CN106965934A - The landing modes and device of a kind of aircraft - Google Patents
The landing modes and device of a kind of aircraft Download PDFInfo
- Publication number
- CN106965934A CN106965934A CN201710139325.1A CN201710139325A CN106965934A CN 106965934 A CN106965934 A CN 106965934A CN 201710139325 A CN201710139325 A CN 201710139325A CN 106965934 A CN106965934 A CN 106965934A
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- daughter
- handgrip
- parent
- detection means
- aircraft
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- 238000001514 detection method Methods 0.000 claims abstract description 38
- 238000009434 installation Methods 0.000 claims abstract description 12
- 238000004891 communication Methods 0.000 claims description 6
- 238000005183 dynamical system Methods 0.000 claims description 3
- 230000009187 flying Effects 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
Classifications
-
- 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
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/04—Control of altitude or depth
- G05D1/06—Rate of change of altitude or depth
- G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
- G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
- G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The landing modes and device of a kind of aircraft, belong to technical field of aerospace, more particularly to aircraft landing modes and device；Landing-gear includes daughter and parent；Daughter include fixed wing aircraft, preceding link slot, rear link slot, forward pass sense answering device and after sense answering device；Parent includes multi-rotor aerocraft, controller, afterwards preceding connection handgrip, connection handgrip, front stretching arm, rear telescopic arm, preceding alignment detection means, rear alignment detection means and radar installations.When daughter needs landing；Parent goes up to the air immediately, and two connection handgrips connect two link slots；Parent is connected with daughter, and daughter pushing meanss are stopped working, and parent, which is hung, to be hauled daughter and return to level point.The present invention can utilize multi-rotor aerocraft advantage, combined using multi-rotor aerocraft with fixed wing aircraft, new departure is provided for the landing modes of fixed wing aircraft, fixed wing aircraft can also be landed on narrow and small platform, the construction of runway needed for reducing fixed wing aircraft, is conducive to the popularization of fixed wing aircraft.
Description
Technical field
The landing modes and device of a kind of aircraft, belong to technical field of aerospace, more particularly to aircraft landing modes and dress
Put.
Background technology
With the opening of low altitude airspace, Aircraft Market scale will be skyrocketed through, and fixed-wing flight and multi-rotor aerocraft are all
There are respective advantage and disadvantage；The characteristics of fixed-wing flight flight course safety, fast flying speed, remote voyage and big carrying capacity,
But descent is required for using that runway is slided and the vertical landing that can not hover in the air is to ground；Multi-rotor aerocraft can be vertical
Landing, simple technology, maneuverability, simple to operate and flight vibrations are small, but cruising time is short and security is low；For to safety
Property and endurance consideration, fixed wing aircraft turns into the first choice that people go on a journey, but limited by the field, and most of clients can not
The flight desire of oneself is met, the development and popularization of aircraft is so greatly limited.
The content of the invention
The purpose of the present invention is the above-mentioned deficiency for overcoming traditional fixed wing aircraft, and the present invention is excellent using multi-rotor aerocraft
Point, is combined with fixed-wing flight using multi-rotor aerocraft, provides new departure for the landing modes of aircraft, realize vertical landing.
A kind of landing-gear of aircraft, including daughter and parent；The daughter include fixed wing aircraft, preceding link slot, after
Link slot, forward pass sense answering device and after sense answering device；The fixed wing aircraft includes wing, fuselage, empennage, risen and fallen
Frame, pushing meanss, manipulation device and communication equipment.Groove before the preceding link slot includes left front groove and be right, left front groove is located at fuselage
The left side of first half, right preceding groove is located at the right side of fuselage forebody point, a left side for connection handgrip before left front groove and right preceding groove can allow
Lobe and the insertion of right lobe；The rear link slot includes left back groove and right pit, and left back groove is located at the left side of fuselage latter half,
Right pit is located at the right side of fuselage latter half, and the left lobe and right lobe of connection handgrip are embedding after left back groove and right pit can allow
Enter.The parent includes multi-rotor aerocraft, controller, afterwards preceding connection handgrip, connection handgrip, front stretching arm, rear telescopic arm, preceding
Alignment detection means, rear alignment detection means and radar installations.The multi-rotor aerocraft include dynamical system, control system,
Bracing strut and halfpace.The forward pass sense answering device is identical with rear sensing answering device functional structure, and dress is answered in forward pass sensing
Setting in the fuselage roof between left front groove and right preceding groove, rear sensing answering device is located at the fuselage between left back groove and right pit
Top, the effect of forward pass sense answering device and rear sensing answering device is to reflect preceding alignment detection means and rear alignment detection means
Signal.The controller is located in the halfpace of multi-rotor aerocraft and connects handgrip, afterwards connection handgrip, front stretching with preceding
Arm is connected with rear telescopic arm, can control flexible and preceding connection handgrip and of rear connection handgrip of front stretching arm and rear telescopic arm
Close.Connection handgrip is identical with the functional structure of rear connection handgrip before described；Preceding connection handgrip is fixed on many rotations by front stretching arm
The front lower place of rotor aircraft halfpace, rear connection handgrip is fixed on after multi-rotor aerocraft halfpace by rear telescopic arm
Lower section；Connection handgrip and rear connection handgrip all include left clevis half and right clevis half before described, and left clevis half middle inside carries left double wedge,
Right clevis half middle inside carries right double wedge, and two double wedges can be embedded into two grooves of the preceding link slot of daughter and rear link slot.
