CN115214881A - Electric tilt rotor aircraft - Google Patents
Electric tilt rotor aircraft Download PDFInfo
- Publication number
- CN115214881A CN115214881A CN202211064321.9A CN202211064321A CN115214881A CN 115214881 A CN115214881 A CN 115214881A CN 202211064321 A CN202211064321 A CN 202211064321A CN 115214881 A CN115214881 A CN 115214881A
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- Prior art keywords
- wing
- rotor
- cabin
- tilting
- electric
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Classifications
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- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- 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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
Abstract
The invention discloses an electric tilt rotor aircraft which is characterized by comprising an aircraft body, a wing system, empennages, a rotor system and a tilt device, wherein the wing system comprises wings and canard wings, the wings are symmetrically arranged along two sides of the aircraft body, the canard wings are arranged at the head of the aircraft body and symmetrically arranged along two sides of the aircraft body, the empennages are arranged at the tail of the aircraft body, the rotor system comprises auxiliary wing rotors and tilt rotors, the auxiliary wing rotors are arranged at the wing ends of the wings, the tilt rotors are respectively arranged at the wing ends of the canard wings and the empennages, and the tilt device is used for connecting the rotor system with the wing system and the empennages. The electric tilt rotor aircraft has the advantages of capability of taking off and landing vertically, high flat flying speed, long endurance time and excellent air performance.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an electric tilt rotor aircraft.
Background
With the development of different transportation modes, most of the previous aircrafts are fixed-wing aircrafts and need to run through a runway for assisting in running, so that the existing pressure of the land area and the transportation convenience is inconvenient, the rotor aircraft is emphasized, the rotor aircraft can take off and land when the runway does not run, convenience is provided to the greatest extent, and the rotor aircraft and the fixed-wing aircraft still have respective advantages and disadvantages and need to be improved most.
Chinese patent prior publication No. CN112262075A discloses an electric tilt rotor aircraft comprising a airframe and a plurality of propulsion assemblies coupled to the airframe, wherein each propulsion assembly comprises an electric motor, a propeller coupled to the electric motor, and a tilt mechanism connecting the propulsion assemblies to the airframe and transitioning the propulsion assemblies between a forward configuration and a hover configuration; wherein the plurality of propulsion assemblies are convertible between a forward arrangement and a hover arrangement, wherein each of the plurality of propulsion assemblies is in a forward configuration in the forward arrangement, wherein each of the plurality of propulsion assemblies is in a hover configuration in the hover arrangement, wherein a pitch between at least two of the propellers of the plurality of propulsion assemblies varies between the forward arrangement and the hover arrangement.
This kind of aircraft of two wing cloth office is the comparatively common tiltrotor aircraft layout mode at present, and at the flight of cruising, its tail-flat provides the negative lift and is used for balanced aircraft pitching moment, and this aerodynamic lift with regard to having lost the complete machine has increased aerodynamic drag, leads to whole more electric power that need provide to overcome the resistance for holistic continuation of the journey mileage reduces, and to this one kind can improve the tiltrotor aircraft of complete machine lift-drag ratio urgent the solution of awaiting the opportune moment.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an electric tilt rotor aircraft which has the effects of improving the pneumatic performance of the whole aircraft and increasing the endurance mileage of the whole aircraft.
In order to realize the purpose, the invention provides the following technical scheme:
an electric tiltrotor aircraft comprising: organism, wing system, fin, rotor system and the device that verts, the wing system includes wing and duck wing, the wing sets up along organism bilateral symmetry, the duck wing sets up in the head of organism to set up along organism bilateral symmetry, the organism afterbody is provided with the fin, rotor system is including assisting the wing rotor and the rotor that verts, it sets up in the wingtip of wing to assist the wing rotor, the rotor that verts sets up respectively in the wingtip of duck wing and fin, the device that verts is used for being connected rotor system and wing system and fin.
As a further improvement of the invention, the ratio of the wing area to the canard area is 5-8.
As a further development of the invention, the ratio of the wing area to the tail area is 4 to 6.
As a further improvement of the invention, the sum of the distance between the canard wing and the mass center of the machine body and the distance between the wing and the mass center of the machine body is equal to the distance between the tail wing and the mass center of the machine body.
As a further improvement of the present invention, the auxiliary wing rotor includes a wing cabin and a rotor blade, the wing cabin is connected with the tilting device, and the rotor blade is connected with the wing cabin;
the tilting rotor comprises a tilting cabin and tilting blades, the tilting cabin is connected with the tilting device, and the tilting blades are connected with the tilting cabin.
As a further improvement of the invention, the tilt rotor further comprises an auxiliary wing, the auxiliary wing is connected with one side of the tilt cabin, which is far away from the wing, and when the tilt cabin is driven by the tilt device to rotate to a horizontal position, the auxiliary wing and the wing are horizontally arranged.
