CN105151273A - Multi-propeller airplane - Google Patents

Multi-propeller airplane Download PDF

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Publication number
CN105151273A
CN105151273A CN201510721351.6A CN201510721351A CN105151273A CN 105151273 A CN105151273 A CN 105151273A CN 201510721351 A CN201510721351 A CN 201510721351A CN 105151273 A CN105151273 A CN 105151273A
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CN
China
Prior art keywords
wing
rotor
composite wing
composite
plastic
Prior art date
Application number
CN201510721351.6A
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Chinese (zh)
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CN105151273B (en
Inventor
王志成
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佛山市神风航空科技有限公司
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Priority to CN201510721351.6A priority Critical patent/CN105151273B/en
Publication of CN105151273A publication Critical patent/CN105151273A/en
Application granted granted Critical
Publication of CN105151273B publication Critical patent/CN105151273B/en

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Abstract

The invention relates to a multi-propeller airplane and belongs to the technical field of aircrafts. The multi-propeller airplane comprises an airplane body, a left composite aerofoil, a right composite aerofoil, an empennage and an undercarriage. An operation system and airplane-borne equipment are assembled in the airplane body. The empennage is located at the tail of the airplane body and comprises a horizontal empennage body and a perpendicular empennage body. A wheel type structure or a skidding and wheel type combined structure is adopted in the undercarriage. The left composite aerofoil and the right composite aerofoil are of the same structure and are symmetrically installed on the left side and the right side of the airplane body. Two or three or four rotor wings are assembled in the left composite aerofoil, and each rotor wing is driven by an engine. Aerofoil panels of the left composite aerofoil comprise the front aerofoil panel and the rear aerofoil panel, and the front aerofoil panel and the rear aerofoil panel can rotate around a wing shaft in a deflecting mode. All the rotor wings are located below the wing shaft. The multi-propeller airplane needs a small taking-off and landing field and can perpendicularly take off and land. Generated lifting force is large, and the multi-propeller airplane is safe, stable and flexible.

