CN106275420A - Uniclinal switch rotor fuselage holds up VTOL aircraft - Google Patents
Uniclinal switch rotor fuselage holds up VTOL aircraft Download PDFInfo
- Publication number
- CN106275420A CN106275420A CN201510302930.7A CN201510302930A CN106275420A CN 106275420 A CN106275420 A CN 106275420A CN 201510302930 A CN201510302930 A CN 201510302930A CN 106275420 A CN106275420 A CN 106275420A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- landing
- uniclinal
- holds
- vtol
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Toys (AREA)
Abstract
The open a kind of uniclinal switch rotor fuselage of the present invention holds up VTOL aircraft, and including fuselage, wing, empennage, airscrew engine, two longerons of the external fuselage roof of head are stretched out in front end, drive end unit is arranged below landing Curved beam, motor, landing amortisseur etc..At present, domestic and international single screw fixed wing airplane is also not carried out VTOL.It is known that VTOL largest benefit is to need not runway, save soil, saving is built personal runway and parks airport writing expense, it can have smooth just energy VTOL as helicopter, it is higher than what helicopter flew that this aircraft has fixed wing airplane, fly is remote, fly is fast, fuel-efficient, there is the unexpected many advantages such as escape of can parachuting, fixed wing airplane is rolled into one by this aircraft with helicopter advantage, (need not runway landing) is also had superiority than the hovercar occurred in the world at present, fixed-wing can be widely used in and have man-machine, unmanned plane, prototype field.
Description
Technical field
The present invention relates to field of aircraft, have people's aircraft, unmanned aerial vehicle, the model of an airplane particularly to one.
Background technology
At present, single screw fixed wing airplane is also not carried out taking off vertically and vertical landing both at home and abroad, it is known that VTOL largest benefit is to need not airfield runway, need not oneself build personal runway, save soil, build personal runway, park the writing expenses such as airport, it can have smooth just can take off vertically as helicopter, vertical landing, it is higher than what helicopter flew that this aircraft has fixed wing airplane, fly is remote, fly is fast, fuel-efficient, there is the unexpected many advantages such as escape of can parachuting, fixed wing airplane is rolled into one by this aircraft with helicopter advantage, (need not runway landing) is also had superiority than the hovercar occurred in the world at present.
Summary of the invention
The technical problem to be solved is that current single screw fixed wing airplane can not realize VTOL defect, and the present invention seeks to solve this problem by following technical scheme.
A kind of uniclinal switch rotor fuselage holds up VTOL aircraft, and it includes fuselage, wing, empennage, airscrew engine, stretches out landing Curved beam, motor, tail amortisseur, tail photographic head below head outer fuselage roof two longerons, drive end units.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, airscrew engine is verted and is driven by motor, airscrew engine is arranged on stretches out on two longeron front-end brackets of the external fuselage roof of head, the both sides rotating shaft of airscrew engine connects with the axle sleeve on support, both sides shaft axis is close to by airscrew engine center of gravity, and its side rotating shaft and motor drive shaft are bonded.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and drive end unit is provided with landing amortisseur, amortisseur and two fixing connections of longeron rear end screw, it is simple to maintenance is changed.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and for landing Curved beam below drive end unit, its one end is connected with fuselage roof longeron, and its one end is connected with fuselage bottom longeron, and it posts anti-wear rubber.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and drive end unit is provided with outdoor three anti-photographic head and observes for landing used.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and wing is arranged on fuselage roof, and two longerons of wing and fuselage roof are fixing to be connected.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and its airscrew engine is verted and controlled by manually and automatically both of which, increases safety.
Described uniclinal switch rotor fuselage holds up VTOL aircraft, and fuselage both sides are provided with hatch door, is beneficial to the convenient parachute jumping escape of unexpected dangerous situation.
Accompanying drawing explanation
Fig. 1 be invention at ground parked state schematic perspective view.
Fig. 2 is taking off and the state schematic perspective view that lands of invention.
Fig. 3 is the climb mode schematic perspective view of invention.
Fig. 4 is that the flat of invention flies state schematic perspective view.
Fig. 5 is that schematic perspective view is amplified in the fuselage roof one side girder front end of the present invention.
Detailed description of the invention
The present invention is further described with embodiment below in conjunction with the accompanying drawings.
The embodiment of the present invention is developed manufacture based on high mounted wing light aerocraft.
The import aero-engine that the big safety of small in volume horsepower is high selected by electromotor.
Motor used by tilted propeller electromotor uses the high-powered hydraulic motor of small in volume.
Cabin is designed with reference to SUV automotive light weight technology, it is simple to personnel go on or off the plane.
Tail photographic head selects Radix Saposhnikoviae, outdoor pick-up head rainproof, cold-proof.
Claims (6)
1. a uniclinal switch rotor fuselage holds up VTOL aircraft, landing Curved beam, motor, landing amortisseur below the external fuselage roof of head two longerons, drive end units is stretched out including fuselage, wing, empennage, single screw electromotor, front end, it is characterized in that, described single screw electromotor is at head upper and can vert, during VTOL, propeller axis is plumbness all the time, when taking off, head first gradually lifts, and fuselage is gradually holded up and taken off vertically to liftoff, during landing, process is contrary.
Uniclinal switch rotor fuselage the most according to claim 1 holds up VTOL aircraft, it is characterized in that, described airscrew engine (1) is verted and is driven by motor (2), the upper both sides rotating shaft (3) of airscrew engine (1) is arranged on support (4), support (4) is fixed on two longeron (6) front ends that fuselage (5) top is stretched out outside head, the both sides rotating shaft (3) of airscrew engine (1) connects with the axle sleeve (7) on support (4), both sides rotating shaft (3) axis is close to by airscrew engine center of gravity, one side shaft of both sides rotating shaft (3) is bonded with motor (2) axle, motor (2) is fixed on support (4).
Uniclinal switch rotor fuselage the most according to claim 1 holds up VTOL aircraft, it is characterised in that wing (8) is arranged on fuselage (4) top, and wing (8) is fixing with two, fuselage (5) top longeron (6) to be connected.
Uniclinal switch rotor fuselage the most according to claim 1 holds up VTOL aircraft, it is characterized in that, drive end unit is provided with landing amortisseur (9), and amortisseur (9) is screwed with two longeron (6) tail ends and is connected, and amortisseur (9) one end connects yielding rubber pad (10).
Uniclinal switch rotor fuselage the most according to claim 1 holds up VTOL aircraft, it is characterized in that, drive end unit is arranged below landing Curved beam (11), abrasionproof damping rubber (12) is posted on it, landing Curved beam (11) one end is fixing with longeron (6) to be connected, and one end is fixing with fuselage bottom beam to be connected.
Uniclinal switch rotor fuselage the most according to claim 1 holds up VTOL aircraft, it is characterised in that drive end unit is provided with photographic head (13) and observes for landing used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510302930.7A CN106275420A (en) | 2015-06-06 | 2015-06-06 | Uniclinal switch rotor fuselage holds up VTOL aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510302930.7A CN106275420A (en) | 2015-06-06 | 2015-06-06 | Uniclinal switch rotor fuselage holds up VTOL aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275420A true CN106275420A (en) | 2017-01-04 |
Family
ID=57656601
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510302930.7A Pending CN106275420A (en) | 2015-06-06 | 2015-06-06 | Uniclinal switch rotor fuselage holds up VTOL aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275420A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2437330A (en) * | 1944-01-24 | 1948-03-09 | Alexander S Mullgardt | Variable incidence wing control for aircraft of the rotaly wing or airplane sustained type |
| US2994492A (en) * | 1954-07-30 | 1961-08-01 | Dobson | Convertiplane, and method of operating an aircraft |
| CN201371932Y (en) * | 2009-03-20 | 2009-12-30 | 中国人民解放军国防科学技术大学 | Tilt-rotor vector propelling device for underwater propeller |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN104417750A (en) * | 2013-09-03 | 2015-03-18 | 杨家雄 | Tandem tilt rotor aircraft |
| CN204250360U (en) * | 2014-11-06 | 2015-04-08 | 南京航空航天大学 | Culvert type verts aircraft |
| CN204895860U (en) * | 2015-06-06 | 2015-12-23 | 杨林 | Uniclinal changes rotor fuselage and holds up vertical take -off and landing aircraft |
-
2015
- 2015-06-06 CN CN201510302930.7A patent/CN106275420A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2437330A (en) * | 1944-01-24 | 1948-03-09 | Alexander S Mullgardt | Variable incidence wing control for aircraft of the rotaly wing or airplane sustained type |
| US2994492A (en) * | 1954-07-30 | 1961-08-01 | Dobson | Convertiplane, and method of operating an aircraft |
| CN201371932Y (en) * | 2009-03-20 | 2009-12-30 | 中国人民解放军国防科学技术大学 | Tilt-rotor vector propelling device for underwater propeller |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN104417750A (en) * | 2013-09-03 | 2015-03-18 | 杨家雄 | Tandem tilt rotor aircraft |
| CN204250360U (en) * | 2014-11-06 | 2015-04-08 | 南京航空航天大学 | Culvert type verts aircraft |
| CN204895860U (en) * | 2015-06-06 | 2015-12-23 | 杨林 | Uniclinal changes rotor fuselage and holds up vertical take -off and landing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204452934U (en) | The double mode aircraft of rotor, fixed-wing | |
| KR101386959B1 (en) | Flying car with multi-rotor and multi-axis multi-step tilt function | |
| CN105966612B (en) | Become posture VTOL unmanned plane | |
| CN107571994B (en) | Aircraft | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN207631486U (en) | A kind of VTOL composite wing unmanned plane that rotor can vert | |
| CN202728571U (en) | Private aircraft | |
| CN106864744A (en) | A kind of co-axial rotor variant vertically taking off and landing flyer | |
| CN107963209A (en) | Tandem wing tilting rotor wing unmanned aerial vehicle | |
| CN107323660A (en) | A kind of VTOL method of dalta wing unmanned plane | |
| CN104875875B (en) | A kind of gas wing-type air-flow orients load transportation aircraft | |
| CN105523182A (en) | Vertaplane with front tilting rotor wing and rear tilting rotor wing | |
| CN106005371B (en) | Difference directly drives dynamic three rudder face unmanned planes entirely | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| CN204895860U (en) | Uniclinal changes rotor fuselage and holds up vertical take -off and landing aircraft | |
| CN211253017U (en) | Unmanned aerial vehicle with tandem wings capable of vertically taking off and landing | |
| CN104992586A (en) | Airplane system capable of realizing flight experience | |
| CN207523932U (en) | Tandem wing tilting rotor wing unmanned aerial vehicle | |
| CN206691363U (en) | A kind of delta-wing aircraft of energy VTOL | |
| CN107284658B (en) | Composite vertical/short-distance take-off and landing aircraft | |
| CN106275420A (en) | Uniclinal switch rotor fuselage holds up VTOL aircraft | |
| CN202807094U (en) | Vertiplane | |
| CN106882372A (en) | A kind of delta-wing aircraft of energy VTOL | |
| CN211435086U (en) | Novel power model airplane | |
| CN206528642U (en) | A kind of launching apparatus of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170104 |