CN104743112B - Novel tilt wing aircraft - Google Patents
Novel tilt wing aircraft Download PDFInfo
- Publication number
- CN104743112B CN104743112B CN201510197632.6A CN201510197632A CN104743112B CN 104743112 B CN104743112 B CN 104743112B CN 201510197632 A CN201510197632 A CN 201510197632A CN 104743112 B CN104743112 B CN 104743112B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- wing
- fixed
- movable
- fuselage
- 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
Landscapes
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a novel tilt wing aircraft, which is capable of carrying out vertical take-off, landing and hovering, capable of flying in a fixed wing airscrew aircraft mode, and also capable of switching between two modes. The aircraft mainly consists of an aircraft structure, a connection structure and a flying control system, wherein aircraft wings are divided into a fixed part and a movable part; when the aircraft takes off, lands and hovers, the movable wings and non-variable torque airscrew systems fixed to the movable wings tilt along a rotating shaft to a vertical state, and a lift force is provided by airscrews; when the aircraft is in flat flight, the movable wings and the airscrew systems rotate to the fixed wing part, and the aircraft flies like a normal layout fixed wing aircraft; in a switching phase, the aircraft is controlled by the flying control system which is independently researched. The aircraft has the characteristics that the functions are many, the use range is wide, the structure is simple, the cost is low and the like, and can be widely applicable to fields of air photography, expressway patrol, disaster situation reconnaissance, military reconnaissance and the like.
Description
Technical field
The present invention is that a kind of non-bending moment propeller of two axles that is based on provides power, with two kinds of VTOL and fixed-wing
Pattern, and can be flown as desired by the mode of vert movable wing and its propeller dynamical system being fixed thereon
A kind of aircraft of pattern switching, and in particular to new tilt wing aircraft.
Background technology
The birth of VTOL technology is primarily due to the deficiency of aircraft rolling start mode, particularly in all previous war
Performance, allow aircraft VTOL enter people sight line.The war such as World War II and Mideast Asian war is directly attacked enemy airport
The weak point for allowing people to experience the sliding race formula aircraft for needing runway is hit, and cold war is then the catalysis of VTOL technology
Agent.In five sixties after World War II, very likely breaking out under the shade of nuclear war, fears are entertained that general nuclear warfare occurs airport is made
Into the situation that destruction, conventional airplane cannot be set out, so having expedited the emergence of the VTOL technology of fixed wing airplane.VTOL aircraft
Reduce or broken away from substantially the dependence to runway, it is only necessary to which the level land of very little just can rise sheer from level ground and vertical landing, so
Aircraft can be distributed in war, be easy to flexibly to launch an attack, shift and pretend hidden, be difficult to be found by enemy, and the rate of attendance is also big
Width is improved, and the strike to enemy has very high emergentness, substantially increases the battlefield survival rate of aircraft.In addition, having
The aircraft of VTOL ability does not need special airport and runway, eliminates the airport construction expense of costliness, without
Bird repellent, also can be in landing under bad weather condition, and benefit is too many, reduce use cost, thus the VTOL of aircraft into
One direction of aviation development.
The sixties of twentieth century five, some companies in the U.S., Canada and Europe have competitively started one development and have gone straight up to
Machine and fixed wing airplane advantage are in the upsurge of the tilting rotor machine of one.Initially, many aeronautics experts are posted developing this aircraft
Give great expectations.But due to the design structure of this aircraft it is complicated, especially to wing rotational structure and rotary nacelle structure
Development aspect is difficult to make a breakthrough for a long time, along with the accident of fatal crass when taking a flight test occurs in succession, therefore, many states
Family successively abandons development.