The preceding alignment detection means are identical with the functional structure of rear alignment detection means, preceding alignment detection means and rear alignment detection dress
Put the left clevis half for being located at preceding connection handgrip and rear connection handgrip respectively and the junction of right clevis half, preceding alignment detection means and rear right
The effect of quasi- detection means is to send signal, is accurately positioned the position of forward pass sense answering device and rear sensing answering device.It is described
Radar installations is located at below the halfpace of multi-rotor aerocraft, is connected with control system, and the effect of radar installations is that detection is solid
Heading, speed, height and the distance of wing aircraft are determined, so that parent adjusts itself direction, speed and height according to feedback signal
Degree, to complete aerial docking mission.
When multi-rotor aerocraft needs to be parked in ground, preceding connection handgrip and afterwards connection handgrip open can be as many rotations
The undercarriage of rotor aircraft is used.
A kind of landing modes of aircraft：When daughter needs landing, pass through the airborne communication control of daughter earthward base station
Transmission needs information of landing, and ground base station receive information simultaneously sends instruction to parent；Parent goes up to the air immediately, radar installations detection
Heading, speed, height and the distance of body aircraft, parent adjust itself direction, speed and height according to feedback signal；Parent
Fly to the surface of daughter and flown at the same speed in the same direction with daughter, while preceding alignment detection means and rear alignment detection means send letter
Forward pass sense answering device and rear sensing answering device number are accurately positioned, connection handgrip and rear connection are grabbed before the controller control of parent
Left clevis half and right clevis half control front stretching arm and the elongation of rear telescopic arm, current telescopic arm and rear telescopic arm simultaneously to maximum on hand
When pressing close to fuselage, controller controls the double wedge difference grabbed conjunction, handgrip and rear connection handgrip are connected before allowing of left clevis half and right clevis half
It is fitted in the preceding link slot of daughter and rear link slot, parent is combined with daughter connection；Daughter pushing meanss are stopped working, and parent, which is hung, to be hauled
Daughter returns to level point, smoothly completes the landing of fixed wing aircraft.
The present invention can utilize multi-rotor aerocraft advantage, be combined using multi-rotor aerocraft with fixed wing aircraft, for fixation
The landing modes of wing aircraft provide new departure, and fixed wing aircraft can also be landed on narrow and small platform, reduce fixed-wing and fly
The construction of runway needed for machine, is conducive to the popularization of fixed wing aircraft.
Brief description of the drawings
Fig. 1 is the schematic diagram of parent and daughter assembled state；Fig. 2 is daughter structural representation；Fig. 3 is precursor structure signal
Figure.
In figure, 1- fixed wing aircrafts, 11- forward pass sense answering devices sense link slot before answering device, 13-, 14- after 12-
Link slot afterwards, the left front grooves of 131-, groove before 132- is right, the left back grooves of 141-, the right pits of 142-, 2- multi-rotor aerocrafts, 21- controls
Telescopic arm after handgrip, the left clevis halfs of 321-, the right clevis halfs of 322-, 41- is connected before device, 22- radar installations, 31- front stretching arms, 32-,
Alignment detection means before handgrip, the left double wedges of 331-, the right double wedges of 332-, 325- are connected after 42-.
