy | Arrangement in catapult |
-
2018
- 2018-05-30 CN CN201810535872.6A patent/CN108454874B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5695153A (en) * | 1995-11-16 | 1997-12-09 | Northrop Grumman Corporation | Launcher system for an unmanned aerial vehicle |
| US6260797B1 (en) * | 1998-01-13 | 2001-07-17 | Science Applications International Corporation | Transformable gun launched aero vehicle |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| GB0312353D0 (en) * | 2003-05-30 | 2003-07-02 | Qinetiq Ltd | Launching aerial vehicles |
| AU2009200804A1 (en) * | 2006-07-31 | 2009-03-19 | Elbit Systems Ltd. | An unmanned aerial vehicle launching and landing system |
| CN103693207A (en) * | 2013-12-12 | 2014-04-02 | 桂林航龙科讯电子技术有限公司 | Small-sized unmanned aerial vehicle ejector |
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN206679277U (en) * | 2017-04-19 | 2017-11-28 | 桂艳春 | A kind of gas-powered catapult |
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN107352041A (en) * | 2017-08-22 | 2017-11-17 | 成都戎创航空科技有限公司 | Unmanned plane Pneumatic catapult |
| CN207346072U (en) * | 2017-09-01 | 2018-05-11 | 深圳市华讯方舟系统技术有限公司 | Unmanned plane protects structure and UAV system |
| CN208855884U (en) * | 2018-05-30 | 2019-05-14 | 深圳市华讯方舟系统技术有限公司 | Unmanned plane emitter |
Non-Patent Citations (1)
| Title |
|---|
| 无人机气动弹射系统弹射性能的仿真研究;刘晓龙;郑州大学学报;全文 * |
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