CN105799927A - Ducted ring fixed wing helicopter - Google Patents
Ducted ring fixed wing helicopter Download PDFInfo
- Publication number
- CN105799927A CN105799927A CN201610152990.XA CN201610152990A CN105799927A CN 105799927 A CN105799927 A CN 105799927A CN 201610152990 A CN201610152990 A CN 201610152990A CN 105799927 A CN105799927 A CN 105799927A
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- CN
- China
- Prior art keywords
- duct
- air deflector
- wing
- ring fixed
- cylindric
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- 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
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a ducted ring fixed wing helicopter.The helicopter comprises an axial fan, multiple connecting rods, a cylindrical duct, a quasi-cone centrifugal deflector, annular arc-surface wings, multiple V-shaped deflectors, a power system, a transmission shaft and a steering engine; the axial fan is arranged inside the cylindrical duct and connected with the power system through the transmission shaft penetrating through the quasi-cone centrifugal deflector; the quasi-cone centrifugal deflector is arranged in the center inside the cylindrical duct; the connecting rods fixedly connect the quasi-cone centrifugal deflector with the cylindrical duct; the annular arc-surface wings are connected to the bottom end of the cylindrical duct in a smooth mode, the V-shaped deflectors are installed between the annular arc-surface wings and the quasi-cone centrifugal deflector; the steering engine is connected with the V-shaped deflectors.The ducted ring fixed wing helicopter is low in cost, quiet, safe and easy to machine, all the moving parts are wrapped inside a fuselage, and therefore the safety is improved.
Description
Technical field
The invention belongs to vehicle technology field, be specifically related to a kind of duct ring fixed-wing helicopter.
Background technology
Vertically taking off and landing flyer that at present can be practical is based on helicopter and Multi-axis aircraft.Helicopter have drawbacks in that movable part is many, noise is big, and the huge rotor of exposure is more fragile, and landing site be there are certain requirements.And the shortcoming of Multi-axis aircraft includes: multiple propellers are exposed to surrounding and easily get to thing and people, not easily realizing manned and maximize, continuing a journey short, aircraft diameter is bigger than normal, it is not easy in the landing of narrow place.
Such as: Chinese patent literature CN103786881A discloses a kind of tilt rotor helicopter, including fuselage, driving cabin, main cabin, cargo hold, fuselage tail, vertical fin, undercarriage, wing, turbine modiolus electromotor and main rotor sequential combination, the combination vertical section of its fuselage and fuselage tail is wing profile shape, and fuselage tail can spin upside down around the rotating shaft of fuselage afterbody and also serve as tailplane；Wing vertical fuselage is placed on the flat post of hollow of fuselage circular arc end face both sides, and distance fuselage has a segment distance；It is arranged on wing two ends by the main rotor of turbine modiolus driven by engine, and wing can spin upside down relatively.Fuselage plane is done rectangularity by this helicopter, and wing profile shape is all made in each vertical section of fuselage, and so when it aloft circles in the air, fuselage also produces lift；At fuselage backmost, it can rotate up and down fuselage tail around fuselage afterbody, and therefore fuselage tail can also serve as tailplane to control the pitch attitude of fuselage.Additionally by wing vertical fuselage, and being located on the flat post of hollow of fuselage circular arc end face both sides, so as to the circular arc end face of distance fuselage has certain distance, wing stretches to both sides, then the main rotor that turbine modiolus jet engine drives is arranged on wing two ends.Owing to its fuselage produces lift, its wing leaves again fuselage certain distance, and during airflight, streamline compares smooth-going, the efficiency making wing increases, and fuselage is flat, conveniently makes the tilt rotor helicopter of four main rotors, make the type can be bigger, needed for the function of the bigger load of satisfied loading.
Chinese patent literature CN103786878A discloses a kind of Multi-axis aircraft, including support 10 and be installed on the drive system 20 on support and rotor 30.Support 10 is a support platform, can be fixed with undercarriage, holder for aerial photographing etc. below, can carry the parts such as power supply, circuit board above it.Support 10 includes the first side lever 11 and the second side lever 12 be arrangeding in parallel, and the first side lever 11 is two Hollow circular beam that root length degree is identical, diameter is identical with the second side lever 12.Being fixed with mobile jib 13 between first side lever 11 and the second side lever 12, mobile jib 13 is a Hollow circular beam, and its two ends are individually fixed in the centre position of the first side lever 11 and the second side lever 12, and mobile jib 13 is preferably perpendicular to the first side lever 11 and the second side lever 12.Support 10 also includes four the first supports 14, and four the first supports 14 are respectively arranged in four ends of the first side lever 11 and the second side lever 12, and the middle part of the first support 14 is formed with the first guard space 141.Support 10 also includes two the second supports 15, and two the second supports 15 are individually fixed between the first side lever 11 and mobile jib 13 and between the second side lever 12 and mobile jib 13, are formed with the second guard space 151 in the middle part of the second support 15., drive system 20 includes motor the 21, the 3rd synchronous pulley the 22, the 4th synchronous pulley the 23, second Synchronous Transmission belt 24 and a main shaft 25.Rotor 30 includes driving axle the 31, first synchronous pulley the 32, first fin the 331, second fin 332, propeller hub 34 and drive division.
