CN205131630U - Double -oar vertical lift aircraft - Google Patents
Double -oar vertical lift aircraft Download PDFInfo
- Publication number
- CN205131630U CN205131630U CN201520861341.8U CN201520861341U CN205131630U CN 205131630 U CN205131630 U CN 205131630U CN 201520861341 U CN201520861341 U CN 201520861341U CN 205131630 U CN205131630 U CN 205131630U
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- wing
- movable wings
- fuselage
- activity
- dextrorotation
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Abstract
The utility model provides a double -oar vertical lift aircraft, belongs to aircraft technical field, including fuselage, activity wing, the levogyration wing, the dextrorotation wing, left engine, right engine, support, fin and undercarriage. Be furnished with control system and airborne equipment in the fuselage. The levogyration wing is the same with dextrorotation wing structure, turns to on the contrary, arranges with the high level. The fin includes tailplane and vertical tail. The undercarriage adopts wheel -type structure. Blade axis is vertical to be arranged, the activity wing passes through blade axis and installs in the top of fuselage, and control system controls the rotor device and enables the activity wing and can change to the horizontal position by the follow lengthwise position. When the activity wing was in the horizontal position, the leading edge of activity wing was in horizontal horizontal position, and the leading edge of activity wing is higher than the trailing edge of movable wing, the levogyration wing and the dextrorotation wing are in the below of activity wing, the flow field on surface about can improvement activity wing when two rotors rotate, and the increase is xian's air current down, delays the airflow separation of the upper surface of activity wing. Aircraft safety, high efficiency and mobility are strong.
Description
Technical field
A kind of two oar Convertiplane, belongs to vehicle technology field, particularly relates to a kind of Convertiplane.
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 two oar Convertiplane facilitating the efficient safety and stability of short take-off and landing and vertical takeoff and landing.
A kind of two oar Convertiplane, comprises fuselage, movable wings, the left-handed wing, the dextrorotation wing, Left Hand Engine, right driving engine, support, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.The left-handed wing is identical with dextrorotation wing structure, and turn to contrary, their symmetries are installed on the left and right sides of fuselage.The left-handed wing and the dextrorotation wing are with high and all horizontal arrangement.Left Hand Engine is identical with right driving engine, and they are installed on the left and right sides of fuselage by support symmetry, and they are respectively the left-handed wing and the dextrorotation wing provides power.Empennage is positioned at the afterbody of fuselage, and empennage comprises tailplane and vertical tail.Tailplane comprises front fixed part and rear moving part, and tailplane plays horizontal stabilizer and pitch control subsystem effect; Vertical tail comprises front fixed part and rear moving part, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear adopts wheeled construction.Wing axle is vertically arranged, the upper end of wing axle is connected with movable wings, the lower end of wing axle is connected on the rotor device in fuselage, movable wings is installed on the top of fuselage by wing axle, control system manipulation rotor device can make movable wings rotate around wing axle axis, and movable wings can go to horizontal position from lengthwise position.When movable wings is in horizontal position, the leading edge of movable wings is in lateral horizontal position, and the leading edge of movable wings is higher than the trailing edge of movable wings, and the angle of attack of movable wings is maximum is no more than 20 °; The left-handed wing and the dextrorotation wing are in the below of movable wings and are in completely in the downward drop shadow spread of movable wings.The two ends of movable wings with can be movable aileron.
A kind of two oar Convertiplane of the present invention includes but not limited to following beneficial effect: movable wings is placed in lengthwise position, start Left Hand Engine and right driving engine, drive the left-handed wing and right rotor wing rotation respectively, souping up, to time enough large, can make described aircraft vertical go up to the air; As movable wings is placed in horizontal position, start Left Hand Engine and right driving engine, drive the left-handed wing and right rotor wing rotation respectively, described aircraft can realize short range rolling start; When flying, change of flight attitude can be carried out by changing the position of movable wings, the deflecting direction changing port aileron and starboard aileron and the rotating speed of angle, the left-handed wing of change and the dextrorotation wing and the deflecting direction of change tailplane and vertical tail and angle aloft.This air maneuver is flexible.Compare with traditional aircraft, Shuan Jiang Convertiplane landing site of the present invention is little, and can even can hover by vertical lift; Compare with traditional helicopter, the two oar Convertiplane of the present invention is due to the existence of movable wings, 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 turning to of the left-handed wing and the dextrorotation wing is contrary, both sides can offset rotating torque, flight stability and control simple; Movable wings is in time flight in horizontal position because two rotors are all in the below of movable wings, before can improve the flow field of movable wings upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of movable wings, raise the efficiency, lift coefficient is increased greatly, the aspect ratio of wing reduces than conventional airplane also can produce same lift effect, and so, the oad of aircraft just decreases, take up room and diminish, structural strength increases.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on the left side of the present invention's a kind of pair of oar Convertiplane movable wings when being in horizontal position, and Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on the left side of the present invention's a kind of pair of oar Convertiplane movable wings when being in lengthwise position, and Fig. 4 is the schematic top plan view of Fig. 3.
In figure, 1-fuselage, 2-movable wings, 21-wing axle, 22-port aileron, 23-starboard aileron, the left-handed wing of 3-, the 4-dextrorotation wing, 5-Left Hand Engine, the right driving engine of 6-, 7-support, 8-empennage, 9-alighting gear.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of two oar Convertiplane, comprises fuselage 1, movable wings 2, the left-handed wing 3, the dextrorotation wing 4, Left Hand Engine 5, right driving engine 6, support 7, empennage 8 and alighting gear 9.Control system and airborne equipment is furnished with in fuselage 1.The left-handed wing 3 is identical with the dextrorotation wing 4 structure, and turn to contrary, their symmetries are installed on the left and right sides of fuselage 1.The left-handed wing 3 and the dextrorotation wing 4 are with high and all horizontal arrangement.Left Hand Engine 5 is identical with right driving engine 6, and they are installed on the left and right sides of fuselage 1 by support 7 symmetry, and they are respectively the left-handed wing 3 and the dextrorotation wing 4 provides power.Empennage 8 is positioned at the afterbody of fuselage 1, and empennage 8 comprises tailplane and vertical tail.Tailplane comprises front fixed part and rear moving part, and tailplane plays horizontal stabilizer and pitch control subsystem effect; Vertical tail comprises front fixed part and rear moving part, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear 9 adopts wheeled construction.Wing axle 21 is vertically arranged, the upper end of wing axle 21 is connected with movable wings 2, the lower end of wing axle 21 is connected on the rotor device in fuselage 1, movable wings 2 is installed on the top of fuselage 1 by wing axle 21, control system manipulation rotor device can make movable wings 2 rotate around wing axle 21 axis, and movable wings 2 can go to horizontal position from lengthwise position.When movable wings 2 is in horizontal position, the leading edge of movable wings 2 is in lateral horizontal position, and the leading edge of movable wings 2 is higher than the trailing edge of movable wings 2, and the angle of attack of movable wings 2 is 13 °; The left-handed wing 3 and the dextrorotation wing 4 are in the below of movable wings 2 and are in the downward drop shadow spread of movable wings 2 completely; The two ends, left and right of movable wings 2 are with the port aileron that can deflect up and down and starboard aileron.
The two oar Convertiplane of the present invention produces beneficial effect like this: movable wings 2 is placed in lengthwise position, start Left Hand Engine 5 and right driving engine 6, drive the left-handed wing 3 and the dextrorotation wing 4 to rotate respectively, souping up, to time enough large, can make described aircraft vertical go up to the air; As movable wings 2 is placed in horizontal position, start Left Hand Engine 5 and right driving engine 6, drive the left-handed wing 3 and the dextrorotation wing 4 to rotate respectively, described aircraft can realize short range rolling start; When flying, change of flight attitude can be carried out by changing the position of movable wings 2, the deflecting direction changing port aileron 22 and starboard aileron 23 and the rotating speed of angle, the left-handed wing 3 of change and the dextrorotation wing 4 and the deflecting direction of change tailplane and vertical tail and angle aloft.This air maneuver is flexible.Compare with traditional aircraft, Shuan Jiang Convertiplane landing site of the present invention is little, and can even can hover by vertical lift; Compare with traditional helicopter, the two oar Convertiplane of the present invention is due to the existence of movable wings 2, 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 turning to of the left-handed wing 3 and the dextrorotation wing 4 is contrary, both sides can offset rotating torque, flight stability and control simple; Movable wings 2 is in time flight in horizontal position because two rotors are all in the below of movable wings 2, before can improve the flow field of movable wings 2 upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of movable wings 2, raise the efficiency, lift coefficient is increased greatly, the aspect ratio of wing reduces than conventional airplane also can produce same lift effect, and so, the oad of aircraft just decreases, take up room and diminish, structural strength increases.
Claims (3)
1. a two oar Convertiplane, is characterized in that: comprise fuselage (1), movable wings (2), the left-handed wing (3), the dextrorotation wing (4), Left Hand Engine (5), right driving engine (6), support (7), empennage (8) and alighting gear (9); Fuselage is furnished with control system and airborne equipment in (1); The left-handed wing (3) is identical with the dextrorotation wing (4) structure, and turn to contrary, their symmetries are installed on the left and right sides of fuselage (1); The left-handed wing (3) and the dextrorotation wing (4) are with high and all horizontal arrangement; Left Hand Engine (5) is identical with right driving engine (6), and they are installed on the left and right sides of fuselage (1) by support (7) symmetry, and they are respectively the left-handed wing (3) and the dextrorotation wing (4) provides power; Empennage (8) is positioned at the afterbody of fuselage (1), and empennage (8) comprises tailplane and vertical tail; Wing axle (21) is vertically arranged, the upper end of wing axle (21) is connected with movable wings (2), the lower end of wing axle (21) is connected on the rotor device in fuselage (1), movable wings (2) is installed on the top of fuselage (1) by wing axle (21), control system manipulation rotor device can make movable wings (2) rotate around wing axle (21) axis, and movable wings (2) can go to horizontal position from lengthwise position; When movable wings (2) is in horizontal position, the leading edge of movable wings (2) is in lateral horizontal position, and the leading edge of movable wings (2) is higher than the trailing edge of movable wings (2); The left-handed wing (3) and the dextrorotation wing (4) are in the below of movable wings (2) and are in completely in the downward drop shadow spread of movable wings (2).
2. the two oar Convertiplane of one according to claim 1, is characterized in that: the two ends of movable wings (2) are with the aileron of activity.
3. the two oar Convertiplane of one according to claim 1 and 2, is characterized in that: the angle of attack of movable wings (2) is maximum is no more than 20 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861341.8U CN205131630U (en) | 2015-11-02 | 2015-11-02 | Double -oar vertical lift aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520861341.8U CN205131630U (en) | 2015-11-02 | 2015-11-02 | Double -oar vertical lift aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205131630U true CN205131630U (en) | 2016-04-06 |
Family
ID=55617447
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520861341.8U Withdrawn - After Issue CN205131630U (en) | 2015-11-02 | 2015-11-02 | Double -oar vertical lift aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205131630U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173060A (en) * | 2015-11-02 | 2015-12-23 | 佛山市神风航空科技有限公司 | Two-propeller plane capable of taking off and landing vertically |
| CN107089324A (en) * | 2017-04-26 | 2017-08-25 | 浙江点辰航空科技有限公司 | A kind of wing oar attachment structure of unmanned plane |
| CN107323650A (en) * | 2016-04-29 | 2017-11-07 | 杨双来 | Movable wing aircraft |
-
2015
- 2015-11-02 CN CN201520861341.8U patent/CN205131630U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173060A (en) * | 2015-11-02 | 2015-12-23 | 佛山市神风航空科技有限公司 | Two-propeller plane capable of taking off and landing vertically |
| CN107323650A (en) * | 2016-04-29 | 2017-11-07 | 杨双来 | Movable wing aircraft |
| CN107089324A (en) * | 2017-04-26 | 2017-08-25 | 浙江点辰航空科技有限公司 | A kind of wing oar attachment structure of unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160406 Effective date of abandoning: 20170329 |