CN103935512A - High endurable multi-rotor craft - Google Patents
High endurable multi-rotor craft Download PDFInfo
- Publication number
- CN103935512A CN103935512A CN201410196243.7A CN201410196243A CN103935512A CN 103935512 A CN103935512 A CN 103935512A CN 201410196243 A CN201410196243 A CN 201410196243A CN 103935512 A CN103935512 A CN 103935512A
- Authority
- CN
- China
- Prior art keywords
- rotor
- aircraft
- craft
- wing
- fixed
- Prior art date
Links
- 238000004891 communication Methods 0.000 claims description 3
- 238000004146 energy storage Methods 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 3
- 230000001939 inductive effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 4
- 230000000630 rising Effects 0.000 abstract description 3
- 241000272517 Anseriformes Species 0.000 description 3
- 230000000875 corresponding Effects 0.000 description 3
- 241001538365 Accipiter nisus Species 0.000 description 2
- 241000238633 Odonata Species 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 2
- 230000001052 transient Effects 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000013632 homeostatic process Effects 0.000 description 1
- 230000001976 improved Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 230000003014 reinforcing Effects 0.000 description 1
- 238000010200 validation analysis Methods 0.000 description 1
Abstract
The invention belongs to the field of craft design, and relates to a craft which can vertically take off and land and can also carry out a gliding flight by using fixed wings. According to the invention, a craft which can concurrently have the advantages of flexibility and convenience of multi-rotor flight and the advantages of large load and long endurance of fixed wing aircrafts is designed. According to the invention, a multi-rotor craft is taken as a basic form, and fixed wings are taken as auxiliary parts. The fixed wings can be collapsed and expanded, folded and flatted, or overturned for resetting as required. The craft can be powered by multiple rotors or power mechanisms, and rotor parts can also be overturned or covered so as to provide a better aerodynamic performance and provide forward or rising power. In the process of rising or environmental constraint, the craft is mainly powered by rotor mechanisms until flying to a stable height, the fixed wings can be expanded in proper condition, the craft is in a gliding state, and the rotors (or other power supply devices) can be overturned for propelling. After flying to a certain height, the craft carries out gliding by the fixed wings.
Description
Technical field
The invention belongs to Flight Vehicle Design field, relate to a kind of aircraft that can vertical takeoff and landing also can rely on fixed-wing gliding flight.
Background technology
Fixed wing aircraft is traditional type, has outstanding continuation of the journey and load-carrying ability.But problem is necessary runway landing, and need certain landing facility requirement of taking off, also underaction of aloft operation.
Autogiro taking helicopter as representative has good manipulation type, and for complex-terrain, complex conditions comformability, and in emergency repair, the field application such as emergency relief are very extensive.
Design that a kind of aircraft has long battery life flight concurrently and small space landing ability is airplane design person's a dream always.At present in actual applications, comparative maturity can vertical takeoff and landing Fixed Wing AirVehicle have and be similar to the such jet plane in " sparrow hawk " formula attack plane, and tilt rotor aircraft as V-22 " osprey "." sparrow hawk " formula aircraft is conventional fixed wing aircraft layout, mainly utilize deflection engine nozzle, the method that changes the jet spout thrust direction of driving engine has realized vertical takeoff and landing, but this implementation consumption of fuel is larger, require very high to driving engine, when vertical takeoff and landing, Aircraft Load is limited, shorter when voyage and boat; What " osprey " tilt rotor aircraft utilized wing two ends can realize vertical takeoff and landing by tilting rotor, before while flying rotor tilt forward to become before screw propeller provides aircraft and fly pulling force, such aircraft propeller only has two, the span fix and too small safety and the maintainability of causing of area not good, the rotor transient process control difficulty of verting is high, dynamicstability is poor, and aerodynamic interference between rotor and wing is very serious.
The U.S. has also proposed the concept of a kind of canard rotor blade aircraft (CRW), and produces the unmanned flight validation machine of two X-50A " dragonfly Yan ".In current disclosed data, X-50A, by fuselage, is connected to the rotor blade of back by propeller hub, canard, H T tail, turbofan engine and fuel oil system thereof and flight control system composition; Aircraft is in the time carrying out the flight of rotor pattern, and rotor blade high-speed rotary transfers to rotor and uses, and makes aircraft can carry out vertical and landing takeoff, and in the time that rotor blade locks as fixed-wing, aircraft carries out high-speed flight with fixed-wing pattern.But the priority of two " dragonfly Yan " proof machines is crashed and has been illustrated in the technical scheme of current disclosed canard rotor blade aircraft and still have more serious problems, especially aircraft is in the time of rotor flying pattern and transient process flight, between rotor blade downwash flow and empennage, can produce strong interference in air flow, make aircraft produce non-permanent, the nonlinear aerodynamic load of large and difficult control.Therefore also need rotor blade aircraft further to study, make aircraft meet controlled requirement in rotor flying pattern and transition flight process.
