CN105217028A - A kind of compound type autogiro - Google Patents

A kind of compound type autogiro Download PDF

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Publication number
CN105217028A
CN105217028A CN201510721225.0A CN201510721225A CN105217028A CN 105217028 A CN105217028 A CN 105217028A CN 201510721225 A CN201510721225 A CN 201510721225A CN 105217028 A CN105217028 A CN 105217028A
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CN
China
Prior art keywords
wing
port
handed
axle
plane
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CN201510721225.0A
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Chinese (zh)
Inventor
王志成
Original Assignee
佛山市神风航空科技有限公司
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Priority to CN201510721225.0A priority Critical patent/CN105217028A/en
Publication of CN105217028A publication Critical patent/CN105217028A/en

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Abstract

A kind of compound type autogiro, belongs to vehicle technology field, comprises fuselage, port wing, the left-handed wing, left axle, starboard wing, the dextrorotation wing, right axle, propelling unit, empennage and alighting gear.Port wing is identical with starboard wing structure, and symmetry is installed on the left and right sides of fuselage.The left-handed wing and the dextrorotation wing measure-alike, turn to contrary.The left-handed wing is arranged on below the middle part of port wing by bearing and left axle.The dextrorotation wing is arranged on below the middle part of starboard wing by bearing and right axle.The leading edge of port wing is higher than the trailing edge of port wing.The plane of rotation of the left-handed wing and the angle of port wing plane are greater than 10 °.The angle of port wing and horizontal surface is between 15 ~ 30 °, and the plane of rotation of the left-handed wing and the angle of horizontal surface are between 5 ~ 15 °.The turning circumference of the wing tip of the advanced left-handed wing of leading edge of port wing foremost, the rearmost end of the wing tip turning circumference of the delayed left-handed wing of trailing edge of port wing.More stable and the safety of described aircraft flight.

