CN113335517A - Double-fuselage tandem rotor wing composite wing aircraft layout - Google Patents
Double-fuselage tandem rotor wing composite wing aircraft layout Download PDFInfo
- Publication number
- CN113335517A CN113335517A CN202110905789.5A CN202110905789A CN113335517A CN 113335517 A CN113335517 A CN 113335517A CN 202110905789 A CN202110905789 A CN 202110905789A CN 113335517 A CN113335517 A CN 113335517A
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- fuselage
- wing
- fuselages
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- aircraft
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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
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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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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
- B64C2001/0045—Fuselages characterised by special shapes
Abstract
The invention discloses a double-fuselage tandem rotor wing composite aircraft layout, which comprises two parallel fuselages, wherein the side surfaces of the two fuselages are connected through a central wing, the tail parts of the fuselages are provided with power devices, the side surfaces of the two fuselages are provided with wings, the tail parts of the two fuselages are connected through tail wings, the tail wings are of an arch structure, a plurality of rotor wings are arranged above each fuselage, the rotor wings are uniformly distributed, the central wing is a rectangular wing, and the plane of the central wing is vertical to the symmetrical planes of the two fuselages. The invention fully utilizes the rigidity and the strength of the double bodies, enhances the vertical take-off and landing stability of large and heavy composite wing aircrafts, is beneficial to the flight control of the aircrafts, and increases the threshold value of the body bearable lift force compared with the design of the traditional rotor wing support arm.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a double-fuselage tandem rotor wing composite wing aircraft layout.
Background
The composite wing aircraft capable of taking off and landing vertically has the characteristics and advantages of a multi-rotor aircraft and a fixed wing aircraft, can realize vertical take-off and landing by utilizing the multi-rotor aircraft, and can realize high-speed and high-efficiency cruising flight in the air by utilizing the fixed wing. The double-fuselage configuration can realize that two groups of tandem rotors are respectively arranged on two aircraft fuselages, thereby not only enhancing the structural strength and stability of the aircraft, but also being beneficial to increasing the mission load of the aircraft, and being widely applied to the military and civil fields. The research on the layout design of the double-fuselage composite wing of the vertical take-off and landing aircraft has important theoretical and application values.
In the prior art, the small and light composite wing aircraft generally adopts a four-rotor wing/multi-rotor wing layout to realize vertical take-off and landing, and the rotor wings are connected with the wings through support arms, so that the structural layout is difficult to apply the large and heavy composite wing aircraft, because the large aircraft has large weight and large size, the large support arms have poor bending moment resistance, and the support arms deform to cause the rotor wing support arms to emit flutter to influence the flight stability of the aircraft during vertical take-off and landing.
Disclosure of Invention
In view of the above-mentioned deficiencies of the prior art, the present invention provides a dual-fuselage tandem rotor composite wing aircraft layout capable of effectively increasing the maximum takeoff and landing weight and the payload of the aircraft.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the utility model provides a double-fuselage tandem rotor wing composite aircraft overall arrangement, it includes two fuselages that parallel, the side of two fuselages is passed through the central wing and is connected, the afterbody of fuselage is provided with power device, the side of two fuselages is provided with the wing, the afterbody of two fuselages passes through the fin and connects, the fin is domes, the top of every fuselage all is provided with a plurality of rotors, a plurality of rotor evenly distributed, the central wing is the rectangle wing, the plane of central wing place is perpendicular with the plane of symmetry of two fuselages.
Further, the fuselage is long body streamline form appearance, and the cross section of fuselage is oval, and the fuselage head of fuselage sets up to half ellipsoid structure, fuselage head and fuselage smooth connection.
Further, the upper end of fuselage is provided with a plurality of rotors along length direction, and a plurality of rotors are even tandem symmetric distribution on two fuselages.
Furthermore, the tail part of the machine body is provided with a mounting plane, the size of the mounting plane is smaller than the size of the cross section of the machine body, the machine body is connected with the mounting plane through a smooth curved surface, a propeller is mounted outside the mounting plane, and the propeller is connected with an engine arranged at the tail part of the machine body.
