CN112623183B - Portable vertical take-off and landing inclined wing aircraft - Google Patents
Portable vertical take-off and landing inclined wing aircraft Download PDFInfo
- Publication number
- CN112623183B CN112623183B CN202011602373.8A CN202011602373A CN112623183B CN 112623183 B CN112623183 B CN 112623183B CN 202011602373 A CN202011602373 A CN 202011602373A CN 112623183 B CN112623183 B CN 112623183B
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- mechanism box
- fixedly arranged
- boss
- 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.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 47
- 210000001015 abdomen Anatomy 0.000 claims abstract description 14
- 239000007921 spray Substances 0.000 claims description 7
- 230000008859 change Effects 0.000 abstract description 6
- 230000003044 adaptive effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 2
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 230000003187 abdominal effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/04—Noseplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- 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
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides a portable vertical take-off and landing inclined wing aircraft, which comprises wings, an aircraft body and an empennage, wherein the wings are arranged on the top of the aircraft body through a rotating mechanism and a fixed support; the rotating mechanism is arranged in a mechanism box, and the mechanism box is connected with the fixed support in a sliding manner through sliding rods arranged on two sides of the mechanism box; the rotary mechanism comprises a wing rotary shaft and a rotary component, the wing rotary shaft is vertically arranged in the mechanism box, a boss bearing is arranged at the top end of the wing rotary shaft, the outer ring of the boss bearing is fixedly arranged on a support plate of the wing, the wing rotary shaft is rotatably connected with a steering engine fixed on the mechanism box through the rotary component, and the bottom end of the wing rotary shaft is fixedly arranged in the mechanism box; the fixed support is fixedly arranged in the machine body. The invention adopts the shape of asymmetric wings to provide the oblique layout lift force during flight, the oblique angle can be changed along with the speed during flight, the aircraft body is more adaptive to the change of the environment than the traditional fixed wing, and the lift fan is arranged on the belly of the aircraft body to realize short-distance takeoff and vertical landing.
Description
Technical Field
The invention belongs to the field of aircrafts, and particularly relates to a portable vertical take-off and landing inclined wing aircraft.
Background
Researches on aerodynamics and power of an inclined wing aircraft have been carried out at home and abroad, the inclined wing aircraft has good aerodynamic characteristics, is different from a fixed wing aircraft, and can change an included angle between a wing and a fuselage along with the change of the environment so as to change the lift-drag ratio to adapt to the environment; compared with the variable sweepback wing, the inclined wing has the advantages of simple structure, constant aerodynamic center and stronger task capability.
The existing inclined wing technology is a large aircraft researched on the premise of subsonic speed, but related research shows that the inclined wing technology still has a certain speed-increasing advantage under low-speed flight, but the inclined wing is still in a fixed wing state during taking off and landing, and compared with a rotor aircraft, the inclined wing technology is poor in flexibility, long in taking off and landing process and needs a long runway.
Disclosure of Invention
In view of this, the present invention provides a portable vertical take-off and landing inclined wing aircraft, so as to solve the problems of inconvenience in carrying, time-consuming assembly, and poor take-off and landing performance of a fixed wing aircraft.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a portable vertical take-off and landing inclined wing aircraft comprises wings, an aircraft body and an empennage, wherein the wings are arranged on the top of the aircraft body through a rotating mechanism and a fixed support;
the rotating mechanism is arranged in a mechanism box, and the mechanism box is connected with the fixed support in a sliding manner through sliding rods arranged on two sides of the mechanism box;
the rotary mechanism comprises a wing rotary shaft and a rotary component, the wing rotary shaft is vertically arranged in the mechanism box, a boss bearing is arranged at the top end of the wing rotary shaft, an outer ring of the boss bearing is fixedly arranged on a support plate of the wing, the wing rotary shaft is rotatably connected with a steering engine fixed on the mechanism box through the rotary component, and the bottom end of the wing rotary shaft is fixedly arranged in the mechanism box;
the fixed support is fixedly arranged in the machine body.
Furthermore, the rotating assembly comprises an internal tooth slewing bearing, an external boss gear and a steering engine gear; the internal tooth slewing bearing rotary bearing is fixedly arranged in a notch of a mechanism box bottom plate, the boss outer gear is fixedly arranged at the bottom end of the wing rotating shaft, the internal tooth slewing bearing rotary bearing is internally meshed with the boss outer gear, and the boss outer gear is externally meshed with a steering gear fixedly arranged on a steering engine.
Furthermore, the fixed support comprises a fixed base plate and side plates fixedly arranged on two sides of the fixed base plate, wing slideways are arranged on the side plates on two sides, and fixing grooves used for clamping the sliding rods are formed in the wing slideways.