In 1972, Bell Co. was just connected to AUS and American National space flight and aviation office with regard to joint development XV-
The contract of 15 tiltrotors.1981, the U.S. succeeded in developing practical tiltrotor on the basis of XV-15, and 1985
January in year, it was officially named V-22 " osprey ".As a kind of tiltrotor, the fuselage of V-22 " osprey ", wing and general
Logical fixed wing airplane basic simlarity, but its airscrew engine for being located at wing two ends but can be rotated upwardly and downwardly.Work as propeller
Electromotor from horizontality go to plumbness when, V-22 " osprey " just can realize VTOL and outstanding as helicopter
Stop, when airscrew engine is in horizontality, can just give one pulling force forward of aircraft, enable it to as fixed wing airplane one
As fly.
Of course, " osprey " is not without shortcoming.First shortcoming is exactly technical sophistication, and operating difficultiess are gone back so far
When have accident.Second shortcoming, is exactly that pneumatic efficiency is relatively low.Due under VTOL state, the lower gas washing that rotor is produced
Flow and stopped by wing, reduce propeller efficiency.
In recent years, many producers can not at a high speed equal winged shortcoming for helicopter, employ helicopter and fixed-wing two
The form that kind of aircraft layout is combined, solved by the double dynamical way of output can VTOL, can put down the problem for flying at a high speed again.
Propulsion oar is installed in its afterbody.When needing to advance at utmost speed, the propulsion oar for opening its afterbody obtains high-speed flight with this.
But affected by itself configuration, occur that lifting airscrew part produces very big resistance when high speed is flat winged so as to fly
Speed, voyage etc. are subject to larger restriction.Additionally, the aircraft such as sparrow hawk formula, F35 is also capable of achieving the flight of both of which, but due to its knot
Structure is complicated, very high etc. reason of cost, is not used to the design of unmanned plane.
The research of this kind of type is also being actively developed in China, " swift " YY-1 of such as group company of Qingan County of Air China is short
Away from/VUAV.Two main screws for being arranged on wing and together verting with wing are used, and is arranged in
The auxiliary propeller of tail position realizes the flight attitude control of aircraft vertical landing pattern jointly.But the aircraft is switching to
Its auxiliary power unit does not only work during fixed-wing pattern, can also produce resistance, increase the weight of full machine, virtually increases
Fuel consumption, so as to shortening the voyage of aircraft.
It is same, Chinese Helicopter " blue whale " unmanned plane, using four axle propeller arrangements, it is possible to achieve double mode
The target of flight.But it is required pulling force much smaller than VTOL due to putting down the pulling force needed for flying, therefore, substantially without heel row spiral shell
The power of rotation oar, and heel row propeller is subject to the interference in air flow of front-seat rotor when flat winged, efficiency is substantially reduced, or even becomes negative
Load.
The aircraft that be again capable of achieving VTOL ripe for Technical comparing at this stage is mainly four axles, six axles, eight axles
Aircraft etc..These aircraft can be all relatively good in manipulation and stability.But there is voyage short mostly, it is impossible to as fixed-wing
Mode is like that with flat winged, the low shortcoming of efficiency of higher speed.
The content of the invention
The invention provides one kind can VTOL, hovering as helicopter, again can be to fixed wing airplane one
Sample puts down at a high speed what is flown, can also switch between both of which, and by non-bending moment twin screw the new wing that verts of power is provided
Aircraft, it has a simple structure, and control is stable, the advantages of mobility is good.
The present invention is achieved like this, a kind of new tilt wing aircraft, mainly includes：Movable wing, fixed wing, machine
Body, flaperon, horizontal tail, vertical fin, elevator, rudder, propeller system, tail supporting rod and undercarriage；It is characterized in that：Fixed machine
The wing is connected to fuselage middle and upper part, and respectively there are a movable wing, propeller set in fixed wing outside left and right two ends symmetrical for fuselage
System is fixed on movable wing, and movable wing and propeller system can be verted by the steering wheel manipulator inside wing, can motivation
Wing rear portion is provided with flaperon, and horizontal tail and vertical fin are connected by tail supporting rod with fuselage, and horizontal tail and vertical fin rear portion are respectively equipped with elevator
And rudder, fuselage has undercarriage.Under VTOL and floating state, by propeller system, movable wing and the flap
The coordination VTOL of control realization aircraft of aileron, spot hover and it is movable, the action such as rotate；In flat winged state
Under, movable wing section is fixed, and with fixed wing section lift is provided jointly, has flaperon in the same direction or incorgruous its liter of deflection control
Power and crosswise movement.
