CN108791865A - The foldable compound rotor aircraft of single vortex-spraying type afterwards - Google Patents
The foldable compound rotor aircraft of single vortex-spraying type afterwards Download PDFInfo
- Publication number
- CN108791865A CN108791865A CN201810549722.0A CN201810549722A CN108791865A CN 108791865 A CN108791865 A CN 108791865A CN 201810549722 A CN201810549722 A CN 201810549722A CN 108791865 A CN108791865 A CN 108791865A
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- China
- Prior art keywords
- wing
- vertical tail
- rotor aircraft
- magnetic
- single vortex
- 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
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
Abstract
The present invention is a kind of foldable compound rotor aircraft of rear single vortex-spraying type, including body, the hybrid lift wing, the propeller that are fixedly mounted on body both sides；Wherein, the body is set as deck platform；Vertical tail is additionally provided with above or below body, vertical tail is arranged in wing both sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail;Self-enclosed ducted fan built in the hybrid lift wing, hybrid lift wing outside are designed with wing hinge and electro-hydraulic gas interface；It is turbojet to close lifting wing front and back and be respectively set to magnetic-type self interlocking interface male connector and magnetic-type self interlocking interface female propeller.The characteristics of present invention combination turbojet, 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, the foldable compound rotor aircraft of specifically a kind of rear single vortex-spraying type belongs to winged
Row device 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 body, is mounted on body both sides by the way that folding hinge is folding
Hybrid lift wing, propeller；Wherein, the body is set as deck platform；It is additionally provided with above or below body vertical
Empennage, vertical tail are arranged in wing both sides；Vertical tail may be implemented to fold；It is equipped with behind the vertical tail movable
The vertical rudder wing;Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge
(1028) and electro-hydraulic gas interface；Hybrid lift wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type
Self interlocking interface female；The magnetic-type self interlocking interface male connector and magnetic-type self interlocking interface female size phase
Together；The propeller is turbojet.
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（104）.
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；Socket is female or male.
Further, electro-hydraulic gas interface carries lid.
Further, it is provided with video camera in front of body；Video camera is monopod video camera.
Further, vertical tail, forms an angle with body planar shaped, and haulage gear is equipped on vertical tail, realizes vertical
The deflection of the rudder wing.
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, foldable pattern is used between body and both sides wing；Fold mechanism is folding hinge；After the wing expansion of both sides
It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier
It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double
The aircraft of quantity；Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, 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.
4, the present invention uses turbojet, simple in structure, high-altitude high speed performance is good, greatly improves aircraft
Flying speed.
5, the present invention can realize multiple functions using hardware and software platform, modularized design,
6, 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.
7. thrust device modularization can very easily realize that repair is replaced.
8. 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；
1036, electro-hydraulic gas interface；10361, lid；1026：Magnetic-type self interlocking interface male connector；1027：Magnetic-type automatic mutual interlocking
Mouth female；1059：Folding hinge.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, the foldable compound rotor aircraft of single vortex-spraying type after a kind of, which is characterized in that including body 101, lead to
Cross folding hybrid lift wing 102, the propeller 106 mounted on 101 both sides of body of folding hinge 1059；Wherein, described
Body 101 be set as deck platform；Vertical tail 105 is additionally provided with above or below body 101, vertical tail 105 is arranged
In wing both sides；The vertical tail 105 may be implemented to fold；It is equipped with behind the vertical tail 105 mobilizable vertical
The rudder wing 1051;Self-enclosed ducted fan 104 built in the hybrid lift wing 102,102 outside of hybrid lift wing are designed with
Wing hinge 1028 and electro-hydraulic gas interface 1036；102 front and back of hybrid lift wing are respectively set to magnetic-type automatic mutual interlocking
Mouth male connector 1026 and magnetic-type self interlocking interface female 1027；The magnetic-type self interlocking interface male connector 1026 and magnetic
Formula self interlocking interface 1027 sizes of female are identical；The propeller 106 is turbojet.
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.
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 1026 carries lid 10261.
As further improvement of the invention, 101 front of body is provided with video camera 108；Video camera 108 images for holder
Machine.
As further improvement of the invention, electro-hydraulic gas interface 1036 carries lid 10361.
As further improvement of the invention, vertical tail, 105 forms an angle with body planar shaped, and is installed on vertical tail,
There is haulage gear, realizes the deflection of the vertical rudder wing.
