CN104743112A - Novel tilt wing aircraft - Google Patents
Novel tilt wing aircraft Download PDFInfo
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- CN104743112A CN104743112A CN201510197632.6A CN201510197632A CN104743112A CN 104743112 A CN104743112 A CN 104743112A CN 201510197632 A CN201510197632 A CN 201510197632A CN 104743112 A CN104743112 A CN 104743112A
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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 a kind ofly provides power based on the non-bending moment screw propeller of diaxon, there are vertical takeoff and landing and fixed-wing two kinds of patterns, and the aircraft of offline mode switching can be carried out as required by the mode of vert movable wing and screw propeller power system fixed thereon thereof, be specifically related to a kind of novel tilt wing aircraft.
Background technology
The birth of vertical takeoff and landing technology is mainly because the deficiency of aircraft rolling start mode, and the performance particularly in all previous war, allows the vertical takeoff and landing of aircraft enter the sight line of people.The war such as World War II and Mideast Asian war has directly allowed people experience to the attack on enemy airport needs the weak point of the sliding race formula aircraft of runway, and cold war is then the catalyst of vertical takeoff and landing technology.In five sixties after World War II, under the shade very likely breaking out nuclear war, fears are entertained that there is the situation that general nuclear warfare damages airport, conventional airplane cannot be set out, so expedited the emergence of the vertical takeoff and landing technology of fixed wing aircraft.The dependence that vertical take-off and landing aircraft (VTOL aircraft) reduces or substantially broken away from runway, only need very little level land just can rise sheer from level ground and vertical landing, so aircraft can decentralized configuration in war, be convenient to launch an attack flexibly, shift and pretend hidden, not easily found by enemy, the attendance rate also significantly improves, and has very high emergentness to the strike of enemy, substantially increases the battlefield survival rate of aircraft.In addition, the aircraft with vertical takeoff and landing ability does not need special airport and runway, eliminate expensive airport construction expense, bird need not be driven, also can in landing under bad weather condition, benefit is too many, reduces use cost, so the vertical takeoff and landing of aircraft has become a direction of aviation development.
In twentieth century five sixties, the U.S., Canada and some European companies have competitively started one development helicopter and fixed wing aircraft advantage in the upsurge of tilting rotor machine of one.At first, many aeronautics experts place high hopes to this aircraft of development.But because the project organization of this aircraft is complicated, especially be difficult to for a long time make a breakthrough in the development to wing rotational structure and rotary nacelle structure, the accident of fatal crass when taking a flight test of adding occurs in succession, and therefore, many countries successively abandon development.
In 1972, Bell Co. just received United States Army and the American National space flight and aviation office contract about common development XV-15 tiltrotor.1981, the U.S. succeeded in developing practical tiltrotor on the basis of XV-15, and in January, 1985, it was V-22 " osprey " by definite designation.As a kind of tiltrotor, the fuselage of V-22 " osprey ", wing and common fixed wing aircraft basic simlarity, but its airscrew engine being positioned at wing two ends but can be rotated up and down.When airscrew engine forwards plumbness to from horizontality, V-22 " osprey " just can realize vertical takeoff and landing and hovering as helicopter, when airscrew engine is in horizontality, just can gives one, aircraft pulling force forward, make it can fly as fixed wing aircraft.
Of course, " osprey " neither be impeccable.First shortcoming is exactly technical sophistication, operating difficulties, has accident to occur time so far also.Second shortcoming is exactly that pneumatic efficiency is lower.Due under vertical takeoff and landing state, the downwash flow that rotor produces is subject to the stop of wing, reduces propeller efficiency.
In recent years, many producers can not equal at a high speed the shortcoming flown for helicopter, have employed form helicopter and fixed-wing two kinds of aircraft layouts combined, and being solved by the double dynamical way of output can vertical takeoff and landing, can equal at a high speed the problem flown again.Install at its afterbody and advance oar.When needs advance at utmost speed time, the propelling oar opening its afterbody with this to obtain high-speed flight.But be subject to the impact of self configuration, there will be lifting airscrew parts when putting down and fly at a high speed and produce very large resistance, make its flying speed, voyage etc. be subject to larger restriction.In addition, the aircrafts such as sparrow hawk formula, F35 also can realize the flight of two kinds of patterns, but due to the very high reason of its complex structure, cost, all cannot be used for the design of unmanned plane.
Also the research of this kind of type is being actively developed, as " swift " YY-1 short distance/VUAV of group company of Qingan County of Air China in China.What adopt is two and is arranged in the main screw together verted on wing and with wing, and the flight attitude that the auxiliary propeller being arranged in tail position realizes aircraft vertical landing pattern jointly controls.But this aircraft its auxiliary power unit when transferring fixed-wing pattern to is not only inoperative, also can produces resistance, increasing the weight of full machine, virtually adding fuel oil consumption, thus shorten the voyage of aircraft.