New tilt wing aircraft of the present invention under VTOL state, can by propeller system, movable wing and
Flaperon collective effect controls the flight attitude of aircraft.
Under the flat winged state of new tilt wing aircraft of the present invention, movable wing and fixed wing can be combined shape
Into complete wing, lift is provided for aircraft under the pulling force effect that propeller system is provided.
New tilt wing aircraft of the present invention is total in offline mode transformation process by movable wing and fixed wing
Same-action.
Aircraft of the present invention flies control plate program development：This VTOL aircraft has three kinds of offline mode, that is, be divided into vertical
Straight landing pattern, transition at a slow speed front winged pattern and it is quick before winged pattern.Due to the difference of offline mode, generally require to mould
Formula passage needs opening or closing etc. in different offline mode.Based in this, it is necessary to can select for each passage
Select.So being the offline mode do not fixed the characteristics of this winged control program, flying each passage of control plate can be set to arbitrarily
Output or mixing output.
The present invention effect be：VTOL, hovering and fixed-wing mode flight can be realized.Compare traditional sense
On two axle fixed wing airplanes there is more preferable versatility, more traditional three axle, four axles, six axle aircrafts more save combustion
Oil.Possess good mobility and flight speed, this is significant to the use range for improving aircraft, while the present invention is equipped with certainly
The winged control plate of main exploitation so that the security performance of aircraft is higher, stability more preferably, also be adapted for producing in enormous quantities.Aircraft has work(
Can be many, extensively, simple structure the features such as low cost, is widely portable to aerophotography, highway patrol, the condition of a disaster to use range
The every field such as prospecting and military investigation.
Description of the drawings
Fig. 1 is the structural representation one of the present invention.
Fig. 2 is the structural representation two of the present invention.
1st, movable wing, 2, fixed wing, 3, fuselage, 4, flaperon, 5, horizontal tail, 6, vertical fin, 7, elevator, 8, direction
Rudder, 9, propeller system, 10. tail supporting rod, 11, undercarriage.
Specific embodiment
As shown in Figure 1 and Figure 2, the present invention be such to implement, a kind of new tilt wing aircraft, it include aircaft configuration,
Aircraft connecting mode, the part of flight control system three composition.The aircaft configuration includes fuselage 1, movable wing 2, fixed wing 3, machine
Body 4, flaperon 5, horizontal tail 6, vertical fin 7, elevator 8, rudder 9, non-bending moment propeller system 10, tail supporting rod 11, undercarriage；Its
It is characterized in that：Fixed wing 2 is connected to the middle and upper part of fuselage 3, and fixed wing 2 outside symmetrical for fuselage 3 respectively has with movable wing
1, propeller system 9 is fixed on movable wing, and the steering wheel that movable wing 1 and propeller system 9 can pass through inside wing is manipulated
Device verts, and the rear portion of movable wing 1 is provided with flaperon 4, and horizontal tail 5 and vertical fin 6 are connected by tail supporting rod 10 with fuselage 3, horizontal tail 5 and hang down
The rear portion of tail 6 is respectively equipped with elevator 7 and rudder 8, and fuselage 3 has undercarriage 11.Under VTOL and floating state, lead to
Cross the coordination VTOL of control realization aircraft of propeller system 9, movable wing 1 and flaperon 4, spot hover and in front and back
The actions such as mobile, rotation；Under flat winged state, the part of movable wing 1 is fixed, and with the fixed part of wing 2 lift is provided jointly, has
Flaperon is in the same direction or incorgruous deflection controls its lift and crosswise movement.
