CN106043685A - Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft - Google Patents
Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft Download PDFInfo
- Publication number
- CN106043685A CN106043685A CN201610380319.0A CN201610380319A CN106043685A CN 106043685 A CN106043685 A CN 106043685A CN 201610380319 A CN201610380319 A CN 201610380319A CN 106043685 A CN106043685 A CN 106043685A
- Authority
- CN
- China
- Prior art keywords
- wing
- rotor
- vector
- oar
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft and belongs to the technical field of aviation aircraft design. The aircraft is composed of a special-shaped rotor, wings, vector propellers, an aircraft body and tail wings. In the vertical take-off and landing process, main lift force is provided through the special-shaped rotor, the thrust directions of the two vector propellers on the tail wings are left and right in the horizontal direction, and transverse thrust is provided so as to balance the reverse torsion of the special-shaped rotor. In the process of conversion transition from a vertical take-off and landing mode to a flat flying mode, the two vector propellers horizontally deflect by 90 degrees backwards to generate forward thrust, and the lift force is gradually provided through the wings. The aircraft has the vertical take-off and landing capacity and the high-speed flat flying capacity at the same time, and the two modes can be switched in the air. The flat flying speed, the voyage and the endurance are improved by about 50% compared with those of a conventional helicopter. The larger operation range and the higher operation capacity are achieved, and the helicopter can be replaced with the aircraft in future.
Description
Technical field
The present invention relates to a kind of double vector and advance oar rotor/fixed-wing combined type vertically taking off and landing flyer, its both had with
VTOL that helicopter is the same and hovering ability, again can as fixed wing airplane high speed cruise flight, belong to aviation
Technical field of aircraft design.
Background technology
The outstanding feature of helicopter is to do low latitude (several meters), low speed (from the beginning of hovering) and head side at present
To constant maneuvering flight, particularly can be in little area place VTOL.But there is Speed Obstacles in helicopter, it is impossible to realize height
Speed flight.
And combined type vertically taking off and landing flyer layout to make aircraft can obtain rotor craft distinctive at low-altitude low-speed
Under the conditions of flexible flight and VTOL, hovering, after fly, excellent properties that side flies, possess again Fixed Wing AirVehicle
High-altitude, at a high speed, efficiently, the advantage such as combat radius is big.The flying quality of two kinds of variety classes aircrafts has not only been merged in this design,
Improve respective flight envelope, but also there is relatively low signal characteristic value and good high-speed flight survivability.So phase
Compare pure helicopter, it is necessary to invent a kind of novel combined type vertically taking off and landing flyer layout.
At present ripe vertically taking off and landing flyer, has a following deficiency:
1, vertically taking off and landing flyer conversion and control based on tilting rotor technology is complicated.
2, vertically taking off and landing flyer rotor based on stall rotor technology flies to be main load parts under pattern flat, and revolves
The general aspect ratio of the wing is relatively big, and the fixing aerofoil that overall structure rigidity is more general is low, is susceptible to tremor when flight speed is very fast
Deng Aeroelastic Problems, it is unfavorable for high-speed flight.
Summary of the invention
In order to solve problems of the prior art, the present invention provides a kind of double vector to advance oar rotor/fixed-wing multiple
Box-like vertically taking off and landing flyer, described aircraft is mainly advanced oar, fuselage and empennage to form by special type rotor, wing, vector.?
During VTOL, special type rotor providing prevailing lift, two vectors on empennage advance oar thrust direction level respectively
To from left to right, it is provided that it is anti-twisted that lateral thrust balances special type rotor.It is transitioned into the flat mistake flying pattern by VTOL patten transformation
Cheng Zhong, two vectors advance oar horizontal deflection 90 degree backward, produce thrust forward, and aircraft ramps up flat flying, lift by
Gradually being provided by wing, special type rotor tapers off rotation and is locked in appointment position, parallel with fixed-wing, forms double-vane layout.
It is an advantage of the current invention that:
(1) vertical and landing takeoff rapidly can be realized, landing site is required relatively low.
(2) at a high speed flat can be realized to fly, when there is bigger voyage and boat.
(3) there is take off vertically landing and the most flat ability flown simultaneously, and can aloft carry out both patterns
Conversion.
(4) special type rotor is similar to the rotor of pure helicopter, has identical flight efficiency, VTOL flying quality
Close with pure helicopter with low-speed operations performance, and level speed, voyage improve about with comparing pure helicopter during boat
50%, there is bigger job area and higher performance capacity, helicopter can be replaced in the future.