At present, the synonym that becomes course of new aircraft gradually of the Multi-axis aircraft taking four axle rotor crafts as representative.Various exploitations are in the ascendant with application.With its excellent performance, manipulation flexibly, stable and be well received by the public.A little less than but problem is that flying power too, aerodynamic structure is unfavorable for long-time continuation of the journey.
On the whole, many rotors and the current problem of single autogiro are to lack flying power, must rely on the continuous rotation of rotor that the power that rises and advance is provided, still efficiency is not high flexibly for this mode, a little less than flying power, once and the rotor situation that breaks down or run out of steam, aircraft cannot glide, and safety reduces thus.Fixed wing aircraft, inertia is larger, and landing requires high, keeps away barrier difficulty, cannot hover, and overall underaction, cannot meet the short-range user demand of complex situations.
Summary of the invention
The present invention has designed a kind of flexible convenient advantage and the fixed wing aircraft heavy－duty that can take into account many rotor flyings, the aircraft of long continuation of the journey advantage.A kind of aircraft that can adapt to following multiple demand use is provided.
The present invention is taking multi-rotor aerocraft as basic form, and fixed-wing is accessory.Fixed-wing can shrink expansion with demand, fold-flat, or upset resets.This aircraft can provide power with multiple rotors or actuating unit, and rotor part also can be overturn, or hides to better aerodynamic performance is provided, and the power that advances or rise is provided.When rising or when environment is narrow, the main rotor mechanism that relies on provides power, until fly to standing height, can be fixed thriving exhibition and open, aircraft enters glide state, and the rotor that can overturn (or other power provide dress system) advances.Walking to certain altitude glides with fixed-wing.While running out of steam, also can carry out safe forced landing by glide.
Key point of the present invention
1. many (three and more than) rotor craft that can vertical takeoff and landing is equipped with fixing hang gliding.Fixed-wing system can fold,
Shrink, turn to the degree to many rotor flyings systematic influence minimum.
2. the aircraft based on claim 1, many rotor systems can fold, overturn, shrink, hide extremely fixed-wing system
Reduce load, increase and advance, control attitude.
3. the additional solar power of the aerocraft system based on claim 1 or 2, wireless energy storage device.
4. the aircraft based on claim 1 or 2 or 3, the additional wing control of system and strengthening system, and empennage, balance wing,
Vertical tail etc.
5. the additional multi-machine collaborative function of the aerocraft system based on claim 1 or 2 or 3 or 4.
Aerocraft system additional external environment based on claim 1 or 2 or 3 or 4 or 5 and s own situation induction system and
Adjustment System.
Based on the aerocraft system of claim 1 or 2 or 3 or 4 or 5 or 6 additionally make a video recording, take a picture, capture, send,
The systems such as operating equipment.
8. the aerocraft system additional intelligence control system based on claim 1 or 2 or 3 or 4 or 5 or 6 or 7.
Based on the aircraft of claim 1 or 2 or 3 or 4 or 5 or 6 or 7 or 8 additional mutual with people and other equipment,
Communication system.
Brief description of the drawings
8, accompanying drawing of the present invention, taking quadrotor system as example, other rotor numbers can be analogized, and fixed-wing part is similar.
Fig. 1 is top-down birds-eye view after fixed-wing launches.
It is below the note of the various piece of Fig. 1.
1 is fuselage base portion.Can comprise that fixed-wing folding shrinking function, stored energy function, collection of energy function, control function, environment sensing function, deformation operation function, Container Loading function, personnel take function, protection function, cleaning function, extra machine function etc.
2, for being mainly aircraft, the many groups rotor on fuselage provides power, and maybe can be improved to other power system is provided.
3, the fixed-wing that can stretch or overturn, for aircraft provides the ability of gliding flight.
4, the empennage that can stretch or overturn, for aircraft provides the ability that keeps balance and change glide attitude.
5, the vertical tail that can stretch or overturn, for aircraft deployed condition provides level to turn to and the ability of whole machine balancing.
6, the balance wing that can stretch or overturn, for aircraft provides the ability that keeps balance and change glide attitude.
Fig. 2 is after fixed-wing launches and rotor rotates up the top-down birds-eye view after 90 degree.
Content number is consistent with Fig. 1 same section meaning.
7, the covering version of rotor, can help improve the aerodynamic performance of aircraft.
