CN220164163U - Novel-configuration electric duct tilting rotor aircraft - Google Patents
Novel-configuration electric duct tilting rotor aircraft Download PDFInfo
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- CN220164163U CN220164163U CN202321332787.2U CN202321332787U CN220164163U CN 220164163 U CN220164163 U CN 220164163U CN 202321332787 U CN202321332787 U CN 202321332787U CN 220164163 U CN220164163 U CN 220164163U
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- 230000005611 electricity Effects 0.000 claims description 2
- 238000005406 washing Methods 0.000 description 8
- 238000004134 energy conservation Methods 0.000 description 3
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- 230000003416 augmentation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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Abstract
The utility model discloses a novel-configuration electric duct tilting rotor craft which comprises a fuselage, wherein the fuselage is provided with a wing system, a rotor system, a power system and a tilting system, and a horn is arranged at the lower side of a main wing and parallel to the fuselage; the rotor system comprises a tilting duct rotor and a fixed duct rotor; in a helicopter mode, the fixed duct rotor maintains the vertical state of the rotor shaft, the tilting system drives the rotor shaft of the tilting duct rotor to be vertical and far away from the main wing, the influence of rotor down-wash is reduced, and the aerodynamic efficiency is improved; in the fixed wing mode, the rotor shaft of the tilting system driving tilting duct rotor is in a horizontal state, and the tilting duct rotor provides forward flying power, so that the tilting system can vertically lift and lower the lifting field requirement.
Description
Technical Field
The utility model relates to the technical field of aircraft manufacturing, in particular to a novel-configuration electric duct tilting rotor aircraft.
Background
The tilting rotor craft is a novel craft integrating the fixed wing craft and the rotor craft, which has the capability of vertical take-off, landing and hovering of the traditional rotor craft and the capability of high-speed cruising of the fixed wing craft. The tiltrotor aircraft comprises a set of rotor tilting systems capable of rotating alternately between a horizontal position and a vertical position, and a power system for providing power, wherein when the aircraft is in a vertical lift mode of vertical take-off and landing, a rotor shaft is vertical to the ground; when the aircraft is in fixed wing mode in cruise mode, the rotor shaft is parallel to the ground.
The chinese patent with application No. 202210848974.X discloses a "tilting six-rotor electric vertical take-off and landing aircraft employing wingtip slipstream rudder", including fuselage, main wing, horizontal tail wing, front wing, propeller, tilting propeller nacelle and tilting mechanism; the wing tip parts of the main wing, the horizontal tail wing and the front wing of the airplane are all provided with tilting propeller nacelle, each tilting propeller nacelle is provided with a propeller and a nacelle with a slipstream rudder, the tilting mechanism is arranged inside the tilting propeller nacelle, the output end of the tilting mechanism is connected with the wing tip part of the wing, and the tilting mechanism drives the tilting propeller nacelle to rotate at two horizontal and vertical positions. Because the propeller of the aircraft is exposed outside, the requirement on the landing site is high, and the noise is high during working.
Disclosure of Invention
The utility model aims to provide a novel-configuration electric ducted tilting rotor aircraft, which reduces the take-off and landing requirements, reduces noise and improves riding comfort.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a new configuration electric duct rotor aircraft that verts, includes the fuselage, wing system, rotor system, driving system and the system that verts are installed to the fuselage, the wing system includes main wing, horn and fin, main wing, horn and fin all symmetry the fuselage distributes, the horn is in the downside of main wing and parallel fuselage setting;
the rotor system comprises a tilting duct rotor and a fixed duct rotor, and the tilting duct rotor and the fixed duct rotor are respectively arranged at the front side and the rear side of the horn; the tilting system drives the tilting duct rotor to do alternating motion independently under the state that the rotor shaft is horizontal, transitional and vertical.
Through the technical scheme, in the helicopter mode, the fixed bypass rotor maintains the vertical state of the rotor shaft, the tilting system drives the rotor shaft of the tilting bypass rotor to be vertical and far away from the main wing, the influence of downward washing of the rotor is reduced, and the aerodynamic efficiency is improved; in the fixed wing mode, the tilting system drives the rotor shaft of the tilting duct rotor to be in a horizontal state, and the tilting duct rotor provides forward flying power.
Preferably, the horn comprises an inner horn and an outer horn, and the inner horn and the outer horn are respectively arranged in the direction close to and far from the machine body; and the front side and the rear side of the inner horn and the outer horn are respectively provided with a tilting duct rotor wing and a fixed duct rotor wing.
Through the technical scheme, the flight efficiency is further improved.
Preferably, the tilting system comprises a linear steering engine, a connecting rod mechanism and a fixing seat, wherein one end of the connecting rod mechanism is fixed at the output end of the linear steering engine, and the other end of the connecting rod mechanism is fixedly connected with the tilting duct rotor wing.
