CN106005394A - Rescue aircraft - Google Patents
Rescue aircraft Download PDFInfo
- Publication number
- CN106005394A CN106005394A CN201610585853.5A CN201610585853A CN106005394A CN 106005394 A CN106005394 A CN 106005394A CN 201610585853 A CN201610585853 A CN 201610585853A CN 106005394 A CN106005394 A CN 106005394A
- Authority
- CN
- China
- Prior art keywords
- rescue
- tail
- tailplane
- flight device
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000007599 discharging Methods 0.000 claims description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract 2
- 230000000694 effects Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 3
- 238000011282 treatment Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 230000002153 concerted effect Effects 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- -1 infuse Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention provides a rescue aircraft which comprises an airframe (1), lift engines (2), attitude jet devices (3), a tail thrust engine (4), a horizontal tail (5), a vertical tail (6), an undercarriage (7), a flight control equipment cabin (8) and a rescue accommodating cabin (9). The two lift engines (2) are arranged on the two sides of the airframe (1) in the heading direction, the four attitude jet devices (3) are arranged in pairs on the two sides of the airframe (1) in the spanwise direction, the horizontal tail (5) and the vertical tail (6) which are perpendicular to each other are installed at the tail end of the airframe (1) in the heading direction, the tail thrust engine (4) is installed on the vertical tail (6), and the flight control equipment cabin (8) and the rescue accommodating cabin (9) are installed between the lift engines (2) on the two sides in the airframe (1). The rescue aircraft has vertical take-off and landing capability, the airframe with built-in paddles can be used for rescue in a narrow space, and the rescue aircraft has the advantages of being quick, efficient and subjected to little geographic space limitation and the like.
Description
Technical field
The invention belongs to field of airplane design, be specifically related to rescue flight device.
Background technology
Due to air rescue there is fast response time, maneuverability is strong, rescue scope wide, rescue effect
Good etc. have advantage, therefore plays vital effect during disaster assistance.
The aircraft being generally used for rescue is mainly helicopter, and the rotor grown greatly is external, cannot at all
Rescue task is implemented in the space narrow and small, complicated at some.Again, rescue helicopters are substantially by military
Helicopter is reequiped, and machine often lacks the equipment such as monitoring, treatment, oxygen supply, power supply, in conveying
The emergency treatments such as the sick and wounded can not carry out recovering in way, transfuse blood, infuse, oxygen supply.
Summary of the invention
It is an object of the invention to provide a kind of rescue flight device, solve helicopter owing to rotor is big
The problem that long feature cannot implement rescue task at small space.
The purpose of the present invention is achieved through the following technical solutions: a kind of rescue flight device, including body,
Lift engine, attitude jet flow device, tail push away electromotor, tailplane, vertical tail, undercarriage,
Flying control equipment cabin, rescue storage cabin；
Multiple described lift engines are built in both sides, direction, described body course；
Multiple described attitude jet flow devices are built in described body spanwise direction both sides in pairs；
Described body course steering wheel tail end be provided with orthogonal described tailplane and described vertically
Empennage, wherein, described tailplane is arranged according to described body spanwise direction, on described vertical tail
Described tail is installed and pushes away electromotor；
Described flying control equipment cabin and described is installed between lift engine described in both sides in described body
Rescue storage cabin；
Described undercarriage for landing is installed on the vertical direction of described body.
Preferably, described lift engine is two, and comprises fan and duct electromotor, institute
State duct electromotor and power is provided, drive described fan to rotate, produce lift, and then aircraft vertical
Take off.
Preferably, described vertical tail is two, and described tailplane is one, described vertical end
The wing is installed vertically on described tailplane two ends, and described tailplane, described vertical tail and institute
State body course machine tail end to be connected.
Preferably, described tailplane is provided with the elevator for adjusting aircraft lifting.
Preferably, described vertical tail is provided with for adjusting the rudder that aircraft turns to.
Preferably, it is two that described tail pushes away electromotor, is respectively arranged in described vertical tail away from institute
State tailplane side.
Preferably, described flying control equipment cabin and described rescue storage cabin are along described body spanwise direction also
Arrangement is put, and the hatch door in described rescue storage cabin is opened in away from side, described flying control equipment cabin.
Preferably, described body is provided with grid, is used for discharging described lift engine and described
The air-flow that attitude jet flow device produces.
Preferably, described undercarriage is four, is symmetrically arranged on described body spanwise direction both sides,
Every side installs two.