Embodiment
The present invention is illustrated below in conjunction with the accompanying drawings：A kind of landing-gear of aircraft, including daughter and parent；It is described
Daughter includes fixed wing aircraft 1, preceding link slot 13, rear link slot 14, forward pass sense answering device 11 and rear sensing answering device 12；
The fixed wing aircraft 1 includes wing, fuselage, empennage, undercarriage, pushing meanss, manipulation device and communication equipment.Before described
Link slot 13 includes groove 132 before left front groove 131 and the right side, and left front groove 131 is located at the left side of fuselage forebody point, right preceding groove 132
In the right side of fuselage forebody point, the left lobe 331 and right lobe of connection handgrip 32 before groove 132 can allow before left front groove 131 and the right side
332 insertions；The rear link slot 14 includes left back groove 141 and right pit 142, and left back groove 141 is located at a left side for fuselage latter half
Side, right pit 142 is located at the right side of fuselage latter half, and a left side for connection handgrip 42 is dashed forward after left back groove 141 and right pit 142 can allow
Tooth 331 and right lobe 332 are embedded in.The parent includes multi-rotor aerocraft 2, controller 21, the preceding handgrip 32, rear connection of connecting and grabbed
Hand 42, front stretching arm 32, rear telescopic arm 41, preceding alignment detection means 325, rear alignment detection means and radar installations 22.It is described
Multi-rotor aerocraft 2 includes dynamical system, control system, bracing strut and halfpace.The forward pass sense answering device 11 is with after
The sensing functional structure of answering device 12 is identical, the fuselage before forward pass sense answering device 11 is located at left front groove 131 and is right between groove 132
Top, rear sensing answering device 12 is located at the fuselage roof between left back groove 141 and right pit 142, forward pass sense answering device 11
Effect with rear sensing answering device 12 is the signal for reflecting preceding alignment detection means 325 and rear alignment detection means；Controller
21 be located in the halfpace of multi-rotor aerocraft 2 and with preceding connection handgrip 32, rear connection handgrip 42, front stretching arm 32 and after stretch
Contracting arm 41 is connected, and can control flexible and preceding connection handgrip 32 and of rear connection handgrip 42 of front stretching arm 32 and rear telescopic arm 41
Close.Connection handgrip 32 is identical with the functional structure of rear connection handgrip 42 before described；Preceding connection handgrip 32 is solid by front stretching arm 32
The front lower place of the halfpace of multi-rotor aerocraft 2 is scheduled on, rear connection handgrip 42 is fixed on many rotor flyings by rear telescopic arm 41
The back lower place of the halfpace of device 2；Connection handgrip 32 and rear connection handgrip 42 all include left clevis half 321 and right clevis half 322 before described,
The left middle inside of clevis half 321 carries left double wedge 331, and the right middle inside of clevis half 322 carries right double wedge 332, and two double wedges can be embedding
Enter into two grooves of the preceding link slot 13 of daughter and rear link slot 14.The preceding alignment detection means 325 and rear alignment detection dress
The functional structure put is identical, and preceding alignment detection means 325 and rear alignment detection means are located at preceding connection handgrip 32 and connected with after respectively
Connect the left clevis half 321 of handgrip 42 and the junction of right clevis half 322, the work of preceding alignment detection means 325 and rear alignment detection means
With being to send signal, the position of forward pass sense answering device 11 and rear sensing answering device 12 is accurately positioned.The radar installations 22
Below the halfpace of multi-rotor aerocraft 2, it is connected with control system, the effect of radar installations 22 is that detection fixed-wing flies
Heading, speed, height and the distance of machine 1, so that parent adjusts itself direction, speed and height according to feedback signal, with
Just aerial docking mission is completed.
When multi-rotor aerocraft 2 needs to be parked in ground, preceding connection handgrip 32 and rear connection handgrip 42 open and can made
Undercarriage for multi-rotor aerocraft 2 is used.
A kind of landing modes of aircraft：When daughter needs landing, pass through the airborne communication control of daughter earthward base station
Transmission needs information of landing, and ground base station receive information simultaneously sends instruction to parent；Parent is gone up to the air immediately, and radar installations 22 is detected
Heading, speed, height and the distance of daughter aircraft, parent adjust itself direction, speed and height according to feedback signal；It is female
Body flies to the surface of daughter and flown at the same speed in the same direction with daughter, while preceding alignment detection means 325 and rear alignment detection means
Send signal and be accurately positioned forward pass sense answering device 11 and rear sensing answering device 12, connection is grabbed before the controller 21 of parent is controlled
Left clevis half 321 and right clevis half 322 controls front stretching arm 32 and rear telescopic arm simultaneously to maximum on hand 32 and rear connection handgrip 42
41 elongations, when current telescopic arm 32 and rear telescopic arm 41 press close to fuselage, controller 21 controls left clevis half 321 and right clevis half 322
Conjunction is grabbed, allows preceding connection handgrip 32 and the double wedge of rear connection handgrip 42 to be fitted to the preceding link slot 13 of daughter and rear link slot 14 respectively
In, parent is combined with daughter connection；Daughter pushing meanss are stopped working, and parent, which is hung, to be hauled daughter and return to level point, smoothly completes fixation
The landing of wing aircraft 1.