Description

A kind of many oars aircraft
Technical field
A kind of many oars aircraft, belongs to vehicle technology field, particularly relates to a kind of many oars aircraft.
Background technology
Traditional taking off and land needs comparatively long runway, can not vertical takeoff and landing, also inconvenient Ultra-Low Speed or hovering flight, more can not realize retreating flight, and comparatively short take-off and landing is also very difficult.Traditional helicopter energy consumption is large, and efficiency is low, and safety and stability is not high.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional aircraft and helicopter, inventing a kind of short take-off and landing that facilitates even can many oars aircraft of efficient safety and stability of vertical takeoff and landing.
A kind of many oars aircraft, comprises fuselage, left composite wing, right composite wing, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.Empennage is positioned at the afterbody of fuselage, and empennage comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevating rudder, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear adopts wheeled construction or sled and wheeled unitized construction.
The structure of left composite wing is: left composite wing comprises front flaps, rear plastic, wing axle, outer rotor, interior rotor, outer driving engine, intrinsic motivation and support.The rear end of front flaps is connected with wing axle, and front flaps can deflect up and down around wing axle.The front end of rear plastic is connected with wing axle, and rear plastic can deflect up and down around wing axle.Relative level face, the maximum angle that front flaps upward deflects is no more than 45 °, and the maximum angle that front flaps deflects down is no more than 30 °; The maximum angle that rear plastic upward deflects is no more than 45 °, and the maximum angle that rear plastic deflects down is no more than 30 °.Interior rotor near fuselage installation, install away from fuselage by outer rotor.The diameter of outer rotor is not more than the diameter of interior rotor.Outer driving engine and intrinsic motivation are arranged on the support that is all connected with fuselage and wing axle, and outer driving engine provides power for outer rotor, and intrinsic motivation provides power for interior rotor.Wing axle horizontal arrangement.The line of the centre of gration of interior rotor and the centre of gration of outer rotor is in the below of wing axle.The plane of rotation of outer rotor and the plane of rotation of interior rotor coplanar.The plane of rotation of interior rotor tilts slightly toward front lower place or is horizontal, and the angle of the plane of rotation of interior rotor and the forward downward of horizontal surface is not more than 10 °.Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor and rear plastic is greater than 10mm.The chord length of rear plastic is equal to or slightly greater than the radius of rotation of interior rotor.The chord length of front flaps is equal to or slightly greater than the radius of rotation of interior rotor.The length of left composite wing is greater than the diameter of interior rotor and the diameter sum of outer rotor.
Rotor in the present invention's many oars aircraft and the quantity of driving engine also have six covers and eight covers, two kinds of forms except four covers: the first form is: three rotors are housed and supporting three driving engines in left composite wing, these three rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of three rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.The second form is: four rotors are housed and supporting four driving engines in left composite wing, these four rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of four rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.
In order to improve manoevreability, will leave a blank in the middle of the canned paragraph of the vertical tail of described many oars aircraft, longitudinally vertically arranging installation electric propeller in this position of leaving a blank, when facilitating described hang or low speed like this, wide-angle turns to.
The principle of work of a kind of many oars of this invention aircraft is: as the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected downwards to extreme lower position, the front flaps of the front flaps of left composite wing and right composite wing is all deflected upward into extreme higher position, and alighting gear is adjusted to wheeled state, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize advance rolling start; As the front flaps of the rear plastic of the rear plastic of left composite wing, right composite wing, the front flaps of left composite wing and right composite wing is all deflected upward into extreme higher position, described aircraft can realize taking off vertically; As the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected upward into extreme higher position, the front flaps of the front flaps of left composite wing and right composite wing is all deflected downwards to extreme lower position, described aircraft can realize retreating flight.Adjust the deflection angle of the front flaps of the rear plastic of left composite wing, the rear plastic of right composite wing, the front flaps of left composite wing and right composite wing and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Pitching and the course of described aircraft is controlled by empennage.Compare with traditional aircraft, the landing site of the present invention's many oars aircraft requirements is little, and can vertical lift.Compare with traditional helicopter, the present invention's many oars aircraft is due to the existence of left composite wing and right composite wing, and the lift that described aircraft produces is comparatively large, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because the rotor of left composite wing and the corresponding rotor of right composite wing turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, front fly or after can improve the flow field of fin upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor, described air maneuver is flexible.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of many oars aircraft of the present invention, and Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on a left side for the left composite wing be exaggerated, and Fig. 4 is the schematic top plan view of Fig. 3.
In figure, 1-fuselage, the left composite wing of 2-, the right composite wing of 3-, 4-empennage, 5-alighting gear; The component belonging to left composite wing 2 comprises: 21-front flaps, 22-rear plastic, 23-wing axle, the outer rotor of 24-, rotor in 25-, the outer driving engine of 26-, 27-intrinsic motivation, 28-support.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of many oars aircraft, comprised fuselage 1, left composite wing 2, right composite wing 3, empennage 4 and alighting gear 5.Control system and airborne equipment is furnished with in fuselage 1.Left composite wing 2 is identical with right composite wing 3 structure, and their symmetries are installed on the left and right sides of fuselage 1.Empennage 4 is positioned at the afterbody of fuselage 1, and empennage 4 comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevating rudder, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear 5 adopts wheeled construction.The structure of left composite wing 2 is: left composite wing 2 comprises front flaps 21, rear plastic 22, wing axle 23, outer rotor 24, interior rotor 25, outer driving engine 26, intrinsic motivation 27 and support 28.The rear end of front flaps 21 is connected with wing axle 23, and front flaps 21 can deflect around wing axle about 23.The front end of rear plastic 22 is connected with wing axle 23, and rear plastic 22 can deflect around wing axle about 23.The leading edge of front flaps 21 is perfectly round, and the trailing edge of rear plastic 22 is sharp-pointed.Relative level face, the maximum angle that front flaps 21 upward deflects is 20 °, and the maximum angle that front flaps 21 deflects down is 15 °; The maximum angle that rear plastic 22 upward deflects is 20 °, and the maximum angle that rear plastic 22 deflects down is 15 °.Interior rotor 25 to be installed and outer rotor 24 is installed away from fuselage 1 near fuselage 1.The diameter of outer rotor 24 is not more than the diameter of interior rotor 25.Outer driving engine 26 and intrinsic motivation 27 are arranged on the support 28 that is all connected with fuselage 1 and wing axle 23, and outer driving engine 26 provides power for outer rotor 24, and intrinsic motivation 27 provides power for interior rotor 25.Wing axle 23 horizontal arrangement.The line of the centre of gration of interior rotor 25 and the centre of gration of outer rotor 24 is in immediately below wing axle 23.The plane of rotation of outer rotor 24 and the plane of rotation of interior rotor 25 are all horizontal.Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor 25 and rear plastic 22 is greater than 10mm.The chord length of rear plastic 22 is a bit larger tham the radius of rotation of interior rotor 25.The chord length of front flaps 21 is a bit larger tham the radius of rotation of interior rotor 25.The length of left composite wing 2 is greater than the diameter of interior rotor 25 and the diameter sum of outer rotor 24.
The present invention's many oars aircraft produces beneficial effect like this: as the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected downwards to extreme lower position, the front flaps 21 of left composite wing 2 and the front flaps of right composite wing 3 are all deflected upward into extreme higher position, and alighting gear 5 is adjusted to wheeled state, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize rolling start; As the front flaps of the rear plastic of the rear plastic 22 of left composite wing 2, right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3 is all deflected upward into extreme higher position, described aircraft can realize taking off vertically.As the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected upward into extreme higher position, the front flaps 21 of left composite wing 2 and the front flaps of right composite wing 3 are all deflected downwards to extreme lower position, and described aircraft can realize retreating flight.Adjust the deflection angle of the front flaps of the rear plastic 22 of left composite wing 2, the rear plastic of right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3 and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Pitching and the course of described aircraft is controlled by empennage 4.Compare with traditional aircraft, the present invention's many oars takeoff and landing place is little, and can vertical lift.Compare with traditional helicopter, the present invention's many oars aircraft is due to the existence of left composite wing 2 and right composite wing 3, the lift that described aircraft produces is larger, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because the rotor of left composite wing 2 and the corresponding rotor of right composite wing 3 turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, front fly or after can improve the flow field of fin upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor, described air maneuver is flexible.The rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 can also play wing flap and the aileron of traditional aircraft.Therefore described many oars air maneuver is flexible.