Having the beneficial effects that of a kind of rescue flight device provided by the present invention, not only has VTOL
Ability, and for traditional helicopter, the duct lift fan of small and exquisite fuselage and employing
Make it almost can perform the task of rescuing anywhere, have rapidly and efficiently, flexible multipurpose,
The advantages such as few are limited by geographical space.
Accompanying drawing explanation
Fig. 1 be the present invention rescue flight device in the structural front view of body；
Fig. 2 be the present invention rescue flight device in the structure top view of body；
Fig. 3 be the present invention rescue flight device in the structure front view of body；
Fig. 4 be the present invention rescue flight device in flying control equipment cabin and rescue storage cabin schematic internal view.
Reference:
1-body, 2-lift engine, 3-attitude jet flow device, 4-tail push away electromotor, 5-tailplane, 6-
Vertical tail, 7-undercarriage, 8-flying control equipment cabin, 9-rescue storage cabin, 11-grid, 21-fan,
22-duct electromotor, 51-elevator, 61-rudder, 81-master fly control screen, 82-is auxiliary flies control screen, 83-
Receiver, 84-life-detection instrument, 85-fuel tank, 91-seat, 92-chaise longue, 93-Multifunctional medical equipment.
Detailed description of the invention
Clearer, below in conjunction with this for the purpose making the present invention implement, technical scheme and advantage
Accompanying drawing in bright embodiment, is further described in more detail the technical scheme in the embodiment of the present invention.
In the accompanying drawings, the most same or similar label represents same or similar element or has identical
Or the element of similar functions.Described embodiment is a part of embodiment of the present invention rather than all
Embodiment.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining this
Invention, and be not considered as limiting the invention.Based on the embodiment in the present invention, this area is general
The every other embodiment that logical technical staff is obtained under not making creative work premise, all belongs to
In the scope of protection of the invention.
Below in conjunction with the accompanying drawings rescue flight device of the present invention is described in further details.
As in figure 2 it is shown, the rescue flight device of the present embodiment, exactly like sport car, including body 1, rise
Force engine 2, attitude jet flow device 3, tail push away electromotor 4, tailplane 5, vertical tail 6, rise and fall
Frame 7, flying control equipment cabin 8, rescue storage cabin 9.
Be provided with on the vertical direction of body 1 multiple for land undercarriage 7, the present embodiment preferably 4,
Being symmetrically arranged on body 1 spanwise direction both sides, every side installs two, and it is vertical to be all located at body 1
The same side in direction, as shown in Figure 1.Now regulation body 1 is provided with the side of undercarriage 7 is body 1
Lower direction, opposite direction is upper direction.
Multiple lift engines 2 are built in the both sides in direction, body 1 course respectively, the liter of the present embodiment
Force engine 2 comprises fan 21 and duct electromotor 22, and quantity elects 2 as, wherein, and fan 21
With duct electromotor 22 along the vertical layout of body 1, fan 21 is positioned at the top of duct electromotor 22,
Duct electromotor 22 provides power, drives fan 21 to rotate, and produces lift, and then aircraft vertical
Take off.
Multiple attitude jet flow devices 3 are built in body 1 spanwise direction both sides in pairs, are used for adjusting flight appearance
State, the present embodiment preferably 4, flight demand can be met.Body 1 is also equipped with grid 11,
The installation site of grid 11 is positioned in the vertical direction of lift engine 2 and attitude jet flow device 3, is used for
Discharge lift engine 2 and the air-flow of attitude jet flow device 3 generation, as shown in Figure 3.
Body 1 course steering wheel tail end is provided with orthogonal tailplane 5 and vertical tail 6, its
In, tailplane 5 selects 1, arranges according to body 1 spanwise direction, and vertical tail 6 selects 2
Individual, it is installed vertically on tailplane 5 two ends, tailplane 5, vertical tail 6 and body 1 course machine
Tail end is connected.Away from tailplane 5 side, tail is installed at vertical tail 6 and pushes away electromotor 4, tail
Pushing away electromotor 4 is 2, is i.e. equipped with a tail on each vertical tail 6 and pushes away electromotor 4, and tail pushes away
Electromotor 4 provides thrust, for the high-speed flight of the rescue flight device of the present invention, as shown in Figure 3.
