CN105197233A - Double-engine aircraft - Google Patents
Double-engine aircraft Download PDFInfo
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- CN105197233A CN105197233A CN201510721057.5A CN201510721057A CN105197233A CN 105197233 A CN105197233 A CN 105197233A CN 201510721057 A CN201510721057 A CN 201510721057A CN 105197233 A CN105197233 A CN 105197233A
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Abstract
The invention discloses a double-engine aircraft and belongs to the field of aircrafts. The double-engine aircraft comprises an aircraft body, a left wing, a left rotor wing, a left engine, a right wing, a right rotor wing, a right engine, a tail and undercarriages, wherein the left wing and the right wing are symmetrically mounted on the left side and the right side of the aircraft body; the left wing comprises a front-section fixed part and a rear-section movable part; the left rotor wing and the right rotor wing have the same size, but rotate in opposite directions; with a horizontal plane as a benchmark, the degree of the maximum downward deflection angle of the rear-section movable part of the left wing is equal to that of the included angle between the front-section fixed part of the left wing and the horizontal plane; when the rear-section movable part of the left wing is deflected to the lowest position, the leading edge of the left wing is higher than the trailing edge of the left wing; the rotary plane of the left rotor wing is slightly inclined forwards and downwards or is located in the horizontal position; during rotation of the left rotor wing and the right rotor wing, flow fields of the upper surfaces and the lower surfaces of the left wing and the right wing can be changed, the downwash flow is increased, and airflow separation of the upper surfaces of the left wing and the right wing is delayed. The aircraft is safe, efficient and high in maneuverability.
Description
Technical field
A kind of twin, belongs to vehicle technology field, particularly relates to a kind of twin.
Background technology
Traditional to take off and landing needs runway, can not vertical takeoff and landing, also inconvenient Ultra-Low Speed or hovering flight, 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, invent a kind of twin facilitating the efficient safety and stability of short take-off and landing and vertical takeoff and landing.
A kind of twin, comprises fuselage, port wing, the left-handed wing, Left Hand Engine, starboard wing, the dextrorotation wing, right driving engine, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Port wing is identical with starboard wing structure, and their symmetries are installed on the left and right sides of fuselage.Port wing comprises leading portion fixed part and back segment moving part.The left-handed wing and the dextrorotation wing measure-alike, turn to contrary, one is levoform, and one is right-spiral.Left Hand Engine and right driving engine respectively symmetry are arranged in port wing and starboard wing.The output shaft of Left Hand Engine is connected with the left-handed wing, and the output shaft of right driving engine is connected with the dextrorotation wing.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 plane of rotation of the left-handed wing and the plane of rotation of the dextrorotation wing coplanar.When the back segment moving part of port wing and the back segment moving part of starboard wing are all deflected downwards to extreme lower position, port wing and starboard wing coplanar.Take horizontal surface as benchmark, the number of degrees of the maximum deflection angle that the back segment moving part of port wing is downward are identical at the number of degrees of the angle in front with horizontal surface with the leading portion fixed part of port wing; The number of degrees of the back segment moving part angle of inclination upwards of port wing are no more than 20 °.When the back segment moving part of port wing deflect into lowermost position put time, the plane of rotation of the left-handed wing and the angle forward of port wing plane are greater than 10 °, and 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 5 ~ 20 °.The plane of rotation of the left-handed wing tilts slightly toward front lower place or is horizontal, and the angle of the plane of rotation of the left-handed wing and the forward downward of horizontal surface is not more than 8 °.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 tangential length of the back segment moving part of port wing equals or is slightly smaller than the radius of rotation of the left-handed wing.The length of port wing is greater than the diameter of the left-handed wing.
The principle of work of a kind of twin of this invention is: start Left Hand Engine and right driving engine, drive the left-handed wing and right rotor wing rotation, as the back segment moving part of port wing and the back segment moving part of starboard wing are all deflected downwards to extreme lower position, described aircraft can realize short field take-off; As the back segment moving part of port wing and the back segment moving part of starboard wing are all deflected upward into extreme higher position, described aircraft can realize taking off vertically.The deflection angle of the adjustment back segment moving part of port wing and the back segment moving part of starboard wing and direction can change aerodynamic direction and the size of the generation of described aircraft, also can be changed aerodynamic size of described aircraft by the rotating speed adjusting the left-handed wing and the dextrorotation wing.Pitching and the course of described aircraft is controlled by empennage.Compare with traditional aircraft, twin landing site of the present invention is little, and can vertical lift.Compare with traditional helicopter, twin of the present invention is due to the existence of port wing and starboard 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 left-handed wing and the dextrorotation wing turn on the contrary, both sides can offset rotating torque, flight stability and control simple; 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, 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 also increases.
