CN113353260A - Medium-short distance emission type transportation device and method - Google Patents
Medium-short distance emission type transportation device and method Download PDFInfo
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- CN113353260A CN113353260A CN202110673958.7A CN202110673958A CN113353260A CN 113353260 A CN113353260 A CN 113353260A CN 202110673958 A CN202110673958 A CN 202110673958A CN 113353260 A CN113353260 A CN 113353260A
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- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000004891 communication Methods 0.000 claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 6
- 230000003139 buffering effect Effects 0.000 description 2
- 238000003912 environmental pollution Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 239000000969 carrier Substances 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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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
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Traffic Control Systems (AREA)
Abstract
The invention discloses a medium and short distance launching type transportation device and a method, wherein the medium and short distance launching type transportation device comprises an aircraft, a launching platform and a ground control center; the aircraft is loaded with cargo; the launching platform comprises an ejection platform, a hydraulic rod, a towing hook and a sliding runway, and an electromagnetic track and an electromagnetic assembly are arranged on the ejection platform; the ejection platform drives the aircraft to eject and take off along the electromagnetic track through the electromagnetic assembly; the ground control center comprises a navigation database, a user interface module, a map navigation module and a serial port communication module. When the aircraft is transported in middle and short distance, the launching platform applies electromagnetic force to the aircraft to drive the aircraft to launch and take off, and the ground control center monitors the flight state of the aircraft in the whole distance through the GPS after the aircraft takes off. The invention applies the electromagnetic technology to the low-altitude transportation field in the undeveloped city, adopts the electromagnetic force as the launching power, realizes high-efficiency, quick, safe and green transportation, and saves resources.
Description
Technical Field
The invention relates to a conveying device and a conveying method, in particular to a medium-short distance emission type conveying device and a medium-short distance emission type conveying method.
Background
In short-distance transportation at home and abroad, several existing main transportation methods have certain limitations more or less, for example, the problems of serious insufficient ground transportation supply capacity, difficult trip and difficult goods transportation are prominent, the 'more, small, scattered and weak' transportation main bodies become the fatal weakness of the road transportation industry, and the problems of road traffic congestion and environmental pollution are particularly easily caused; in addition, the problems of high altitude resource shortage, energy consumption and high cost are also serious.
In recent years, the electromagnetic technology is developed very rapidly, the electromagnetic technology is often applied to aircraft carriers, and the electromagnetic catapult drives the carrier-based aircraft to move forwards, so that the carrier-based aircraft obtains a large enough initial speed, and the carrier-based aircraft can load more weapons and ammunitions to improve the operational capability. In addition, the carrier-based aircraft can also be filled with more fuel oil, and the cruising ability is improved.
How to apply the electromagnetic technology to the current short and medium distance transportation to improve the transportation efficiency and realize the fast and safe green transportation becomes a technical problem which needs to be solved urgently.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a medium-short distance emission type transportation device and method, aiming at solving a series of problems of low transportation efficiency and environmental pollution caused by urban road congestion, inconvenient traffic or rugged roads between regions in the current medium-short distance transportation, and solving the defects in the prior art.
The technical scheme is as follows: the short-distance launching type transportation device comprises an aircraft, a launching platform and a ground control center; the aircraft is loaded with cargo;
the launching platform comprises an ejection platform, a hydraulic rod, a towing hook and a sliding runway, and an electromagnetic track and an electromagnetic assembly are arranged on the ejection platform; the ejection platform drives the aircraft to eject and take off along the electromagnetic track through the electromagnetic assembly;
the ground control center comprises a navigation database, a user interface module, a map navigation module and a serial port communication module; the ground control center monitors the flight state of the aircraft after the aircraft takes off.
The aircraft comprises an aircraft body, a speed reducing umbrella, a propeller, an auxiliary engine, an undercarriage, a retracting rod and a traction device; the towing device drives the aircraft to catapult and take off along the electromagnetic track through the towing hook.
The electromagnetic assembly comprises an electromagnetic coil and an electromagnetic slider, and the aircraft slides along the electromagnetic track and the taxiing runway under the action of the electromagnetic coil and the electromagnetic slider.