As a further improvement of the invention, the tilting device comprises an electric cylinder, a driving part and a tilting part, wherein a first connecting shaft for connecting a wing cabin is arranged on the wing, second connecting shafts for connecting the tilting cabin are respectively arranged on the canard wing and the empennage, the tilting part is respectively connected to the first connecting shaft and the second connecting shaft, rotating shafts are respectively arranged in the wing cabin and the tilting cabin, the driving part is connected with the rotating shaft, the electric cylinder is respectively arranged in the wing cabin and the tilting cabin, an output shaft of the electric cylinder is connected with the driving part and is used for controlling the driving part to rotate along the rotating shaft, the driving part is meshed with the tilting part, and the driving part is used for driving the wing cabin and the tilting cabin to rotate.
As a further improvement of the present invention, the driving member and the tilting member are respectively a half-shaped gear, and the output shaft of the electric cylinder is eccentrically connected to the driving member.
As a further improvement of the invention, the tail is V-shaped.
As a further improvement of the invention, the bottom of the machine body is provided with a front three-point landing gear.
The invention has the beneficial effects that: through set up wing and duck wing on the organism, set up the rotor that verts on duck wing and the fin, set up the auxiliary wing rotor on the wing, the device of verting is used for controlling the rotor that verts and the auxiliary wing rotor verts, vert to different states in order to provide different attitude control through controlling the rotor that verts and the auxiliary wing rotor, when flying flatly, the duck wing acts as partial lift face, for the complete machine lift provides the gain effect, the attack angle of complete machine is less during the flight that cruises, reduce aerodynamic drag, improve the effect of the mileage of continuation of the journey of the complete machine.
Drawings
FIG. 1 is a schematic view of a three-dimensional structure embodying a fixed-wing mode of a whole machine;
FIG. 2 is a top view of the embodiment of the fixed wing mode;
figure 3 is a schematic view of a configuration embodying only tilt of the auxiliary wing rotor;
fig. 4 is a schematic view of a structure embodying non-tilting of only the auxiliary wing rotor;
FIG. 5 is a schematic diagram of a helicopter mode embodiment;
fig. 6 is a schematic view showing a structure of the tilting device.
Reference numerals are as follows: 1. a body; 11. a landing gear; 2. a tilting device; 21. an electric cylinder; 22. a drive member; 23. a tilting member; 3. an airfoil; 4. duck wings; 5. a tail wing; 6. an auxiliary wing rotor wing; 61. a wing tank; 62. a rotor blade; 63. auxiliary wings; 7. a tilt rotor; 71. a tilting cabin; 72. a tilting blade.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. In which like parts are designated by like reference numerals. It should be noted that as used in the following description, the terms "front", "back", "left", "right", "upper" and "lower" refer to directions in the drawings, and the terms "bottom" and "top", "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.
Referring to fig. 1 to 6:
the electric tilt rotor aircraft comprises an aircraft body 1, a wing system, a rotor system and a tilt device 2, wherein the wing system comprises wings 3 and canard wings 4, the wings 3 are symmetrically arranged along two sides of the aircraft body 1, the canard wings 4 are arranged at the head of the aircraft body 1 and symmetrically arranged along two sides of the aircraft body 1, tail wings 5 are arranged at the tail of the wings, the rotor system comprises auxiliary wing rotors 6 and tilt rotors 7, the auxiliary wing rotors 6 are arranged at the wing ends of the wings 3, the tilt rotors 7 are respectively arranged at the wing ends of the canard wings 4 and the tail wings 5, the tilt device 2 is used for connecting the rotor system with the wings and the tail wings 5, the tail wings 5 are V-shaped, the tail wings 5 can be swept back or front swept, flaps and ailerons are arranged on the wings 3 so as to adjust and control the attitude, and a front three-point undercarriage 11 is arranged at the bottom of the aircraft body 1.
The ratio of the area of the wing 3 to the area of the canard wing 4 is 5-8, the ratio of the area of the wing 3 to the area of the tail wing is 4-6, the airflow generated by the canard wing 4 is not easy to interfere with the wing 3 in the area ratio, the stability of the whole body 1 is improved, the sum of the distance between the canard wing 4 and the mass center of the body 1 and the distance between the wing 3 and the mass center of the body 1 is equal to the distance between the tail wing 5 and the mass center of the body 1, so that the tension of the wing systems on the canard wing 4, the wing 3 and the tail wing 5 is kept equal in the hovering mode, and the longitudinal, transverse and heading moments are balanced; the distance of canard 4 apart from the barycenter is far away than the distance of wing 3 apart from the barycenter, realizes canard 4 can play the pressure to hold stable effect to the head of organism 1, further improves the stability of whole organism 1 to canard 4's design makes the aircraft provide partial lift when the tie flies, reduces the trim resistance of complete machine when the tie flies, thereby reduces the loss of electric energy when flying.