Through the technical scheme, the linear steering engine drives the connecting rod mechanism to rotate around the fixed seat, and the rotor shaft of the tilting duct rotor is driven to do alternate motion in horizontal, transitional and vertical states.
Preferably, the tail fin comprises a pair of vertical tails and a horizontal tail, the pair of vertical tails and the horizontal tail form an inverted U-shaped structure, and two sides of the pair of vertical tails are fixedly connected with the tail end of the inner horn respectively.
Through the technical scheme, the whole structure has better rigidity.
Preferably, the horizontal tail is provided with an elevator, and the vertical tail is provided with a rudder.
Through the technical scheme, the elevator controls the pitching motion of the whole machine, and the rudder controls the yawing motion of the whole machine.
Preferably, the horn is arranged to be of a structure with a wide upper part and a narrow lower part, and the contour of the horn is smoothly transited by an arc surface structure.
Through the technical scheme, the influence of downwash of the rotor wing can be reduced in a helicopter mode, and the pneumatic interference of the horn and the rotor wing is reduced; meanwhile, the front flight resistance is reduced, the interference of wing down wash on the horn is reduced, the flight efficiency is improved, and the energy conservation and emission reduction are facilitated.
Preferably, the tilting duct rotor and the fixed duct rotor are composed of a motor, an electric regulator, blades and a duct, the duct is fixedly connected with a horn, and the motor provides rotating power for the blades and is arranged inside the duct.
Through the technical scheme, vibration and noise are small, and riding comfort is improved.
Preferably, the main wing rear side is provided with a flap and an aileron.
Through the technical scheme, in the fixed wing mode, the roll gesture is controlled through differential deflection of the aileron, and the flap plays a role in increasing lift.
Preferably, the tilting system further comprises an electronic governor.
Through above-mentioned scheme, control rotor rotational speed.
Preferably, the machine body is in a streamline shape, and the joints of the machine body, the arm, the main wing and the tail wing are in smooth transition.
The beneficial effects are that:
according to the utility model, the tilting system, the tilting duct rotor and the fixed duct rotor are arranged, so that in a helicopter mode, the fixed duct rotor maintains the vertical state of the rotor shaft, the tilting system drives the rotor shaft of the tilting duct rotor to be vertical and far away from the main wing, the influence of downward washing flow of the rotor is reduced, and the aerodynamic efficiency is improved; in the fixed wing mode, the tilting system drives the rotor shaft of the tilting duct rotor to be in a horizontal state, and the tilting duct rotor provides forward flying power. Can vertically take off and land, and reduce the requirements of take off and land sites.
According to the utility model, the streamline machine body is arranged, the horn is arranged to be of a structure with wide upper part and narrow lower part, and the contour of the horn is smoothly transited by the cambered surface structure, so that the influence of downward washing of the rotor wing can be reduced in a helicopter mode, and the pneumatic interference of the horn and the rotor wing can be reduced; meanwhile, the front flight resistance is reduced, the interference of wing down wash on the horn is reduced, the flight efficiency is improved, and the energy conservation and emission reduction are facilitated.
The utility model reduces forward flight resistance by arranging the duct, and has less vibration and noise because the blade is not directly exposed outside, thereby improving riding comfort.
According to the utility model, the inverted U-shaped tail wing structure is arranged, so that the rigidity of the whole structure is better, and the tail wing is arranged outside the downward air washing flow of the propeller, so that the resistance of the tail wing is reduced.
Drawings
FIG. 1 is a schematic view of a helicopter mode architecture of the present utility model;
FIG. 2 is a schematic diagram of a transition mode structure according to the present utility model;
FIG. 3 is a schematic view of a fixed wing mode structure according to the present utility model;
FIG. 4 is a schematic diagram of a tilting system according to the present utility model;
FIG. 5 is a schematic view of a bypass structure according to the present utility model;
fig. 6 is a schematic view of the structure of the arm of the present utility model.
In the figure: 1. a body; 2. a main wing; 21. a flap; 22. aileron; 23. wing tip winglets; 3. a horn; 31. an inner arm; 32. an outer arm; 4. a tail wing; 41. a vertical tail; 42. a horizontal tail; 43. an elevator; 44. a rudder; 5. tilting duct rotor wings; 6. fixed wing ducted rotor wing; 7. a tilting system; 71. a linear steering engine; 72. a link mechanism; 73. a fixing seat; 8. a duct; 81. a motor; 82. a blade.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
The following describes embodiments of the present utility model in detail:
the novel-configuration electric ducted tilt rotor aircraft comprises a fuselage 1, wherein the fuselage 1 is provided with a wing system, a rotor system, a power system and a tilt system 7, the wing system comprises a main wing 2, a horn 3 and a tail wing 4, the main wing 2, the horn 3 and the tail wing 4 are symmetrically distributed on the fuselage 1, and the horn 3 is arranged on the lower side of the main wing 2 and parallel to the fuselage 1; the rotor system comprises a tilting duct rotor 5 and a fixed duct rotor 6, wherein the tilting duct rotor 5 and the fixed duct rotor 6 are respectively arranged on the front side and the rear side of the horn 3; the tilting system 7 drives the tilting duct rotor 5 to do alternating motion independently under the state that the rotor shaft is horizontal, transitional and vertical.
