CN105197230A - Aircraft provided with double rotor wings - Google Patents
Aircraft provided with double rotor wings Download PDFInfo
- Publication number
- CN105197230A CN105197230A CN201510721264.0A CN201510721264A CN105197230A CN 105197230 A CN105197230 A CN 105197230A CN 201510721264 A CN201510721264 A CN 201510721264A CN 105197230 A CN105197230 A CN 105197230A
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- wing
- port
- handed
- aircraft
- dextrorotation
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Abstract
The invention discloses an aircraft provided with double rotor wings and belongs to the technical field of aircrafts. The aircraft comprises an aircraft body, a left wing, a left rotor wing, a left stand, a right wing, a right rotor wing, a right stand, a puller, a tail and undercarriages, wherein the left wing and the right wing adopt the same structure and are symmetrically mounted on the left side and the right side of the aircraft body; the left rotor wing and the right rotor wing have the same size, but rotate in the opposite directions; the left rotor wing is mounted in a round hole in the middle of the left wing through the left stand, and a rotating shaft of the left rotor wing is connected with the left stand through a bearing; the right rotor wing is mounted in a round hole in the middle of the right wing through the right stand, and a rotating shaft of the right rotor wing is connected with the right stand through a bearing; a rotary plane of the left rotor wing is parallel to or overlaps with the plane of the left wing; the leading edge of the left wing is higher than the tailing edge of the left wing. The aircraft can more stably and safely fly.
Description
Technical field
A kind of DCB Specimen aircraft, 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 DCB Specimen aircraft growing the safety and stability that distance is glided.
A kind of DCB Specimen aircraft, comprises fuselage, port wing, the left-handed wing, left socle, starboard wing, the dextrorotation wing, right support, chest expander, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Chest expander comprises screw propeller and driving engine.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.The middle part of port wing has a diameter to be a bit larger tham the circular port of the diameter of the wing tip turning circumference of the left-handed wing.The left-handed wing is arranged in the circular port in the middle part of port wing by left socle, and the rotating shaft of the left-handed wing is connected with left socle by bearing.The dextrorotation wing is arranged in the circular port in the middle part of starboard wing by right support, and the rotating shaft of the dextrorotation wing is connected with right support by bearing.Empennage is positioned at the afterbody of fuselage, and empennage comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevating rudder.Tail has hung down the effect of 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.Plane of rotation and the port wing plane parallel or overlapping of the left-handed wing.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 3 ~ 10 °, and the plane of rotation of the left-handed wing and the angle of horizontal surface are also between 3 ~ 10 °.
Power mode can also be like this, chest expander is cancelled, replace as engine installation with the propelling unit being installed on fuselage postmedian, the normal work of airflow influence port wing backward, the left-handed wing, starboard wing and the dextrorotation wing that would not produce because of chest expander like this, also can not affect the visual field of chaufeur.
The principle of work of a kind of DCB Specimen aircraft of this invention is: start chest expander, described aircraft is driven to move ahead, because the angle of the left-handed wing and the dextrorotation wing and front incoming flow is 3 ~ 10 °, 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 some lift, then described in take off.The speed of described aircraft advance is controlled by the rotating speed controlling chest expander.Pitching and the course of described aircraft is controlled by empennage.Because the left-handed wing and the dextrorotation wing turn on the contrary, both sides can offset rotating torque, so described aircraft flight is 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.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of DCB Specimen aircraft 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 32-dextrorotation wing, 41-left socle, 42-right support, 5-chest expander, 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 DCB Specimen aircraft, comprised fuselage 1, port wing 21, the left-handed wing 31, left socle 41, starboard wing 22, the dextrorotation wing 32, right support 42, chest expander 5, empennage 6 and alighting gear 7.Chest expander 5 comprises screw propeller and driving engine.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.The middle part of port wing 21 has a diameter to be a bit larger tham the circular port of the diameter of the wing tip turning circumference of the left-handed wing 31.The left-handed wing 31 is arranged in the circular port in the middle part of port wing 21 by left socle 41, and the rotating shaft of the left-handed wing 31 is connected with left socle 41 by bearing.The dextrorotation wing 32 is arranged in the circular port in the middle part of starboard wing 22 by right support 42, and the rotating shaft of the dextrorotation wing 32 is connected with right support 42 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.Tail has hung down the effect of vertical stabilator and yaw rudder.Alighting gear 7 adopts rear bikini 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.Plane of rotation and port wing 21 plane parallel or overlapping of the left-handed wing 31.The leading edge of port wing 21 is higher than the trailing edge of port wing 21, and port wing 21 is 5 ° with the angle of horizontal surface, and the plane of rotation of the left-handed wing 31 and the angle of horizontal surface are also 5 °.