(5) wing of this aircraft is similar to the wing and empennage to conventional fixed-wing aircraft with empennage, and this aircraft exists
Putting down and have identical flight efficiency with conventional fixed-wing aircraft when flying pattern, the flat performance that flies is close with conventional fixed-wing aircraft, and
Then there is compared with conventional fixed-wing aircraft the landing ability with low-speed operations that takes off vertically, be more suitable for field usage and low latitude
Low speed operation.
(6) the special type rotor of this aircraft, wing, empennage and vector advance oar independently to control, and each other
Disturbing less, the peaceful pattern that flies of VTOL pattern can aloft realize stable switch transition, compares tail sitting posture VTOL
Aircraft, tiltrotor, tilting wing formula vertically taking off and landing flyer etc. have higher safety and comfortableness.
Accompanying drawing explanation
Fig. 1 is that the double vectors under VTOL pattern advance oar rotor/fixed-wing combined type vertically taking off and landing flyer.
Fig. 2 is that the flat double vectors flying under pattern advance oar rotor/fixed-wing combined type vertically taking off and landing flyer.
In figure:
1. special type rotor；2. wing；3. vector advances oar；4. fuselage；5. empennage.
Detailed description of the invention
The present invention is described in detail with embodiment below in conjunction with the accompanying drawings.
The present invention provides a kind of double vector to advance oar rotor/fixed-wing combined type vertically taking off and landing flyer, as it is shown in figure 1,
Described aircraft includes that special type rotor 1, wing 2, vector advance oar 3, fuselage 4 and empennage 5.Described special type rotor 1 is positioned at machine
Top at body 4 the most about 40% length, the flat shape of its blade is isosceles trapezoid, length of blade and mean width ratio
For 6-10, compare pure helicopter rotor blade (length-width ratio 15-20) wider, taper ratio about 0.6, select relative thickness 8%-
12%, aerofoil profile symmetrical before and after upper lower curve is all elliptic curve.Described wing 2 is positioned at below fuselage with fuselage 4 junction,
The geometric center of wing 2 and the center superposition of special type rotor 1, the area of wing 2 is special type rotor 1 rotation status rotor disk area
20%-25%, the aspect ratio of wing 2 about 13-17, select the airfoil with high ratio of lift over drag of relative thickness 10%-15%.Described empennage 5
Being positioned at fuselage 4 afterbody, the distance of empennage 5 leading edge root to special type rotor 1 center is equal to the radius of special type rotor 1, empennage 5 area
For the 15%-20% of the area of wing 2, aspect ratio is about 5-8, selects the aerofoil profile symmetrical above and below of relative thickness 8%-12%.Institute
Stating vector advances oar 3 to have two, is separately positioned at the trailing edge at two ends, left and right of empennage 5, and vector propelling oar 3 can horizontal deflection 90
Degree, when VTOL pattern, the vector of two advances the thrust direction of oar 3 respectively the most to the left and to the right, VTOL pattern with
Putting down flies in patten transformation transient process, and two vectors advance oars 3 simultaneously to post deflection 90 degree, put down and fly two vectors propellings during pattern
The direction of oar 3 the most backward, produces thrust forward.Special type rotor 1 and vector advance oar 3 by the dynamical system within fuselage 4
Drive.
When aircraft vertical takes off, dynamical system drives special type rotor 1 to rotate and provides lift, and aircraft is lifted torr at sky
In, dynamical system simultaneously the most also output power advance oar 3 to vector, advance oars 3 pushing away to the left and to the right by adjusting two vectors
Power size can offset the counteracting force under the different rotating speeds that special type rotor 1 produces, and produces driftage control moment.Such as Fig. 2 institute
Show, arrive after certain altitude, when aircraft by VTOL patten transformation be transitioned into flat fly mode flight time, vector advances oar 3
Oar axle half-twist backward in fuselage plane, produce thrust forward, and increase thrust, be gradually increased level speed, wing
2 provide prevailing lift, and for special type rotor 1 off-load, now special type rotor 1 rotating speed is gradually lowered, when level speed increases to make
When wing 2 produces enough lift, special type rotor 1 rotating speed reduces to zero, stops operating and is locked in and wing 2 keeping parallelism
Position, whole airplane is that double-vane layout is flat forward to fly, thus realizes the steady switching of two kinds of offline mode.Fly when carrying out putting down-hang down
During straight landing switch transition flight, special type rotor 1 unlocks, and gradually steps up rotating speed, increases pulling force upwards, and vector pushes away simultaneously
Enter oar 3 partially turn 90 degrees to both sides respectively and be gradually reduced thrust, finally can be completely counterbalanced by special type rotor 1 by adjustment thrust and produce
Different rotating speeds under counteracting force.Now aircraft is transformed into VTOL pattern, and realizes vertical landing.