The map navigation module marks the current position of the aircraft on a map according to longitude, latitude and elevation information uploaded by the aircraft through a GPS, and simultaneously marks the flight track of the aircraft.
The airframe includes wings and empennage that fold during takeoff to reduce drag during launch.
The serial port communication module adjusts the folding angle of the upper wing of the aircraft.
The launching platform also comprises a rotating wheel, and the launching platform adjusts the angle between the sliding runway and the ground through the rotating wheel and the hydraulic rod.
The navigation database stores waypoint and route information, task record information, system configuration information and historical flight data.
The serial port communication module and the navigation module monitor the flight process of the aircraft and control the takeoff and landing of the aircraft.
The short-distance emission type transportation method comprises the following steps:
(1) adjusting an included angle between the taxiway and the ground by the launching platform according to meteorological conditions, fixing the aircraft on the launching platform, adjusting parameters of the aircraft, and loading cargoes by the aircraft;
(2) the landing gear of the aircraft is opened by the retraction and extension rod, the ejection platform drives the aircraft to eject and take off through the electromagnetic assembly, and the ground control center monitors the flight state of the aircraft through the GPS whole process after the aircraft takes off;
(3) unfolding folded wings and empennage after the aircraft flies out of the launching platform, starting an auxiliary engine, climbing and flying by using self auxiliary power, and retracting an undercarriage;
(4) the aircraft closes the auxiliary engine after reaching the preset flying speed and distance and automatically glides;
(5) after the aircraft lands in a preset area, the parachute is opened to shorten the landing sliding distance, and after the aircraft lands, the goods are shunted to finish transportation.
Has the advantages that: compared with the prior art, the invention has the following advantages:
(1) the short-distance emission type transportation device and the short-distance emission type transportation method apply the electromagnetic technology to the low-altitude transportation field in the undeveloped city, adopt the electromagnetic force as the emission power, provide larger kinetic energy for the aircraft, and have the advantages of high emission speed, high precision and long range.
(2) Compared with other transportation methods, the short-distance emission type transportation method further promotes the application of new energy technology, realizes efficient, quick, safe and green transportation, and saves resources.
Drawings
FIG. 1 is a schematic view of a short haul transport process of the present invention;
FIG. 2 is a schematic view of the overall structure of the short-haul transport device of the present invention;
FIG. 3 is a schematic view of the overall structure of the aircraft of the present invention;
FIG. 4 is a top view of the inventive aircraft;
FIG. 5 is a schematic diagram of a towing attachment for the aircraft of the present invention;
FIG. 6 is a top view of a launch pad of the present invention;
FIG. 7 is a side cross-sectional view of a launch pad of the present invention;
fig. 8 is a front sectional view of the launch pad of the present invention.
Detailed Description
Example (b):
as shown in fig. 1 and 2, the short-haul launch type transportation device of the present invention includes an aircraft a, a launch pad b, and a ground control center, wherein the aircraft a is loaded with cargo. The launch pad adjusts the runway 5 to form an included angle with the ground according to weather conditions to transmit and receive the aircraft.
As shown in fig. 3 to 5, the aircraft includes a drogue 8, a propeller 9, an auxiliary engine 10, a landing gear 11, wings 12, a tail 13, a retraction lever 14, and a towing device 15. The speed reducing umbrella 8 is positioned at the tail end of the aircraft, is automatically opened when the aircraft lands, and plays a role in reducing speed and buffering. The propeller 9 is located at the upper end of the aircraft, and the propeller 9 provides lift for the aircraft by rotating. An auxiliary engine 10 is located below the propeller 9 to power the aircraft a after it leaves the launch pad b.
The landing gear 11 is located at the bottom of the aircraft and assists in the phases of aircraft preparation for takeoff and landing. The retraction lever 14 extends and retracts the landing gear 11 to open and retract the landing gear. The aircraft wing 12, the fuselage and the empennage 13 are connected into a whole, namely the fuselage. The wings 12 are connected to two sides of the fuselage through joints, and a plurality of buffer pieces are arranged at two ends of the wings 12, so that up-and-down buffering is facilitated.