Fig. 3 is plan view from front to back after fixed-wing launches.
Content number and Fig. 1, Fig. 2 same section meaning are consistent.
8, aircraft load-carrying element, can provide support for aircraft, stablizes, the function of reinforcing etc.Have ready conditions and also can hang in the air.
Fig. 4 is after fixed-wing launches and rotor rotates up the plan view from front to back after 90 degree.
Content number and Fig. 1, Fig. 2, Fig. 3 same section meaning are consistent.
Fig. 5 is plan view from left to right after fixed-wing launches.
Content number and Fig. 1, Fig. 2, Fig. 3 same section meaning are consistent.
Fig. 6 is after fixed-wing launches and rotor rotates up the plan view from left to right after 90 degree.
Content number and Fig. 1, Fig. 2, Fig. 3 same section meaning are consistent.
Fig. 7 is that all fixed-wings all shrink the top-down birds-eye view of rear rotor armed state.
Content number and Fig. 1, Fig. 2, Fig. 3 same section meaning are consistent.
Fig. 8 is the plan view that all fixed-wings all shrink rear rotor armed state.
Content number and Fig. 1, Fig. 2, Fig. 3 same section meaning are consistent.
Detailed description of the invention
The at present design of multi-rotor aerocraft is fairly perfect, its heavy burden ability and dynamically manipulation, complex operations, homeostasis, emergently keeps away barrier and has more complete solution.The present invention adds on this basis, and wing scalable, folding, upset is load.When aircraft flight is to enough height, under many rotor hoverings or stable case, the fixed wing of unfolded.The standby glide ability preferably of flying instrument after launching, more rotor systems are adjusted according to heading as required, onward impulse and corresponding stability can be provided.Also can use independent fixed-wing propulsion system
In order to strengthen glide ability, and improve aerodynamic performance, rotor can be covered the perforated on body.The aircraft launching after fixed-wing will possess stronger heavy burden ability, the flying power of longer time, higher speed, and more stable flight stability.
Can solar power or other wireless energy receiving devices be installed at fuselage and wing deploying portion, because glide process consumed energy is little, under the condition of Conditional Access energy, can carry out energy storage to aircraft, even realize uninterrupted continuation of the journey.
Retractable wing itself requires more frivolous, can aspect material, structure, form, design and improve, and to strengthen its load-bearing capacity, comprises cable traction, structural strengthening etc.The direction of fixed-wing regulates part also can to improve and optimize.
This aircraft is suitable for building Unmanned Aircraft Systems (UAS), or the automanual system of human intervention.There is extraordinary meticulous manipulation ability because it is the same with many rotor systems, and strengthened the load-carrying capacity of fixed-wing, can coordinate multimachine by communication mechanism each other and complete complicated work.
System can be carried out the optimization of sensor, completes the perception for aircraft s own situation and external environment, and carries out the adjustment of self state of flight taking these information as basis.Can reach the effect of bionical flight.
Because system has high-precision action executing operator perforniance, there is again the transport capacity of high capacity, so can install shooting, photograph additional, capture the additional functioies such as article, delivering goods, operating equipment to system, can reach design and expect.
System has extraordinary handling and realizability, can in system, increase intelligent chip and corresponding program and hardware mechanism; To reach automatic operation, the degree of utonomous working.
System can be carried out Long-distance Control, and for ground or corresponding data path is provided in the air, and data interaction is processed etc. to function.
Claims (9)
1. many (three and more than) rotor craft that can vertical takeoff and landing is equipped with fixing hang gliding; Fixed-wing system can fold, and shrinks, and turn to the degree to many rotor flyings systematic influence minimum.
2. the aircraft based on claim 1, many rotor systems can fold, overturn, shrink, hide to fixed-wing system is reduced to load, increase and advance, and control attitude.
3. the additional solar power of the aerocraft system based on claim 1 or 2, wireless energy storage device.
4. the aircraft based on claim 1 or 2 or 3, the additional wing control of system and strengthening system, and empennage, balance wing, vertical tail etc.
5. the additional multi-machine collaborative function of the aerocraft system based on claim 1 or 2 or 3 or 4.
6. the aerocraft system additional external environment based on claim 1 or 2 or 3 or 4 or 5 and s own situation induction system and adjustment System.
Based on the aerocraft system of claim 1 or 2 or 3 or 4 or 5 or 6 additionally make a video recording, take a picture, capture, send, the system such as operating equipment.
8. the aerocraft system additional intelligence control system based on claim 1 or 2 or 3 or 4 or 5 or 6 or 7.