Furthermore, the number of the slide bars is two, the two slide bars are arranged in parallel, one slide bar penetrates through the mechanism box and is arranged in the wing slideway, the other slide bar penetrates through the mechanism box and is arranged in a fixed groove arranged on the wing slideway, and two end parts of the slide bars extending to the outer side of the wing slideway are respectively provided with a limiting block.
Further, the wings are integrally inclined, and the shapes of the wings are arranged by adopting slightly elliptical front and rear edges of the wings with asymmetric geometric shapes;
and one side of the wing, which is far away from the nose, is also provided with ailerons, which are asymmetrically arranged and controlled by a steering engine.
Further, two strip-shaped columns are fixedly arranged between wing ribs of the wing, the two strip-shaped columns are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns, and the support plate is correspondingly arranged in the strip-shaped grooves;
the support plate is provided with a mounting hole for mounting the boss bearing.
Further, a machine body duct is arranged in the machine body, an air inlet is formed in the end portion, close to the machine head, of the machine body duct, a machine body duct engine is arranged in the machine body duct, and a spray pipe air outlet is formed in the end portion, close to the tail, of the machine body duct.
Furthermore, a vector device is arranged on the outer side of the air outlet of the spray pipe of the tail.
Furthermore, the empennage comprises a vertical empennage and a horizontal empennage, wherein the vertical empennage is provided with a rudder, and the horizontal empennage is provided with an elevator.
Further, the aircraft further comprises a lift device, wherein the lift device is vertically arranged at the belly of the aircraft body;
an abdomen ducted engine is arranged in the lift device and provides power for the aircraft;
the lift device is also provided with an annular air inlet which is symmetrically distributed in a fan shape.
Compared with the prior art, the portable vertical take-off and landing inclined wing aircraft has the following advantages:
(1) The portable vertical take-off and landing inclined wing aircraft adopts an asymmetric wing shape, provides inclined layout lift force during flight, can change an inclined angle along with speed during flight, is more adaptive to environmental change than the traditional fixed wing, and is provided with a lift fan at the belly part of the aircraft body to realize short take-off and vertical landing;
(2) The portable vertical take-off and landing inclined wing aircraft adopts the design of the rotating shafts of the wings and the aircraft body, so that when the aircraft is stored, the rotating wings and the aircraft body are in a straight line and are convenient to carry;
(3) The portable vertical take-off and landing inclined wing aircraft overcomes the defects of inconvenience in carrying and time-consuming assembly of the conventional fixed wing aircraft, and simultaneously improves the take-off and landing performance of the fixed wing aircraft by the aid of the additional fuselage abdominal lifting fan.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation of the invention. In the drawings:
fig. 1 is a schematic view of an overall structure of a portable vertical take-off and landing inclined wing aircraft according to an embodiment of the present invention;
FIG. 2 is a left side view of a portable VTOL oblique wing aircraft according to an embodiment of the present invention;
FIG. 3 is a schematic view of an inverted structure of a portable VTOL oblique wing aircraft rotation mechanism according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a local wing and a fixed support of a portable VTOL oblique wing aircraft according to an embodiment of the present invention;
FIG. 5 is a rear view of a portable VTOL tilt-wing aircraft according to an embodiment of the present invention;
fig. 6 is a front view of a portable vertical take-off and landing inclined wing aircraft according to an embodiment of the invention.
Description of reference numerals:
1-an airfoil; 101-ribs; 102-ailerons; 2-a fuselage; 3-tail fin; 301-vertical tail; 302-horizontal tail; 303-rudder; 304-elevators; 4-fuselage ducted engines; 5-a fuselage duct; 6-an air inlet; 7-spray pipe air outlet; 8-abdominal ducted engine; 9-annular air inlet; 10-a rotating mechanism; 11-a wing glide slope; 12-an internally toothed slewing bearing swivel bearing; 13-wing shaft; 14-boss outer gear; 15-mechanism box; 16-a slide bar; 1601-a limiting block; 17-a fixed support; 18-a support plate; 19-a bar column; 20-elevator; 21-a steering gear; 22-boss bearings; 23-vector means.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1 to 6, the aircraft comprises a wing 1, a fuselage 2 and an empennage 3, wherein the wing 1 is mounted on the top of the fuselage 2 through a rotating mechanism 10 and a fixed support 17;
the rotating mechanism 10 is arranged in a mechanism box 15, and the mechanism box 15 is connected with a fixed support 17 in a sliding manner through sliding rods 16 arranged on two sides;
the rotating mechanism 10 comprises a wing rotating shaft 13 and a rotating assembly, the wing rotating shaft 13 is vertically arranged in a mechanism box 15, a boss bearing 22 is arranged at the top end of the wing rotating shaft 13, the outer ring of the boss bearing 22 is fixedly arranged on a support plate 18 of the wing 1, the wing rotating shaft 17 is rotatably connected with a steering engine fixed on the mechanism box 15 through the rotating assembly, and the bottom end of the wing rotating shaft 17 is fixedly arranged in the mechanism box 15;
the fixed support 17 is fixedly arranged in the machine body 2.