In the helicopter mode, the fixed ducted rotor 6 maintains the vertical state of the rotor shaft, the tilting system 7 drives the rotor shaft of the tilting ducted rotor 5 to be vertical and far away from the main wing 2, the influence of rotor down-wash is reduced, and the aerodynamic efficiency is improved; in the fixed wing mode, the tilting system 7 drives the rotor shaft of the tilting ducted rotor 5 to be in a horizontal state, and forward flying power is supplied by the tilting ducted rotor 5. Can vertically take off and land, and reduce the requirements of take off and land sites.
Specifically, the airframe 1 is in a streamline shape, the connection parts of the airframe 1, the airframe 3, the main wing 2 and the tail wing 4 are in smooth transition, the airframe 3 is in a structure with a wide upper part and a narrow lower part, the outline of the airframe 3 is in smooth transition in a cambered surface structure, the influence of downward washing flow of a rotor wing can be reduced in a helicopter mode, and the pneumatic interference of the airframe 3 and the rotor wing is reduced; meanwhile, the front flight resistance is reduced, the interference of wing down wash on the horn 3 is reduced, the flight efficiency is improved, and the energy conservation and emission reduction are facilitated.
Wherein, tilting duct rotor 5 and fixed duct rotor 6 are by motor 81, electricity transfer, paddle 82 and duct 8 constitute, duct 8 and horn 3 fixed connection, and motor 81 provides paddle 82 rotation power and sets up inside duct 8. The motor 81 and the electric adjuster are installed on the inner support rod to form an integrated structure, so that forward flying resistance is reduced, and the paddle 82 is not directly exposed to the outside, so that vibration and noise are small, and riding comfort is improved.
As a preferred embodiment, the horn 3 includes an inner horn 31 and an outer horn 32, the inner horn 31 and the outer horn 32 being disposed in directions approaching and separating from the fuselage 1, respectively; and both sides all are provided with tilting duct rotor 5 and fixed duct rotor 6 around interior horn 31 and the outer horn 32, further improve flight efficiency.
As a preferred embodiment, the tilting system 7 includes a linear steering engine 71, a link mechanism 72 and a fixing seat 73, wherein one end of the link mechanism 72 is fixed at the output end of the linear steering engine 71, and the other end is fixedly connected with the tilting duct rotor 5. The linear steering engine 71 drives the link mechanism 72 to rotate around the fixed seat 73, so as to drive the rotor shaft of the tilting duct rotor 5 to do alternate motion in the horizontal, transitional and vertical states. The tilting system 7 also comprises an electronic governor to control the rotor speed.
As a preferred embodiment, the tail fin 4 comprises a pair of vertical tails 41 and a horizontal tail 42, the pair of vertical tails 41 and the horizontal tail 42 form an inverted U-shaped structure, two sides of the pair of vertical tails 41 are fixedly connected with the tail end of the inner horn 31 respectively, the rigidity of the overall structure of the inverted U-shaped structure is better, and the tail fin 4 is placed outside the air washing flow under the propeller, so that the resistance of the tail fin 4 is reduced. Further, an elevator 43 is installed on the horizontal tail 42, a rudder 44 is installed on the vertical tail 41, the elevator 43 controls pitching motion of the whole machine, and the rudder 44 controls yawing motion of the whole machine.
As a preferred embodiment, the rear side of the main wing 2 is provided with a flap 21 and an aileron 22, in a fixed wing mode, the roll attitude is controlled by differential deflection of the aileron 22, the flap 21 plays a role in lift augmentation, and the heading attitude is controlled by controlling the magnitude of the rotor tension on the main wing 2. Further, the main wing 2 is provided with a tip winglet 23, and the tip winglet 23 plays a role of suppressing tip vortex in the fixed wing mode flight.
Working principle:
in the helicopter mode, the fixed ducted rotor 6 maintains the vertical state of the rotor shaft, and the linear steering engine 71 drives the link mechanism 72 to rotate around the fixed seat 73 so as to drive the rotor shaft of the tilting ducted rotor 5 to be in the vertical state; in the fixed wing mode, the linear steering engine 71 drives the link mechanism 72 to rotate around the fixed seat 73 to drive the rotor shaft of the tilting duct rotor 5 to be in a horizontal state, so that the tilting duct rotor can vertically lift and lower the lifting field requirement, and the paddle 82 is not directly exposed to the outside, so that the vibration and noise are small, and the riding comfort is improved.
