CN107618659A - A kind of double hair aircraft - Google Patents
A kind of double hair aircraft Download PDFInfo
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- CN107618659A CN107618659A CN201710817342.6A CN201710817342A CN107618659A CN 107618659 A CN107618659 A CN 107618659A CN 201710817342 A CN201710817342 A CN 201710817342A CN 107618659 A CN107618659 A CN 107618659A
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Abstract
The present invention relates to a kind of double hair aircraft, including fuselage, port wing, left-hand airscrew, Left Hand Engine, left floating drum, starboard wing, right-hand screw oar, right engine, right floating drum, empennage and undercarriage；Port wing is on the left of fuselage, and starboard wing is on the right side of fuselage；Left Hand Engine is on port wing, and for right engine on starboard wing, Left Hand Engine and right engine location are symmetrical；The output shaft of Left Hand Engine is connected with left-hand airscrew, and the output shaft of right engine is connected with right-hand screw oar；Empennage is located at the afterbody of fuselage, and left floating drum is below port wing, and right floating drum is below starboard wing, and undercarriage is in fuselage；The invention provides a kind of amphibian flight stability and the low double hair aircraft of oil consumption rate.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of double hair aircraft.
Background technology
Aircraft such as balloon, aerodone, dirigible, aircraft, helicopter etc., they are transported relatively by the quiet buoyancy or air of air
Air force lift-off flight caused by dynamic.But the aircraft of prior art can only take off in land runway mostly, can not realize
The water surface steadily takes off.
Patent No. CN205131652U Chinese patent, disclose a kind of twin, including fuselage, port wing, a left side
Rotor, Left Hand Engine, starboard wing, the dextrorotation wing, right engine, empennage and undercarriage.Port wing and starboard wing knot are symmetrically arranged on
The left and right sides of fuselage.Port wing includes leading portion fixed part and back segment movable part.The left-handed wing is identical with dextrorotation wing size, turns
To opposite.On the basis of horizontal plane, before the number of degrees and port wing of the downward maximum deflection angle of the back segment movable part of port wing
Section fixed part is identical in the number of degrees of the angle in front with horizontal plane.Put when the back segment movable part of port wing deflects into lowermost position
When, the leading edge of port wing is higher than the trailing edge of port wing.The Plane of rotation of the left-handed wing slightly forward downward is tilted or is horizontal.
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 lower Xian's air-flow, delay left machine
The air-flow separation of the upper surface of the wing and starboard wing.Although the aircraft of this patent can realize relatively short distance landing and VTOL,
Still suffer from the problems such as flight is unstable and oil consumption rate is high.
Therefore, the aircraft of prior art also in the presence of only limit, taken off, unstable and technology high oil consumption rate of flying is asked by land
Topic.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of amphibian flight stability and the low double hairs of oil consumption rate
Aircraft.
In order to solve the above technical problems, the technical scheme is that：A kind of double hair aircraft, including fuselage, port wing,
Left-hand airscrew, Left Hand Engine, left floating drum, starboard wing, right-hand screw oar, right engine, right floating drum, empennage and undercarriage；The left side
Wing is on the left of the fuselage, and the starboard wing is on the right side of the fuselage；The Left Hand Engine is located on the port wing,
For the right engine on the starboard wing, the Left Hand Engine and the right engine location are symmetrical；The Left Hand Engine
Output shaft be connected with the left-hand airscrew, the output shaft of the right engine is connected with the right-hand screw oar；The empennage position
In the afterbody of the fuselage, the left floating drum is below the port wing, and the right floating drum is below the starboard wing, institute
Undercarriage is stated in the fuselage；
The fuselage is provided with control system and airborne equipment；The control system transmits control command, drives rudder face and its
His mechanism is to control double hair aircraft flight postures, and the airborne equipment is to various information, instruction and manipulation in-flight
Measure, handle, transmit, show and control.
Due to the presence of port wing and starboard wing, lift caused by the aircraft is larger, if running out of steam can also slide
The longer distance of Xiang, it can strive for that more times carry out maintenance of equipment or find safe landing point, it is so relatively safer；Due to a left side
Propeller and right-hand screw oar turn on the contrary, both sides can offset rotating torque, flight stability and control is simple.
As preferable technical scheme, the bottom of the fuselage is in Ship Structure so that double hair aircraft can be
Landing on the water surface.
As preferable technical scheme, the port wing and the starboard wing all include aileron and winglet；The pair
For the wing on the outside of the wingtip trailing edge of the port wing and the starboard wing, the winglet is located at the port wing and the right side
Wing wingtip；The aileron is used for the rolling for controlling aircraft, and the winglet is integrally pneumatic for improving double hair aircraft
Performance；Oil consumption rate is reduced, lifts economic benefit.
As preferable technical scheme, the empennage includes tailplane and vertical tail, and the tailplane plays level
The effect of stabilization and elevator, elevator are used for the pitching for controlling double hair aircraft；The vertical tail plays vertical stabilization
With the effect of rudder, rudder is used for the deflection for controlling double hair aircraft.
By adopting the above-described technical solution, the beneficial effects of the invention are as follows：The present invention is by twin fuselage
Bottom is arranged to Ship Structure, and installs left floating drum with right floating drum in the lower section of wing so that aircraft can the landing on the water surface,
Adaptability is wider；By being molded winglet in twin wing end, improve twin entirety aeroperformance, reduce consumption
Oil cut rate, increase economic efficiency.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, without having to pay creative labor, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 is the structural representation of the embodiment of the present invention.
Embodiment
To describe the technology contents of the present invention, construction feature in detail, below in conjunction with embodiment and accompanying drawing is coordinated to give in detail
With explanation.
As shown in figure 1, the partial structural diagram of double hair aircraft of the present invention, including fuselage 1, port wing 2, left-hand screw
Oar 3, Left Hand Engine 4, starboard wing 6, right-hand screw oar 7, right engine 8, left floating drum 5, right floating drum 9 and empennage 10；
Port wing 2 is identical with the structure of starboard wing 6, and they are symmetrically arranged on the left and right sides of fuselage 1, left-hand airscrew 3 and the right side
The size of propeller 7 is identical, turns on the contrary, one is levoform, one is right-spiral.Left Hand Engine 4 and right engine 8 divide
Be not symmetrically mounted on port wing 2 and starboard wing 3, the output shaft of Left Hand Engine 4 is connected with left-hand airscrew 3, right engine 4 it is defeated
Shaft is connected with right-hand screw oar 7, and empennage 10 is located at the afterbody of fuselage 1, and empennage 10 includes tailplane 10.1 and vertical tail
10.2, tailplane plays horizontal stabilizer and elevator, and vertical tail plays vertical stabilization and rudder.It is left
The Plane of rotation of propeller 3 and the Plane of rotation of right-hand screw oar 7 are coplanar.
Left Hand Engine 4 and right engine 8 are started, drives left-hand airscrew 3 and right-hand screw oar 7 to rotate, aircraft starts to take off.
When double hair aircraft run out of steam, due to the presence of port wing 2 and starboard wing 6, lift caused by the aircraft
It is larger, even if the longer distance that can also glide that runs out of steam, it can strive for that more times carry out maintenance of equipment or find safety
Lu Dian is so relatively safer.
Undercarriage uses wheeled construction, in water surface landing, then packs up undercarriage；In continental rise landing, then drop.
Water surface landing, left floating drum is installed with the right side by being arranged to Ship Structure in the bottom of twin fuselage, and in the lower section of wing
Floating drum so that aircraft can the landing on the water surface, adaptability is wider.
General principle, principal character and the advantages of the present invention of the present invention has been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the simply explanation described in above-described embodiment and specification is originally
The principle of invention, without departing from the spirit and scope of the present invention, various changes and modifications of the present invention are possible, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (4)
- A kind of 1. double hair aircraft, it is characterised in that：Including fuselage, port wing, left-hand airscrew, Left Hand Engine, left floating drum, right machine The wing, right-hand screw oar, right engine, right floating drum, empennage and undercarriage；The port wing is on the left of the fuselage, the right machine The wing is on the right side of the fuselage；On the port wing, the right engine is located on the starboard wing Left Hand Engine, The Left Hand Engine and the right engine location are symmetrical；The output shaft of the Left Hand Engine is connected with the left-hand airscrew, institute The output shaft for stating right engine is connected with the right-hand screw oar；The empennage is located at the afterbody of the fuselage, and the left floating drum is set Below the port wing, the right floating drum is below the starboard wing, and the undercarriage is in the fuselage；The fuselage is provided with control system and airborne equipment；The control system transmits control command, driving rudder face and other machines For structure to control double hair aircraft flight postures, the airborne equipment is to various information in-flight, instruction and manipulates progress Measurement, processing, transmit, show and control.
- 2. double hair aircraft as claimed in claim 1, it is characterised in that：The bottom of the fuselage is in Ship Structure.
- 3. double hair aircraft as claimed in claim 1, it is characterised in that：The port wing and the starboard wing are designed with aileron And winglet, on the outside of the wingtip trailing edge of the port wing and the starboard wing, the winglet is located at the aileron The port wing and the starboard wing wingtip；The aileron is used for the rolling for controlling aircraft, and the winglet is used to improve Double hair aircraft entirety aeroperformances.
- 4. double hair aircraft as claimed in claim 1, it is characterised in that：The empennage includes tailplane and vertical tail, The tailplane and the vertical tail vertical connection；The tailplane plays horizontal stabilizer and elevator, institute State vertical tail and play vertical stabilization and rudder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817342.6A CN107618659A (en) | 2017-09-12 | 2017-09-12 | A kind of double hair aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817342.6A CN107618659A (en) | 2017-09-12 | 2017-09-12 | A kind of double hair aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107618659A true CN107618659A (en) | 2018-01-23 |
Family
ID=61089540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817342.6A Pending CN107618659A (en) | 2017-09-12 | 2017-09-12 | A kind of double hair aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107618659A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
| CN108725750A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A method of improving aircraft VTOL using winglet and flight controls |
| CN109353499A (en) * | 2018-11-08 | 2019-02-19 | 南京航空航天大学 | A kind of air foil profile seaplane |
| CN111099014A (en) * | 2019-12-09 | 2020-05-05 | 湖南浩天翼航空技术有限公司 | Buoy for overwater unmanned aerial vehicle with weak interference force |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1073643A (en) * | 1991-12-24 | 1993-06-30 | 杨亚黎 | Super energy-saving surface effect flight vehicle |
| EP0798207A2 (en) * | 1993-08-26 | 1997-10-01 | David E. Gevers | Multi-purpose aircraft |
| CN2642674Y (en) * | 2003-10-17 | 2004-09-22 | 吴征 | Hull type amphibious super-light airplane with two seats arranged longitudinally |
| CN2696988Y (en) * | 2003-04-11 | 2005-05-04 | 北京天道恒地效飞行器技术有限公司 | Ground effect vehicle mounted detector and launching device on body top |
| CN203528804U (en) * | 2012-12-14 | 2014-04-09 | 中航通飞研究院有限公司 | Large-size rescue amphibious aircraft |
-
2017
- 2017-09-12 CN CN201710817342.6A patent/CN107618659A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1073643A (en) * | 1991-12-24 | 1993-06-30 | 杨亚黎 | Super energy-saving surface effect flight vehicle |
| EP0798207A2 (en) * | 1993-08-26 | 1997-10-01 | David E. Gevers | Multi-purpose aircraft |
| CN2696988Y (en) * | 2003-04-11 | 2005-05-04 | 北京天道恒地效飞行器技术有限公司 | Ground effect vehicle mounted detector and launching device on body top |
| CN2642674Y (en) * | 2003-10-17 | 2004-09-22 | 吴征 | Hull type amphibious super-light airplane with two seats arranged longitudinally |
| CN203528804U (en) * | 2012-12-14 | 2014-04-09 | 中航通飞研究院有限公司 | Large-size rescue amphibious aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 北京未来新世纪教育科学发展中心: "《科学目击者 飞天之翼》", 31 December 2007, 新疆青少年出版社，喀什维吾尔文出版社 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
| CN108725750A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A method of improving aircraft VTOL using winglet and flight controls |
| CN108706093B (en) * | 2018-04-28 | 2023-09-12 | 昆明鞘翼科技有限公司 | Plate wing machine |
| CN109353499A (en) * | 2018-11-08 | 2019-02-19 | 南京航空航天大学 | A kind of air foil profile seaplane |
| CN111099014A (en) * | 2019-12-09 | 2020-05-05 | 湖南浩天翼航空技术有限公司 | Buoy for overwater unmanned aerial vehicle with weak interference force |
| CN111099014B (en) * | 2019-12-09 | 2022-04-05 | 湖南浩天翼航空技术有限公司 | Buoy for overwater unmanned aerial vehicle with weak interference force |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180123 |