The tail wing 13 comprises a horizontal tail wing and a vertical tail wing, and the tail wing 13 is connected with a mounting seat on a strengthening frame of the tail section of the machine body through bolts. The wing 12 is arranged between the front wheel and the rear wheel, the tail wing 13 is arranged at the tail part of the aircraft, and the wing 12 and the tail wing 13 are folded to reduce the resistance in launching. The towing attachment 15 tows the aircraft to take off.
After the aircraft flies for a certain distance in the air, the folded wings 12 and the empennage 13 are unfolded, the aircraft climbs and flies by using self auxiliary power, and the landing gear 11 is retracted. The aircraft shuts off the auxiliary engine 10 and performs autonomous gliding after reaching a predetermined flying speed and distance.
The ground control center comprises a navigation database, a user interface module, a map navigation module and a serial port communication module. The map navigation module marks the current position of the aircraft on a map according to longitude, latitude and elevation information uploaded by the aircraft through a GPS, and marks the flight track of the aircraft to monitor the aircraft. The aircraft arrives at a preset area to land, the landing sliding distance is shortened by using the speed reducing parachute 8, the receiving and releasing rod 14 is released, and after the aircraft lands, the goods are shunted, so that the transportation is completed.
As shown in fig. 3 to 5, the launching platform b comprises a base, an ejection platform, a hydraulic rod 2, a towing hook 3, a sliding runway 5 and a runner 6; an electromagnetic track 7 and an electromagnetic assembly are arranged on the ejection platform, and the ejection platform drives the aircraft to eject and take off through the electromagnetic assembly. The electromagnetic assembly comprises an electromagnetic coil 1 and an electromagnetic sliding block 4, wherein the electromagnetic coil 1 is positioned below a traction device of the aircraft, and electromagnetic force is applied to the aircraft through current control to enable the aircraft to catapult and take off. The aircraft glides along the electromagnetic track 7 and the glide track 5 under the action of the electromagnetic coil 1 and the electromagnetic slider 4.
In the embodiment, 3 hydraulic rods 2 are positioned below a taxiway 5, a towing hook 3 and an electromagnetic slide block 4 form a whole and are connected with a traction device 15, and the towing hook 3 hooks an aircraft to be launched through the traction device 15, so that the aircraft obtains a larger initial speed; the electromagnetic sliders 4 are arranged on the electromagnetic tracks 7 on both sides of the launching pad.
The taxiway 5 is arranged in the middle of the electromagnetic track 7, and an aircraft to be launched is placed above the taxiway 5. The launching platform is connected with the launching platform base through a rotating wheel 6, and the rotating wheel 6 is matched with the hydraulic rod 2 to adjust the angle between the sliding runway 5 and the ground.
The current generated by the electromagnetic coil 1 provides power for the launching platform and maintains the running of the whole launching platform; the electromagnetic coil 1 is provided in plurality.
The electromagnetic slide block 4 is under the action of the electromagnetic force of the electromagnetic track 7, slides and drives the aircraft connected with the towing hook 3 to slide. The sliding runway 5 forms a certain included angle with the ground under the adjustment of the rotating wheels 6, so that a slope is formed, and the boosting effect is achieved for the rising of the aircraft.
The taxiway 5 provides a cushioned area for the aircraft to increase takeoff efficiency. The sliding distances of the sliding track 5 and the electromagnetic track 7 are tens of meters long. The angle between the sliding runway 5 and the ground is adjusted by the matching of the poking rotating wheels 6 and the hydraulic rods 2, so that the aircraft can fly out of the launching platform under the traction of the traction device 15 under various climatic conditions.
The ground control center comprises a navigation database, a user interface module, a map navigation module and a serial port communication module. The waypoint and route information, task record information, system configuration information and historical flight data are all stored in a database. The user interface module is a window for ground control personnel to interact with the aircraft, and is controlled by the aircraft operator.
