CN105667781A - Aircraft capable of changing layout between rotor wing and fixed wing - Google Patents
Aircraft capable of changing layout between rotor wing and fixed wing Download PDFInfo
- Publication number
- CN105667781A CN105667781A CN201610208061.6A CN201610208061A CN105667781A CN 105667781 A CN105667781 A CN 105667781A CN 201610208061 A CN201610208061 A CN 201610208061A CN 105667781 A CN105667781 A CN 105667781A
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- axis
- rotor
- 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.)
- Pending
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
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses an aircraft capable of changing layout between a rotor wing and a fixed wing. The aircraft capable of changing the layout between the rotor wing and the fixed wing comprises a fuselage, wings at the two sides, two wing shafts, a driving module and a transmission module, wherein the wings are symmetric airfoils which are provided with a control vane surface at the trailing edge and longitudinally symmetric, and a thrust device is arranged on the wings; the wings at the two sides are respectively connected with the fuselage by virtue of one wing shaft; one end of each wing shaft is fixedly connected with the wings or fuselage, and the other end of the corresponding wing shaft is connected with the driving module by virtue of the transmission module; and the driving module outputs torsion to the transmission module, the transmission module drives the wing shafts to rotate, so that the wings and the fuselage rotate relatively, and further the aircraft changes the layout between the rotor wing and the fixed wing. The aircraft disclosed by the invention has the advantages of a helicopter and a fixed wing aircraft at the same time, when in a fixed wing layout, cruising speed is high, when in a rotor wing layout, the aircraft can hover and vertically take off and land, taking-off and landing site requirement is low, and flying effect of the helicopter can be realized; and meanwhile, the aircraft still can normally vertically land when losing power.
Description
Technical field
The present invention relates to air line technical field, particularly relate to a kind of aircraft of variable layout between rotor and fixed-wing.
Background technology
In traditional field, vertically taking off and landing flyer is divided into two kinds, and the first is helicopter, the rotor at top produce lift and realize VTOL. During helicopter cruise, then the direction of pull changing rotor is motor-driven aloft; The second is VTOL aircraft (VTOL), and such aircraft carrys out VTOL by changing motor power direction (such as thrust becomes down forward), puts down and is produced lift by wing when flying, identical with fixed wing airplane.
The cruising speed of the first helicopter is relatively low, and under same engine power, load ratio fixed wing airplane is little.
The second VTOL aircraft (VTOL), represents aircraft for " sparrow hawk " formula fighter plane (HarrierJet) and osprey V-22 tiltrotor. In order to realize VTOL, both is all made that in structure and efficiency some are sacrificed. In the VTOL stage, wing does not play a role substantially, becomes useless load, aircraft causes extra burden, result in higher oil consumption rate. Although the propeller of this aircraft is through particular design, it is possible to take into account the requirement of VTOL, but result in aircraft at fixed-wing mission phase, the relative reduction of propulsive efficiency.
In addition, the control mode of helicopter and fixed-wing also has bigger difference.
Fixed wing airplane relies on the deflection up and down of rudder face, produces control power. And owing to the rudder face distance center of gravity of airplane has certain distance, just aircraft is created a moment, controls flight attitude with this.
The control mode of helicopter is more complicated. Helicopter static state hovering time, the change of rotor angle-of-attack be called always from: when the angle of attack is 0 °, rotor does not produce lift; When the angle of attack is more than or less than 0 °, the lift that rotor produces is directly proportional to the angle of attack, to rotor square being directly proportional around axle 3 rotary rpm.
During aircraft maneuvering flight, the change in angle of attack of rotor is called the feathering of rotor: assume aircraft forward flight, and rotor wing rotation is to time parallel with heading, and the angle of attack of two panels rotor is equal, and the lift of generation is also equal;When rotor continues half-twist, rotor is vertical with heading, and advancing blade (blade identical with the heading) angle of attack obtains minimum, and the lift of generation is also less; Retreating blade (blade contrary with the heading) angle of attack obtains maximum, and the lift of generation is also bigger.