Description

A kind of compound type autogiro
Technical field
A kind of compound type autogiro, belongs to vehicle technology field, particularly relates to a kind of autogiro.
Background technology
Traditional cyclogyro only has a main rotor to produce lift, and safety and stability is not high.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional cyclogyro, invent a kind of compound type autogiro growing the safety and stability that distance is glided.
A kind of compound type autogiro, comprises fuselage, port wing, the left-handed wing, left axle, starboard wing, the dextrorotation wing, right axle, propelling unit, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Propelling unit adopts ducted fan to make propelling unit, is used as power with motor, adopts lithium cell or aluminum cell to power.Port wing is identical with starboard wing structure, and their symmetries are installed on the left and right sides of fuselage.The left-handed wing and the dextrorotation wing measure-alike, turn to contrary, one is levoform, and one is right-spiral.Left axle and right axle respectively symmetry are fixed on below the middle part of port wing and starboard wing.The left-handed wing is connected with left axle by bearing, and the dextrorotation wing is connected with right axle by bearing.The upper end of left axle is connected with port wing, and the lower end of left axle is connected with the left-handed wing by bearing.The upper end of right axle is connected with starboard wing, and the lower end of right axle is connected with the dextrorotation wing by bearing.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.The plane of rotation of the left-handed wing and the plane of rotation of the dextrorotation wing coplanar.Port wing and starboard wing coplanar.The plane of rotation of the left-handed wing and the angle of port wing plane are greater than 10 °, and the opening of this angle is towards front upper place.The leading edge of port wing is higher than the trailing edge of port wing, and the angle of port wing and horizontal surface is between 15 ~ 30 °, and the plane of rotation of the left-handed wing and the opening of horizontal surface angle are forward between 5 ~ 15 °.The turning circumference of the wing tip of the advanced left-handed wing of leading edge of port wing foremost, the rearmost end of the wing tip turning circumference of the delayed left-handed wing of trailing edge of port wing.The rearmost end of the wing tip turning circumference of the left-handed wing is greater than 10mm to the shortest distance of port wing.
The principle of work of a kind of compound type autogiro of this invention is: start propelling unit, described aircraft is driven to move ahead, because the angle of the left-handed wing and the dextrorotation wing and front incoming flow is 5 ~ 15 °, at effect bottom left rotor and the right rotor wing rotation generation lift of air-flow, simultaneously port wing and starboard wing also can produce lift, then described in take off.The speed of described aircraft advance is controlled by controlling angle of rake thrust.Pitching and the course of described aircraft is controlled by empennage.Compare with traditional cyclogyro, compound type autogiro of the present invention turns on the contrary due to the left-handed wing and the dextrorotation wing, and both sides can offset rotating torque, fly more stable; Due to the existence of port wing and starboard wing, the lift that described aircraft produces is comparatively large, if run out of steam longer distance of also gliding, can strive for more time docking facility or find safe landing point, safer like this.Because the left-handed wing and the dextrorotation wing are arranged on the below of port wing and starboard wing respectively, the flow field of port wing and starboard wing upper and lower surface can be improved when the left-handed wing and right rotor rotational, increase downwash flow, delay the burbling of the upper surface of port wing and starboard wing, raise the efficiency, lift coefficient is increased greatly, and the span reduces than conventional airplane just can produce same lift, so, the oad of aircraft just greatly reduces, take up room and diminish, structural strength increases, and manoevreability strengthens.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of compound type autogiro of the present invention; Fig. 2 is the schematic top plan view of Fig. 1.
In figure, 1-fuselage, 21-port wing, 22-starboard wing, the left-handed wing of 31-, the wing tip turning circumference of the left-handed wing of 311-, the 32-dextrorotation wing, the wing tip turning circumference of the 321-dextrorotation wing, the left axle of 41-, the right axle of 42-, 5-propelling unit, 6-empennage, 7-alighting gear.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of compound type autogiro, comprised fuselage 1, port wing 21, the left-handed wing 31, left axle 41, starboard wing 22, the dextrorotation wing 32, right axle 42, propelling unit 5, empennage 6 and alighting gear 7.Propelling unit 5 adopts ducted fan to make propelling unit, is used as power with motor, adopts lithium battery power supply.Port wing 21 is identical with starboard wing 22 structure, and their symmetries are installed on the left and right sides of fuselage 1.The left-handed wing 31 and the dextrorotation wing 32 measure-alike, turn to contrary, one is levoform, and one is right-spiral.Left axle 41 and right axle 42 respectively symmetry are fixed on below the middle part of port wing 21 and starboard wing 22.The left-handed wing 31 is connected with left axle 41 by bearing, and the dextrorotation wing 32 is connected with right axle 42 by bearing.The upper end of left axle 41 is connected with port wing 21, and the lower end of left axle 41 is connected with the left-handed wing 31 by bearing.The upper end of right axle 42 is connected with starboard wing 22, and the lower end of right axle 42 is connected with the dextrorotation wing 32 by bearing.Empennage 6 is positioned at the afterbody of fuselage 1, and empennage 6 comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevating rudder, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear 7 adopts first three point type wheeled construction.The plane of rotation of the left-handed wing 31 and the plane of rotation of the dextrorotation wing 32 coplanar.Port wing 21 and starboard wing 22 coplanar.The plane of rotation of the left-handed wing 31 and the opening of port wing 21 plane are 15 ° towards the angle of front upper place.The leading edge of port wing 21 is higher than the trailing edge of port wing 21, and port wing 21 is 20 ° with the angle of horizontal surface, and the plane of rotation of the left-handed wing 31 and the opening of horizontal surface angle are forward 5 °.The turning circumference of the wing tip of the advanced left-handed wing 31 of leading edge of port wing 21 foremost, the rearmost end of the wing tip turning circumference of the delayed left-handed wing 31 of trailing edge of port wing 21.The rearmost end of the wing tip turning circumference of the left-handed wing 31 is 15mm to the shortest distance of port wing 21.
Compound type autogiro of the present invention produces beneficial effect like this: start propelling unit, described aircraft is driven to move ahead, because the angle of the left-handed wing 31 and the dextrorotation wing 32 and front incoming flow is 5 °, at effect bottom left rotor 31 and the dextrorotation wing 32 rotation generation lift of air-flow, simultaneously port wing 21 and starboard wing 22 also can produce lift, then described in take off.The speed of described aircraft advance is controlled by the thrust controlling propelling unit 5.Pitching and the course of described aircraft is controlled by empennage 6.Compare with traditional cyclogyro, compound type autogiro of the present invention turns on the contrary due to the left-handed wing 31 and the dextrorotation wing 32, and both sides can offset rotating torque, fly more stable; Due to the existence of port wing 21 and starboard wing 22, the lift that described aircraft produces is comparatively large, if run out of steam longer distance of also gliding, can strive for more time docking facility or find safe landing point, safer like this.Because the left-handed wing 31 and the dextrorotation wing 32 are arranged on the below of port wing 21 and starboard wing 22 respectively, the left-handed wing 31 and the dextrorotation wing 32 can improve the flow field of port wing 21 and starboard wing 32 upper and lower surface when rotating, increase downwash flow, delay the burbling of the upper surface of port wing 21 and starboard wing 22, raise the efficiency, lift coefficient is increased greatly, the span reduces than conventional airplane just can produce same lift, so, the oad of aircraft just greatly reduces, take up room and diminish, structural strength increases, and manoevreability strengthens.