9. additional, the communication system mutual with people and other equipment of the aircraft based on claim 1 or 2 or 3 or 4 or 5 or 6 or 7 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410196243.7A CN103935512A (en) | 2014-05-12 | 2014-05-12 | High endurable multi-rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410196243.7A CN103935512A (en) | 2014-05-12 | 2014-05-12 | High endurable multi-rotor craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103935512A true CN103935512A (en) | 2014-07-23 |
Family
ID=51183458
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410196243.7A CN103935512A (en) | 2014-05-12 | 2014-05-12 | High endurable multi-rotor craft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103935512A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608914A (en) * | 2014-12-12 | 2015-05-13 | 宁波高新区甬晶微电子有限公司 | Intelligent multipurpose rescue unmanned aircraft |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
| CN107972860A (en) * | 2017-12-03 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of stabilized flight device |
| CN108482663A (en) * | 2018-05-31 | 2018-09-04 | 江苏常探机器人有限公司 | The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin |
| CN108502164A (en) * | 2018-05-31 | 2018-09-07 | 江苏常探机器人有限公司 | A kind of rear single-screw paddle composite wing aircraft with the compound auxiliary wing of airscrew thrust |
| CN108528699A (en) * | 2018-05-31 | 2018-09-14 | 江苏常探机器人有限公司 | Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust |
| CN108545179A (en) * | 2018-05-31 | 2018-09-18 | 江苏常探机器人有限公司 | Single ducted fan formula composite wing manned vehicle afterwards |
| CN108639327A (en) * | 2018-05-31 | 2018-10-12 | 江苏常探机器人有限公司 | A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts |
| CN108750099A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing |
| CN108773487A (en) * | 2018-05-31 | 2018-11-09 | 江苏常探机器人有限公司 | Rear single-screw paddle composite wing cargo aircraft with the compound auxiliary wing and additional fin |
| CN108791862A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | Double culverts push away the compound auxiliary wing and rear single culvert pushing-type composite wing manned vehicle of additional fin |
| CN108791869A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle |
| CN108820202A (en) * | 2018-05-31 | 2018-11-16 | 江苏常探机器人有限公司 | It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula |
| CN108820201A (en) * | 2018-05-31 | 2018-11-16 | 江苏常探机器人有限公司 | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust |
| CN108839796A (en) * | 2018-05-31 | 2018-11-20 | 江苏常探机器人有限公司 | A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust |
| CN108860593A (en) * | 2018-05-31 | 2018-11-23 | 江苏常探机器人有限公司 | Rear single ducted fan formula composite wing manned vehicle with solar energy additional fin |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1384019A (en) * | 2001-05-08 | 2002-12-11 | 赵润生 | Airplane with multi-point deflecting wings |
| US20030062443A1 (en) * | 2001-10-02 | 2003-04-03 | Joseph Wagner | VTOL personal aircraft |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN101044034A (en) * | 2004-10-12 | 2007-09-26 | J·W·D·巴克 | Personal land and air vehicle |
| CN101372198A (en) * | 2008-07-08 | 2009-02-25 | 陈博 | Hovercar |
| CN101380881A (en) * | 2007-09-04 | 2009-03-11 | 刘新广 | Deformable flying device |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
| CN102991668A (en) * | 2011-09-16 | 2013-03-27 | 赵文志 | Airplane |
| US20130112804A1 (en) * | 2010-05-07 | 2013-05-09 | Ohio University | Multi-Modal Vehicle |
| CN103350753A (en) * | 2013-05-03 | 2013-10-16 | 姚丹华 | Moveable wing aircraft |
| CN103482057A (en) * | 2013-09-17 | 2014-01-01 | 无锡振华机械有限公司 | Telescopic wing of aircraft |
-
2014
- 2014-05-12 CN CN201410196243.7A patent/CN103935512A/en not_active Application Discontinuation
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1384019A (en) * | 2001-05-08 | 2002-12-11 | 赵润生 | Airplane with multi-point deflecting wings |
| US20030062443A1 (en) * | 2001-10-02 | 2003-04-03 | Joseph Wagner | VTOL personal aircraft |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN101044034A (en) * | 2004-10-12 | 2007-09-26 | J·W·D·巴克 | Personal land and air vehicle |
| CN101380881A (en) * | 2007-09-04 | 2009-03-11 | 刘新广 | Deformable flying device |
| CN101372198A (en) * | 2008-07-08 | 2009-02-25 | 陈博 | Hovercar |
| US20130112804A1 (en) * | 2010-05-07 | 2013-05-09 | Ohio University | Multi-Modal Vehicle |
| CN102991668A (en) * | 2011-09-16 | 2013-03-27 | 赵文志 | Airplane |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