The structural design of the horn 3 with the wide upper part and the narrow lower part can reduce the influence of the downward washing flow of the rotor wing in a helicopter mode, reduce the pneumatic interference of the horn 3 and the rotor wing, reduce the front flight resistance, reduce the interference of the downward washing flow of the wing to the horn 3 and reduce the pneumatic interference of the horn 3 and the rotor wing; meanwhile, the front flight resistance is reduced, the interference of wing down wash on the horn 3 is reduced, and the flight efficiency is improved. The design of the inner and outer horn 31, 32 further improves the flight efficiency.
It will be evident to those skilled in the art that the utility model is not limited to the details of the foregoing illustrative embodiments, and that the present utility model may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (10)
1. The utility model provides a new configuration electric duct rotor aircraft that verts, includes fuselage (1), wing system, rotor system, driving system and tilting system (7) are installed to fuselage (1), its characterized in that: the wing system comprises a main wing (2), a horn (3) and a tail wing (4), wherein the main wing (2), the horn (3) and the tail wing (4) are symmetrically distributed on the main body (1), and the horn (3) is arranged on the lower side of the main wing (2) and parallel to the main body (1);
the rotor system comprises a tilting duct rotor (5) and a fixed duct rotor (6), wherein the tilting duct rotor (5) and the fixed duct rotor (6) are respectively arranged on the front side and the rear side of the horn (3); the tilting system (7) drives the tilting duct (8) and the rotor (5) to do alternating motion independently under the state that the rotor shaft is horizontal, transitional and vertical.
2. The newly configured electric ducted tiltrotor aircraft according to claim 1, characterized in that: the horn (3) comprises an inner horn (31) and an outer horn (32), and the inner horn (31) and the outer horn (32) are respectively arranged in the direction close to and far from the machine body (1); and the front side and the rear side of the inner horn (31) and the outer horn (32) are respectively provided with a tilting duct rotor wing (5) and a fixed duct rotor wing (6).
3. The newly configured electric ducted tiltrotor aircraft according to claim 1, characterized in that: the tilting system (7) comprises a linear steering engine (71), a connecting rod mechanism (72) and a fixing seat (73), one end of the connecting rod mechanism (72) is fixed at the output end of the linear steering engine (71), and the other end of the connecting rod mechanism is fixedly connected with the tilting duct rotor wing (5).
4. The newly configured electric ducted tiltrotor aircraft according to claim 2, characterized in that: the tail wing (4) comprises a pair of vertical tails (41) and a pair of flat tails (42), the pair of vertical tails (41) and the flat tails (42) form an inverted U-shaped structure, and two sides of the pair of vertical tails (41) are fixedly connected with the tail ends of the inner horn (31) respectively.
5. The newly configured electric ducted tiltrotor aircraft according to claim 4, characterized in that: an elevator (43) is arranged on the horizontal tail (42), and a rudder (44) is arranged on the vertical tail (41).
6. The newly configured electric ducted tiltrotor aircraft according to any of claims 1-5, characterized in that: the horn (3) is arranged to be of a structure with a wide upper part and a narrow lower part, and the outline of the horn (3) is smoothly transited by an arc surface structure.
7. The newly configured electric ducted tiltrotor aircraft according to claim 6, characterized in that: the utility model discloses a rotor of a wind turbine, including tilting duct rotor (5) and fixed duct rotor (6), by motor (81), electricity transfer, paddle (82) and duct (8) are constituteed, duct (8) and horn (3) fixed connection, motor (81) provide paddle (82) rotation power and set up inside duct (8).
8. The newly configured electric ducted tiltrotor aircraft according to claim 7, characterized in that: the rear side of the main wing (2) is provided with a flap (21) and an aileron (22).
9. The newly configured electric ducted tiltrotor aircraft according to claim 8, characterized in that: the tilting system (7) further comprises an electronic governor.
10. The newly configured electric ducted tiltrotor aircraft according to claim 9, characterized in that: the machine body (1) is in a streamline shape, and the joint of the machine body (1) and the machine arm (3), the main wing (2) and the tail wing (4) is in smooth transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321332787.2U CN220164163U (en) | 2023-05-25 | 2023-05-25 | Novel-configuration electric duct tilting rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321332787.2U CN220164163U (en) | 2023-05-25 | 2023-05-25 | Novel-configuration electric duct tilting rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220164163U true CN220164163U (en) | 2023-12-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321332787.2U Active CN220164163U (en) | 2023-05-25 | 2023-05-25 | Novel-configuration electric duct tilting rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220164163U (en) |
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2023
- 2023-05-25 CN CN202321332787.2U patent/CN220164163U/en active Active
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