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 uses turbojet, simple in structure, high-altitude high speed performance is good, greatly improves aircraft
Flying speed.
4, 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 (6)
1. the foldable compound rotor aircraft of single vortex-spraying type after a kind of, which is characterized in that including body（101）, pass through folding hinge
（1059）It is folding to be mounted on body（101）The hybrid lift wing of both sides（102）, propeller（106）；
Wherein, the body（101）It is set as deck platform；Body（101）Above or below be additionally provided with vertical tail
（105）, vertical tail（105）It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail
（105）Mobilizable vertical rudder wing is installed below（1051）;
The hybrid lift wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）It designs in outside
There are wing hinge (1028) and electro-hydraulic gas interface（1036）；Hybrid lift wing（102）Front and back be respectively set to it is magnetic-type from
Move mutual lock interface male connector（1026）With magnetic-type self interlocking interface female（1027）；The magnetic-type self interlocking interface is public
Head（1026）With magnetic-type self interlocking interface female（1027）Size is identical；
The propeller（106）For turbojet.
2. a kind of foldable compound rotor aircraft of rear single vortex-spraying type 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 multiple
Close lifting wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between be reserved with space, set in space
It is equipped 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）.
3. a kind of foldable compound rotor aircraft of rear single vortex-spraying type 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 is flat
Socket is designed on platform（1001）；The socket（1001）For female or male.
4. a kind of foldable compound rotor aircraft of rear single vortex-spraying type according to claim 1, which is characterized in that described
Electro-hydraulic gas interface（1026）With lid（10261）.
5. a kind of foldable compound rotor aircraft of rear single vortex-spraying type according to claim 1, which is characterized in that described
Body（101）Front is provided with video camera（108）；Video camera（108）For monopod video camera.
6. a kind of foldable compound rotor aircraft of rear single vortex-spraying type according to claim 1, which is characterized in that described
Vertical tail,（105）It forms an angle with body planar shaped, and haulage gear is installed on vertical tail, realize the inclined of the vertical rudder wing
Turn.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810549722.0A CN108791865A (en) | 2018-05-31 | 2018-05-31 | The foldable compound rotor aircraft of single vortex-spraying type afterwards |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810549722.0A CN108791865A (en) | 2018-05-31 | 2018-05-31 | The foldable compound rotor aircraft of single vortex-spraying type afterwards |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108791865A true CN108791865A (en) | 2018-11-13 |
Family
ID=64089903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810549722.0A Pending CN108791865A (en) | 2018-05-31 | 2018-05-31 | The foldable compound rotor aircraft of single vortex-spraying type afterwards |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108791865A (en) |
Citations (7)
| 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 |
| US8052081B2 (en) * | 2008-08-22 | 2011-11-08 | Draganfly Innovations Inc. | Dual rotor helicopter with tilted rotational axes |
| US8146855B2 (en) * | 2008-09-03 | 2012-04-03 | Anvar Ismailov | Unmanned air vehicle |
| CN202414160U (en) * | 2011-11-15 | 2012-09-05 | 成都飞机设计研究所 | Vertical take-off and landing morphing aircraft |
| CN103979107A (en) * | 2014-05-21 | 2014-08-13 | 北京理工大学 | Folding rotor-type unmanned aerial vehicle |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN206218213U (en) * | 2016-11-03 | 2017-06-06 | 湖南星思科技有限公司 | A kind of culvert type bionic Aircraft |
-
2018
- 2018-05-31 CN CN201810549722.0A patent/CN108791865A/en active Pending
Patent Citations (7)
| 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 |
| US8052081B2 (en) * | 2008-08-22 | 2011-11-08 | Draganfly Innovations Inc. | Dual rotor helicopter with tilted rotational axes |
| US8146855B2 (en) * | 2008-09-03 | 2012-04-03 | Anvar Ismailov | Unmanned air vehicle |
| CN202414160U (en) * | 2011-11-15 | 2012-09-05 | 成都飞机设计研究所 | Vertical take-off and landing morphing aircraft |
| CN103979107A (en) * | 2014-05-21 | 2014-08-13 | 北京理工大学 | Folding rotor-type unmanned aerial vehicle |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN206218213U (en) * | 2016-11-03 | 2017-06-06 | 湖南星思科技有限公司 | A kind of culvert type bionic Aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20181113 |