Tailplane 5 is also equipped with elevator 51, elevator 51 be can the wallboard of pitching,
And it is positioned at tailplane 5 and ensures that aircraft has pitching stability away from fuselage 1 one end, one side,
On the other hand the pitch control of aircraft when high-speed flight, as shown in Figure 2.At vertical tail 6
On be also equipped with rudder 61, rudder 61 be can the wallboard of course swing, and be positioned at vertical tail
6 away from fuselage 1 one end, on the one hand ensures that aircraft has shipping-direction stability, on the other hand at a high speed
The directional control of aircraft during flight, as shown in Figure 1.
It is also equipped with flying control equipment cabin 8 between 2 lift engines 2 in body 1 and rescue is received
Receiving cabin 9, flying control equipment cabin 8 and rescue storage cabin 9 select to be arranged side by side along body 1 spanwise direction.Fly
Be provided with in control equipment compartment 8 main fly to control screen 81, auxiliary flying controls screen 82, receiver 83, life-detection instrument
84, fuel tank 85, as shown in Figure 4, main control screen 81 and the auxiliary control screen 82 that flies of flying is for handling rescue flight
Device, state of ground is detected and is obtained the situation etc. of each parts of rescue flight device, life-detection instrument
84 are used for detecting ground life entity, and receiver 83 is for receiving the life signal that life entity sends, fuel tank
85 provide fuel oil for rescue flight device.Rescue storage is provided with seat 91, chaise longue 92, many merits in cabin 9
Energy armarium 93, seat 91 and chaise longue 92 are used for placing the wounded, and Multifunctional medical equipment 93 is used for
The wounded are carried out emergency aid and treatment, wherein, for the quick boarding of the wounded, by the hatch door in rescue storage cabin 9
It is opened in away from side, flying control equipment cabin 8, convenient entrance.
The hovering of rescue flight device, catenary motion, horizontally rotate, open up to telemechanical, yawing rotation and bow
Facing upward motion etc. is to be pushed away electromotor 4,4 attitude jet flow devices 3, levels by 2 lift engines 2, tail
Empennage 5 and vertical tail 6 Comprehensive Control realize.
Hovering is the state of flight that this aircraft is most basic, is also one of most basic forms of motion.When 2
During the fan 21 blade constant velocity rotation in the opposite direction of platform lift engine 2,2 lift engines
Moment of torsion is cancelled out each other, and mutually balancing with aircraft gravity with joint efforts of lift, now aircraft just can be protected
Hold floating state.Simultaneously in order to increase stability, it is also possible to utilize 4 attitude jet flow devices 3 to spray downwards
Gas carries out assist control.
The catenary motion of this rescue flight device is easier to control.2 lift engines 2 are increased when simultaneously
Fan 21 blade rotating speed time, the moment of torsion of 2 lift engines 2 cancels out each other, the now conjunction of lift
Power is more than aircraft gravity, and aircraft will move upward.2 lifting engine before and after simultaneously reducing
During the fan 21 blade rotating speed of machine 2, the moment of torsion of lift engine 2 is cancelled out each other equally, now lift
Make a concerted effort less than aircraft gravity, aircraft will move downward.Same in order to increase stability, also
The downward jet of 4 attitude jet flow devices 3 can be utilized to carry out assist control.
Horizontally rotate and be by mean of the torsion that fan 21 blade produces and realize.Rotate at fan 21
During, owing to the drag effect of air forms torsion.The size of torsion is relevant with rotating speed, when front and back 2
Platform lift engine 2 fan 21 rotating speed is identical but when turning to contrary, aircraft will not rotate；Work as increase
During lift engine 2 fan 21 rotating speed at the head of course, the now power torsion of 2 lift engines
Can not cancel out each other, just produce the moment around body 1 vertical (vertical Z axis) and make aircraft water
Flat turn is moved.Now in order to ensure the balance of power, need 2 jet flow device upwards jets at head,
Producing a downward power makes aircraft making a concerted effort on gravity direction be zero, offset aircraft come back or
Bow tendency.Otherwise fan 21 rotating speed increasing another lift engine 2 rotates the most round about.
Under floating state, aircraft stress balance.When 2 attitude jet flow devices 3 by body 1 the same side
Downwards during jet, aircraft can produce a power upwards, and this power produces one around direction, body 1 course
Individual moment makes aircraft body 1 tilt, and produces the component of horizontal direction, make aircraft exhibition to
Opposite side (i.e. away from the side starting attitude jet flow device 3) moves.Vice versa.