DCB Specimen aircraft of the present invention produces beneficial effect like this: start chest expander, 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 some lift, then described in take off.The speed of described aircraft advance is controlled by the rotating speed controlling chest expander 5.Pitching and the course of described aircraft is controlled by empennage 6.Because the left-handed wing 31 and the dextrorotation wing 32 turn on the contrary, both sides can offset rotating torque, so described aircraft flight is 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 the Distance geometry time also gliding longer, can strive for more time docking facility or find safe landing point, safer like this.
Claims (4)
1. a DCB Specimen aircraft, is characterized in that: comprise fuselage (1), port wing (21), the left-handed wing (31), left socle (41), starboard wing (22), the dextrorotation wing (32), right support (42), chest expander (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; The left-handed wing (31) is arranged in the circular port at port wing (21) middle part by left socle (41), and the rotating shaft of the left-handed wing (31) is connected with left socle (41) by bearing; The dextrorotation wing (32) is arranged in the circular port at starboard wing (22) middle part by right support (42), and the rotating shaft of the dextrorotation wing (32) is connected with right support (42) 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; Plane of rotation and port wing (21) plane parallel or overlapping of the left-handed wing (31); The leading edge of port wing (21) is higher than the trailing edge of port wing (21).
2. a kind of DCB Specimen aircraft according to claim 1, is characterized in that: cancelled by chest expander, replaces chest expander (5) as engine installation with the propelling unit being installed on fuselage (1) postmedian.
3. a kind of DCB Specimen aircraft according to claim 1 and 2, is characterized in that: the plane of rotation of the left-handed wing (31) and the angle of horizontal surface are between 3 ~ 10 °.
4. a kind of DCB Specimen aircraft according to claim 1 and 2, is characterized in that: port wing (21) is 5 ° with the angle of horizontal surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721264.0A CN105197230A (en) | 2015-10-30 | 2015-10-30 | Aircraft provided with double rotor wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721264.0A CN105197230A (en) | 2015-10-30 | 2015-10-30 | Aircraft provided with double rotor wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105197230A true CN105197230A (en) | 2015-12-30 |
Family
ID=54945298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721264.0A Pending CN105197230A (en) | 2015-10-30 | 2015-10-30 | Aircraft provided with double rotor wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105197230A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
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| US20090114771A1 (en) * | 2007-11-05 | 2009-05-07 | Qian Mu | Split Return Wing |
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN102897315A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN203845003U (en) * | 2014-05-25 | 2014-09-24 | 何长青 | Three-duct fan double-mode aircraft |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| CN104477381A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Double-variable-pitch-propeller aircraft |
| WO2015094859A2 (en) * | 2013-12-20 | 2015-06-25 | Google Inc. | Methods and systems for determining a priority sequence for changing a position or an attitude of an aircraft in hover flight |
| US20150266571A1 (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 |
| CN205131637U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Two gyroplane |
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2015
- 2015-10-30 CN CN201510721264.0A patent/CN105197230A/en active Pending
Patent Citations (11)
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|---|---|---|---|---|
| DE4140139A1 (en) * | 1991-12-05 | 1993-06-09 | Klaus Dipl.-Werkmeister 6600 Saarbruecken De Lellig | Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed |
| US20090114771A1 (en) * | 2007-11-05 | 2009-05-07 | Qian Mu | Split Return Wing |
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN102897315A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| WO2015094859A2 (en) * | 2013-12-20 | 2015-06-25 | Google Inc. | Methods and systems for determining a priority sequence for changing a position or an attitude of an aircraft in hover flight |
| US20150266571A1 (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 |
| CN203845003U (en) * | 2014-05-25 | 2014-09-24 | 何长青 | Three-duct fan double-mode aircraft |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| CN104477381A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Double-variable-pitch-propeller aircraft |
| CN205131637U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Two gyroplane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730676B (en) * | 2016-03-22 | 2019-06-04 | 王一 | A kind of aircraft |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151230 |