CN112009675A - Unmanned rotorcraft overall pneumatic layout that verts - Google Patents
Unmanned rotorcraft overall pneumatic layout that verts Download PDFInfo
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- CN112009675A CN112009675A CN202010879148.2A CN202010879148A CN112009675A CN 112009675 A CN112009675 A CN 112009675A CN 202010879148 A CN202010879148 A CN 202010879148A CN 112009675 A CN112009675 A CN 112009675A
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- 230000007246 mechanism Effects 0.000 claims abstract description 16
- 230000007704 transition Effects 0.000 claims abstract description 6
- 230000004927 fusion Effects 0.000 abstract description 3
- 230000003028 elevating effect Effects 0.000 abstract 1
- 238000005406 washing Methods 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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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
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0045—Fuselages characterised by special shapes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
An unmanned tiltrotor aircraft overall pneumatic layout comprising: fuselage, wing, engine compartment, rotor, tilting mechanism and V tail. The fuselage adopts a streamline shape, and the wings and the fuselage are in fusion transition. The wing comprises an inner section wing and an outer section wing, the inner section wing is a straight wing, a flap and an aileron are arranged on the straight wing, the outer section wing is tapered and is inverted upwards, and the aspect ratio of the wing is 10-15. And an elevating rudder is arranged on the V tail. The engine cabin, the rotor wings and the tilting mechanism are arranged between the inner section of wing and the outer section of wing in a clinging mode. When the aircraft vertically takes off or lands, the rotor wing is in a vertical state, the outer section of the wing, the wing flap and the aileron deflect downwards by about 90 degrees, and the influence of the rotor wing on the downward washing flow is reduced. When flying forward, the rotor wing is in the horizontal state, and the outer section wing, the flap and the aileron are restored to the normal state. When the aircraft is stored, the outer section wings and the rotor blades are folded, and the wings rotate around the rotation center to be parallel to the aircraft body. The overall pneumatic layout of the unmanned tilt rotor aircraft provided by the invention has the advantages of capability of vertical take-off and landing, high lift-drag ratio, long endurance time, high hovering efficiency, small storage space and the like, and can be used for the pneumatic layout design of large and medium unmanned tilt rotor aircraft.
Description
Technical Field
The invention belongs to the field of overall design of unmanned aerial vehicles, and relates to an overall pneumatic layout of an unmanned tilt rotor aircraft.
Background
The tilt rotor aircraft is an aircraft which can vertically fly and can fly at high speed in a fixed wing mode, integrates the advantages of a helicopter and a fixed wing aircraft, and has the characteristics of capability of vertical take-off and landing, high flying speed, long voyage and the like. Because of the numerous advantages that tiltrotor aircraft have, tiltrotor aircraft, including unmanned tiltrotor aircraft and manned tiltrotor aircraft, are being studied in a number of countries, wherein the united states is in a leading position in the field of tiltrotor aircraft, and its developed V-22 tiltrotor aircraft has been deployed for many racks.
At present, due to the limitation of a plurality of factors, the tilt rotor aircraft has the problems of small wing aspect ratio and low lift drag.
Disclosure of Invention
The technical problem solved by the invention is as follows: the unmanned tilting rotor aircraft has the advantages that the overall pneumatic layout is provided, and the cruise lift-drag ratio is improved while the storage size is not increased.
An unmanned tiltrotor aircraft overall pneumatic layout comprising: the aircraft comprises a rotor wing, a tilting mechanism, wings, a fuselage, an engine cabin and a V tail;
the fuselage adopts a streamline shape, and the surfaces of the fuselage and the wings are in smooth transition;
the wing includes: an inner wing section and an outer wing section;
an engine cabin is arranged on the wing; the rotor wings are arranged on the wings through the tilting mechanisms; the V tail is arranged at the rear part of the fuselage;
the outer section wing is arranged outside the engine compartment.
When the helicopter flies in a helicopter mode, the rotor wing is operated by the tilting mechanism to be in a vertical state;
during fixed wing mode flight, the rotor is operated by the tilt mechanism to be in a horizontal state.
The rotor includes: three blades are uniformly distributed in the circumferential direction;
the blades can be folded, and the blades are folded inwards to be parallel to the direction of the wing when in storage.