The rotating assembly comprises an internal tooth slewing bearing rotating bearing 12, an external boss gear 14 and a steering engine gear 21; the internal tooth slewing bearing rotary bearing 12 is fixedly arranged in a notch of a bottom plate of the mechanism box 15, the boss outer gear 14 is fixedly arranged at the bottom end of the wing rotating shaft 13, the internal tooth slewing bearing rotary bearing 12 is internally meshed with the boss outer gear 14, and the boss outer gear 14 is meshed with a steering gear 21 fixedly arranged on a steering engine.
The fixed support 17 comprises a fixed base plate and side plates fixedly arranged on two sides of the fixed base plate, wherein the side plates on two sides are provided with airfoil slideways 11, and the airfoil slideways 11 are provided with fixing grooves for clamping the sliding rods 16.
The number of the slide bars 16 is two, the two slide bars 16 are arranged in parallel, one slide bar 16 penetrates through the mechanism box 15 and is arranged in the wing slideway 11, the other slide bar 16 penetrates through the mechanism box 15 and is arranged in a fixing groove formed in the wing slideway 11, and two end parts of the slide bars 16 extending to the outer side of the wing slideway 11 are respectively provided with a limiting block 1601.
The wing 1 is an integral oblique wing, and the shape of the wing 1 is arranged by adopting the front edge and the rear edge of a slightly elliptical wing with an asymmetric geometric shape;
the aircraft is characterized in that ailerons 102 are further arranged on one side, away from the aircraft nose, of the wing 1, the ailerons 102 are arranged asymmetrically, the ailerons 102 are controlled by a steering engine and used for twisting the ailerons 102, and a flier observes and adjusts the twisting angle of the ailerons 102 during flight so as to adjust the attitude of the aircraft stably.
Strip-shaped columns 19 are fixedly arranged between wing ribs 101 of the wing 1, the number of the strip-shaped columns 19 is two, the two strip-shaped columns 19 are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns 19, and the support plate 18 is correspondingly arranged in the strip-shaped grooves;
the support plate 18 is provided with a mounting hole for mounting the boss bearing 22.
The aircraft is characterized in that an aircraft body duct 5 is arranged in the aircraft body, an air inlet 6 is formed in the end portion, close to the aircraft nose, of the aircraft body duct 5, an aircraft body duct engine 4 is arranged in the aircraft body duct 5, and a spray pipe air outlet 7 is formed in the end portion, close to the aircraft tail, of the aircraft body duct 5.
And a vector device 23 is arranged on the outer side of the jet pipe air outlet 7 of the tail.
The empennage comprises a vertical empennage 301 and a horizontal empennage 302, a rudder 303 is arranged on the vertical empennage 301, an elevator 304 is arranged on the horizontal empennage 302, and the rudder 303 and the vector device 23 share one steering engine for control.
The lifting device is vertically arranged at the belly of the machine body 2;
an abdomen ducted engine 8 is arranged in the lift device, and the abdomen ducted engine 8 provides power for the aircraft;
the lift device is also provided with an annular air inlet 9, and the annular air inlets 9 are symmetrically distributed in a fan shape; when the aircraft accelerates forwards, the front part of the annular air inlet 9 is used for air inlet, the lift force of the aircraft is increased, and the takeoff distance of the aircraft is shortened.
The aircraft is provided with eight receiver channels; wherein, two sets of power systems arranged on the aircraft occupy two receiver channels; two receiver channels are occupied by the wing ailerons on two sides controlled by the steering engine; elevators of the horizontal rear wings 302 on both sides controlled by the steering engine occupy one receiver channel; a vertical tail 301 and a vector device 23 controlled by a steering engine occupy one receiver channel; a receiver channel is occupied by a rotating mechanism 10 controlled by a steering engine; a steering engine for controlling the steering of the front wheels occupies a receiver channel;
the eight receiver channels are controlled by six rockers of the remote control.