The map navigation module marks the current position of the aircraft on a map according to longitude and latitude and elevation information downloaded by the aircraft through a GPS, and marks the flight track of the aircraft to monitor the flight of the aircraft. The folding angle of the upper wing of the aircraft and the opening of the speed reducing umbrella are adjusted through the serial port communication module. The serial port communication module and the navigation module monitor the flight process of the aircraft and control the aircraft to land stably under the combined action.
When the launching type transportation is carried out, the aircraft a is firstly fixed on the launching platform b, namely, the transportation process is started, and the aircraft a waits for transportation after goods are loaded and unloaded; and adjusting relevant parameters of the aircraft according to natural factors of weather conditions at that time, ensuring that the whole aircraft is in an optimal state, and entering a launching preparation stage after the whole aircraft is checked to be correct.
After the launching platform is ready for launching, electromagnetic force is applied to the aircraft through current to drive the aircraft to catapult and take off; and the ground control center monitors the flight state of the aircraft in the whole process through the GPS sensing equipment after the aircraft takes off. The aircraft is unfolded with the folded wings 12 and the empennage 13 after flying out of the launching platform, and the auxiliary engine 10 is started after flying for a certain distance, and self auxiliary power is applied to climb and fly.
The aircraft shuts off the auxiliary engine 10 after reaching the preset flying speed and distance and glides autonomously. In this embodiment, when the predetermined aircraft is 400 meters away from the landing area, the aircraft shuts down its own auxiliary power to perform autonomous gliding. After landing in a preset area, the parachute 8 is opened to shorten the landing sliding distance, and after the aircraft lands, the cargo is shunted to finish the transportation process.
Claims (10)
1. The utility model provides a well short distance transmission formula conveyer which characterized in that: the transportation device comprises an aircraft (a), a launching platform (b) and a ground control center; the aircraft (a) is loaded with cargo;
the launching platform (b) comprises an ejection platform, a hydraulic rod (2), a towing hook (3) and a sliding runway (5), and an electromagnetic track (7) and an electromagnetic assembly are arranged on the ejection platform; the ejection platform drives the aircraft to eject and take off along the electromagnetic track (7) through the electromagnetic assembly;
the ground control center comprises a navigation database, a user interface module, a map navigation module and a serial port communication module; the ground control center monitors the flight state of the aircraft (a) after takeoff.
2. The medium-short haul launch vehicle according to claim 1, wherein: the aircraft (a) comprises an aircraft body, a speed-reducing umbrella (8), a propeller (9), an auxiliary engine (10), an undercarriage (11), a retractable rod (14) and a traction device (15); the towing device (15) drives the aircraft to catapult and take off along the electromagnetic track (7) through the towing hook (3).
3. The medium-short haul launch vehicle according to claim 1, wherein: the electromagnetic assembly comprises an electromagnetic coil (1) and an electromagnetic slider (4), and the aircraft slides along an electromagnetic track (7) and a sliding runway (5) under the action of the electromagnetic coil (1) and the electromagnetic slider (4).
4. The medium-short haul launch vehicle according to claim 1, wherein: the map navigation module marks the current position of the aircraft on a map according to longitude and latitude and elevation information uploaded by the aircraft through a GPS, and simultaneously marks the flight track of the aircraft.
5. The medium-short haul launch vehicle according to claim 1, wherein: the airframe includes wings (12) and empennage (13) that fold upon takeoff of the aircraft to reduce drag upon launch.
6. The medium-short haul launch vehicle according to claim 5, wherein: the serial port communication module adjusts the folding angle of the upper wing of the aircraft.
7. The medium-short haul launch vehicle according to claim 1, wherein: the launching platform further comprises a rotating wheel (6), and the angle between the sliding runway (5) and the ground is adjusted through the rotating wheel (6) and the hydraulic rod (2).
8. The medium-short haul launch vehicle according to claim 1, wherein: the navigation database stores waypoint and route information, task recording information, system configuration information and historical flight data.
9. The medium-short haul launch vehicle according to claim 1, wherein: the serial port communication module and the navigation module monitor the flight process of the aircraft and control the takeoff and landing of the aircraft.