Claims (3)
1. a kind of landing-gear of aircraft, it is characterised in that：Including daughter and parent；The daughter includes fixed wing aircraft（1）、
Preceding link slot（13）, rear link slot（14）, forward pass sense answering device（11）With rear sensing answering device（12）；The fixed-wing flies
Machine（1）Including wing, fuselage, empennage, undercarriage, pushing meanss, manipulation device and communication equipment；The preceding link slot（13）
Including left front groove（131）With groove before the right side（132）, left front groove（131）Positioned at the left side of fuselage forebody point, right preceding groove（132）Position
In the right side of fuselage forebody point, left front groove（131）With groove before the right side（132）Connection handgrip before allowing（32）Left lobe（331）
With right lobe（332）It is embedded；The rear link slot（14）Including left back groove（141）With right pit（142）, left back groove（141）Position
In the left side of fuselage latter half, right pit（142）Positioned at the right side of fuselage latter half, left back groove（141）With right pit
（142）Handgrip is connected after allowing（42）Left lobe（331）With right lobe（332）It is embedded；The parent includes many rotor flyings
Device（2）, controller（21）, preceding connection handgrip（32）, connect handgrip afterwards（42）, front stretching arm（32）, rear telescopic arm（41）, it is preceding right
Quasi- detection means（325）, rear alignment detection means and radar installations（22）；The multi-rotor aerocraft（2）Including dynamical system,
Control system, bracing strut and halfpace；The forward pass sense answering device（11）With rear sensing answering device（12）Functional structure
It is identical, forward pass sense answering device（11）Positioned at left front groove（131）With groove before the right side（132）Between fuselage roof, response is sensed afterwards
Device（12）Positioned at left back groove（141）With right pit（142）Between fuselage roof；Controller（21）Positioned at multi-rotor aerocraft
（2）Halfpace in and with preceding connection handgrip（32）, connect handgrip afterwards（42）, front stretching arm（32）With rear telescopic arm（41）Phase
Even, front stretching arm can be controlled（32）With rear telescopic arm（41）Flexible and preceding connection handgrip（32）With rear connection handgrip（42）
Close；Connection handgrip before described（32）With rear connection handgrip（42）Functional structure it is identical；Preceding connection handgrip（32）Pass through front stretching
Arm（32）It is fixed on multi-rotor aerocraft（2）The front lower place of halfpace, connects handgrip afterwards（42）Pass through rear telescopic arm（41）Gu
It is scheduled on multi-rotor aerocraft（2）The back lower place of halfpace；Connection handgrip before described（32）With rear connection handgrip（42）All include
Left clevis half（321）With right clevis half（322）, left clevis half（321）Middle inside carries left double wedge（331）, right clevis half（322）In inner side
Portion carries right double wedge（332）, two double wedges can be embedded into link slot before daughter（13）With rear link slot（14）Two grooves in；
The preceding alignment detection means（325）It is identical with the functional structure of rear alignment detection means, preceding alignment detection means（325）With it is rear
Alignment detection means are located at preceding connection handgrip respectively（32）With rear connection handgrip（42）Left clevis half（321）With right clevis half（322）
Junction；The radar installations（22）Positioned at multi-rotor aerocraft（2）Halfpace below, be connected with control system.
2. a kind of landing-gear of aircraft, it is characterised in that：Work as multi-rotor aerocraft（2）When needing to be parked in ground, preceding connection
Handgrip（32）With rear connection handgrip（42）Opening can be as multi-rotor aerocraft（2）Undercarriage use.