Claims (5)
1. pair vector advances oar rotor/fixed-wing combined type vertically taking off and landing flyer, it is characterised in that: described aircraft is by special type
Rotor, wing, vector advance oar, fuselage and empennage composition, during VTOL, special type rotor provide lift, empennage
On two vectors advance oar thrust directions levels respectively to from left to right, it is provided that it is anti-twisted that lateral thrust balances special type rotor；By
VTOL patten transformation is transitioned into flat during flying pattern, and two vectors advance oar horizontal deflection 90 degree backward, produce to
Front thrust, aircraft ramps up flat flying, and lift is gradually provided by wing, and special type rotor tapers off rotation and is locked in finger
Location is put, parallel with fixed-wing, forms double-vane layout.
The most according to claim 1 pair of vector advances oar rotor/fixed-wing combined type vertically taking off and landing flyer, and its feature exists
In: described special type rotor is positioned at the top at fuselage 40% length from front to back, and the flat shape of its blade is isosceles trapezoid, leaf
Leaf length and mean width ratio are 6-10, taper ratio 0.6, select relative thickness 8%-12%, upper lower curve to be all elliptic curve
Before and after symmetrical aerofoil profile.
The most according to claim 1 pair of vector advances oar rotor/fixed-wing combined type vertically taking off and landing flyer, and its feature exists
In: described wing and fuselage junction are positioned at below fuselage, the geometric center of wing and the center superposition of special type rotor, wing
Area is the 20%-25% of special type rotor 1 rotation status rotor disk area, aspect ratio 13-17 of wing, selects relative thickness
The airfoil with high ratio of lift over drag of 10%-15%.
The most according to claim 1 pair of vector advances oar rotor/fixed-wing combined type vertically taking off and landing flyer, and its feature exists
In: described empennage is positioned at afterbody, and the distance of empennage leading edge root to special type rotor centers is equal to the radius of special type rotor, tail
Wing area is the 15%-20% of the area of wing, and aspect ratio is 5-8, selects the aerofoil profile symmetrical above and below of relative thickness 8%-12%.
The most according to claim 1 pair of vector advances oar rotor/fixed-wing combined type vertically taking off and landing flyer, and its feature exists
In: described vector advances oar to have two, is separately positioned at the trailing edge at two ends, left and right of empennage, and vector propelling oar can horizontal deflection
90 degree, when VTOL pattern, the vector of two advances the thrust direction of oar respectively the most to the left and to the right, in VTOL pattern
Flying in patten transformation transient process with flat, two vectors advance oar simultaneously to post deflection 90 degree, put down two vectors when flying pattern and push away
Enter the direction of oar the most backward, produce thrust forward.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610056129 | 2016-01-27 | ||
| CN2016100561293 | 2016-01-27 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043685A true CN106043685A (en) | 2016-10-26 |
| CN106043685B CN106043685B (en) | 2018-09-11 |
Family
ID=57172473
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610380319.0A Active CN106043685B (en) | 2016-01-27 | 2016-06-01 | Double vectors promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106043685B (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106807095A (en) * | 2017-03-23 | 2017-06-09 | 高桂霞 | A kind of cloudling offline mode signal switching apparatus |
| CN108327837A (en) * | 2018-04-28 | 2018-07-27 | 苏州智泉农业科技有限公司 | A kind of self-balancing two-wheeled agricultural vehicle |
| CN109050908A (en) * | 2018-08-24 | 2018-12-21 | 安徽云翼航空技术有限公司 | A kind of composite wing aviation aircraft and its flight control method |
| CN109815528A (en) * | 2018-12-13 | 2019-05-28 | 航天神舟飞行器有限公司 | A method of the aircraft parameters optimization based on large-scale composite wing gas |
| CN109823520A (en) * | 2019-02-26 | 2019-05-31 | 徐桂敏 | Aircraft and flight system |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机***研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
| CN110949662A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Novel concept layout airplane with double-wing configuration |
| CN112141328A (en) * | 2019-06-27 | 2020-12-29 | 沃科波特有限公司 | Aircraft with a flight control device |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN114954932A (en) * | 2021-09-28 | 2022-08-30 | 熊磊 | Vertical take-off and landing aircraft based on variable paddle technology and double-paddle layout |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070095969A1 (en) * | 2005-11-02 | 2007-05-03 | The Boeing Company | Rotor wing aircraft having a bypassable radial inflow turbine |