When helicopter is motor-driven forward, in the whole process of rotor wing rotation, the angle of attack of blade is continually changing according to sinusoidal rule between minimum and maximum, thus create the deflection torque on a roll axle on board the aircraft, this deflection torque is under gyroscopic effect, delay 90 ° of effects on board the aircraft, the lift that the Plane of rotation (oar dish plane) at control two panels rotor place produces turns forward along pitch axis, construct a component forward, so that aircraft forward flight.
When aircraft is to other yaw maneuvers, control method is also similar.
In addition, the deflection up and down using trailing edge primary control surface replaces the change of rotor angle-of-attack, it is also possible to realize the control to oar dish plane, is equivalent to the camber changing rotor to change lift coefficient.
Summary of the invention
The technical problem to be solved is for defect involved in background technology, a kind of aircraft of variable layout between rotor and fixed-wing is provided, can in flight overall process, including, in takeoff phase, landing phases and cruising phase, arbitrarily changing layout between rotor and fixed-wing.
The present invention solves above-mentioned technical problem by the following technical solutions:
A kind of aircraft of variable layout between rotor and fixed-wing, comprises fuselage, both sides wing, two wing axis, drives module and transmission module;
Described wing is the laterally zygomorphic symmetrical airfoil that trailing edge is provided with primary control surface, and wing arranges thrust device, and the thrust line of thrust device is positioned at the plane of symmetry of wing;
Described both sides wing is connected with described fuselage respectively through a wing axis;
Described wing axis one end is fixedly linked with wing or fuselage, and the other end is connected with driving module by transmission module;
Described driving module gives described transmission module for outputting torsion;
Described transmission module is for rotating according to the dynamic wing axis of the torque band being subject to so that relatively rotates between wing and fuselage, and then makes aircraft change layout between rotor and fixed-wing.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described driving module comprises a steering wheel, and described transmission module comprises first to third hand tap gear;
Described steering wheel is fixedly installed in fuselage, and its output shaft and described first bevel gear are fixedly linked;
Described second bevel gear, respectively and two wing axis of third hand tap gear one end be fixedly linked;
The other end of described two wing axis is fixedly linked with the wing of its correspondence respectively;
Described first bevel gear engages with the second bevel gear, third hand tap gear simultaneously.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described driving module comprises two steering wheels, and described transmission module comprises two shaft couplings;
Said two steering wheel is separately positioned in two wings;
Said two wing axis one end and fuselage are fixedly linked, and the other end is connected each through the outfan of the steering wheel in a corresponding wing of shaft coupling.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described thrust device comprises propeller and electromotor.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described thrust device adopts any one in piston type ducted fan electromotor, jet engine, turbofan, blade tip jet engine.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described fuselage is provided with some bearings rotated for wing axis.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, in said two wing, it is equipped with some bearings rotated for wing axis.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described wing is solid construction, and its wing root place has groove;
The one end of the wing axis that described wing is corresponding is stretched into groove and is connected in groove;
Described wing is additionally provided with the cover plate for covering groove.
As a kind of further prioritization scheme of the aircraft of variable layout between rotor and fixed-wing of the present invention, described wing is thin-shell type structure, is provided with rib, root is provided with the fixing seat of the wing axis for fixing wing axis inside wing shell;
The wing axis that described wing is corresponding fixes seat, airfoil root and rib through wing axis, is fixed with wing by the fixing seat of wing axis.
The present invention adopts above technical scheme compared with prior art, has following technical effect that
1. the advantage having helicopter and fixed wing airplane concurrently, it is achieved that a tractor serves several purposes, an airplane can meet different aerial missions;
2. during fixed-wing layout, cruising speed is fast, can hover and VTOL during rotor-hub configuration, requires low to landing site, and can realize the flight effect of helicopter;
3. no matter being fixed-wing layout or rotor-hub configuration, wing is all in duty, and useless parts are few, and flight efficiency is high, and cruising time is long;
4., when running out of steam, can still rely on spin effect, regular descent.