Driftage control is divided at a high speed and two kinds of situations of low speed, due to vertical tail 6 efficiency during low-speed operations
Relatively low, the thrust difference that now driftage of aircraft pushes away electromotor 4 mainly by 2 tails realizes.Work as increasing
Add side tail when pushing away electromotor 4 thrust, at barycenter, now produce one around vertical (the vertical Z of body 1
Axle) moment, aircraft to opposite side (i.e. away from the side starting tail and pushing away electromotor 4) driftage,
Vice versa；During high-speed flight, rudder 61 efficiency on vertical tail 6 is higher, for saving fuel oil,
Go off course and realize mainly by the rudder 61 on deflection vertical tail 6.The most double vertical tails 6 design
Ensure that this aircraft has shipping-direction stability.
The pitch control of this aircraft is also classified into low speed and two kinds of situations of high speed.Horizontal tail under lower-speed state
The wing 5 is inefficient, and pitch control realizes mainly by attitude jet flow device 3 jet flow, with exhibition to controlling class
Seemingly.When aircraft is in poised state, 2 attitude jet flow devices 3 at the tail of body 1 course to
During lower jet, aircraft can produce a power upwards, and this power produces one around machine at body barycenter
Body 1 open up to moment (exhibition to axle Y) aircraft is bowed, and produce the component of horizontal direction, make
Aircraft travels forward.Otherwise then come back backward during 2 attitude jet flow devices, 3 downward jet at head
Motion.During high-speed flight, for saving fuel oil, pitching is mainly by the elevator on deflection level empennage 5
51 realize.The effect of horizontal tail simultaneously also assures that this aircraft has pitching stability.
Due in the rescue flight device fan 21 built-in body of blade 1 of the present invention, and can realize vertical
The flight progress such as landing, low altitude flight, and then may be implemented in the task such as rescue in small space.
The above, the only detailed description of the invention of the present invention, but protection scope of the present invention not office
Being limited to this, any those familiar with the art, can in the technical scope that the invention discloses
The change readily occurred in or replacement, all should contain within protection scope of the present invention.Therefore, this
Bright protection domain should be as the criterion with described scope of the claims.
Claims (9)
1. a rescue flight device, it is characterised in that include body (1), lift engine (2),
Attitude jet flow device (3), tail push away electromotor (4), tailplane (5), vertical tail (6), rise and fall
Frame (7), flying control equipment cabin (8), rescue storage cabin (9)；
Multiple described lift engines (2) are built in both sides, described body (1) direction, course；
Multiple described attitude jet flow devices (3) are built in described body (1) spanwise direction both sides in pairs；
Described body (1) course steering wheel tail end is provided with orthogonal described tailplane (5)
With described vertical tail (6), wherein, described tailplane (5) according to described body (1) exhibition to
Direction is arranged, described vertical tail (6) is provided with described tail and pushes away electromotor (4)；
Fly control described in being provided with between lift engine (2) described in both sides in described body (1) to set
Standby cabin (8) and described rescue storage cabin (9)；
Described undercarriage (7) for landing is installed on described body (1) vertical direction.
Rescue flight device the most according to claim 1, it is characterised in that described lift engine
(2) it is two, and comprises fan (21) and duct electromotor (22), described duct electromotor
(22) provide power, drive described fan (21) to rotate, produce lift, and then aircraft vertical
Take off.
Rescue flight device the most according to claim 1, it is characterised in that described vertical tail (6)
Being two, described tailplane (5) is one, and described vertical tail (6) is installed vertically on described
Tailplane (5) two ends, and described tailplane (5), described vertical tail (6) are with described
Body (1) course machine tail end is connected.
Rescue flight device the most according to claim 1, it is characterised in that described tailplane (5)
On be provided with for adjust aircraft lifting elevator (51).
Rescue flight device the most according to claim 1, it is characterised in that described vertical tail (6)
On be provided with for adjusting the rudder (61) that aircraft turns to.
Rescue flight device the most according to claim 3, it is characterised in that described tail pushes away electromotor
(4) it is two, is respectively arranged in described vertical tail (6) away from described tailplane (5) side.
Rescue flight device the most according to claim 1, it is characterised in that described flying control equipment cabin
(8) with described rescue storage cabin (9) be arranged side by side along described body (1) spanwise direction, described in rescue
The hatch door helping storage cabin (9) is opened in away from described flying control equipment cabin (8) side.
Rescue flight device the most according to claim 1, it is characterised in that described body (1)
On grid (11) is installed, be used for discharging described lift engine (2) and described attitude jet flow device (3)
The air-flow produced.
