CN103192981A - Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft - Google Patents
Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft Download PDFInfo
- Publication number
- CN103192981A CN103192981A CN2013101281205A CN201310128120A CN103192981A CN 103192981 A CN103192981 A CN 103192981A CN 2013101281205 A CN2013101281205 A CN 2013101281205A CN 201310128120 A CN201310128120 A CN 201310128120A CN 103192981 A CN103192981 A CN 103192981A
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- landing
- stol
- short take
- 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
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Wind Motors (AREA)
Abstract
The invention provides a motor-driven low-noise short-distance taking-off and landing wing-connected aircraft. The motor-driven low-noise short-distance taking-off and landing wing-connected aircraft is characterized by comprising an aircraft body (1), front wings (2), rear wings (4), end plates (3) and vertical fins (5), wherein the front wings (2) are flat and straight ladder-shaped wings, and are positioned on the upper part of the aircraft body; the rear wings (4) are sweep forward upper reverse aircraft wings, and are positioned below the aircraft body; and the end plates (3) are used for connecting wing tips of the front wings (2) and the rear wings (4) together so as to form a case-shaped structure. The motor-driven low-noise short-distance taking-off and landing wing-connected aircraft provided by the invention has the advantages and beneficial effects that the excellent structure performance of a wing-connected-type aircraft is inherited; the short-distance taking-off and landing capabilities are realized through slide flow deviation power; a motor-driven airscrew thrust device and a power generating unit arranged in the tail of the aircraft lower the whole noise level of the aircraft effectively; and the backup design of a power system enables the aircraft to have extremely high reliability, and the safety in short-distance taking-off and landing and cruising is ensured. Each technique adopted by the invention has high maturity, and is integrally simple, and easy to achieve, and the construction and using costs are low.
Description
Technical field
The present invention relates to a kind of electronic low noise short take-off and landing (STOL) and connect wing aircraft, belong to fixed wing aircraft design field in the aviation aircraft.
Background technology
Connecting wing layout aircraft all has a clear superiority on pneumatic and structure.Aerodynamic characteristic is seen, connects wing layout actv. and has weakened the aircraft induced drag, often has very high 1ift-drag ratio, therefore can obtain cruise performance efficiently, saves fuel oil or increases voyage.See on the structure, connect the case type structures good integral strength of wing layout, reduced the requirement to local structural strength, saved architecture quality greatly, thereby increase capacity weight.But, for conventional airplane, pneumatic and structural behaviour can get a promotion by other means, and on even more important takeoff and landing performance and noise control, connect wing layout and do not provide better solution, therefore connect wing layout in the civil and military field and be not used widely.
Summary of the invention
The present invention is directed to the above weakness, provide a kind of electronic low noise short take-off and landing (STOL) to connect the technical scheme of wing aircraft, combine unique power system and slipstream redirecting power-boosting technology on the basis that connects wing layout.
The of the present invention company in the wing topological design, front wing is straight tapered wing, and rear wing is sweepforward, and front wing is connected by an end plate at the wing tip place with rear wing, and circular fuselage is positioned at the centre in the box-like space of front wing and rear wing formation.Preceding nose of wing is installed four electric propellers, about each two, the slip-stream of screw propeller covers the full-span flap of most front wing aerofoil and front wing trailing edge, the high speed slip-stream of screw propeller can effectively improve the usefulness of wing and wing flap, be power-boosting, thereby realize the short take-off and landing (STOL) ability.
In order to reduce in the cabin noise out of my cabin, power system of the present invention adopts the form of four electrical motor screw propellers and two groups of piston engine generatings, compare four piston engines of direct employing and drive screw propeller, can obviously reduce the overall aircraft noise level, and piston engine can be cut off the further noise in the cabin that reduces as for afterbody and by the cabin.This form has also reduced the requirement of avicade's fuel oil in addition, need not be confined to aircraft gasoline.
The present invention when inherit connecting the pneumatic and structural advantage of wing layout aircraft, effectively reduce noise level and and realized short take-off and landing (STOL) ability, overall plan reliability height, technology maturation, realize that easily construction and use cost are cheap, are conducive to the popularization of this layout.
According to an aspect of the present invention, provide a kind of electronic low noise short take-off and landing (STOL) to connect wing aircraft, it is characterized in that comprising: fuselage; Front wing, it is straight tapered airfoil, is positioned at body upper; Rear wing, it is the sweepforward dihedral wing, is positioned at the fuselage below; End plate, its wing tip with front wing and rear wing connects together, and constitutes case type structures; Vertical fin.
Description of drawings
Fig. 1 is the integral layout scheme drawing that electronic low noise short take-off and landing (STOL) according to an embodiment of the invention connects wing aircraft.
Fig. 2 is the power system scheme drawing that electronic low noise short take-off and landing (STOL) according to an embodiment of the invention connects wing aircraft.