10. A medium-short distance emission type transportation method is characterized in that: the medium-short distance emission type transportation device of claim 1 is adopted, and the transportation method comprises the following steps:
(1) the launching platform adjusts the included angle between the taxiway (5) and the ground according to meteorological conditions, then the aircraft (a) is fixed on the launching platform (b), the parameters of the aircraft are adjusted, and the aircraft (a) loads goods;
(2) the landing gear (11) of the aircraft is opened by the retraction rod (14), the aircraft is driven to catapult and take off by the catapult platform through the electromagnetic assembly, and the ground control center monitors the flight state of the aircraft through the GPS (global positioning system) in the whole process after the aircraft takes off;
(3) the aircraft is unfolded with the folded wings (12) and the empennage (13) after flying out of the launching platform, the auxiliary engine (10) is started, self auxiliary power is applied to climb and fly, and the landing gear is retracted;
(4) the aircraft closes the auxiliary engine (10) after reaching the preset flying speed and distance and glides autonomously;
(5) after the aircraft lands in a preset area, the parachute (8) is opened to shorten the landing sliding distance, and after the aircraft lands, the goods are shunted to finish transportation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110673958.7A CN113353260A (en) | 2021-06-17 | 2021-06-17 | Medium-short distance emission type transportation device and method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110673958.7A CN113353260A (en) | 2021-06-17 | 2021-06-17 | Medium-short distance emission type transportation device and method |
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| Publication Number | Publication Date |
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| CN113353260A true CN113353260A (en) | 2021-09-07 |
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| CN202110673958.7A Pending CN113353260A (en) | 2021-06-17 | 2021-06-17 | Medium-short distance emission type transportation device and method |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050096800A1 (en) * | 2003-10-22 | 2005-05-05 | Minas Tanielian | Virtuality attached node |
| CN1669874A (en) * | 2004-03-16 | 2005-09-21 | 清华大学 | Automatic pilot for aircraft |
| CN104192298A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Short-distance cargo transportation equipment |
| CN104192301A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Manpowered variable wing airplane |
| CN208134648U (en) * | 2018-05-07 | 2018-11-23 | 刘伟 | A kind of catapult for aeroplane |
| CN110758720A (en) * | 2019-09-26 | 2020-02-07 | 四川天砺航空科技有限公司 | Empty dual-purpose unmanned aerial vehicle of water |
| WO2020254512A1 (en) * | 2019-06-18 | 2020-12-24 | Dae | Assembly comprising a launch motor vehicle and a jet-powered drone aircraft, and method for transporting and releasing a load |
| CN112937904A (en) * | 2021-03-22 | 2021-06-11 | 贵州航天特种车有限责任公司 | Electromagnetic ejection device for unmanned aerial vehicle |
-
2021
- 2021-06-17 CN CN202110673958.7A patent/CN113353260A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050096800A1 (en) * | 2003-10-22 | 2005-05-05 | Minas Tanielian | Virtuality attached node |
| CN1669874A (en) * | 2004-03-16 | 2005-09-21 | 清华大学 | Automatic pilot for aircraft |
| CN104192298A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Short-distance cargo transportation equipment |
| CN104192301A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Manpowered variable wing airplane |
| CN208134648U (en) * | 2018-05-07 | 2018-11-23 | 刘伟 | A kind of catapult for aeroplane |
| WO2020254512A1 (en) * | 2019-06-18 | 2020-12-24 | Dae | Assembly comprising a launch motor vehicle and a jet-powered drone aircraft, and method for transporting and releasing a load |
| CN110758720A (en) * | 2019-09-26 | 2020-02-07 | 四川天砺航空科技有限公司 | Empty dual-purpose unmanned aerial vehicle of water |
| CN112937904A (en) * | 2021-03-22 | 2021-06-11 | 贵州航天特种车有限责任公司 | Electromagnetic ejection device for unmanned aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 杜聪聪;李武军;陈朝浪;马明旭;: "固定翼无人机回收与发射系统发展综述", 科技传播, no. 07, pages 113 - 115 * |
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