Furthermore, the tail wing comprises two inclined tail wing plates, one ends of the two tail wing plates are fixed on the machine body, and the other ends of the two tail wing plates are mutually connected.
The invention has the beneficial effects that: the invention fully utilizes the rigidity and the strength of the double bodies, enhances the vertical take-off and landing stability of large and heavy composite wing aircrafts, is beneficial to the flight control of the aircrafts, and increases the threshold value of the body which can bear the lift force compared with the design of the traditional rotor wing support arm; on the other hand, the invention fully utilizes the characteristics of large volume and large capacity of the double aircraft bodies, and compared with the single aircraft body layout of the traditional composite wing aircraft, the invention not only improves the size and the weight of the loadable mission load, but also can place the mission load in the aircraft body and reduce the flight resistance caused by the external load of the aircraft body.
The double bodies are slender streamline bodies, so that the flight resistance during cruising can be reduced, and the cruising efficiency is improved; the fuselage cross-section is oval and direction of height is oval major axis, can reduce the mutual interference of fuselage and tandem rotor slipstream, increases the effective lift of tandem rotor, improves the operating efficiency of tandem rotor.
The invention increases the internal space of the composite wing aircraft, increases the size and the volume of the load of the built-in task, avoids the loss of the flight performance of the aircraft caused by the externally-hung load, improves the range and the time of the aircraft, and is beneficial to the aircraft to carry out harder tasks.
Drawings
Fig. 1 is a perspective view of a double-fuselage tandem rotor wing composite aircraft layout.
Fig. 2 is a structural view of the body.
Fig. 3 is a structural view of the rear wing.
The aircraft comprises an aircraft body 1, an aircraft body 2, a central wing 3, an aircraft body head 4, a rotor wing 5, an aircraft wing 6, a tail wing plate 7, an aircraft body tail 8, a curved surface 9, a propeller 10 and an installation plane.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
As shown in fig. 1 to 3, the double-fuselage tandem rotor composite wing aircraft layout of the scheme includes two fuselages 1 arranged in parallel, the sides of the two fuselages 1 are connected through a central wing 2, the tail of the fuselage 1 is provided with a power device, the sides of the two fuselages 1 are provided with wings 5, the tails of the two fuselages 1 are connected through a tail wing, the tail wing is of an arch structure, a plurality of rotors 4 are arranged above each fuselage 1, the rotors 4 are uniformly distributed, the central wing 2 is a rectangular wing, and the plane where the central wing 2 is located is perpendicular to the symmetric planes of the two fuselages 1.
The fuselage 1 is the streamlined appearance of slender bodies, and the cross section of fuselage 1 is oval, and the fuselage head 3 front end of fuselage 1 sets up to half ellipsoid structure, fuselage head 3 and fuselage 1 smooth connection. The upper end of fuselage 1 is provided with a plurality of rotors 4 along length direction, and a plurality of rotors 4 even tandem symmetric distribution are on two fuselages 1.
The tail part 7 of the fuselage 1 is provided with a mounting plane 10, the size of the mounting plane 10 is smaller than the size of the cross section of the fuselage 1, the fuselage 1 is connected with the mounting plane 10 through a smooth curved surface 8, the mounting plane 10 is provided with a propeller 9, and the propeller 9 is connected with an engine arranged in the tail part 7 of the fuselage.
The empennage comprises two inclined empennage plates, one ends of the two empennages are fixed on the machine body 1, and the other ends of the two empennages are connected with each other.
The invention fully utilizes the rigidity and the strength of the double bodies, enhances the vertical take-off and landing stability of large and heavy composite wing aircrafts, is beneficial to the flight control of the aircrafts, and increases the threshold value of the body 1 capable of bearing the lift force compared with the design of the traditional rotor wing support arm; on the other hand, the invention fully utilizes the characteristics of large volume and large capacity of the double aircraft bodies, and compared with the single aircraft body layout of the traditional composite wing aircraft, the invention not only improves the size and the weight of the loadable mission load, but also can place the mission load in the aircraft body 1 and reduce the flight resistance caused by the external load of the aircraft body 1.