The aircraft is mainly made up of aircaft configuration, aircraft connecting mode and flight control system.Aircraft wing is divided into fixed and can
Dynamic two parts, when VTOL and hovering, the non-bending moment propeller system that movable wing is fixed thereon is tilted to along rotating shaft
Plumbness, has propeller to provide lift；Flat when flying, movable wing and propeller system rotate back into fixed-wing position, and normally
Layout fixed wing airplane equally flies；The conversion stage is controlled by the flight control system of self-service development.
The present invention specifically includes three kinds of offline mode：VTOL and hovering pattern, fixed-wing pattern and transition mode.
In when VTOL and hovering pattern, by non-bending moment propeller dynamical system 9, movable wing 1 and flaperon 4
Coordination control, wing center of rotation, center of gravity and flaperon produce wing tilt torque effect under realize the vertical of aircraft
Landing, spot hover and movable, differential by two motors realizes pivot stud and rolling etc..
When being in flat winged state, movable wing 1 rotates back into and fixes the identical position of wing 2, is formed and fixed-wing flies
The same distribution form of machine, lift is provided under the pulling force effect of propeller system 9 jointly with fixed wing 2, same by flaperon
To or incorgruous deflection control its lift and roll action.
In excessive pattern when, lift is progressively transitioned into by fixing from all being provided by two non-bending moment propeller systems 9
Wing 2 and movable wing 1 are provided, and motor speed, aircraft flight speed and aerodynamic force are central all in change, this stage, by
It is arranged in fuselage, the flight control system of autonomous Design to be realizing.
Claims (3)
1. a kind of new tilt wing aircraft, its structure mainly includes：Movable wing, fixed wing, fuselage, flaperon, horizontal tail, hang down
Tail, elevator, rudder, propeller system, tail supporting rod and undercarriage；It is characterized in that：The propeller system is non-bending moment
Propeller system；Fixed wing is connected to fuselage middle and upper part, and fixed wing outside left and right two ends symmetrical for fuselage respectively have one
Movable wing, propeller system is fixed on movable wing, and movable wing and propeller system can be by the steering wheels inside wing
Manipulator verts, and movable wing rear portion is provided with flaperon, and horizontal tail and vertical fin are connected by tail supporting rod with fuselage, after horizontal tail and vertical fin
Portion is respectively equipped with elevator and rudder, and fuselage has undercarriage；The new tilt wing aircraft under VTOL state,
By propeller system, movable wing and flaperon collective effect, coordinate to control the flight attitude of aircraft.
2. a kind of new tilt wing aircraft according to claim 1, it is characterised in that：The new tilt wing aircraft is flat to fly
Under state, movable wing section is fixed, and with fixed wing section lift is provided jointly, has flaperon in the same direction or incorgruous deflection control
Its lift and crosswise movement.
3. a kind of new tilt wing aircraft according to claim 1, it is characterised in that：The new tilt wing aircraft is flying
In row mode transformation process, lift from all being provided by two non-bending moment propeller systems, be progressively transitioned into by fixed wing and
Movable wing is provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510197632.6A CN104743112B (en) | 2015-04-24 | 2015-04-24 | Novel tilt wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510197632.6A CN104743112B (en) | 2015-04-24 | 2015-04-24 | Novel tilt wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104743112A CN104743112A (en) | 2015-07-01 |
| CN104743112B true CN104743112B (en) | 2017-04-12 |
Family
ID=53583528
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510197632.6A Active CN104743112B (en) | 2015-04-24 | 2015-04-24 | Novel tilt wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104743112B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083551B (en) * | 2015-08-03 | 2017-07-07 | 江苏工程职业技术学院 | One kind can tiltrotor and its control method |
| CN105404310B (en) * | 2015-11-27 | 2019-01-15 | 深圳一电航空技术有限公司 | UAV Flight Control method and device |