The wing is an upper single wing, the span-chord ratio ranges from 10 to 15, and the wing can rotate around the center of the wing to be parallel to the fuselage.
The upper surface of the inner section wing is parallel to the horizontal plane, and the trailing edge of the inner section wing is provided with an aileron and a flap;
when flying in a helicopter mode, the ailerons and the flaps deflect downwards by 90 degrees, so that the interference of the rotor downwash and the wings is reduced;
during fixed wing mode flight, the ailerons and flaps are always horizontal.
The section of the outer section wing is trapezoidal, the oblique edge of the trapezoid deviates from the direction of the rotor wing, and meanwhile, the outer section wing can be bent downwards;
when the helicopter flies in a helicopter mode, the outer section of the wing is folded downwards, and the interference of the rotor wing wash-down flow and the wing is reduced.
The V-shaped tail forms a V-shaped included angle with an upward opening; and an elevator rudder is arranged on the rear edge of the V tail.
When the wing is stored, the blades of the rotor wing are folded to be parallel to the wings in the direction of the fuselage, the wings rotate to be longitudinally parallel to the fuselage, and the outer section wings are folded downwards.
The length of the radius of the folding position of the paddle is 0.2-0.35 times of the radius of the paddle.
Compared with the prior art, the invention has the beneficial effects that:
1) the invention provides an overall pneumatic layout of an unmanned tilt rotor aircraft, which has the advantages of capability of vertical take-off and landing, high lift-drag ratio, long navigation time and long navigation distance.
2) The rotor wing and the wing of the invention can be folded, and the storage space is small.
Drawings
FIG. 1 is an isometric view of a fixed wing mode of the present invention;
FIG. 2 is a schematic top view of a fixed wing version of the present invention;
FIG. 3 is an isometric view of a helicopter mode of the present invention;
FIG. 4 is a schematic top view of a helicopter of the present invention;
figure 5 is an isometric view of the present invention in a storage folded state.
Detailed Description
As shown in fig. 1, the invention provides an overall aerodynamic layout of an unmanned tilt rotor aircraft, a fuselage 4 adopts a streamline shape and is in fusion transition with wings 3, the wings 3 comprise an inner section wing 5 and an outer section wing 7, an engine compartment 6, a rotor 1 and a tilt mechanism 2 are arranged on the wings 3 in a clinging manner, and a V-tail 11 is arranged at the rear part of the fuselage 4.
The utility model provides an unmanned rotorcraft overall pneumatic overall arrangement that verts, rotor 1, mechanism 2, wing 3, fuselage 4, engine compartment 6 and V tail 11 vert. The fuselage 4 adopts a streamline shape, and the surfaces of the fuselage 4 and the wings 3 are in smooth transition and fusion transition; the wing 3 comprises: an inner wing section 5 and an outer wing section 7; an engine compartment 6 is arranged on the wing 3; the rotor wing 1 is arranged on the wing 3 through the tilting mechanism 2; the V-tail 5 is arranged at the rear part of the fuselage 4; the outer wing section 7 is disposed outside the engine compartment 6.
As shown in fig. 3 and 4, in helicopter mode flight, rotor 1 is operated in vertical position by tilt mechanism 2;
as shown in fig. 1 and 2, in fixed-wing mode flight, rotor 1 is operated in a horizontal position by tilt mechanism 2.
Each set of rotor 1 comprises: three blades 8 are evenly distributed in the circumferential direction. The blades 8 are foldable, and in storage the blades 8 are folded inwards to be parallel to the direction of the wing 3.
The wing 3 is an upper single wing, the span-chord ratio ranges from 10 to 15, and the wing 3 can rotate around the center of the wing 3 to be parallel to the fuselage 4.
The inner section of the wing 5 is a straight wing, namely the upper surface of the inner section of the wing 5 is parallel to the horizontal plane, and the trailing edge of the inner section of the wing 5 is provided with an aileron 9 and a flap 10; when flying in a helicopter mode, the ailerons 9 and the flaps 10 deflect downwards by about 90 degrees, so that the interference of the downwash of the rotor 1 and the wings 3 is reduced; in fixed wing mode flight, the ailerons 9 and flaps 10 are always horizontal.