The auxiliary wing rotor 6 includes wing cabin 61 and rotor blade 62, wing cabin 61 is connected with tilting device 2, rotor blade 62 in wing cabin 61 is connected, tilting rotor 7 is including tilting cabin 71, tilting blade 72 and auxiliary wing 63, tilting cabin 71 is connected with tilting device 2, tilting blade 72 with tilting cabin 71 connects, auxiliary wing 63 deviates from wing 3 one side with tilting cabin 71 and is connected, tilting cabin 71 rotates to horizontal position under tilting device 2's drive when, auxiliary wing 63 with 3 horizontal settings of wing.
The tilting device 2 comprises an electric cylinder 21, a driving piece 22 and a tilting piece 23, a first connecting shaft used for connecting a wing cabin 61 is arranged on the wing 3, a second connecting shaft used for connecting a tilting cabin 71 is respectively arranged on the wing 4 and the empennage 5, the tilting piece 23 is respectively connected on the first connecting shaft and the second connecting shaft, rotating shafts are respectively arranged in the wing cabin 61 and the tilting cabin 71, the driving piece 22 is connected with the rotating shafts, bearings are respectively arranged on the first connecting shaft, the second connecting shaft and the rotating shafts so as to reduce the friction resistance during rotation, the electric cylinder 21 is respectively arranged in the wing cabin 61 and the tilting cabin 71, the output shaft of the electric cylinder 21 is connected with the driving piece 22 and used for controlling the driving piece 22 to rotate along the rotating shafts, drive piece 22 and the meshing of tilting 23, drive piece 22 is used for the drive wing cabin 61, the cabin 71 that verts rotate, drive piece 22 and tilting 23 are half type gear respectively, the output shaft of electricity jar 21 with drive piece 22 eccentric coupling to the messenger under the impetus of electricity jar 21, can drive piece 22 and rotate along the pivot to drive tilting 23 and rotate, drive auxiliary wing rotor 6, tilting rotor 7 and rotate when tilting 23 rotates, realize the control of verting to auxiliary rotor and tilting rotor 7, because drive piece 22 and tilting 23 are half type gear, make the pivoted range rotate for 90 degrees.
Different modes can be provided when tilt control is performed:
in a first mode: helicopter mode, when the helicopter mode, the device 2 control that verts auxiliary wing rotor 6 and verts rotor 7 and rotate to with organism 1 vertical state, auxiliary wing 63 on the auxiliary wing rotor 6 sets up with wing 3 is perpendicular this moment, so that reduce the influence of downwash when going up and down, be difficult for producing the resistance because of auxiliary wing 63, and can also play the effect of restraining the wingtip vortex, further provide the lifting surface under the effect of canard 4, make and provide more abundant lift when carrying out the VTOL.
And a second mode: fixed wing mode, when the fixed wing mode, the device 2 control that verts auxiliary wing rotor 6 and vert rotor 7 rotate to with 1 horizontal state of organism, auxiliary wing 63 on the auxiliary wing rotor 6 sets up with wing 3 level this moment, auxiliary wing rotor 6 all provides the pulling force when organism 1 gos forward with verting rotor 7, and when navigating, the horizontal wing structure of canard wing 4 plays the effect the same with wing 3, make the drag reduction that can further when flying flatly, improve organism 1's voyage.
And a third mode: compound wing mode, when compound wing mode, the device 2 control that verts is assisted wing rotor 6 and organism 1 and is the horizontality, and control verts rotor 7 and organism 1 and sets up perpendicularly, provides the pulling force effect that advances to organism 1 under the effect of assisting wing rotor 6 this moment, provides the lift of taking off and land to organism 1 under the effect of rotor 7 that verts to improve whole organism 1's gesture controllability.
Carry out the regulation control of different combinations to auxiliary wing rotor 6 and rotor 7 that verts through device 2 that verts for can multiple form adjust the switching when handling the different situation, reach the flight demand of handling under the different environment, set up independent duck wing 4 structures on organism 1, make and to provide more lifting surfaces when VTOL, act as the wing when navigating, reduce the resistance when flying, in order to improve holistic flight journey.
The working principle and the effect are as follows:
through set up wing 3 and duck wing 4 on organism 1, set up tilting rotor 7 on duck wing 4 and the fin 5, set up auxiliary wing rotor 6 on the wing 3, tilting device 2 is used for controlling tilting rotor 7 and auxiliary wing rotor 6 and verts, through control tilting rotor 7 and auxiliary wing rotor 6 vert to different states in order to provide different attitude control, setting at duck wing 4, make provide sufficient lift when carrying out the VTOL, organism 1 is when carrying out the flat flight, duck wing 4 acts as the wing, reduce the resistance of organism 1 when flight, realize reducing the resistance of complete machine, improve the effect of the continuation of the journey mileage of complete machine.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and adaptations to those skilled in the art without departing from the principles of the present invention should also be considered as within the scope of the present invention.