Claims (6)

1. a compound type autogiro, is characterized in that: comprise fuselage (1), port wing (21), the left-handed wing (31), left axle (41), starboard wing (22), the dextrorotation wing (32), right axle (42), propelling unit (5), empennage (6) and alighting gear (7); Port wing (21) is identical with starboard wing (22) structure, and their symmetries are installed on the left and right sides of fuselage (1); The left-handed wing (31) and the dextrorotation wing (32) measure-alike, turn to contrary; Left axle (41) and right axle (42) respectively symmetry are fixed on below the middle part of port wing (21) and starboard wing (22); The upper end of left axle (41) is connected with port wing (21), and the lower end of left axle (41) is connected with the left-handed wing (31) by bearing; The upper end of right axle (42) is connected with starboard wing (22), and the lower end of right axle (42) is connected with the dextrorotation wing (32) by bearing; Empennage (6) is positioned at the afterbody of fuselage (1), and empennage (6) comprises tailplane and vertical tail; Alighting gear (7) adopts wheeled construction; The plane of rotation of the left-handed wing (31) and the plane of rotation of the dextrorotation wing (32) coplanar; Port wing (21) and starboard wing (22) coplanar; The plane of rotation of the left-handed wing (31) and the opening of port wing (21) plane are greater than 10 ° towards the angle of front upper place; The leading edge of port wing (21) is higher than the trailing edge of port wing (21), and the angle of port wing (21) and horizontal surface is between 15 ~ 30 °, and the plane of rotation of the left-handed wing (31) and the opening of horizontal surface angle are forward between 5 ~ 15 °; The turning circumference of the wing tip of the advanced left-handed wing (31) of leading edge of port wing (21) foremost, the rearmost end of the wing tip turning circumference of the delayed left-handed wing (31) of trailing edge of port wing (21).
2. a kind of compound type autogiro according to claim 1, is characterized in that: the plane of rotation of the left-handed wing (31) and the opening of port wing (21) plane are 15 ° towards the angle of front upper place.
3. a kind of compound type autogiro according to claim 1, is characterized in that: port wing (21) is 20 ° with the angle of horizontal surface.
4. a kind of compound type autogiro according to claim 1, is characterized in that: the plane of rotation of the left-handed wing (31) and the opening of horizontal surface angle are forward 5 °.
5. a kind of compound type autogiro according to claim 1 or 2 or 3 or 4, is characterized in that: the rearmost end of the wing tip turning circumference of the left-handed wing (31) is greater than 10mm to the shortest distance of port wing (21).
6. a kind of compound type autogiro according to claim 1 or 2 or 3 or 4, is characterized in that: propelling unit (5) adopts ducted fan to make propelling unit, is used as power with motor, adopts lithium battery power supply.
CN201510721225.0A 2015-10-30 2015-10-30 A kind of compound type autogiro CN105217028A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106945822A (en) * 2017-03-09 2017-07-14 杭州米为科技有限公司 A kind of method and apparatus of the pitching of control aircraft
CN108860592A (en) * 2018-05-31 2018-11-23 江苏常探机器人有限公司 Single vortex-spraying type composite wing manned vehicle afterwards

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR735472A (en) * 1932-04-06 1932-11-09 Aircraft lifting device
US3139244A (en) * 1961-08-15 1964-06-30 Cooper B Bright Inflatable vtol aircraft
US20120280091A1 (en) * 2009-08-26 2012-11-08 Manuel Munoz Saiz Lift, propulsion and stabilising system for vertical take-off and landing aircraft
CN204452934U (en) * 2015-02-05 2015-07-08 仉军 The double mode aircraft of rotor, fixed-wing
WO2015143093A2 (en) * 2014-03-18 2015-09-24 Joby Aviation, Inc. Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
CN205131656U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Compound gyroplane

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR735472A (en) * 1932-04-06 1932-11-09 Aircraft lifting device
US3139244A (en) * 1961-08-15 1964-06-30 Cooper B Bright Inflatable vtol aircraft
US20120280091A1 (en) * 2009-08-26 2012-11-08 Manuel Munoz Saiz Lift, propulsion and stabilising system for vertical take-off and landing aircraft
WO2015143093A2 (en) * 2014-03-18 2015-09-24 Joby Aviation, Inc. Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
CN204452934U (en) * 2015-02-05 2015-07-08 仉军 The double mode aircraft of rotor, fixed-wing
CN205131656U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Compound gyroplane

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106945822A (en) * 2017-03-09 2017-07-14 杭州米为科技有限公司 A kind of method and apparatus of the pitching of control aircraft
CN106945822B (en) * 2017-03-09 2019-08-02 杭州米为科技有限公司 A kind of method and apparatus for the pitching controlling aircraft
CN108860592A (en) * 2018-05-31 2018-11-23 江苏常探机器人有限公司 Single vortex-spraying type composite wing manned vehicle afterwards

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