Accompanying drawing explanation
Fig. 1 is the fixed-wing schematic layout pattern of aircraft in the present invention;
Fig. 2 is the rotor-hub configuration schematic diagram of aircraft in the present invention;
Fig. 3 is that in the present invention, wing is structural representation during solid construction;
Fig. 4 is that in the present invention, wing is structural representation during thin-shell type structure;
Fig. 5 is present invention explosive view of fuselage inner body when driving module in fuselage;
Fig. 6 is present invention general assembly drawing of fuselage inner body when driving module in fuselage;
Fig. 7 is bevel pinion axonometric drawing;
Fig. 8 is bevel gear wheel axonometric drawing;
Fig. 9 is present invention explosive view of fuselage inner body when driving module in wing;
Figure 10 is present invention general assembly drawing of fuselage inner body when driving module in wing;
Figure 11 shaft coupling axonometric drawing;
Figure 12 is the fixing seat axonometric drawing of wing axis;
Figure 13 is the fixed-wing schematic diagram with angle of sweep;
Figure 14 is the state after the fixed-wing with angle of sweep becomes rotor;
Figure 15 is the normal arrangement fixed-wing schematic diagram with fuselage;
Figure 16 is the state after the normal arrangement fixed-wing with fuselage becomes rotor.
In figure, 01-X axle, 02-Y axle, 03-Z axle, 04-Z' axle, 05-X' axle, 06-wing, 07-electromotor, 08-propeller, 09-primary control surface, 10-wing axis hole, 11-groove, 12-wing axis, 13-cover plate, 14-rib, seat fixed by 15-wing axis, seat screw fixed by 16-wing axis, seat elastic joint fixed by 17-wing axis, seat lock screw fixed by 18-wing axis, 19-fuselage, 20-steering wheel, 21-bevel pinion, 22-bevel gear wheel, 23-steering wheel mounting seat, 24-steering wheel installs screw, 25-bevel pinion spline, 26-wing axis snap ring, 27-Bearing washer, 28-wing axis snap ring elastic joint, 29-wing axis snap ring groove, 30-wing axis snap ring screw, 31-fuselage bulkhead, 32-outer shaft bearing bore, 33-inner bearing hole, 34-outward flange bearing, 35-inner flange bearing, 36-fuselage axis hole, 37-wing axis fuselage fixes seat, 38-wing axis fuselage fixes seat screw, 39-wing axis fuselage fixes seat elastic joint, 40-wing axis fuselage fixes seat lock screw, 41-inner bearing, 42-outer bearing, 43-gasket ring, 44-shaft coupling, 45-shaft coupling elastic joint, 46-shaft coupling groove, 47-shaft coupling lock screw, 48-shaft coupling spline, 49-port wing sweepback rotation axis, 50-starboard wing sweepback rotation axis, 51-port wing rotation axis, 52-starboard wing rotation axis, 53-rotating ring.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme is described in further detail:
The invention discloses a kind of aircraft of variable layout between rotor and fixed-wing, comprise fuselage 19, both sides wing 06, wing axis 10, drive module and transmission module;
Described wing is the laterally zygomorphic symmetrical airfoil that trailing edge is provided with primary control surface, and wing arranges thrust device, and the thrust line of thrust device is positioned at the plane of symmetry of wing;
Said two wing 06 is connected with described fuselage 19 respectively through a wing axis 10;
Described wing axis 10 one end is fixedly linked with wing 06 or fuselage 19, and the other end is connected with driving module by transmission module;
Described driving module gives described transmission module for outputting torsion;
Described transmission module is for rotating according to the dynamic wing axis 10 of the torque band being subject to so that rotates between wing 06 and fuselage 19, and then makes aircraft change layout between rotor and fixed-wing.
Described wing axis axis can be parallel with aircraft roll axle, it is also possible to forms an angle with roll axle.