Identical with it, Chinese Helicopter " blue whale " unmanned plane, adopt four axle propeller arrangements, the target of double mode flight can be realized.But to fly required pulling force much smaller than vertical takeoff and landing be required pulling force due to flat, therefore, substantially without the need to the power of rear row's screw propeller, and flat when flying after arrange the interference in air flow that screw propeller is subject to front-seat rotor, efficiency reduces greatly, even becomes burden.
For the aircraft that can realize again vertical takeoff and landing mainly four axles, six axles, the eight axle aircraft etc. of present stage Technical comparing maturation.These aircraft can be all relatively good in manipulation and stability.But mostly there is voyage short, as fixed-wing mode, can not equal with higher speed fly, efficiency is low etc. shortcoming.
Summary of the invention
The invention provides one can vertical takeoff and landing, hovering as helicopter, can put down to fixed wing aircraft the same high speed again and fly, also can switch between two kinds of patterns, the novel tilt wing aircraft of power is provided by non-bending moment twin screw, it is simple that it has structure, control stable, the advantages such as manoevreability is good.
The present invention is achieved like this, and a kind of novel tilt wing aircraft, mainly comprises: movable wing, fixed wing, fuselage, flaperon, horizontal tail, vertical fin, elevating rudder, yaw rudder, propeller system, tail supporting rod and alighting gear; It is characterized in that: fixed wing is connected to fuselage middle and upper part, a movable wing is respectively had for left and right two ends outside the fixed wing of fuselage symmetry, propeller system is fixed on movable wing, movable wing and propeller system vert by the steering wheel effector of wing inside, movable wing rear portion is provided with flaperon, horizontal tail is connected with fuselage by tail supporting rod with vertical fin, and horizontal tail and vertical fin rear portion are respectively equipped with elevating rudder and yaw rudder, and fuselage has alighting gear.Under vertical takeoff and landing and floating state, realized the actions such as the vertical takeoff and landing of aircraft, spot hover and movable, rotation by the cooperation control of propeller system, movable wing and flaperon; Flat fly state under, movable wing section is fixed, and jointly provides lift with fixed wing part, has flaperon in the same way or incorgruous deflection its lift of control and crosswise movement.
Novel tilt wing aircraft of the present invention, under vertical takeoff and landing state, controls the flight attitude of aircraft by propeller system, movable wing and flaperon combined action.
Movable wing and fixed wing can combine and form complete wing, for aircraft provides lift under the pulling force effect that propeller system provides under putting down and flying state by novel tilt wing aircraft of the present invention.
Novel tilt wing aircraft of the present invention in offline mode switching process, by movable wing and fixed wing combined action.
Aircraft of the present invention flies control plate program development: this vertical take-off and landing aircraft (VTOL aircraft) has three kinds of offline mode, be namely divided into vertical takeoff and landing pattern, transition before fly at a slow speed pattern and fast before fly pattern.Due to the difference of offline mode, often need to open mode passageway needs when different offline mode or closedown etc.Based in this, being necessary for each passage can select.So the feature originally flying control program does not have fixing offline mode, each passage flying to control plate can be set to arbitrary output or mixing output.
Effect of the present invention is: can realize vertical takeoff and landing, hovering and fixed-wing mode flight.Have better commonality than traditional diaxon fixed wing aircraft, more traditional three axles, four axles, six axle aircrafts save fuel oil more.Have good manoevreability and flying speed, this is significant to improving the range of use of aircraft, the present invention be simultaneously equipped with independent development fly control plate, such that the safety performance of aircraft is higher, stability better, be also applicable to producing in enormous quantities.It is many that aircraft has function, and range of use is wide, and structure is simple, the features such as cost is low, can be widely used in the every field such as aerophotography, highway patrol, the condition of a disaster prospecting and military investigation.
Accompanying drawing explanation
Fig. 1 is structural representation one of the present invention.
Fig. 2 is structural representation two of the present invention.
1, movable wing, 2, fixed wing, 3, fuselage, 4, flaperon, 5, horizontal tail, 6, vertical fin, 7, elevating rudder, 8, yaw rudder, 9, propeller system, 10. tail supporting rod, 11, alighting gear.
Detailed description of the invention
As shown in Figure 1 and Figure 2, the present invention implements like this, a kind of novel tilt wing aircraft, and it comprises aircaft configuration, aircraft connecting mode, flight control system three part composition.Described aircaft configuration comprises fuselage 1, movable wing 2, fixed wing 3, fuselage 4, flaperon 5, horizontal tail 6, vertical fin 7, elevating rudder 8, yaw rudder 9, non-bending moment propeller system 10, tail supporting rod 11, alighting gear; It is characterized in that: fixed wing 2 is connected to fuselage 3 middle and upper part, respectively have outside fixed wing 2 for fuselage 3 symmetry with movable wing 1, propeller system 9 is fixed on movable wing, movable wing 1 and propeller system 9 vert by the steering wheel effector of wing inside, movable wing 1 rear portion is provided with flaperon 4, horizontal tail 5 is connected with fuselage 3 by tail supporting rod 10 with vertical fin 6, and horizontal tail 5 and vertical fin 6 rear portion are respectively equipped with elevating rudder 7 and yaw rudder 8, and fuselage 3 has alighting gear 11.Under vertical takeoff and landing and floating state, realized the actions such as the vertical takeoff and landing of aircraft, spot hover and movable, rotation by the cooperation control of propeller system 9, movable wing 1 and flaperon 4; Flat fly state under, movable wing 1 partial fixing, provides lift jointly with fixed wing 2 part, has flaperon in the same way or incorgruous deflection its lift of control and crosswise movement.