Claims (7)

1. the aircraft of oar more than, is characterized in that: comprise fuselage (10), left composite wing (2), right composite wing (3), empennage (4) and alighting gear (5); Fuselage is furnished with control system and airborne equipment in (1); Left composite wing (2) is identical with right composite wing (3) structure, and their symmetries are installed on the left and right sides of fuselage (1); Empennage (4) is positioned at the afterbody of fuselage (1), and empennage (4) comprises tailplane and vertical tail; Alighting gear (5) adopts wheeled construction or sled and wheeled unitized construction; The structure of left composite wing (2) is: left composite wing (2) comprises front flaps (21), rear plastic (22), wing axle (23), outer rotor (24), interior rotor (25), outer driving engine (26), intrinsic motivation (27) and support (28); The rear end of front flaps (21) is connected with wing axle (23), and front flaps (21) can deflect up and down around wing axle (23); The front end of rear plastic (22) is connected with wing axle (23), and rear plastic (22) can deflect up and down around wing axle (23); Interior rotor (25) near fuselage (1) installation, install away from fuselage (1) by outer rotor (24); The diameter of outer rotor (24) is not more than the diameter of interior rotor (25); Outer driving engine (26) and intrinsic motivation (27) are arranged on the support (28) that is all connected with fuselage (1) and wing axle (23), and outer driving engine (26) provides power for outer rotor (24), and intrinsic motivation (27) provides power for interior rotor (25); Wing axle (23) horizontal arrangement; The line of the centre of gration of interior rotor (25) and the centre of gration of outer rotor (24) is in the below of wing axle (23); The plane of rotation of outer rotor (24) and the plane of rotation of interior rotor (25) coplanar; The plane of rotation of interior rotor (25) tilts slightly toward front lower place or is horizontal; Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor (25) and rear plastic (22) is greater than 10mm; The chord length of rear plastic (22) is equal to or slightly greater than the radius of rotation of interior rotor (25); The chord length of front flaps (21) is equal to or slightly greater than the radius of rotation of interior rotor (25); The length of left composite wing (2) is greater than the diameter of interior rotor (25) and the diameter sum of outer rotor (24).
2. one many oars aircraft according to claim 1, it is characterized in that: the leading edge of front flaps (21) is perfectly round, the trailing edge of rear plastic (22) is sharp-pointed; Relative level face, the maximum angle that front flaps (21) upward deflects is no more than 45 °, and the maximum angle that front flaps (21) deflects down is no more than 30 °; The maximum angle that rear plastic (22) upward deflects is no more than 45 °, and the maximum angle that rear plastic (22) deflects down is no more than 30 °; The angle of the plane of rotation of interior rotor (25) and the forward downward of horizontal surface is not more than 10 °.
3. one many oars aircraft according to claim 2, is characterized in that: relative level face, and the maximum angle that front flaps (21) upward deflects is 20 °, and the maximum angle that front flaps (21) deflects down is 15 °; The maximum angle that rear plastic (22) upward deflects is 20 °, and the maximum angle that rear plastic (22) deflects down is 15 °.
4. one many oars aircraft according to claim 1, is characterized in that: the line of the centre of gration of interior rotor (25) and the centre of gration of outer rotor (24) is in immediately below wing axle (23).
5. the one many oars aircraft according to claim 1 or 2 or 3 or 4, it is characterized in that: the quantity of rotor and driving engine also has the form of six covers except four covers: three rotors are housed and supporting three driving engines in left composite wing, these three rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of three rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.
6. the one many oars aircraft according to claim 1 or 2 or 3 or 4, it is characterized in that: the quantity of rotor and driving engine also has the form of eight covers except four covers: four rotors are housed and supporting four driving engines in left composite wing, these four rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of four rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.
7. the one many oars aircraft according to claim 1 or 2 or 3 or 4, is characterized in that: leave a blank in the middle of the canned paragraph of vertical tail, and this position of leaving a blank longitudinally vertically is arranged and is installed with an electric propeller.
CN201510721351.6A 2015-10-30 2015-10-30 A kind of more paddle aircrafts CN105151273B (en)