Fig. 1 is the fixed-wing schematic layout pattern of aircraft in the present invention, and roll axle (X-axis) 01, pitch axis (Y-axis) 02 and course axle (Z axis) 03 form body axis system. In the present invention, port wing is identical with the frame for movement of starboard wing, it is possible to right and left mutually changing. Now illustrate for wherein side wing.
Wing 06 is laterally zygomorphic symmetrical airfoil, it is therefore an objective to after ensureing that fixed-wing layout changes into rotor-hub configuration, and the aerodynamic force of two wing 06 generations is consistent.
Wing 06 is provided with electromotor 07, drives propeller 08, provide thrust for aircraft. The line of pull of propeller 08 is in the wing plane of symmetry, to ensure wing not to be produced the turning moment of pitch orientation. Aircraft can be controlled by the primary control surface 09 of wing 06 trailing edge. Both sides wing 06 is connected with the fuselage 19 of central authorities. Aircraft does not have vertical tail, relies on traditional drag rudder or the differential rotation of two propellers to produce Heading control moment.
Electromotor 07 can be piston type airscrew engine, whirlpool paddle electromotor, electric propeller motor.
Propeller 08 and electromotor 07 on wing 06 can also be replaced as all devices that can produce thrust such as piston type ducted fan electromotor, jet engine, turbofan, blade tip jet engine.
Fig. 2 is the rotor-hub configuration schematic diagram of aircraft in the present invention, port wing and starboard wing are under the effect driving module, and respectively after different direction half-twists, aircraft is overall under air force and action of gravity, it is rotated down 90 °, completes by fixed-wing layout to the conversion of rotor-hub configuration. Course axle (Z' axle) 04 when roll axle (X-axis) 01 during fixed-wing layout and course axle (Z axis) 03 become rotor-hub configuration respectively and roll axle (X' axle) 05, aircraft pitch axis (Y-axis) 02 remains unchanged.
The present invention drives the driving module that wing rotates can be arranged in fuselage 19, it is also possible to be arranged in wing 06.
When drive module setting is in fuselage 19, aircraft wing 06 can select solid construction, it is also possible to selects thin-shell type structure.
As it is shown on figure 3, when aircraft wing selects solid construction, the wing root place of wing 06 has groove 11, and the length of wing axis 12 is more than the length of groove 11. Groove 11 is stretched in one end of wing axis 12, uses glue to be connected in groove 11 by wing axis 12 simultaneously, and fills out breach with cover plate 13.Wing axis 12 other end stretches out wing 06.
As shown in Figure 4, when wing is thin-shell type structure, wing 06 shell is internally provided with rib 14. Wing axis 12 is through the fixing seat 15 of wing axis, also cross the wing axis hole 10 on airfoil root and rib 14.
The fixing seat 15 of wing axis is fixed seat screw 16 by wing axis and is fixed on airfoil root. Fixing seat 15 side opening of wing axis has wing axis to fix seat elastic joint 17, it is possible to by screwing the fixing seat lock screw 18 of wing axis, lock wing axis 12, is connected as a single entity by fixing to wing 06, wing axis 12 and wing axis seat 15.
Drive module setting layout in fuselage 19 as shown in Figure 5 and Figure 6, in fuselage 19, equipped with steering wheel 20, drives module as wing. Drive mechanism is simultaneously engaged two bevel gear wheels 22 by a bevel pinion 21 and forms. The axis of bevel pinion 21 is parallel with aircraft roll axle (X-axis) 01; The dead in line of the axis of bevel gear wheel 22 and wing axis 12.
The first bevel gear that bevel pinion 21 is that is mentioned above, second, third bevel gear that two bevel gear wheels 22 are that is mentioned above.
Fuselage 19 is internal is provided with steering wheel mounting seat 23.
Steering wheel 20 is installed screw 24 by steering wheel and is arranged in steering wheel mounting seat 23, thus completing the steering wheel 20 location on fuselage 19 and fastening.