The specific embodiment
Shown in the integral layout scheme drawing of Fig. 1, electronic low noise short take-off and landing (STOL) according to an embodiment of the invention connects wing aircraft and comprises fuselage (1), front wing (2), end plate (3), rear wing (4) and vertical fin (5).Front wing (1) is straight tapered airfoil, is positioned at body upper, and rear wing (4) is the sweepforward dihedral wing, is positioned at the fuselage below.The wing tip of front wing (2) and rear wing (4) is connected together by end plate (3), constitute case type structures, has good structural strength, the integral structure lighter weight, this layout also makes electrical motor (10) and screw propeller (11) height put in addition, make this layout can be used as amphibious layout, fuselage (1) bottom Ye Xiangying changes the hull bottom form into.The primary control surface of aircraft comprises: be positioned at the yaw rudder (6) of vertical fin (5) trailing edge, be used for course control; Be positioned at a pair of aileron (8) and a pair of elevating rudder (7) of rear wing trailing edge, be respectively applied to lift-over control and pitch control subsystem.
As shown in Figure 1, front wing (2), wing flap (9) and electrical motor (10), screw propeller (11) constitute slipstream redirecting power-boosting system jointly, are used for realizing the short take-off and landing (STOL) ability.Four electrical motors (10) are arranged in front wing (2) leading edge altogether, and each drives a large scale screw propeller (11).The high speed slip-stream of screw propeller (11) will cover the full-span flap (9) of the most of wing area of front wing (2) and front wing (2) trailing edge, effectively promote the performance of wing and wing flap, significantly improve lift coefficient.In addition, when down inclined to one side wing flap (9) is flow through in slip-stream since the wall attachment effect air flow line also with under partially, thereby make screw propeller (11) pulling force produce component upwards, direct lift is provided.
The according to an embodiment of the invention electronic low noise short take-off and landing (STOL) of Xian Shiing connects in the power system of wing aircraft as schematically shown in Figure 2, the electric power that is positioned over the cover piston engine (16) of two in fuselage (1) the afterbody cabin, the generation of electrical generator (15) group sends electric power diverter (13) to by cable (14), diverter (13) then sends electric power to four electrical motors (10) by four cables (12), and drives screw propeller (11) rotation.Under the normal circumstances, the rating horsepower of driving engine (16) can only provide two motors (10) power demand, but its maximum power can drive four electrical motors (10) simultaneously, but can not do long-time running under the maximum power.If the piston engine of a certain side (16) or electrical generator (15) lost efficacy, then diverter (13) can symmetry cut off one group of electrical motor (10), the normal operation that keeps other two motors (10), this emergency mode is applicable to the cruising flight stage, perhaps opposite side driving engine (10) can be transferred to maximum power, guarantee the running of four electrical motors (10), this emergency mode is applicable to the short take-off and landing (STOL) mission phase, can avoid the sudden change of lift.If some electrical motors (10) of a certain side or screw propeller (11) lost efficacy, then the electrical motor (10) that can cut off the opposite side symmetric position by the output of adjustment diverter (13) is avoided disadvantageous yawing moment.See on the whole, this power system simple in structure, driving engine (16) is built in fuselage, the less size of electrical motor (10) has all effectively reduced the interference of power system to aerodynamic configuration, the backup design of electrical motor (10) and driving engine (16) makes system reliability higher, it is also safer to fly, and electronic thruster also makes control simple more quick.In addition, the less noise of electrical motor (10) itself, and driving engine (16) is built in the noise level that fuselage all effectively reduces overall aircraft.
Advantage of the present invention and beneficial effect comprise:
-inherited and connected the outstanding structural behaviour of wing formula aircraft.
-realized the short take-off and landing (STOL) ability by the slipstream redirecting power-boosting.
-electric propeller thruster and place the generator set of tail inside to effectively reduce the noise level of overall aircraft.
The backup of-power system design makes aircraft have high reliability, has guaranteed short take-off and landing (STOL) and the safety when cruising.
-every technology of the present invention all has higher degree of ripeness, and comparatively simple on the whole, realizes easily, and construction and use cost are cheap.
Claims (9)
1. electronic low noise short take-off and landing (STOL) connects wing aircraft, it is characterized in that comprising:
Fuselage (1),
Front wing (2), it is straight tapered airfoil, is positioned at body upper,
Rear wing (4), it is the sweepforward dihedral wing, is positioned at the fuselage below,
End plate (3), its wing tip with front wing (2) and rear wing (4) connects together, and constitutes case type structures,
Vertical fin (5).
2. the electronic low noise short take-off and landing (STOL) according to claim 1 connects wing aircraft, it is characterized in that further comprising:
Be positioned at the yaw rudder (6) of vertical fin (5) trailing edge, be used for course control;
Be positioned at a pair of aileron (8) of rear wing (4) trailing edge, lift-over control respectively,
Be positioned at a pair of elevating rudder (7) of rear wing (4) trailing edge, be used for pitch control subsystem,
Be arranged on the full-span flap (9) of front wing (2) trailing edge.