In the implementation of the scheme, when taking off, the aircraft is accelerated by the main power of the fuselage ducted engine 4, after sliding starts, the belly ducted engine 8 mainly takes in air from the front part of the annular air inlet to generate upward thrust to increase the lift force of the aircraft and shorten the take-off distance of the aircraft, and in the process, an aircraft operator observes the attitude of the aircraft and adjusts the states of the vector devices 23 at the positions of the vertical tail wing 301 and the air outlet 7 of the nozzle pipe at the tail end of the aircraft body to enable the aircraft to take off stably;
in the flying process, an aircraft operator properly adjusts the states of the aileron 102, the elevator 304, the rudder 303, the vector device 23 of the nozzle air outlet 7 at the tail end of the aircraft body and the belly ducted engine 8 by observing the attitude of the aircraft, controls the steering engine of the rotating mechanism 10 to rotate the wing 1 anticlockwise for 20 degrees when the flying speed reaches the fastest speed so as to increase the speed, and adjusts the wing 1 back to the conventional state when the aircraft is ready for deceleration landing.
When the aircraft is close to the ground and is ready to land, the power of the fuselage ducted engine 4 is gradually reduced to zero, meanwhile, the power of the belly ducted engine 8 is increased, the air inlet at the rear part of the annular air inlet 9 is gradually increased in the deceleration process, the work efficiency of the belly ducted engine 8 is controlled while the aircraft is decelerated, the aircraft is approximately landed vertically to shorten the braking distance, in the process, an aircraft operator observes the attitude of the aircraft, and the states of the vector devices 23 of the vertical tail wing 301 and the tail end spray pipe air outlet 7 of the aircraft body are adjusted, so that the aircraft lands stably.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (5)
1. The utility model provides a portable VTOL's oblique wing aircraft that puts, includes wing (1), fuselage (2) and fin (3), its characterized in that: the wing (1) is arranged on the top of the fuselage (2) through a rotating mechanism (10) and a fixed support (17);
the rotating mechanism (10) is arranged in a mechanism box (15), and the mechanism box (15) is connected with a fixed support (17) in a sliding manner through sliding rods (16) arranged on two sides;
the rotating mechanism (10) comprises a wing rotating shaft (13) and a rotating assembly, the wing rotating shaft (13) is vertically arranged in a mechanism box (15), a boss bearing (22) is arranged at the top end of the wing rotating shaft (13), the outer ring of the boss bearing (22) is fixedly arranged on a support plate (18) of the wing (1), the wing rotating shaft (13) is rotatably connected with a steering engine fixed on the mechanism box (15) through the rotating assembly, and the bottom end of the wing rotating shaft (13) is fixedly arranged in the mechanism box (15);
the fixed support (17) is fixedly arranged in the machine body (2);
the rotating assembly comprises an inner tooth slewing bearing (12), an outer boss gear (14) and a steering engine gear (21); the internal tooth slewing bearing rotary bearing (12) is fixedly arranged in a notch of a bottom plate of a mechanism box (15), the boss outer gear (14) is fixedly arranged at the bottom end of a wing rotating shaft (13), the internal tooth slewing bearing rotary bearing (12) is internally meshed with the boss outer gear (14), and the boss outer gear (14) is externally meshed with a steering gear (21) fixedly arranged on a steering engine;
the wing (1) is an integral inclined wing, and the shape of the wing (1) is arranged by adopting the front edge and the rear edge of a wing with an asymmetric geometric shape which is slightly elliptical;
an aileron (102) is further arranged on one side of the wing (1) far away from the nose, the ailerons (102) are arranged asymmetrically, and the ailerons (102) are controlled by a steering engine;
the lifting device is vertically arranged at the belly of the machine body (2);
an abdomen ducted engine (8) is arranged in the lift device, and the abdomen ducted engine (8) provides power for the aircraft;
the lift device is also provided with an annular air inlet (9), and the annular air inlets (9) are symmetrically distributed in a fan shape;
the fixed support (17) comprises a fixed bottom plate and side plates fixedly arranged on two sides of the fixed bottom plate, wing slideways (11) are arranged on the side plates on two sides, and fixing grooves used for clamping the sliding rods (16) are arranged on the wing slideways (11);
the number of the sliding rods (16) is two, the two sliding rods (16) are arranged in parallel, one sliding rod (16) penetrates through the mechanism box (15) and is arranged in the wing slideway (11), the other sliding rod (16) penetrates through the mechanism box (15) and is arranged in a fixing groove formed in the wing slideway (11), and two end parts, extending to the outer side of the wing slideway (11), of the sliding rods (16) are respectively provided with a limiting block 1601.