As it is shown in fig. 7, bevel pinion 21 is arranged on the output shaft of steering wheel 20. There is bevel pinion spline 25 in the axis hole of bevel pinion 21, match with the output shaft of steering wheel 20.
Bevel gear wheel 22 engages with bevel pinion 21, and as shown in Figure 8, wing axis snap ring 26 is then connected as a single entity with the back side of bevel gear wheel 22, and Bearing washer 27 and wing axis snap ring 26 are connected as a single entity. Having wing axis snap ring elastic joint 28 on wing axis snap ring 26 and Bearing washer 27, the distribution of wing axis snap ring 26 circumferential surface has wing axis snap ring groove 29. By screwing the wing axis snap ring screw 30 in wing axis snap ring groove 29, it is possible to wing axis 12 is fixed in wing axis snap ring 26.
The left surface of fuselage 19 and right flank, the axis place of corresponding bevel gear wheel 22, have outer shaft bearing bore 32. In addition, on the left side and right side fuselage bulkhead 31 of bevel gear wheel 22, inner bearing hole 33 is also had.
It is separately installed with flange bearing in the dead eye of four, fuselage 19 both sides. Outward flange bearing 34 in outer shaft bearing bore 32, flange is outside fuselage 19; Inner flange bearing 35 in inner bearing hole 33, flange is inside fuselage 19.
Wing axis 08 stretches out one end of wing, is sequentially inserted into outward flange bearing 34 and inner flange bearing 35, is inserted in the Bearing washer 27 that is integrally forming with bevel gear wheel 22 and wing axis snap ring 26. Bearing washer 27 has certain thickness, just can be in close contact with the inner ring of inner flange bearing 35. Screw the wing axis snap ring screw 30 on wing axis snap ring 26, allow wing axis snap ring elastic joint 28 shrink, wing axis 08 is clamped in wing axis snap ring 26, complete the connection of wing 06 and fuselage 19.
The bevel pinion 21 that steering wheel 20 drives is driving gear, and after completing the connection of wing and fuselage 19, bevel gear wheel 22 is driven gear, should keep good engagement with bevel pinion 21.
When aircraft is deformed into rotor-hub configuration, steering wheel 20 is started working, and drives two panels wing rotating around aircraft pitch axis (Y-axis) 02 half-twist. Now two electromotors 07 of wing work in the opposite direction, and the moment that two propellers 08 produce drives overall course axle (Z' axle) 04 high speed rotating when rotor-hub configuration aloft of aircraft;Along with rotor is around the rotation of course axle (Z' axle) 04, steering wheel 20 constantly drives wing to rotate up and down in scope by a small margin, to allow rotor produce angle with air current flow direction, to provide rotor at ensuing lift required in-flight and operating torque.
When drive module setting is in wing 06, as shown in Figure 9 and Figure 10, wing axis 12, through the fuselage axis hole 36 on fuselage 19, extend in the fixing seat 37 of the wing axis fuselage within fuselage 19. The fixing seat 37 of fixing 38 the wing axis fuselages of seat screw of wing axis fuselage is fixed with one with fuselage 19, as shown in figure 12, the fixing seat 37 of wing axis fuselage also has the fixing seat elastic joint 39 of wing axis fuselage, after wing axis 12 inserts the fixing seat 37 of wing axis fuselage, screw the fixing seat lock screw 40 of wing axis fuselage, fixing to wing axis 12, fuselage 19 and wing axis fuselage seat 37 is fixed together.
Wing 06 is internally installed inner bearing 41 and outer bearing 42. Steering wheel 20 is installed screw 24 by steering wheel and is fixed in wing.
Wing axis 12 stretches out one end of fuselage and is cased with gasket ring 43, and inserts in inner bearing 41 and outer bearing 42. Gasket ring 43 side contacts with fuselage 19, and gasket ring 43 opposite side contacts with the inner ring of outer bearing 42. By adjusting the axial width of gasket ring 43, it is possible to produce gap between wing 06 wing root position and fuselage 19, it is prevented that the direct friction of wing 06 and fuselage 19.