3. the electronic low noise short take-off and landing (STOL) according to claim 2 connects wing aircraft, it is characterized in that further comprising:
Be arranged in four electrical motors (10) of front wing (2) leading edge, each drives a large scale screw propeller (11),
Described four screw propellers (11), the high speed slip-stream of its generation covers the most of wing area of front wing (2) and full-span flap (9), thereby effectively promotes the performance of wing and wing flap, improves lift coefficient.
4. the electronic low noise short take-off and landing (STOL) according to one of claim 1-3 connects wing aircraft, it is characterized in that:
Electrical motor (10) and screw propeller (11) height are put, and fuselage (1) bottom leaf has the hull bottom form, make this electronic low noise short take-off and landing (STOL) connect wing aircraft and can be used as amphibious aircraft.
5. the electronic low noise short take-off and landing (STOL) according to claim 4 connects wing aircraft, it is characterized in that:
Front wing (2), wing flap (9) and electrical motor (10), screw propeller (11) constitute slipstream redirecting power-boosting system jointly, be used for realizing the short take-off and landing (STOL) ability, wherein, when inclined to one side down wing flap (9) is flow through in slip-stream, since the wall attachment effect air flow line also with under partially, thereby make screw propeller (11) pulling force produce component upwards, direct lift is provided.
6. the electronic low noise short take-off and landing (STOL) according to one of claim 1-3 connects wing aircraft, it is characterized in that further comprising:
Be positioned over the cover piston engine (16) of two in fuselage (1) the afterbody cabin,
By described two cover piston engine (16) separately-driven two electrical generators (15),
Electric power diverter (13), it receives the electric power that two electrical generators (15) produce by first cable (14), and by four second cables (12) electric power is sent to four electrical motors (10) respectively.
7. the electronic low noise short take-off and landing (STOL) according to claim 6 connects wing aircraft, it is characterized in that:
Under the normal circumstances, the rating horsepower of every driving engine (16) can only provide two motors (10) power demand, but the maximum power of every driving engine (16) can drive four electrical motors (10) simultaneously, but driving engine (16) can not be done long-time running under this maximum power.
8. the electronic low noise short take-off and landing (STOL) according to claim 7 connects wing aircraft, it is characterized in that:
Under the situation that the piston engine (15) of a certain side and/or electrical generator (15) lost efficacy, diverter (13) can cut off one group of electrical motor (10) by symmetry, keep the normal operation of other two motors (10), thereby enter a kind of emergency pattern that is applicable to the cruising flight stage.
9. the electronic low noise short take-off and landing (STOL) according to claim 7 connects wing aircraft, it is characterized in that:
Under the situation that the piston engine (15) of a certain side and/or electrical generator (15) lost efficacy, another driving engine (10) that is transferred to maximum power can guarantee the running of four electrical motors (10), thereby enter a kind of this emergency pattern that is applicable to the short take-off and landing (STOL) mission phase, to avoid the sudden change of lift
When some electrical motors (10) of a certain side or screw propeller (11) lost efficacy, diverter (13) can be avoided disadvantageous yawing moment by cutting off the electrical motor (10) of opposite side symmetric position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101281205A CN103192981A (en) | 2013-04-12 | 2013-04-12 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101281205A CN103192981A (en) | 2013-04-12 | 2013-04-12 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103192981A true CN103192981A (en) | 2013-07-10 |
Family
ID=48715839
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101281205A Pending CN103192981A (en) | 2013-04-12 | 2013-04-12 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103192981A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN107000841A (en) * | 2014-09-25 | 2017-08-01 | 安德拉斯·海尔纳迪 | Method for improving the concept of a boxed wing aircraft and corresponding aircraft construction |
| CN108569399A (en) * | 2018-04-10 | 2018-09-25 | 西北工业大学 | A kind of short take-off and landing unmanned plane using distributed duct power |
| CN109476373A (en) * | 2016-05-18 | 2019-03-15 | 空中客车A^3有限责任公司 | For passenger or the auto-navigation aircraft of cargo transport |
| CN110091998A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift based on all-electric driving |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN116252944A (en) * | 2023-05-11 | 2023-06-13 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4053125A (en) * | 1973-08-30 | 1977-10-11 | Alexander Ratony | Staggered channel wing-type aircraft |
| US4856736A (en) * | 1987-06-26 | 1989-08-15 | Skywardens Limited | Aircraft with paired aerofoils |
| US5927655A (en) * | 1996-09-09 | 1999-07-27 | Aerospatiale Societe Nationale Industrielle | Device for controlling the thrust of a multi-engine aircraft |
| CN201077530Y (en) * | 2007-08-02 | 2008-06-25 | 叶万章 | Vertically taking off and landing energy-saving pre-warning device |
| RU106222U1 (en) * | 2011-02-17 | 2011-07-10 | Государственное образовательное учреждение высшего профессионального образования "Санкт-Петербургский государственный университет Аэрокосмического приборостроения" | HYDROPLANE AMPHIBIA |
| CN202728573U (en) * | 2012-04-05 | 2013-02-13 | 唐粮 | Double-engine rotor-wing unmanned aerial vehicle system |
-
2013
- 2013-04-12 CN CN2013101281205A patent/CN103192981A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4053125A (en) * | 1973-08-30 | 1977-10-11 | Alexander Ratony | Staggered channel wing-type aircraft |
| US4856736A (en) * | 1987-06-26 | 1989-08-15 | Skywardens Limited | Aircraft with paired aerofoils |
| US5927655A (en) * | 1996-09-09 | 1999-07-27 | Aerospatiale Societe Nationale Industrielle | Device for controlling the thrust of a multi-engine aircraft |
| CN201077530Y (en) * | 2007-08-02 | 2008-06-25 | 叶万章 | Vertically taking off and landing energy-saving pre-warning device |
| RU106222U1 (en) * | 2011-02-17 | 2011-07-10 | Государственное образовательное учреждение высшего профессионального образования "Санкт-Петербургский государственный университет Аэрокосмического приборостроения" | HYDROPLANE AMPHIBIA |
| CN202728573U (en) * | 2012-04-05 | 2013-02-13 | 唐粮 | Double-engine rotor-wing unmanned aerial vehicle system |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107000841A (en) * | 2014-09-25 | 2017-08-01 | 安德拉斯·海尔纳迪 | Method for improving the concept of a boxed wing aircraft and corresponding aircraft construction |
| CN107000841B (en) * | 2014-09-25 | 2019-08-16 | 安德拉斯·海尔纳迪 | Method for improving the concept of a boxed wing aircraft and corresponding aircraft construction |
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN109476373A (en) * | 2016-05-18 | 2019-03-15 | 空中客车A^3有限责任公司 | For passenger or the auto-navigation aircraft of cargo transport |
| CN111315655B (en) * | 2017-11-02 | 2023-10-27 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for an air, water, land or space vehicle |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN108569399A (en) * | 2018-04-10 | 2018-09-25 | 西北工业大学 | A kind of short take-off and landing unmanned plane using distributed duct power |
| CN108569399B (en) * | 2018-04-10 | 2022-07-26 | 西北工业大学 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
| CN110091998A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift based on all-electric driving |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
| CN110481771B (en) * | 2019-09-26 | 2024-06-07 | 成都纵横大鹏无人机科技有限公司 | Fixed wing aircraft capable of taking off and landing vertically and unmanned aerial vehicle system |
| CN116252944B (en) * | 2023-05-11 | 2023-08-11 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
| CN116252944A (en) * | 2023-05-11 | 2023-06-13 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20210206487A1 (en) | Aircraft and Modular Propulsion Unit | |
| US9096312B2 (en) | Aircraft | |
| US9475579B2 (en) | Vertical take-off and landing vehicle with increased cruise efficiency | |
| CN107499506B (en) | Distributed propulsion tailstock type vertical take-off and landing fixed-wing aircraft | |
| US6659394B1 (en) | Compound tilting wing for high lift stability and control of aircraft | |
| CN103192981A (en) | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft | |
| CN108569399B (en) | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power | |
| EP3976470A2 (en) | A novel aircraft design using tandem wings and a distributed propulsion system | |
| EP3663197B1 (en) | High-speed hybrid propulsion for aircraft | |
| CN107089328B (en) | Control method of hybrid tail-seat type vertical take-off and landing long-endurance unmanned aerial vehicle | |
| CN202728574U (en) | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| WO2013056493A1 (en) | Composite aircraft consisting of fixed-wing and electrically driven propellers | |
| CN103287576A (en) | Tailless layout single tail seat type vertical take-off and landing aircraft | |
| CN105059542A (en) | Vertical take-off and landing fixed wing long-endurance air vehicle | |
| US11407507B2 (en) | Lift rotor system | |
| CN211468780U (en) | Short-distance take-off and landing unmanned conveyor | |
| CN206857002U (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN213323678U (en) | Power distribution type unmanned aerial vehicle capable of taking off and landing vertically | |
| CN210793660U (en) | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle | |
| CN111532426A (en) | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout | |
| CN112027080B (en) | Hybrid electric propulsion vertical take-off and landing unmanned aerial vehicle using bimodal power cabin | |
| CN212951108U (en) | Variable-diameter unmanned tilt rotorcraft | |
| CN211223827U (en) | Unmanned aerial vehicle capable of taking off and landing vertically |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130710 |