| CN107323650A (en) * | 2016-04-29 | 2017-11-07 | 杨双来 | Movable wing aircraft |
| CN105711830B (en) * | 2016-05-10 | 2018-06-01 | 左建章 | A kind of two axial vector balancing flap tiltrotor aircrafts |
| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| CN106965928A (en) * | 2017-03-08 | 2017-07-21 | 贾杰 | The rotatable wing vertically taking off and landing flyer of multistage |
| CN106843276A (en) * | 2017-04-06 | 2017-06-13 | 苏州全翼空智能科技有限公司 | A kind of tilting rotor wing unmanned aerial vehicle control system |
| CN107380427B (en) * | 2017-09-04 | 2023-06-20 | 陈超 | Wing dual-purpose type tilting wing unmanned aerial vehicle |
| CN109703753A (en) * | 2019-02-12 | 2019-05-03 | 欧阳军 | A kind of new vertical takeoff and landing vehicle |
| CN109911189A (en) * | 2019-03-27 | 2019-06-21 | 南京航空航天大学 | A kind of horizontal double rotor unmanned plane based on 3D printing |
| CN111409821A (en) * | 2020-04-26 | 2020-07-14 | 北京航空航天大学合肥创新研究院 | Solar unmanned aerial vehicle with tilting wings |
| CN113697097B (en) * | 2021-09-01 | 2024-01-02 | 中国航空研究院 | Fixed wing aircraft overall aerodynamic layout with tiltable outer wings and rotor wings |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8371520B2 (en) * | 2009-07-31 | 2013-02-12 | William Craig Easter | Rapidly convertible hybrid aircraft and manufacturing method |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| CN203528810U (en) * | 2013-05-29 | 2014-04-09 | 山东英特力光通信开发有限公司 | Unmanned plane |
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN103979105A (en) * | 2014-05-23 | 2014-08-13 | 深圳市艾特航空科技股份有限公司 | Vertical take-off and landing type variable-wing aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7861967B2 (en) * | 2008-04-25 | 2011-01-04 | Abe Karem | Aircraft with integrated lift and propulsion system |
-
2015
- 2015-04-24 CN CN201510197632.6A patent/CN104743112B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8371520B2 (en) * | 2009-07-31 | 2013-02-12 | William Craig Easter | Rapidly convertible hybrid aircraft and manufacturing method |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| CN203528810U (en) * | 2013-05-29 | 2014-04-09 | 山东英特力光通信开发有限公司 | Unmanned plane |
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN103979105A (en) * | 2014-05-23 | 2014-08-13 | 深圳市艾特航空科技股份有限公司 | Vertical take-off and landing type variable-wing aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104743112A (en) | 2015-07-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104743112B (en) | Novel tilt wing aircraft | |
| CN105775117B (en) | A kind of helicopter of VTOL horizontal flight and its application | |
| CA2947974C (en) | Vtol aircraft | |
| CN103043212B (en) | The composite aircraft that fixed-wing forms with electronic many rotors | |
| RU180474U1 (en) | Vertical takeoff and landing airplane | |
| CN202728575U (en) | Composite aircraft with fixed wing and electric multi-rotor-wing combined | |
| CN108082466A (en) | A kind of tilting duct connection wing layout vertically taking off and landing flyer | |
| CN202728574U (en) | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function | |
| CN202011472U (en) | Tilting duct unmanned aerial vehicle | |
| CN108001679A (en) | Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN108639328A (en) | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone | |
| CN102514712A (en) | Vertical take-off and landing aircraft | |
| CN103332293A (en) | Tilting double-duct subminiature unmanned plane | |
| CN113212753A (en) | Imitative dragonfly multi-mode conversion microminiature unmanned aerial vehicle of upset airfoil | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN106915459A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN105818980A (en) | Novel large-lift-force vertical take-off and landing aircraft | |
| CN106828918B (en) | Three-wing-surface vertical take-off and landing aircraft | |
| CN102897319A (en) | Fuselage variant type vertical take off and landing aircraft | |
| CN205738073U (en) | A kind of helicopter of VTOL horizontal flight | |
| CN106697282A (en) | Duct type tilting aircraft with vertical take-off and landing functions | |
| CN105905295A (en) | Vertical take-off and landing fixed wing aircraft | |
| CN108725773A (en) | A kind of unmanned transporter |
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 |