The cross-section of outer section wing 7 is trapezoidal, and trapezoidal hypotenuse deviates from rotor 1 direction, and simultaneously, outer section wing 7 can buckle downwards. Namely, the outer wing section 7 is tapered to be turned upside down and can be folded downwards.
When flying in helicopter mode, the outer section of the wing 7 is folded downwards, reducing the interference of the downwash of the rotor 1 and the wing 3.
The V tail 11 is an outward-inclined double V tail, namely the V tail 11 forms a V-shaped included angle with an upward opening; on the rear edge of the V-tail 11 is arranged an elevator rudder 12.
As shown in fig. 5, during storage, the blades 8 of the rotor 1 are folded to be parallel to the wings 3 in the direction of the fuselage 4, the wings 3 are rotated to be longitudinally parallel to the fuselage 4, and the outer wings 7 are folded downward.
The length of the radius of the folding position of the paddle 8 is 0.2-0.35 times of the radius of the paddle 8.
Examples
As shown in fig. 1 and 3, the rotor 1 is operated by the tilt mechanism 2 to be in a vertical state in the helicopter mode flight and to be in a horizontal state in the fixed wing mode flight.
As shown in fig. 1 and 5, each rotor 1 comprises three blades 8, and the blades 8 can be folded to be parallel to the direction of the wing 1 when stored.
As shown in figures 1 and 5, the wing 3 is an upper single wing, has an aspect ratio of 10-15, and can rotate around the center of the wing 3 to be parallel to the fuselage 4.
As shown in fig. 1 and 3, the inner-section wing 5 is a straight wing and is provided with an aileron 9 and a flap 10, the aileron 9 and the flap 10 deflect downwards by about 90 degrees in helicopter mode flight, so that the interference between the downwash flow of the rotor 1 and the wing 3 is reduced, and the aileron 9 and the flap 10 are initially in a horizontal state in fixed-wing flight.
As shown in fig. 1 and 3, the outer wing section 7 is tapered upwards and backwards and can be folded downwards, and the outer wing section 7 is folded downwards during helicopter mode flight, so that the interference of the downwash of the rotor 1 and the wing 3 is reduced.
As shown in FIG. 1, the V-tail 11 is a camber double V-tail, and an elevator rudder 12 is arranged on the V-tail 5 and is used for longitudinal and heading control during fixed wing mode flight.
When the rotor wing is stored as shown in fig. 5, the blades 8 of the rotor wing 1 are folded to be parallel to the wings 3 in the direction of the fuselage 4, the wings 3 are rotated to be longitudinally parallel to the fuselage 4, and the outer wings 7 are folded downwards.
The folding position of the blade 8 is positioned between the blade radius of 0.2R and 0.35R.
The invention is described as an example of a specific application in this field, but any person skilled in the art should understand that the invention includes but is not limited to this example, and any modification made on the basis of this example is within the scope of protection of intellectual and technical property rights of the invention.
Claims (9)
1. The utility model provides an unmanned rotorcraft overall pneumatic layout that verts which comprises: the aircraft comprises a rotor wing (1), a tilting mechanism (2), wings (3), a fuselage (4), an engine cabin (6) and a V-tail (11);
the fuselage (4) adopts a streamline shape, and the surfaces of the fuselage (4) and the wings (3) are in smooth transition;
the wing (3) comprises: an inner section wing (5) and an outer section wing (7);
an engine cabin (6) is arranged on the wing (3); the rotor wing (1) is arranged on the wing (3) through the tilting mechanism (2); the V-tail (5) is arranged at the rear part of the machine body (4);
the outer section of the wing (7) is arranged outside the engine compartment (6).
2. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 1, wherein:
when the helicopter flies in a helicopter mode, the rotor wing (1) is operated to be in a vertical state through the tilting mechanism (2);
during fixed wing mode flight, the rotor (1) is operated by the tilting mechanism (2) to be in a horizontal state.
3. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 2, wherein: the rotor (1) comprises: three blades (8) are uniformly distributed in the circumferential direction;
the blades (8) can be folded, and the blades (8) are folded inwards to be parallel to the direction of the wing (3) during storage.
4. An unmanned tiltrotor aircraft overall aerodynamic configuration according to any one of claims 1 to 3, wherein: the wing (3) is an upper single wing, the span-chord ratio value range is 10-15, and the wing (3) can rotate around the center of the wing (3) to be parallel to the fuselage (4).
5. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 4, wherein: the upper surface of the inner section wing (5) is parallel to the horizontal plane, and the trailing edge of the inner section wing (5) is provided with an aileron (9) and a flap (10);
when flying in a helicopter mode, the ailerons (9) and the flaps (10) deflect downwards by 90 degrees, so that the interference of the downwash of the rotor (1) and the wings (3) is reduced;
during the fixed wing mode of flight, the ailerons (9) and flaps (10) are always horizontal.
6. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 5, wherein: the cross-section of outer section wing (7) is trapezoidal, and trapezoidal hypotenuse deviates from rotor (1) direction, and simultaneously, outer section wing (7) can buckle downwards.
When the helicopter flies in a helicopter mode, the outer section of the wing (7) is folded downwards, so that the interference of the downwash of the rotor (1) and the wing (3) is reduced.
7. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 1, wherein: the V-shaped tail (11) forms a V-shaped included angle with an upward opening; an elevator rudder (12) is arranged on the rear edge of the V tail (11).
8. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 6, wherein: during storage, paddle (8) of rotor (1) are folded to being parallel with wing (3) to fuselage (4) direction, wing (3) are rotatory to being vertically parallel with fuselage (4), outer section wing (7) fold down.
9. An unmanned tiltrotor aircraft overall aerodynamic configuration according to claim 8, wherein: the length of the radius of the folding position of the paddle (8) is 0.2-0.35 times of the radius of the paddle (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010879148.2A CN112009675A (en) | 2020-08-27 | 2020-08-27 | Unmanned rotorcraft overall pneumatic layout that verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010879148.2A CN112009675A (en) | 2020-08-27 | 2020-08-27 | Unmanned rotorcraft overall pneumatic layout that verts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112009675A true CN112009675A (en) | 2020-12-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010879148.2A Pending CN112009675A (en) | 2020-08-27 | 2020-08-27 | Unmanned rotorcraft overall pneumatic layout that verts |
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| Country | Link |
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| CN (1) | CN112009675A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113716033A (en) * | 2021-09-03 | 2021-11-30 | 中电科芜湖通用航空产业技术研究院有限公司 | Multipurpose airplane |
| CN115092389A (en) * | 2022-06-22 | 2022-09-23 | 上海电气集团股份有限公司 | Tilt-rotor duck type vertical take-off and landing unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| US20180079499A1 (en) * | 2016-09-19 | 2018-03-22 | Bell Helicopter Textron Inc. | Storage Modes for Tiltrotor Aircraft |
| CN111169631A (en) * | 2020-02-21 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Rotor unmanned aerial vehicle verts |
| WO2020136460A1 (en) * | 2018-12-28 | 2020-07-02 | Leonardo S.P.A. | Convertiplane and related control method |
| CN212951107U (en) * | 2020-08-27 | 2021-04-13 | 彩虹无人机科技有限公司 | Unmanned rotorcraft overall pneumatic layout that verts |
-
2020
- 2020-08-27 CN CN202010879148.2A patent/CN112009675A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| US20180079499A1 (en) * | 2016-09-19 | 2018-03-22 | Bell Helicopter Textron Inc. | Storage Modes for Tiltrotor Aircraft |
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| WO2020136460A1 (en) * | 2018-12-28 | 2020-07-02 | Leonardo S.P.A. | Convertiplane and related control method |
| CN111169631A (en) * | 2020-02-21 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Rotor unmanned aerial vehicle verts |
| CN212951107U (en) * | 2020-08-27 | 2021-04-13 | 彩虹无人机科技有限公司 | Unmanned rotorcraft overall pneumatic layout that verts |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113716033A (en) * | 2021-09-03 | 2021-11-30 | 中电科芜湖通用航空产业技术研究院有限公司 | Multipurpose airplane |
| CN113716033B (en) * | 2021-09-03 | 2023-12-05 | 中电科芜湖通用航空产业技术研究院有限公司 | Multipurpose aircraft |
| CN115092389A (en) * | 2022-06-22 | 2022-09-23 | 上海电气集团股份有限公司 | Tilt-rotor duck type vertical take-off and landing unmanned aerial vehicle |
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