Wing axis 12 inserts shaft coupling 44 at the least significant end within wing 06. As shown in figure 11, shaft coupling 44 has shaft coupling elastic joint 45, and the circumferential surface of shaft coupling 44 has shaft coupling groove 46, screws the shaft coupling lock screw 47 in shaft coupling groove 46, it is possible to shaft coupling 44 and wing axis 12 are fixed together. Shaft coupling 44 opposite side has shaft coupling spline 48, and the outfan of steering wheel 20 is connected with shaft coupling 44 by shaft coupling spline 48, delivers torque to wing axis 12, and then controls the anglec of rotation between wing 06 and fuselage 19.
As shown in Figure 13 and Figure 14, when aircraft wing 06 is with angle of sweep, its port wing sweepback rotation axis 49 and starboard wing sweepback rotation axis 50 are not arranged on the same straight line be, and also discord aircraft pitch axis 02 overlaps.
As shown in Figure 15 and Figure 16, when aircraft fuselage is with empennage, its port wing rotation axis 51 and starboard wing rotation axis 52 are not arranged on the same straight line be, and also discord aircraft pitch axis 02 overlaps. Aircraft wing 06 is connected with fuselage by rotating ring 53. When being under rotor mode, wing 06 rotates together with rotating ring 53, and fuselage 19 then keeps fixing with course axle (Z' axle) 04, can't rotate together along with wing 06.
During rotor-hub configuration, the flight theory of aircraft is similar with conventional helicopters with control method, need to drive at any time rotor, along with rotor changes around the rotation of course axle (Z' axle) 04, rotation is constantly adjusted within small angle range, to meet the requirement of flight vehicle aerodynamic control aspect, that is: rotor-blade airfoil is allowed to produce angle (angle of attack) with air current flow direction, to provide rotor at ensuing lift required in-flight and operating torque, namely always from the control with feathering.
The watt level of electromotor output determines the rotating speed that aircraft rotates around course axle (Z' axle) 04.
Those skilled in the art of the present technique it is understood that unless otherwise defined, all terms used herein (include technical term and scientific terminology) and have with the those of ordinary skill in art of the present invention be commonly understood by identical meaning.Should also be understood that in such as general dictionary, those terms of definition should be understood that have the meaning consistent with the meaning in the context of prior art, and unless defined as here, will not explain by idealization or excessively formal implication.
Above-described detailed description of the invention; the purpose of the present invention, technical scheme and beneficial effect have been further described; it is it should be understood that; the foregoing is only the specific embodiment of the present invention; it is not limited to the present invention; all within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (9)
1. the aircraft of a variable layout between rotor and fixed-wing, it is characterised in that comprise fuselage, both sides wing, two wing axis, drive module and transmission module;
Described wing is the laterally zygomorphic symmetrical airfoil that trailing edge is provided with primary control surface, and wing arranges thrust device, and the thrust line of thrust device is positioned at the plane of symmetry of wing;
Described both sides wing is connected with described fuselage respectively through a wing axis;
Described wing axis one end is fixedly linked with wing or fuselage, and the other end is connected with driving module by transmission module;
Described driving module gives described transmission module for outputting torsion;
Described transmission module is for rotating according to the dynamic wing axis of the torque band being subject to so that relatively rotates between wing and fuselage, and then makes aircraft change layout between rotor and fixed-wing.
2. the aircraft of variable layout between rotor and fixed-wing according to claim 1, it is characterised in that described driving module comprises a steering wheel, described transmission module comprises first to third hand tap gear;
Described steering wheel is fixedly installed in fuselage, and its output shaft and described first bevel gear are fixedly linked;
Described second bevel gear, respectively and two wing axis of third hand tap gear one end be fixedly linked;
The other end of described two wing axis is fixedly linked with the wing of its correspondence respectively;
Described first bevel gear engages with the second bevel gear, third hand tap gear simultaneously.