| CN103350753A (en) * | 2013-05-03 | 2013-10-16 | 姚丹华 | Moveable wing aircraft |
| CN103482057A (en) * | 2013-09-17 | 2014-01-01 | 无锡振华机械有限公司 | Telescopic wing of aircraft |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608914A (en) * | 2014-12-12 | 2015-05-13 | 宁波高新区甬晶微电子有限公司 | Intelligent multipurpose rescue unmanned aircraft |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
| CN105270622B (en) * | 2015-10-30 | 2018-08-03 | 佛山市神风航空科技有限公司 | A kind of compound wing aircraft in the band upper counterangle |
| CN107972860A (en) * | 2017-12-03 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of stabilized flight device |
| CN108639327A (en) * | 2018-05-31 | 2018-10-12 | 江苏常探机器人有限公司 | A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts |
| CN108502164A (en) * | 2018-05-31 | 2018-09-07 | 江苏常探机器人有限公司 | A kind of rear single-screw paddle composite wing aircraft with the compound auxiliary wing of airscrew thrust |
| CN108528699A (en) * | 2018-05-31 | 2018-09-14 | 江苏常探机器人有限公司 | Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust |
| CN108545179A (en) * | 2018-05-31 | 2018-09-18 | 江苏常探机器人有限公司 | Single ducted fan formula composite wing manned vehicle afterwards |
| CN108482663A (en) * | 2018-05-31 | 2018-09-04 | 江苏常探机器人有限公司 | The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin |
| CN108750099A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing |
| CN108773487A (en) * | 2018-05-31 | 2018-11-09 | 江苏常探机器人有限公司 | Rear single-screw paddle composite wing cargo aircraft with the compound auxiliary wing and additional fin |
| CN108791862A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | Double culverts push away the compound auxiliary wing and rear single culvert pushing-type composite wing manned vehicle of additional fin |
| CN108791869A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle |
| CN108820202A (en) * | 2018-05-31 | 2018-11-16 | 江苏常探机器人有限公司 | It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula |
| CN108820201A (en) * | 2018-05-31 | 2018-11-16 | 江苏常探机器人有限公司 | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust |
| CN108839796A (en) * | 2018-05-31 | 2018-11-20 | 江苏常探机器人有限公司 | A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust |
| CN108860593A (en) * | 2018-05-31 | 2018-11-23 | 江苏常探机器人有限公司 | Rear single ducted fan formula composite wing manned vehicle with solar energy additional fin |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3439951B1 (en) | Rotating wing assemblies for tailsitter aircraft | |
| JP5943289B2 (en) | Vertical takeoff and landing vehicle | |
| CN106184739B (en) | Flying equipment capable of vertically taking off | |
| US10259577B2 (en) | Vertical takeoff and landing (VTOL) air vehicle | |
| EP3140188B1 (en) | Vertical takeoff and landing (vtol) unmanned aerial vehicle (uav) | |
| CN105620735B (en) | High-speed multi-rotor vertical take-off and landing aircraft | |
| US20180065737A1 (en) | Personal aircraft | |
| US10053213B1 (en) | Multi-copter lift body aircraft with tail pusher | |
| US10370100B2 (en) | Aerodynamically actuated thrust vectoring devices | |
| US8991750B2 (en) | Modular miniature unmanned aircraft with vectored thrust control | |
| US10538321B2 (en) | Tri-rotor aircraft capable of vertical takeoff and landing and transitioning to forward flight | |
| AU2013360005B2 (en) | Aircraft and methods for operating an aircraft | |
| US9187174B2 (en) | Aircraft with wings and movable propellers | |
| US9004393B2 (en) | Supersonic hovering air vehicle | |
| TWI538852B (en) | Personal aircraft | |
| US8800912B2 (en) | Three wing, six-tilt propulsion unit, VTOL aircraft | |
| US20170057631A1 (en) | Vertical Takeoff and Landing Vehicle with Increased Cruise Efficiency | |
| US9540101B2 (en) | System, apparatus and method for long endurance vertical takeoff and landing vehicle | |
| US20170057630A1 (en) | Aircraft | |
| EP2760739B1 (en) | Control of an unmanned aerial vehicle | |
| US9919796B2 (en) | Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable | |
| US20190071174A1 (en) | Vertical take off and landing aircraft with four tilting wings and electric motors | |
| US8733690B2 (en) | Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials | |
| US10287011B2 (en) | Air vehicle | |
| WO2016053452A1 (en) | Noise modes for rotary wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| C06 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C10 | Entry into substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140723 |
|
| RJ01 | Rejection of invention patent application after publication |