Rescue flight device the most according to claim 1, it is characterised in that described undercarriage (7)
Being four, be symmetrically arranged on described body (1) spanwise direction both sides, every side installs two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585853.5A CN106005394A (en) | 2016-07-22 | 2016-07-22 | Rescue aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585853.5A CN106005394A (en) | 2016-07-22 | 2016-07-22 | Rescue aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106005394A true CN106005394A (en) | 2016-10-12 |
Family
ID=57116345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610585853.5A Pending CN106005394A (en) | 2016-07-22 | 2016-07-22 | Rescue aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005394A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494628A (en) * | 2016-10-25 | 2017-03-15 | 徐洪恩 | A kind of round-the-clock unmanned plane |
| CN106667670A (en) * | 2017-02-06 | 2017-05-17 | 浙江建设职业技术学院 | Lift air cushion for field lifesaving |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Vertical lift can be had both and determine the simple pitch control device of aircraft of wing flight |
| CN109263628A (en) * | 2018-08-02 | 2019-01-25 | 哈尔滨工程大学 | It is a kind of improve aircushion vehicle and bow bury first bow Effuser device |
| CN110027708A (en) * | 2019-03-06 | 2019-07-19 | 胡成 | A kind of military superelevation velocity of sound flight system |
| CN112498660A (en) * | 2020-12-24 | 2021-03-16 | 中国直升机设计研究所 | Duck wing high-speed tilt rotor aircraft and control method thereof |
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| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1978277A (en) * | 2005-12-09 | 2007-06-13 | 赵润生 | Combined rotor aircraft |
| US20110042507A1 (en) * | 2009-08-19 | 2011-02-24 | Seiford Sr Donald S | Convertible Vehicle For Road, Air, and Water Usage |
| KR101037995B1 (en) * | 2009-06-25 | 2011-05-31 | 주식회사 썬에어로시스 | Wing-In-Ground effect ship for vertical taking-off and landing |
| CN102190085A (en) * | 2011-05-21 | 2011-09-21 | 魏少康 | Control structure for realizing ultrahigh maneuvering and short take off and landing of aircraft |
| CN202175198U (en) * | 2011-07-21 | 2012-03-28 | 苏一 | Multifunctional rescue aircraft |
| CN103693193A (en) * | 2012-09-27 | 2014-04-02 | 赵润生 | Multipurpose universal airplane |
| CN104176250A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Vertical take-off and landing rotor aircraft with ducts built in wings |
| CN105366049A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical takeoff and landing unmanned aerial vehicle |
| CN105667782A (en) * | 2014-11-22 | 2016-06-15 | 吴建伟 | Combined type vertical take-off and landing aircraft |
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2016
- 2016-07-22 CN CN201610585853.5A patent/CN106005394A/en active Pending
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|---|---|---|---|---|
| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1978277A (en) * | 2005-12-09 | 2007-06-13 | 赵润生 | Combined rotor aircraft |
| KR101037995B1 (en) * | 2009-06-25 | 2011-05-31 | 주식회사 썬에어로시스 | Wing-In-Ground effect ship for vertical taking-off and landing |
| US20110042507A1 (en) * | 2009-08-19 | 2011-02-24 | Seiford Sr Donald S | Convertible Vehicle For Road, Air, and Water Usage |
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| CN103693193A (en) * | 2012-09-27 | 2014-04-02 | 赵润生 | Multipurpose universal airplane |
| CN104176250A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Vertical take-off and landing rotor aircraft with ducts built in wings |
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| CN105366049A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical takeoff and landing unmanned aerial vehicle |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494628A (en) * | 2016-10-25 | 2017-03-15 | 徐洪恩 | A kind of round-the-clock unmanned plane |
| CN106667670A (en) * | 2017-02-06 | 2017-05-17 | 浙江建设职业技术学院 | Lift air cushion for field lifesaving |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Vertical lift can be had both and determine the simple pitch control device of aircraft of wing flight |
| CN109263628A (en) * | 2018-08-02 | 2019-01-25 | 哈尔滨工程大学 | It is a kind of improve aircushion vehicle and bow bury first bow Effuser device |
| CN110027708A (en) * | 2019-03-06 | 2019-07-19 | 胡成 | A kind of military superelevation velocity of sound flight system |
| CN112498660A (en) * | 2020-12-24 | 2021-03-16 | 中国直升机设计研究所 | Duck wing high-speed tilt rotor aircraft and control method thereof |
| CN112498660B (en) * | 2020-12-24 | 2022-12-30 | 中国直升机设计研究所 | Duck wing high-speed tilt rotor aircraft and control method thereof |
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Application publication date: 20161012 |