3. the aircraft of variable layout between rotor and fixed-wing according to claim 1, it is characterised in that described driving module comprises two steering wheels, and described transmission module comprises two shaft couplings;
Said two steering wheel is separately positioned in two wings;
Said two wing axis one end and fuselage are fixedly linked, and the other end is connected each through the outfan of the steering wheel in a corresponding wing of shaft coupling.
4. the aircraft of variable layout between rotor and fixed-wing according to claim 1, it is characterised in that described thrust device comprises propeller and electromotor.
5. the aircraft of variable layout between rotor and fixed-wing according to claim 1, it is characterized in that, described thrust device adopts any one in piston type ducted fan electromotor, jet engine, turbofan, blade tip jet engine.
6. the aircraft of variable layout between rotor and fixed-wing according to claim 2, it is characterised in that described fuselage is provided with some bearings rotated for wing axis.
7. the aircraft of variable layout between rotor and fixed-wing according to claim 3, it is characterised in that be equipped with some bearings rotated for wing axis in said two wing.
8. the aircraft of variable layout between rotor and fixed-wing according to claim 2, it is characterised in that described wing is solid construction, and its wing root place has groove;
The one end of the wing axis that described wing is corresponding is stretched into groove and is connected in groove;
Described wing is additionally provided with the cover plate for covering groove.
9. the aircraft of variable layout between rotor and fixed-wing according to claim 2, it is characterised in that described wing is thin-shell type structure, is provided with rib, root is provided with the fixing seat of the wing axis for fixing wing axis inside wing shell;
The wing axis that described wing is corresponding fixes seat, airfoil root and rib through wing axis, is fixed with wing by the fixing seat of wing axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610208061.6A CN105667781A (en) | 2016-04-06 | 2016-04-06 | Aircraft capable of changing layout between rotor wing and fixed wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610208061.6A CN105667781A (en) | 2016-04-06 | 2016-04-06 | Aircraft capable of changing layout between rotor wing and fixed wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105667781A true CN105667781A (en) | 2016-06-15 |
Family
ID=56308467
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610208061.6A Pending CN105667781A (en) | 2016-04-06 | 2016-04-06 | Aircraft capable of changing layout between rotor wing and fixed wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105667781A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672786A (en) * | 2017-11-02 | 2018-02-09 | 中国科学院、水利部成都山地灾害与环境研究所 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
| CN108238232A (en) * | 2016-12-27 | 2018-07-03 | 韩国科学技术院 | It can take off vertically and land, vertically and horizontally fly and generate the aircraft of energy in the air |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN109956024A (en) * | 2017-12-25 | 2019-07-02 | 内蒙古宝亮信息技术股份有限公司 | A kind of aircraft |
| CN110371287A (en) * | 2019-07-05 | 2019-10-25 | 深圳市道通智能航空技术有限公司 | Vert wing mechanism and tilting rotor wing unmanned aerial vehicle |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| 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 |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2132289C1 (en) * | 1996-10-24 | 1999-06-27 | Клименко Алексей Геннадьевич | Vertical take-off and landing flying vehicle |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN203005747U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor aircraft |
| CN103180208A (en) * | 2010-09-17 | 2013-06-26 | 约翰内斯·赖特 | Tilt wing rotor vtol |
| CN203714177U (en) * | 2014-02-21 | 2014-07-16 | 刘浩 | Tandem tilt wing aircraft |
| CN105000176A (en) * | 2015-08-10 | 2015-10-28 | 徐金鹏 | Jet aircraft |
| CN204895858U (en) * | 2015-05-07 | 2015-12-23 | 张庆伟 | Aerial variant stationary vane four -axis unmanned aerial vehicle of VTOL |