3. a kind of landing modes of aircraft, it is characterised in that：When daughter needs landing, by the airborne communication control of daughter to
Ground base station, which is sent, needs information of landing, and ground base station receive information simultaneously sends instruction to parent；Parent goes up to the air immediately, radar dress
Put（22）Heading, speed, height and the distance of daughter aircraft are detected, parent adjusts itself direction, speed according to feedback signal
Degree, height；Parent flies to the surface of daughter and flown at the same speed in the same direction with daughter, while preceding alignment detection means（325）With it is rear
Alignment detection means send signal and are accurately positioned forward pass sense answering device（11）With rear sensing answering device（12）, the control of parent
Device（21）Connection handgrip before control（32）With rear connection handgrip（42）Upper left clevis half（321）With right clevis half（322）Open and arrive most Datong District
When control front stretching arm（32）With rear telescopic arm（41）Elongation, current telescopic arm（32）With rear telescopic arm（41）When pressing close to fuselage,
Controller（21）Control left clevis half（321）With right clevis half（322）Grab conjunction, allow before connection handgrip（32）With rear connection handgrip（42）
Double wedge be fitted to link slot before daughter respectively（13）With rear link slot（14）In, parent is combined with daughter connection；Daughter is promoted
Device stops working, and parent, which is hung, to be hauled daughter and return to level point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139325.1A CN106965934A (en) | 2017-03-10 | 2017-03-10 | The landing modes and device of a kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139325.1A CN106965934A (en) | 2017-03-10 | 2017-03-10 | The landing modes and device of a kind of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106965934A true CN106965934A (en) | 2017-07-21 |
Family
ID=59329321
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710139325.1A Pending CN106965934A (en) | 2017-03-10 | 2017-03-10 | The landing modes and device of a kind of aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN106965934A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018107278A1 (en) * | 2016-12-13 | 2018-06-21 | Ryan Evaristo Pinto | System and method for capturing and releasing fixed-wing aircraft |
| CN108482679A (en) * | 2018-03-19 | 2018-09-04 | 成都飞机工业（集团）有限责任公司 | Towed bird system that is a kind of while lifting two frame unmanned planes |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4267987A (en) * | 1979-03-29 | 1981-05-19 | Mcdonnell William R | Helicopter airborne load systems and composite aircraft configurations |
| US20110049288A1 (en) * | 2008-08-21 | 2011-03-03 | Satoshi Suzuki | Unmanned aircraft system and operation method thereof |
| US8950698B1 (en) * | 2012-10-26 | 2015-02-10 | The Boeing Company | Convertible compounded rotorcraft |
| CN105984582A (en) * | 2015-02-13 | 2016-10-05 | 鸿富锦精密工业（深圳）有限公司 | Aircraft |
| CN106005400A (en) * | 2016-07-13 | 2016-10-12 | 绵阳空天科技有限公司 | Vertical-takeoff auxiliary system for fixed-wing aircraft |
| US20170036762A1 (en) * | 2015-08-03 | 2017-02-09 | Dustin Gamble | Release and Capture of a Fixed-Wing Aircraft |
| CN106428554A (en) * | 2016-08-31 | 2017-02-22 | 天津曙光天成科技有限公司 | A take-off and landing system and method for a fixed-wing unmanned aerial vehicle |
-
2017
- 2017-03-10 CN CN201710139325.1A patent/CN106965934A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4267987A (en) * | 1979-03-29 | 1981-05-19 | Mcdonnell William R | Helicopter airborne load systems and composite aircraft configurations |
| US20110049288A1 (en) * | 2008-08-21 | 2011-03-03 | Satoshi Suzuki | Unmanned aircraft system and operation method thereof |
| US8950698B1 (en) * | 2012-10-26 | 2015-02-10 | The Boeing Company | Convertible compounded rotorcraft |
| CN105984582A (en) * | 2015-02-13 | 2016-10-05 | 鸿富锦精密工业（深圳）有限公司 | Aircraft |
| US20170036762A1 (en) * | 2015-08-03 | 2017-02-09 | Dustin Gamble | Release and Capture of a Fixed-Wing Aircraft |
| CN106005400A (en) * | 2016-07-13 | 2016-10-12 | 绵阳空天科技有限公司 | Vertical-takeoff auxiliary system for fixed-wing aircraft |
| CN106428554A (en) * | 2016-08-31 | 2017-02-22 | 天津曙光天成科技有限公司 | A take-off and landing system and method for a fixed-wing unmanned aerial vehicle |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018107278A1 (en) * | 2016-12-13 | 2018-06-21 | Ryan Evaristo Pinto | System and method for capturing and releasing fixed-wing aircraft |
| US11111019B2 (en) | 2016-12-13 | 2021-09-07 | Ryan Evaristo Pinto | System and method for capturing and releasing fixed-wing aircraft |
| CN108482679A (en) * | 2018-03-19 | 2018-09-04 | 成都飞机工业（集团）有限责任公司 | Towed bird system that is a kind of while lifting two frame unmanned planes |
| CN108482679B (en) * | 2018-03-19 | 2023-09-29 | 成都飞机工业（集团）有限责任公司 | Nacelle system for hoisting two unmanned aerial vehicles simultaneously |
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Application publication date: 20170721 |