2. The portable VTOL oblique wing aircraft of claim 1, wherein: strip-shaped columns (19) are fixedly arranged between wing ribs (101) of the wing (1), the number of the strip-shaped columns (19) is two, the two strip-shaped columns (19) are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns (19), and the support plates (18) are correspondingly arranged in the strip-shaped grooves;
and the support plate (18) is provided with a mounting hole for mounting a boss bearing (22).
3. The portable VTOL oblique wing aircraft of claim 1, wherein: the aircraft is characterized in that an aircraft body duct (5) is arranged in the aircraft body, an air inlet (6) is formed in the end portion, close to the aircraft nose, of the aircraft body duct (5), an aircraft body duct engine (4) is arranged in the aircraft body duct (5), and a spray pipe air outlet (7) is formed in the end portion, close to the aircraft tail, of the aircraft body duct (5).
4. The portable VTOL oblique wing aircraft of claim 3, wherein: and a vector device (23) is arranged on the outer side of a spray pipe air outlet (7) of the tail.
5. The portable VTOL oblique wing aircraft of claim 1, wherein: the empennage (3) comprises a vertical empennage (301) and a horizontal empennage (302), a rudder (303) is arranged on the vertical empennage (301), and an elevator (304) is arranged on the horizontal empennage (302).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011602373.8A CN112623183B (en) | 2020-12-29 | 2020-12-29 | Portable vertical take-off and landing inclined wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011602373.8A CN112623183B (en) | 2020-12-29 | 2020-12-29 | Portable vertical take-off and landing inclined wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112623183A CN112623183A (en) | 2021-04-09 |
| CN112623183B true CN112623183B (en) | 2023-01-17 |
Family
ID=75287003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011602373.8A Active CN112623183B (en) | 2020-12-29 | 2020-12-29 | Portable vertical take-off and landing inclined wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112623183B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009078745A (en) * | 2007-09-27 | 2009-04-16 | Japan Aerospace Exploration Agency | Electric vertical takeoff/landing aircraft |
| CN107804456A (en) * | 2016-09-08 | 2018-03-16 | 朗星无人机系统有限公司 | A kind of how culvert vertical take-off and landing unmanned machine |
| CN107176286B (en) * | 2017-05-16 | 2023-08-22 | 华南理工大学 | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| CN209757520U (en) * | 2019-03-13 | 2019-12-10 | 南京灵龙旋翼无人机系统研究院有限公司 | Device for changing aerodynamic layout of rotary wing in rotary wing aircraft |
-
2020
- 2020-12-29 CN CN202011602373.8A patent/CN112623183B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN112623183A (en) | 2021-04-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN211033016U (en) | Aircraft capable of vertically taking off and landing | |
| CN106882371A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN104816823A (en) | Duct rotary wing aircraft | |
| CN103963959B (en) | Based on Moving technology can floating type folded wing lifting body aircraft | |
| CN106585976A (en) | Aircraft layout of tilt rotors/lift fan during high-speed long endurance | |
| CN106428527A (en) | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings | |
| CN206125421U (en) | VTOL unmanned vehicles | |
| WO2023000571A1 (en) | Flying car | |
| CN106240814A (en) | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer | |
| CN204623838U (en) | A kind of duct rotor craft | |
| CN110217391B (en) | Oil-electricity hybrid power vertical take-off and landing forward-swept fixed wing unmanned aerial vehicle | |
| CN106167096A (en) | Modified model level of approximation rotates propeller wing flap lift-rising and connects wing aircraft | |
| CN206327567U (en) | A kind of compound unmanned vehicle | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN212243812U (en) | Tilting duck type layout aircraft | |
| CN112623183B (en) | Portable vertical take-off and landing inclined wing aircraft | |
| CN116101524B (en) | Fixed wing rotor wing dual-mode tailstock type vertical take-off and landing unmanned aerial vehicle and working method | |
| CN112722263A (en) | Vertical/short-distance take-off and landing aircraft with distributed power coupling lift-increasing wing surfaces | |
| CN111762316A (en) | Tilting component of tilting rotor unmanned aerial vehicle, tilting rotor unmanned aerial vehicle and using method | |
| CN106828911A (en) | String wing unmanned plane | |
| CN103847964B (en) | A kind of can the arc shaped wing aircraft of vrille | |
| CN208165273U (en) | A kind of tail sitting posture unmanned vertical flight | |
| CN207725616U (en) | Double coaxial tilting rotor wing unmanned aerial vehicles of shoe formula | |
| CN206255191U (en) | String wing unmanned plane | |
| CN205819564U (en) | Modified model level of approximation rotates propeller wing flap lift-rising and connects wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |