CN108773484A - Single ducted fan formula composite wing cargo aircraft afterwards - Google Patents
Single ducted fan formula composite wing cargo aircraft afterwards Download PDFInfo
- Publication number
- CN108773484A CN108773484A CN201810549520.6A CN201810549520A CN108773484A CN 108773484 A CN108773484 A CN 108773484A CN 201810549520 A CN201810549520 A CN 201810549520A CN 108773484 A CN108773484 A CN 108773484A
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- CN
- China
- Prior art keywords
- wing
- ducted fan
- fan formula
- formula composite
- lift
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of rear single ducted fan formula composite wing cargo aircraft, is made of the compound rotor aircraft of rear list ducted fan formula and shipping storehouse；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body both sides hybrid lift wing, ducted fan propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge；Shipping storehouse is mounted on mounted on the lower section of body.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, low energy consumption for flight, the hang time is long, safe the features such as.
Description
Technical field
The present invention relates to a kind of aircraft, single ducted fan formula composite wing cargo aircraft, belongs to after specifically a kind of
Aircraft equipment technology field.
Background technology
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer（Such as helicopter and more rotors）Two major classes.When
So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have
It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage；
Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is big, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the shortcomings of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The shortcomings of controllability when flat flight is not satisfactory, and that there is flight resistances is big, and energy consumption is high, and safety coefficient is not still high.
Invention content
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot
Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, hydrous waters
The flat rudder wing can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel.
To achieve the goals above, the present invention includes the compound rotor aircraft of rear single ducted fan formula, shipping storehouse；Wherein, after
Single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body both sides hybrid lift wing, ducted fan propulsion
Device；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are set
In respect of wing hinge；Shipping storehouse is mounted on mounted on the lower section of body.Hybrid lift wing tail end is additionally provided with wing tail.Compound liter
Power wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type self interlocking interface female；The magnetic
Suction self interlocking interface male connector is identical as magnetic-type self interlocking interface female size.Shipping storehouse is mounted on mounted on body
Lower section.
Further, propeller is a variety of dynamic structures such as electric ducted fan, the dynamic ducted fan of oil.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on compound
The front and back of lifting wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Its
In, at least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in wing both sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides；The first
It is designed with socket on plate platform；The socket is female or male.
Further, electro-hydraulic gas interface carries lid.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
5, the present invention also has successive magnetic-type self interlocking interface, and the cluster of aircraft is facilitated to fly, and further drops
Power consumption when low cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with
The flight of long range, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize flight
Air rescue between device, i.e., preceding aircraft take off faulty aircraft dragging below, realize aircraft not seen before
Between rescue phenomenon mutually.
8. thrust device modularization can very easily realize that repair is replaced.
9. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention；
Fig. 2 is the side view of the present invention；
Fig. 3 is the rearview of the present invention；
Fig. 4 is the plan view of the present invention；
Fig. 5 is the oblique view of the present invention；
In figure：101：Body；102：Hybrid lift wing；104：Self-enclosed ducted fan；105：Vertical tail；1051. vertical
The rudder wing；106：Propeller；107：Energy Management System；1021：Lift main wing；1022：The horizontal lifting rudder wing；1023：Balance tail
The wing；1028：Wing hinge；1001：Socket；1002：Cavity；1003：Mounting hole；1006：Battery/fuel；108：Video camera；
1026：Magnetic-type self interlocking interface male connector；1027：Magnetic-type self interlocking interface female；1036, electro-hydraulic gas interface；
10361, lid；113, shipping storehouse.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, single ducted fan formula composite wing cargo aircraft after a kind of, which is characterized in that including rear single duct
The compound rotor aircraft of fan-type, shipping storehouse are mounted on mounted on the lower section of body.
Wherein, rear single compound rotor aircraft of ducted fan formula includes body 101, is fixedly mounted on 101 liang of body
Side hybrid lift wing 102, propeller 106；Wherein, the body 101 is set as deck platform；The hybrid lift machine
Self-enclosed ducted fan 104 built in the wing 102,102 outside of hybrid lift wing are designed with wing hinge 1028；Hybrid lift wing
Tail end is additionally provided with wing tail 1024.102 front and back of hybrid lift wing are respectively set to magnetic-type self interlocking interface male connector
1026 and magnetic-type self interlocking interface female 1027；The magnetic-type self interlocking interface male connector 1026 with it is magnetic-type automatic
Mutual lock interface 1027 sizes of female are identical；The shipping storehouse 113 is mounted on mounted on the lower section of body 101.
As further improvement of the invention, propeller 106 is a variety of power such as electric ducted fan, the dynamic ducted fan of oil
Structure.
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage
1023 two parts, are separately positioned on the front and back of hybrid lift wing 102；Between lift main wing 1021 and balance empennage 1023
It is reserved with space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one certainly for installation inside lift main wing 1021
Close ducted fan 104.
Improved as of the invention further, vertical tail 105, vertical tail 105 be arranged above body 101 or under
Side；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；The vertical tail 105
Mobilizable vertical rudder wing 1051 is installed below.
As further improvement of the invention, body 101 is set as deck platform；The deck platform both sides are regular
The mounting hole 1003 of arrangement；Socket 1001 is designed in the deck platform；The socket 1001 is female or male.
As further improvement of the invention, electro-hydraulic gas interface 1036 carries lid 10361.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
5, the present invention also has successive magnetic-type self interlocking interface, and the cluster of aircraft is facilitated to fly, and further drops
Power consumption when low cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with
The flight of long range, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize flight
Air rescue between device, i.e., preceding aircraft take off faulty aircraft dragging below, realize aircraft not seen before
Between rescue phenomenon mutually.
8. thrust device modularization can very easily realize that repair is replaced.
9. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, are within the scope of protection of the invention.
Claims (5)
1. single ducted fan formula composite wing cargo aircraft after a kind of, which is characterized in that including rear single ducted fan formula composite wing
Aircraft, shipping storehouse（113）；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body（101）, be fixedly mounted on body（101）Two
The hybrid lift wing of side（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described answers
Close lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；Hybrid lift wing（102）Tail end is additionally provided with wing tail（1024）；Propeller（106）For ducted fan propeller；It is multiple
Close lifting wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1026）With magnetic-type automatic mutual interlocking
Mouth female（1027）；The magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female（1027）
Size is identical；
The shipping storehouse（113）Mounted on mounted on body（101）Lower section.
2. a kind of rear single ducted fan formula composite wing cargo aircraft according to claim 1, which is characterized in that described
Propeller（106）For a variety of dynamic structures such as electric ducted fan, the dynamic ducted fans of oil.
3. a kind of rear single ducted fan formula composite wing cargo aircraft according to claim 1, which is characterized in that described
Hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two parts, are separately positioned on
Hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between be reserved with space, in space
It is provided with the horizontal lifting rudder wing（1022）；Wherein, lift main wing（1021）There are one self-enclosed ducted fans for internal at least installation
（104）.
4. a kind of rear single ducted fan formula composite wing cargo aircraft according to claim 1, which is characterized in that also wrap
Include vertical tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；The vertical tail（105）
It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）Being equipped with below can live
The dynamic vertical rudder wing（1051）.
5. a kind of rear single ducted fan formula composite wing cargo aircraft according to claim 1, which is characterized in that described
Body（101）It is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides（1003）；The deck
Socket is designed on platform（1001）；The socket（1001）For female or male.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810549520.6A CN108773484A (en) | 2018-05-31 | 2018-05-31 | Single ducted fan formula composite wing cargo aircraft afterwards |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810549520.6A CN108773484A (en) | 2018-05-31 | 2018-05-31 | Single ducted fan formula composite wing cargo aircraft afterwards |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108773484A true CN108773484A (en) | 2018-11-09 |
Family
ID=64028257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810549520.6A Pending CN108773484A (en) | 2018-05-31 | 2018-05-31 | Single ducted fan formula composite wing cargo aircraft afterwards |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108773484A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
-
2018
- 2018-05-31 CN CN201810549520.6A patent/CN108773484A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
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| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for 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: 20181109 |