The aircraft body 1 is a slender streamlined aircraft body, so that the flight resistance during cruising can be reduced, and the cruising efficiency is improved; the fuselage 1 cross-section is oval and the direction of height is oval major axis, can reduce the mutual interference of fuselage 1 and the tandem rotor 4 slipstream, increases the effective lift of tandem rotor 4, improves the operating efficiency of tandem rotor 4.
The invention increases the internal space of the composite wing aircraft, increases the size and the volume of the load of the built-in task, avoids the loss of the flight performance of the aircraft caused by the externally-hung load, improves the range and the time of the aircraft, and is beneficial to the aircraft to carry out harder tasks.
Claims (5)
1. The utility model provides a double fuselage tandem rotor composite wing aircraft overall arrangement, its characterized in that includes two fuselages that parallel, two the side of fuselage passes through the central authorities wing and connects, the afterbody of fuselage is provided with power device, two the side of fuselage is provided with the wing, two the afterbody of fuselage passes through the fin and connects, the fin is domes, every the top of fuselage all is provided with a plurality of rotors, and is a plurality of rotor evenly distributed, the central authorities wing is the rectangle wing, the plane of central authorities wing place is perpendicular with the plane of symmetry of two fuselages.
2. The twin-fuselage tandem rotor composite wing aircraft layout of claim 1, wherein the fuselage is in the shape of an elongated body with a streamlined outer shape, the cross section of the fuselage is elliptical, the nose of the fuselage is configured as a semi-ellipsoidal structure, and the nose of the fuselage is connected smoothly with the fuselage.
3. The twin-fuselage tandem rotor composite wing aircraft layout of claim 2, wherein the upper end of the fuselage is provided with a plurality of rotors along the length direction, and the plurality of rotors are evenly distributed symmetrically in tandem on both fuselages.
4. The twin-fuselage tandem rotor composite wing aircraft layout of claim 2, wherein the fuselage tail of the fuselage is provided with a mounting plane, the size of the mounting plane is smaller than the cross-sectional size of the fuselage, the fuselage is connected with the mounting plane through a smooth curved surface, the mounting plane is externally provided with a propeller, and the propeller is connected with an engine arranged at the fuselage tail.
5. The twin fuselage tandem rotor composite wing aircraft configuration of claim 1, wherein the tail wing comprises two inclined wing panels, both of which are fixed to the fuselage at one end and are connected to each other at the other end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110905789.5A CN113335517A (en) | 2021-08-09 | 2021-08-09 | Double-fuselage tandem rotor wing composite wing aircraft layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110905789.5A CN113335517A (en) | 2021-08-09 | 2021-08-09 | Double-fuselage tandem rotor wing composite wing aircraft layout |
Publications (1)
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| CN113335517A true CN113335517A (en) | 2021-09-03 |
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| CN202110905789.5A Pending CN113335517A (en) | 2021-08-09 | 2021-08-09 | Double-fuselage tandem rotor wing composite wing aircraft layout |
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2021
- 2021-08-09 CN CN202110905789.5A patent/CN113335517A/en active Pending
Patent Citations (18)
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| US20120318908A1 (en) * | 2011-06-20 | 2012-12-20 | Richard David Morris | VTOL twin fuselage amphibious aircraft with tilt-center wing, engine and rotor |
| CN202754143U (en) * | 2012-07-26 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Rotating engine vertical take-off and landing aircraft |
| US20140158815A1 (en) * | 2012-12-10 | 2014-06-12 | Joseph Raymond RENTERIA | Zero Transition Vertical Take-Off and Landing Aircraft |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| US20190382115A1 (en) * | 2017-03-02 | 2019-12-19 | Fly-R | Aircraft with variable-geometry rhombohedral wing structure |
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Application publication date: 20210903 |