| CN102632992A (en) * | 2012-03-28 | 2012-08-15 | 北京航空航天大学 | Single-power horizontal tractor type high-speed high-mobility helicopter |
| US20130327879A1 (en) * | 2012-06-11 | 2013-12-12 | Sikorsky Aircraft Corporation | High speed compound rotary wing aircraft |
-
2016
- 2016-06-01 CN CN201610380319.0A patent/CN106043685B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070095969A1 (en) * | 2005-11-02 | 2007-05-03 | The Boeing Company | Rotor wing aircraft having a bypassable radial inflow turbine |
| CN102632992A (en) * | 2012-03-28 | 2012-08-15 | 北京航空航天大学 | Single-power horizontal tractor type high-speed high-mobility helicopter |
| US20130327879A1 (en) * | 2012-06-11 | 2013-12-12 | Sikorsky Aircraft Corporation | High speed compound rotary wing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 张啸迟等: "旋翼固定翼复合式垂直起降飞行器概念设计研究", 《航空学报》 * |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN106807095A (en) * | 2017-03-23 | 2017-06-09 | 高桂霞 | A kind of cloudling offline mode signal switching apparatus |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN108327837A (en) * | 2018-04-28 | 2018-07-27 | 苏州智泉农业科技有限公司 | A kind of self-balancing two-wheeled agricultural vehicle |
| CN109050908A (en) * | 2018-08-24 | 2018-12-21 | 安徽云翼航空技术有限公司 | A kind of composite wing aviation aircraft and its flight control method |
| CN109815528A (en) * | 2018-12-13 | 2019-05-28 | 航天神舟飞行器有限公司 | A method of the aircraft parameters optimization based on large-scale composite wing gas |
| CN109823520A (en) * | 2019-02-26 | 2019-05-31 | 徐桂敏 | Aircraft and flight system |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机***研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| CN112141328A (en) * | 2019-06-27 | 2020-12-29 | 沃科波特有限公司 | Aircraft with a flight control device |
| CN112141328B (en) * | 2019-06-27 | 2023-11-24 | 沃科波特有限公司 | Aircraft |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
| CN110481771B (en) * | 2019-09-26 | 2024-06-07 | 成都纵横大鹏无人机科技有限公司 | Fixed wing aircraft capable of taking off and landing vertically and unmanned aerial vehicle system |
| CN110949662A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Novel concept layout airplane with double-wing configuration |
| CN114954932A (en) * | 2021-09-28 | 2022-08-30 | 熊磊 | Vertical take-off and landing aircraft based on variable paddle technology and double-paddle layout |
| CN114954932B (en) * | 2021-09-28 | 2023-09-26 | 熊磊 | Vertical take-off and landing aircraft based on variable-pitch wing technology and double-pitch wing layout |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043685B (en) | 2018-09-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106043685A (en) | Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft | |
| CN112937849A (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN106043684B (en) | A kind of connectible combined type aircraft of rotor wing | |
| CN105923154A (en) | Longitudinal column type double-rotor-wing fixed wing combined vertical take-off and landing aircraft | |
| CN106043687B (en) | Double hair back-pushed canard rotor/fixed-wing combined type vertically taking off and landing flyer | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN112896499A (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller | |
| CN111942581B (en) | Distributed lift force duck-type layout vertical take-off and landing unmanned aerial vehicle and control method | |
| CN112027073A (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle | |
| CN210083543U (en) | Aerodynamic layout of four-blade rotary wing aircraft | |
| CN111762314A (en) | Rotor aircraft capable of vertically taking off and landing | |
| CN218463872U (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN215043673U (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller | |
| CN212829059U (en) | Distributed lift duck type layout vertical take-off and landing unmanned aerial vehicle | |
| CN117858831A (en) | Aircraft, control method and device thereof, and computer readable storage medium | |
| CN109941430B (en) | Four-blade rotary wing, rotary wing airplane and control method | |
| CN113682471A (en) | Rotor solar energy unmanned aerial vehicle verts | |
| WO2024103279A1 (en) | Dual-rotor tilt aircraft and flight control method therefor | |
| WO2024103278A1 (en) | Multi-propeller tilting aircraft and flight control method therefor | |
| CN114954932B (en) | Vertical take-off and landing aircraft based on variable-pitch wing technology and double-pitch wing layout | |
| CN112027074A (en) | Combined type tilting wing longitudinal wing-changing counter-speed rotor aircraft | |
| CN112208757B (en) | Three-rotor tailstock type vertical take-off and landing unmanned aerial vehicle | |
| CN212501015U (en) | Small unmanned tilt rotor aircraft overall pneumatic layout | |
| CN213566469U (en) | Combined type side-propulsion longitudinal-row autorotation double-rotor aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |