CN105270621A - Aircraft with skylight on wing - Google Patents
Aircraft with skylight on wing Download PDFInfo
- Publication number
- CN105270621A CN105270621A CN201510721055.6A CN201510721055A CN105270621A CN 105270621 A CN105270621 A CN 105270621A CN 201510721055 A CN201510721055 A CN 201510721055A CN 105270621 A CN105270621 A CN 105270621A
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- wing
- aircraft
- skylight
- rotor
- composite
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Abstract
The invention relates to an aircraft with a skylight on a wing, which belongs to the technical field of aircrafts. The aircraft with the skylight on the wing comprises an aircraft body, a left composite wing, a right composite wing, a tail wing and a landing gear. An operation system and airborne equipment are mounted in the aircraft body. The tail wing is positioned at the tail part of the aircraft body; and the tail wing comprises a horizontal tail wing and a vertical tail wing. The landing gear uses a wheel type structure or a skid and wheel combined structure. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The left composite wing comprises a main wing, a movable wing, a rotor wing, an engine and a bracket. The front edge of the main wing is higher than the back edge of the main wing; the right end of the main wing is connected with the aircraft body; a push-and-pull skylight is arranged at the middle part, close to the aircraft body, of the main wing; the movable wing can cover the window of the skylight under the pushing and pulling of external forces; and the skylight is opened when the movable wing is inserted into the left section of the main wing. The rotor wing and the engine are mounted right under the window through the bracket. The rotating plane of the rotor wing is horizontally placed. The aircraft can vertically take off and land and is safe, energy-saving and efficient.
Description
Technical field
The aircraft in wing band skylight, belongs to vehicle technology field, particularly relates to a kind of aircraft of wing band skylight.
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, inventing a kind of short take-off and landing that facilitates even can the aircraft in wing band skylight of efficient safety and stability of vertical takeoff and landing.
The aircraft in wing band skylight, comprises fuselage, left composite wing, right composite wing, empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Empennage is positioned at the afterbody of fuselage, and empennage comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and pitch control subsystem effect, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear adopts wheeled construction or sled and wheeled unitized construction.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.
Left composite wing concrete structure is: left composite wing comprises host wing, movable wing, rotor, driving engine and support.The leading edge of host wing is higher than the trailing edge of host wing, the angle of attack of host wing is between 3 ~ 12 °, the right-hand member of host wing is connected with fuselage, a push-pull skylight is provided with in the middle part of the close frame sections of host wing, movable wing can cover window under the push-and-pull of external force, and when movable wing inserts left section of host wing, skylight is opened.Rotor and driving engine by support installing immediately below window.The plane of rotation horizontal arrangement of rotor.The diameter of rotor is less than the inscribe circle diameter of window.
The aircraft in this invention a kind of wing band skylight includes but not limited to following beneficial effect: pushed by the movable wing of left composite wing in the host wing of left composite wing left, the movable wing of right composite wing is pushed in the host wing of right composite wing to the right, start two driving engines and drive two rotor wing rotations respectively, augment horsepower, described aircraft can realize taking off vertically, vertical landing or hovering.By the movable wing of left composite wing to the right pushing cover live the window of left composite wing, even if the movable wing of left composite wing is positioned at directly over the rotor of left composite wing; By the movable wing of right composite wing left pushing cover live the window of right composite wing, even if the movable wing of right composite wing is positioned at directly over the rotor of right composite wing.Start two driving engines and drive two rotor wing rotations respectively, augment horsepower, described aircraft can realize short range and move ahead and take off and cruise.The position adjusting the movable wing of left composite wing and right composite wing coordinates the rotating speed of adjustment two rotors can change aerodynamic direction and the size of the generation of described aircraft.Pitching and the course of described aircraft is controlled by empennage.Compare with traditional aircraft, the aircraft landing site in wing band skylight of the present invention is little, and can vertical lift.Compare with traditional helicopter, the aircraft in wing band skylight of the present invention is due to the existence of left composite wing and right composite wing, 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 turning to of two rotors is contrary, both sides can offset rotating torque, flight stability and control simple; During owing to cruising, two rotors are in the below of movable wing, the flow field of movable wing upper and lower surface can be improved during rotor rotational, increase downwash flow, delay the burbling of the upper surface of movable 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 also increases.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for the aircraft in a kind of wing band of the present invention skylight; Fig. 2 is the schematic top plan view of Fig. 1, and the movable wing in the movable wing in Fig. 2 in left composite wing and right composite wing is in the right intersegmental part of the left intersegmental part of the host wing of left composite wing and the host wing of right composite wing respectively.Fig. 3 is the schematic diagram that movable wing is all in when rotating top accordingly.
In figure, 1-fuselage, the left composite wing of 2-, the right composite wing of 3-, 4-empennage, 5-alighting gear.Belong to the component of left composite wing 2: 21-host wing, 211-main wing leading edge, 212-host wing trailing edge, 22-movable wing, 23-rotor, 24-driving engine, 25-support.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of aircraft of wing band skylight, comprises 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.Empennage 4 is positioned at the afterbody of fuselage 1, and empennage 4 comprises tailplane and vertical tail.Tailplane plays horizontal stabilizer and pitch control subsystem effect, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear 5 adopts wheeled construction.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.
Left composite wing 2 concrete structure is: left composite wing 2 comprises host wing 21, movable wing 22, rotor 23, driving engine 24 and support 25.The leading edge 211 of host wing is higher than the trailing edge 212 of host wing, the angle of attack of host wing 2 is 10 °, the right-hand member of host wing 21 is connected with fuselage 1, close fuselage 1 section of middle part of host wing 21 is provided with a push-pull skylight, movable wing 22 can cover window under the push-and-pull of external force, and when movable wing 22 inserts left section of host wing 21, skylight is opened.Rotor 23 and driving engine 24 are arranged on immediately below window by support 25.The plane of rotation horizontal arrangement of rotor 23.The diameter of rotor 23 is less than the inscribe circle diameter of window.
The aircraft in wing band skylight of the present invention produces beneficial effect like this: pushed by the movable wing 21 of left composite wing 2 in the host wing 21 of left composite wing 2 left, the movable wing of right composite wing 3 is pushed in the host wing of right composite wing 3 to the right, start two driving engines and drive two rotor wing rotations respectively, augment horsepower, described aircraft can realize taking off vertically, vertical landing or hovering.By the movable wing 22 of left composite wing 2 to the right pushing cover live the window of left composite wing 2, even if the movable wing 22 of left composite wing 2 is positioned at directly over the rotor 23 of left composite wing 2; By the movable wing of right composite wing 3 left pushing cover live the window of right composite wing 3, even if the movable wing of right composite wing 3 is positioned at directly over the rotor of right composite wing 3.Start two driving engines and drive two rotor wing rotations respectively, augment horsepower, described aircraft can realize short range and move ahead and take off and cruise.The position adjusting the movable wing of left composite wing 2 and right composite wing 3 coordinates the rotating speed of adjustment two rotors can change aerodynamic direction and the size of the generation of described aircraft.Pitching and the course of described aircraft is controlled by empennage 4.Compare with traditional aircraft, the aircraft landing site in wing band skylight of the present invention is little, and can vertical lift.Compare with traditional helicopter, the aircraft in wing band skylight of the present invention is due to the existence of left composite wing and right composite wing, 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 turning to of two rotors is contrary, both sides can offset rotating torque, flight stability and control simple; During owing to cruising, two rotors are in the below of corresponding movable wing, the flow field of corresponding movable wing upper and lower surface can be improved during rotor rotational, increase downwash flow, delay the burbling of the upper surface of movable 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 also increases.
Claims (2)
1. the aircraft in wing band skylight, is characterized in that: comprise fuselage (1), 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); 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; 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); Left composite wing (2) concrete structure is: left composite wing (2) comprises host wing (21), movable wing (22), rotor (23), driving engine (24) and support (25); The leading edge (211) of host wing is higher than the trailing edge (212) of host wing, the right-hand member of host wing (21) is connected with fuselage (1), a push-pull skylight is provided with in the middle part of close fuselage (1) section of host wing (21), movable wing (22) can cover window under the push-and-pull of external force, and when movable wing (22) inserts host wing (21) left section, skylight is opened; Rotor (23) and driving engine (24) are arranged on immediately below window by support (25); The plane of rotation horizontal arrangement of rotor (23); The diameter of rotor (23) is less than the inscribe circle diameter of window.
2. the aircraft in a kind of wing band skylight according to claim 1, is characterized in that: the angle of attack of host wing (2) is between 3 ~ 12 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721055.6A CN105270621A (en) | 2015-10-30 | 2015-10-30 | Aircraft with skylight on wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721055.6A CN105270621A (en) | 2015-10-30 | 2015-10-30 | Aircraft with skylight on wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105270621A true CN105270621A (en) | 2016-01-27 |
Family
ID=55140610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721055.6A Pending CN105270621A (en) | 2015-10-30 | 2015-10-30 | Aircraft with skylight on wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105270621A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278998A (en) * | 2017-07-21 | 2019-01-29 | 通用电气公司 | The aircraft of vertical takeoff and landing |
| FR3119159A1 (en) * | 2021-01-23 | 2022-07-29 | Bernard Etcheparre | Wing for aircraft, with concave dynamic discs. |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4771967A (en) * | 1986-06-17 | 1988-09-20 | Geldbaugh G Richard | Rotor aircraft |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| US20080173769A1 (en) * | 2007-01-22 | 2008-07-24 | George Philip Tharisayi | Stabilized tilt rotor aircraft |
| CN201494624U (en) * | 2008-10-24 | 2010-06-02 | 穆骞 | Venetian blind-type cracking combined airfoil |
| CN103693193A (en) * | 2012-09-27 | 2014-04-02 | 赵润生 | Multipurpose universal airplane |
| CN205131647U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Aircraft in wing area skylight |
-
2015
- 2015-10-30 CN CN201510721055.6A patent/CN105270621A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4771967A (en) * | 1986-06-17 | 1988-09-20 | Geldbaugh G Richard | Rotor aircraft |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| US20080173769A1 (en) * | 2007-01-22 | 2008-07-24 | George Philip Tharisayi | Stabilized tilt rotor aircraft |
| CN201494624U (en) * | 2008-10-24 | 2010-06-02 | 穆骞 | Venetian blind-type cracking combined airfoil |
| CN103693193A (en) * | 2012-09-27 | 2014-04-02 | 赵润生 | Multipurpose universal airplane |
| CN205131647U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Aircraft in wing area skylight |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278998A (en) * | 2017-07-21 | 2019-01-29 | 通用电气公司 | The aircraft of vertical takeoff and landing |
| CN109278998B (en) * | 2017-07-21 | 2022-06-14 | 通用电气公司 | Aircraft for vertical takeoff and landing |
| FR3119159A1 (en) * | 2021-01-23 | 2022-07-29 | Bernard Etcheparre | Wing for aircraft, with concave dynamic discs. |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160127 |