In order to improve manoevreability, will leave a blank in the middle of the canned paragraph of the vertical tail of described twin, 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.
In order to improve manoevreability, leaving a blank in the middle of the canned paragraph of the tailplane of described twin, arranging installation electric propeller in this position transverse horizontal of leaving a blank, facilitating described aircraft steadily hovering or wide-angle pitching like this.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of twin of the present invention; Fig. 2 is the schematic top plan view of Fig. 1.
In figure, 1-fuselage, 21-port wing, the leading portion fixed part of 211-port wing, the back segment moving part of 212-port wing, 22-starboard wing, the leading portion fixed part of 221-starboard wing, the back segment moving part of 222-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, 41-Left Hand Engine, the right driving engine of 42-, 5-empennage, 6-alighting gear.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of twin, comprised fuselage 1, port wing 21, the left-handed wing 31, Left Hand Engine 41, starboard wing 22, the dextrorotation wing 32, right driving engine 42, empennage 5 and alighting gear 6.Port wing 21 is identical with starboard wing 22 structure, and their symmetries are installed on the left and right sides of fuselage 1.Port wing 21 comprises leading portion fixed part 211 and back segment moving part 212.The left-handed wing 31 and the dextrorotation wing 32 measure-alike, turn to contrary, one is levoform, and one is right-spiral.Left Hand Engine 41 and right driving engine 42 respectively symmetry are arranged in port wing 21 and starboard wing 22.The output shaft of Left Hand Engine 41 is connected with the left-handed wing 31, and the output shaft of right driving engine 42 is connected with the dextrorotation wing 32.Empennage 5 is positioned at the afterbody of fuselage 1, and empennage 5 comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevating rudder, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear 6 adopts wheeled construction.The plane of rotation of the left-handed wing 31 and the plane of rotation of the dextrorotation wing 32 coplanar.When the back segment moving part 212 of port wing and the back segment moving part 222 of starboard wing are all deflected downwards to extreme lower position, port wing 21 and starboard wing 22 coplanar.Take horizontal surface as benchmark, the number of degrees of the maximum deflection angle that the back segment moving part 212 of port wing is downward are identical at the number of degrees of the angle in front with horizontal surface with the leading portion fixed part 211 of port wing; The maximum angle that the back segment moving part 212 of port wing upward deflects is 20 °.When the back segment moving part 212 of port wing deflect into lowermost position put time, the plane of rotation of the left-handed wing 31 and the angle forward of port wing 21 plane are 17 °, and the leading edge of port wing 21 is higher than the trailing edge of port wing 21, and port wing 21 is 15 ° with the angle of horizontal surface.The plane of rotation forward downward of the left-handed wing 31 tilts, and the angle of the left-handed plane of rotation of the wing 31 and the forward downward of horizontal surface is 2 °.The turning circumference of the wing tip of the advanced left-handed wing 31 of leading edge of port wing 31 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.The tangential length of the back segment moving part of port wing 21 is slightly smaller than the radius of rotation of the left-handed wing 31.The length of port wing 21 is greater than the diameter of the left-handed wing 31.
Twin of the present invention produces beneficial effect like this: start Left Hand Engine 41 and right driving engine 42, the left-handed wing 31 and the dextrorotation wing 32 is driven to rotate, as the back segment moving part 212 of port wing and the back segment moving part 222 of starboard wing are all deflected downwards to extreme lower position, described aircraft can realize short field take-off; As the back segment moving part 212 of port wing and the back segment moving part 222 of starboard wing are all deflected upward into extreme higher position, described aircraft can realize taking off vertically.The deflection angle of the adjustment back segment moving part 212 of port wing and the back segment moving part 222 of starboard wing and direction can change aerodynamic direction and the size of the generation of described aircraft, also can be changed aerodynamic size of described aircraft by the rotating speed adjusting the left-handed wing 31 and the dextrorotation wing 32.Pitching and the course of described aircraft is controlled by empennage 5.Compare with traditional aircraft, twin landing site of the present invention is little, and can vertical lift.Compare with traditional helicopter, twin of the present invention is due to the existence of port wing 21 and starboard wing 22, 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 left-handed wing 31 and the dextrorotation wing 32 turn on the contrary, both sides can offset rotating torque, flight stability and control simple; 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 22 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 also increases.The back segment moving part 212 of port wing and the back segment moving part 222 of starboard wing can also play wing flap and the aileron of traditional aircraft.Therefore described twin maneuverability.
Claims (7)
1. a twin, is characterized in that: comprise fuselage (1), port wing (21), the left-handed wing (31), Left Hand Engine (41), starboard wing (22), the dextrorotation wing (32), right driving engine (42), empennage (5) and alighting gear (6); Port wing (21) is identical with starboard wing (22) structure, and their symmetries are installed on the left and right sides of fuselage (1); Port wing (21) comprises leading portion fixed part (211) and back segment moving part (212); The left-handed wing (31) and the dextrorotation wing (32) measure-alike, turn to contrary; The output shaft of Left Hand Engine (41) is connected with the left-handed wing (31), and the output shaft of right driving engine (42) is connected with the dextrorotation wing (32); Empennage (5) is positioned at the afterbody of fuselage (1), and empennage (5) comprises tailplane and vertical tail; The plane of rotation of the left-handed wing (31) and the plane of rotation of the dextrorotation wing (32) coplanar; When the back segment moving part (212) of port wing and the back segment moving part (222) of starboard wing are all deflected downwards to extreme lower position, port wing (21) and starboard wing (22) coplanar; Take horizontal surface as benchmark, the number of degrees of the maximum deflection angle that the back segment moving part (212) of port wing is downward are identical at the number of degrees of the angle in front with horizontal surface with the leading portion fixed part (211) of port wing; The number of degrees of back segment moving part (212) angle of inclination upwards of port wing are no more than 20 °; When the back segment moving part (212) of port wing deflect into lowermost position put time, the plane of rotation of the left-handed wing (31) and the angle forward of port wing (21) plane are greater than 10 °, 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 5 ~ 20 °; The plane of rotation of the left-handed wing (31) is horizontal or forward downward tilts, and the angle of the plane of rotation of the left-handed wing (31) and the forward downward of horizontal surface is not more than 8 °; The turning circumference of the wing tip of the advanced left-handed wing (31) of leading edge of port wing (31) foremost; 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); The tangential length of the back segment moving part of port wing (21) equals or is slightly smaller than the radius of rotation of the left-handed wing (31); The length of port wing (21) is greater than the diameter of the left-handed wing (31).
2. a kind of twin according to claim 1, is characterized in that: Left Hand Engine (41) and right driving engine (42) respectively symmetry are arranged in port wing (21) and starboard wing (22).
3. a kind of twin according to claim 1, it is characterized in that: when the back segment moving part (212) of port wing deflect into lowermost position put time, the plane of rotation of the left-handed wing (31) and the angle forward of port wing (21) plane are 17 °, the leading edge of port wing (21) is higher than the trailing edge of port wing (21), and port wing (21) is 15 ° with the angle of horizontal surface; The plane of rotation forward downward of the left-handed wing (31) tilts, and the angle of the plane of rotation of the left-handed wing (31) and the forward downward of horizontal surface is 2 °.
4. a kind of twin according to claim 1, is characterized in that: leave a blank in the middle of the canned paragraph of vertical tail, longitudinally vertically arranges installation screw propeller in this position of leaving a blank.
5. a kind of twin according to claim 1 or 2 or 3 or 4, is characterized in that: alighting gear 6 adopts wheeled construction or sled and wheeled unitized construction.
6. a kind of twin 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 tailplane, arranges installation screw propeller in this position transverse horizontal of leaving a blank.
7. a kind of twin 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 delayed left-handed wing (31) of trailing edge of port wing (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721057.5A CN105197233B (en) | 2015-10-30 | 2015-10-30 | A kind of twin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721057.5A CN105197233B (en) | 2015-10-30 | 2015-10-30 | A kind of twin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105197233A true CN105197233A (en) | 2015-12-30 |
| CN105197233B CN105197233B (en) | 2017-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721057.5A Active CN105197233B (en) | 2015-10-30 | 2015-10-30 | A kind of twin |
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| Country | Link |
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| CN (1) | CN105197233B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| JP5277342B1 (en) * | 2012-12-11 | 2013-08-28 | 和博 高橋 | Vertical take-off and landing aircraft |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
| CN205131652U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Two aircrafts |
-
2015
- 2015-10-30 CN CN201510721057.5A patent/CN105197233B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| JP5277342B1 (en) * | 2012-12-11 | 2013-08-28 | 和博 高橋 | Vertical take-off and landing aircraft |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
| CN205131652U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Two aircrafts |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105197233B (en) | 2017-12-15 |
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Effective date of registration: 20190520 Address after: 226300 North Four Formations of Tushan Village, Xingdong Town, Tongzhou District, Nantong City, Jiangsu Province Patentee after: NANTONG HUAXIA AIRPLANE ENGINEERING TECHNOLOGY CO., LTD. Address before: 528500 room 402, Fu Wan Jiangwan Road, Hecheng street, Gaoming District, Foshan, Guangdong, China, 78 Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City |
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