This aircraft forms primarily of aircaft configuration, aircraft connecting mode and flight control system.Aircraft wing is divided into fixing and movable two parts, and when vertical takeoff and landing and hovering, the non-bending moment propeller system that namely movable wing is fixed thereon is tilted to plumbness along rotating shaft, has screw propeller to provide lift; Flat when flying, movable wing and propeller system rotate back into fixed-wing position, and normal arrangement fixed wing aircraft flies equally; Translate phase is controlled by the flight control system of self-service development.
The present invention specifically comprises three kinds of offline mode: vertical takeoff and landing and hover mode, fixed-wing pattern and transition mode.
When being in vertical takeoff and landing and hover mode, by the cooperation control of non-bending moment screw propeller power system 9, movable wing 1 and flaperon 4, under the wing tilt torque effect that wing center of turn, center of gravity and flaperon produce, realize the vertical takeoff and landing of aircraft, spot hover and move forward and backward, realizing pivot stud and rolling etc. by the differential of two motors.
Be in flat when flying state, movable wing 1 rotates back into the position identical with fixed wing 2, form the distribution form the same with fixed wing aircraft, under the pulling force effect of propeller system 9, jointly provide lift with fixed wing 2, by flaperon in the same way or incorgruous deflection control its lift and roll action.
When being in excessive pattern, lift is from all being provided by two non-bending moment propeller systems 9, progressively be transitioned into and provided by fixed wing 2 and movable wing 1, motor speed, aircraft flight speed and aerodynamic force are all in the middle of change, this one-phase, by being arranged in fuselage, the flight control system of autonomous Design realizes.
Claims (4)
1. a novel tilt wing aircraft, its structure mainly comprises: movable wing, fixed wing, fuselage, flaperon, horizontal tail, vertical fin, elevating rudder, yaw rudder, propeller system, tail supporting rod and alighting gear; It is characterized in that: fixed wing is connected to fuselage middle and upper part, a movable wing is respectively had for left and right two ends outside the fixed wing of fuselage symmetry, propeller system is fixed on movable wing, movable wing and propeller system vert by the steering wheel effector of wing inside, movable wing rear portion is provided with flaperon, horizontal tail is connected with fuselage by tail supporting rod with vertical fin, and horizontal tail and vertical fin rear portion are respectively equipped with elevating rudder and yaw rudder, and fuselage has alighting gear.
2. the novel tilt wing aircraft of one according to claim 1, is characterized in that: described novel tilt wing aircraft, under vertical takeoff and landing state, controls the flight attitude of aircraft by propeller system, movable wing and flaperon combined action.
3. the novel tilt wing aircraft of one according to claim 1, it is characterized in that: under described novel tilt wing aircraft is put down and flown state, movable wing section is fixed, and jointly provides lift with fixed wing part, have flaperon in the same way or incorgruous deflection control its lift and crosswise movement.
4. the novel tilt wing aircraft of one according to claim 1, it is characterized in that: described novel tilt wing aircraft is in offline mode switching process, lift, from all being provided by two non-bending moment propeller systems, is progressively transitioned into and is provided by fixed wing and movable wing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510197632.6A CN104743112B (en) | 2015-04-24 | 2015-04-24 | Novel tilt wing aircraft |
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| CN201510197632.6A CN104743112B (en) | 2015-04-24 | 2015-04-24 | Novel tilt wing aircraft |
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| CN104743112B CN104743112B (en) | 2017-04-12 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN105404310A (en) * | 2015-11-27 | 2016-03-16 | 深圳一电科技有限公司 | Unmanned plane flying control method and unmanned plane flying control device |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| 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 |
| 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 |
| CN106965928A (en) * | 2017-03-08 | 2017-07-21 | 贾杰 | The rotatable wing vertically taking off and landing flyer of multistage |
| CN107323650A (en) * | 2016-04-29 | 2017-11-07 | 杨双来 | Movable wing aircraft |
| CN107380427A (en) * | 2017-09-04 | 2017-11-24 | 陈超 | A kind of wing dual-purpose type verts wing unmanned plane |
| 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 |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN105404310A (en) * | 2015-11-27 | 2016-03-16 | 深圳一电科技有限公司 | Unmanned plane flying control method and unmanned plane flying control device |
| CN107323650A (en) * | 2016-04-29 | 2017-11-07 | 杨双来 | Movable wing aircraft |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| 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 |
| CN107380427A (en) * | 2017-09-04 | 2017-11-24 | 陈超 | A kind of wing dual-purpose type verts wing unmanned plane |
| 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 |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary 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 |
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