| CN205633041U (en) * | 2016-04-06 | 2016-10-12 | 南京航空航天大学 | Changeable aircraft of overall arrangement between rotor and stationary vane |
-
2016
- 2016-04-06 CN CN201610208061.6A patent/CN105667781A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2132289C1 (en) * | 1996-10-24 | 1999-06-27 | Клименко Алексей Геннадьевич | Vertical take-off and landing flying vehicle |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN103180208A (en) * | 2010-09-17 | 2013-06-26 | 约翰内斯·赖特 | Tilt wing rotor vtol |
| CN203005747U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor aircraft |
| CN203714177U (en) * | 2014-02-21 | 2014-07-16 | 刘浩 | Tandem tilt wing aircraft |
| CN204895858U (en) * | 2015-05-07 | 2015-12-23 | 张庆伟 | Aerial variant stationary vane four -axis unmanned aerial vehicle of VTOL |
| CN105000176A (en) * | 2015-08-10 | 2015-10-28 | 徐金鹏 | Jet aircraft |
| CN205633041U (en) * | 2016-04-06 | 2016-10-12 | 南京航空航天大学 | Changeable aircraft of overall arrangement between rotor and stationary vane |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| 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 |
| CN108238232A (en) * | 2016-12-27 | 2018-07-03 | 韩国科学技术院 | It can take off vertically and land, vertically and horizontally fly and generate the aircraft of energy in the air |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN107672786A (en) * | 2017-11-02 | 2018-02-09 | 中国科学院、水利部成都山地灾害与环境研究所 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
| CN109956024A (en) * | 2017-12-25 | 2019-07-02 | 内蒙古宝亮信息技术股份有限公司 | A kind of aircraft |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN109533304B (en) * | 2018-10-19 | 2021-09-17 | 上海交通大学 | Single-wing aircraft with rotor wing and fixed wing flight modes and mode switching method |
| CN110371287A (en) * | 2019-07-05 | 2019-10-25 | 深圳市道通智能航空技术有限公司 | Vert wing mechanism and tilting rotor wing unmanned aerial vehicle |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111268120B (en) * | 2020-03-11 | 2022-03-22 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105667781A (en) | Aircraft capable of changing layout between rotor wing and fixed wing | |
| CN205633041U (en) | Changeable aircraft of overall arrangement between rotor and stationary vane | |
| US7918415B2 (en) | Convertible aircraft operating method | |
| US8256704B2 (en) | Vertical/short take-off and landing aircraft | |
| AU2013360005B2 (en) | Aircraft and methods for operating an aircraft | |
| CN202728576U (en) | Transformable composite aircraft formed by fixed wing and electric multi-propeller | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| CN202728574U (en) | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function | |
| AU2013360005A1 (en) | Aircraft and methods for operating an aircraft | |
| CN103043212A (en) | Combined aircraft composed of fixed wing and electric multi-rotor wing | |
| US20180281942A1 (en) | Flying wing vertical take-off and landing aircraft | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN105000174A (en) | Tiltrotor mixed multi-state aircraft with operational control surfaces | |
| CN107745811A (en) | A kind of VTOL becomes rotor wing unmanned aerial vehicle | |
| CN109896002B (en) | Deformable four-rotor aircraft | |
| RU2749709C1 (en) | Swashplate of multi-rotor aircraft with rigid attachment of blades and method for its operation | |
| CN111942581B (en) | Distributed lift force duck-type layout vertical take-off and landing unmanned aerial vehicle and control method | |
| CN105000179A (en) | Tiltrotor mixed multi-state aircraft | |
| CN204452929U (en) | The fuselage formula of verting of band operation rudder face mixes polymorphic aircraft | |
| RU2539679C1 (en) | High-speed rotary-wing aircraft | |
| CN107662703B (en) | Electric double-coaxial same-side reverse tilting rotor aircraft | |
| CN206734609U (en) | A kind of tail sitting posture VUAV using duct | |
| RU2412869C1 (en) | Universal "push-pull" aircraft | |
| CN106081100A (en) | The double vector of single rotor advances autogyro and control method thereof | |
| CN209192220U (en) | Scissor DCB Specimen seesaw type autogyro |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160615 |
|
| WD01 | Invention patent application deemed withdrawn after publication |