Claims (10)
1. An electric tilt-rotor aircraft, comprising: organism (1), wing system, fin (5), rotor system and device (2) vert, the wing system includes wing (3) and duck wing (4), organism (1) bilateral symmetry sets up is followed in wing (3), duck wing (4) set up in the head of organism (1) to set up along organism (1) bilateral symmetry, the organism afterbody is provided with fin (5), the rotor system is including assisting wing rotor (6) and verting rotor (7), it sets up in the tip of wing (3) to assist wing rotor (6), verting rotor (7) set up respectively in the tip of duck wing (4) and fin (5), the device (2) of verting is used for being connected rotor system and wing system and fin (5).
2. An electric tiltrotor aircraft according to claim 1, wherein: the ratio of the area of the wing (3) to the area of the canard (4) is 5-8.
3. An electric tiltrotor aircraft according to claim 1, wherein: the ratio of the area of the wing (3) to the area of the tail wing (5) is 4-6.
4. An electric tiltrotor aircraft according to claim 1, wherein: the sum of the distance from the canard wing (4) to the mass center of the machine body (1) and the distance from the wing (3) to the mass center of the machine body (1) is equal to the distance from the tail wing (5) to the mass center of the machine body (1).
5. The electric tiltrotor aircraft of claim 4, wherein: the auxiliary wing rotor (6) comprises a wing cabin (61) and a rotor blade (62), the wing cabin (61) is connected with the tilting device (2), and the rotor blade (62) is connected with the wing cabin (61);
tilt rotor (7) including tilting cabin (71) and tilting paddle (72), tilting cabin (71) is connected with tilting device (2), tilting paddle (72) with tilting cabin (71) is connected.
6. The electric tiltrotor aircraft of claim 5, wherein: the tilt rotor wing further comprises an auxiliary wing (63), the auxiliary wing (63) deviates from one side of the wing (3) with the tilt cabin (71) to be connected, the tilt cabin (71) rotates to the horizontal position under the driving of the tilt device (2), and the auxiliary wing (63) is horizontally arranged with the wing (3).
7. An electric tiltrotor aircraft according to claim 6, wherein: tilt device (2) including electric cylinder (21), driving piece (22) and vert a (23), be provided with the first connecting axle that is used for connecting wing cabin (61) on wing (3), be provided with the second connecting axle that is used for connecting verting cabin (71) on duck wing (4) and fin (5) respectively, connect on first connecting axle and the second connecting axle respectively and vert a (23), still be provided with the pivot in wing cabin (61) and the verting cabin (71) respectively, driving piece (22) are connected with the pivot, electric cylinder (21) set up respectively in wing cabin (61) and verting cabin (71), the output shaft of electric cylinder (21) with driving piece (22) are connected and are used for control driving piece (22) rotate along the pivot, driving piece (22) with verting a (23) meshing, driving piece (22) are used for the drive wing cabin (61), the cabin (71) rotate that verts.
8. An electric tiltrotor aircraft according to claim 7, wherein: the driving piece (22) and the tilting piece (23) are respectively a half-shaped gear, and an output shaft of the electric cylinder (21) is eccentrically connected with the driving piece (22).
9. The electric tiltrotor aircraft of claim 8, wherein: the tail wing (5) is V-shaped.
10. An electric tiltrotor aircraft according to any one of claims 1-9, wherein: the bottom of the machine body (1) is provided with a front three-point type undercarriage (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211064321.9A CN115214881A (en) | 2022-09-01 | 2022-09-01 | Electric tilt rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211064321.9A CN115214881A (en) | 2022-09-01 | 2022-09-01 | Electric tilt rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115214881A true CN115214881A (en) | 2022-10-21 |
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ID=83617275
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211064321.9A Pending CN115214881A (en) | 2022-09-01 | 2022-09-01 | Electric tilt rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115214881A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | Vertical take-off and landing aircraft and control method thereof |
| CN117360772A (en) * | 2023-12-07 | 2024-01-09 | 四川沃飞长空科技发展有限公司 | Vertical take-off and landing aircraft and control method |
-
2022
- 2022-09-01 CN CN202211064321.9A patent/CN115214881A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | Vertical take-off and landing aircraft and control method thereof |
| CN117360772A (en) * | 2023-12-07 | 2024-01-09 | 四川沃飞长空科技发展有限公司 | Vertical take-off and landing aircraft and control method |
| CN117360772B (en) * | 2023-12-07 | 2024-02-06 | 四川沃飞长空科技发展有限公司 | Vertical take-off and landing aircraft and control method |
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