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CN201510721351.6A CN105151273B (en) 2015-10-30 2015-10-30 A kind of more paddle aircrafts

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CN105151273A true CN105151273A (en) 2015-12-16
CN105151273B CN105151273B (en) 2018-05-01

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4789115A (en) * 1986-08-29 1988-12-06 Theodore Koutsoupidis VTOL aircraft
JPH05155384A (en) * 1991-12-04 1993-06-22 Mitsubishi Heavy Ind Ltd Wing stalling preventive system for airplane
CN101607600A (en) * 2008-12-12 2009-12-23 于江 Solar-wind hybrid power airplane
US20100148011A1 (en) * 2008-11-12 2010-06-17 Sanderson Terry M Telescoping structure and method
CN103287569A (en) * 2013-05-15 2013-09-11 西北工业大学 Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering
JP2014065477A (en) * 2012-09-24 2014-04-17 Takashi Sasaki Vertical and horizontal takeoff and landing aircraft
CN204452934U (en) * 2015-02-05 2015-07-08 仉军 The double mode aircraft of rotor, fixed-wing
CN205131628U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Many oars aircraft

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4789115A (en) * 1986-08-29 1988-12-06 Theodore Koutsoupidis VTOL aircraft
JPH05155384A (en) * 1991-12-04 1993-06-22 Mitsubishi Heavy Ind Ltd Wing stalling preventive system for airplane
US20100148011A1 (en) * 2008-11-12 2010-06-17 Sanderson Terry M Telescoping structure and method
CN101607600A (en) * 2008-12-12 2009-12-23 于江 Solar-wind hybrid power airplane
JP2014065477A (en) * 2012-09-24 2014-04-17 Takashi Sasaki Vertical and horizontal takeoff and landing aircraft
CN103287569A (en) * 2013-05-15 2013-09-11 西北工业大学 Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering
CN204452934U (en) * 2015-02-05 2015-07-08 仉军 The double mode aircraft of rotor, fixed-wing
CN205131628U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Many oars aircraft

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Address before: Foshan City, Guangdong province 528500 city streets Gaoming District No. 78 Jiangwan Road, room 402 Fu Wan

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Address after: 313000 1-C, building 1, No. 656, Qixing Road, high tech Zone, Wuxing District, Huzhou City, Zhejiang Province

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Patentee before: Huzhou xinbeilian Network Technology Co.,Ltd.