Summary of the invention
The present invention is directed to above-mentioned the deficiencies in the prior art, it is provided that a kind of duct ring fixed-wing helicopter.
Duct ring fixed-wing helicopter of the present invention includes: aerofoil fan, multiple connecting rod, cylindric duct, class conical centrifuge air deflector, annular cambered surface wing, V-arrangement air deflector, dynamical system, power transmission shaft and steering wheel, described aerofoil fan is arranged on cylindric top within duct, and this aerofoil fan power transmission shaft and dynamical system through class conical centrifuge air deflector connects；Class conical centrifuge air deflector is arranged on the position of the inside center of cylindric duct；Multiple connecting rods are fixed together class conical centrifuge air deflector and cylindric duct；Described annular cambered surface wing is connected to the bottom of cylindric duct sleekly；Multiple V-arrangement air deflectors are arranged between annular cambered surface wing and class conical centrifuge air deflector；Steering wheel is connected with V-arrangement air deflector.
Multiple connecting rods are fixed together class conical centrifuge air deflector and cylindric duct；Described multiple connecting rods are radially uniformly arranged on a cylindric circular horizontal plane within duct, and the horizontal plane of this circle is in the central axis of cylindric duct.
Described dynamical system drives aerofoil fan to rotate by power transmission shaft, and the air-flow that aerofoil fan rotation produces is guided by cylindric duct and blows to downwards class conical centrifuge air deflector.
Described dynamical system includes motor or fuel engines.
Described class conical centrifuge air deflector is for becoming centrifugal radiation air-flow downward air-flow.
Described annular cambered surface wing is for guiding downwards centrifugal radiation air-flow thus producing lift.
The projection in the horizontal plane of the outermost edges of the described outermost edges of cylindric duct, the outermost edges of class conical centrifuge air deflector and annular cambered surface wing is circle, the circular diameter that the circular diameter that the projection in the horizontal plane of the outermost edges of cylindric duct is formed is formed less than the outermost edges projection in the horizontal plane of class conical centrifuge air deflector.
The circular diameter that the circular diameter that the projection in the horizontal plane of the outermost edges of class conical centrifuge air deflector is formed is formed less than the outermost edges projection in the horizontal plane of annular cambered surface wing.
Described V-arrangement air deflector includes two coaxial blades, by changing the deflection spin for controlling duct ring fixed-wing helicopter of this V-arrangement air deflector, and by the angle between two coaxial blades of this V-arrangement air deflector of change thus controlling the air flow rate by this V-arrangement air deflector, and then control the heading of duct ring fixed-wing helicopter.
Corner dimension between the deflection of V-arrangement air deflector and two coaxial blades of V-arrangement air deflector changes by servos control.
Compared with prior art, having the beneficial effects that of duct ring fixed-wing helicopter of the present invention: the duct ring fixed-wing helicopter cost safety low, quiet of the present invention and be prone to processing, it is wrapped in the aerofoil fan (propeller) of inside even if encountering slight impact also can continue flight, therefore can in narrow place landing.Aircraft can use motor-driven that internal combustion engine can also be used to drive, so being no matter do unmanned plane or manned vehicle is all easily achieved, its duct air intake can not need the propeller of major diameter, and all movable parts are all wrapped in fuselage interior thus improve safety.
Accompanying drawing explanation
Fig. 1 is the front view of the duct ring fixed-wing helicopter of the present invention.
Fig. 2 is the top view of the duct ring fixed-wing helicopter of the present invention.
Fig. 3 and 4 are the schematic diagrams of the V-arrangement air deflector deflection of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the technical scheme in the application is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the application, rather than whole embodiments.Based on the embodiment in the application, the every other embodiment that those of ordinary skill in the art obtain under the premise not making creative work, broadly fall into the scope of the application protection.
Fig. 1 illustrates the structure of the duct ring fixed-wing helicopter of the present invention, as shown in Figure 1, duct ring fixed-wing helicopter of the present invention includes aerofoil fan 1, multiple connecting rod 2, cylindric duct 3, class conical centrifuge air deflector 4, annular cambered surface wing 5, V-arrangement air deflector 6, dynamical system 7, power transmission shaft 8 and steering wheel 9, described aerofoil fan 1 is arranged on cylindric top within duct 3, and this aerofoil fan 1 power transmission shaft 8 and dynamical system 7 through class conical centrifuge air deflector 4 connects；Class conical centrifuge air deflector 4 is arranged on the position of the inside center of cylindric duct 3；2 class conical centrifuge air deflectors of multiple connecting rods 4 and cylindric duct 3 are fixed together；Described annular cambered surface wing 5 is connected to the bottom of cylindric duct 3 sleekly；Multiple V-arrangement air deflectors 6 are arranged between annular cambered surface wing 5 and class conical centrifuge air deflector 4；Steering wheel 9 is connected with V-arrangement air deflector 6.
As shown in Figure 1, cylindric duct 3 is a cylinder-like structure being vertically arranged, described multiple connecting rods 2 are radially uniformly arranged on a cylindric circular horizontal plane within duct 3, and the horizontal plane of this circle is in the central axis of cylindric duct 3.
Described dynamical system 7 drives aerofoil fan 1 to rotate by power transmission shaft 8, and the air-flow that aerofoil fan 1 rotation produces is guided by cylindric duct 3 and blows to downwards class conical centrifuge air deflector 4.
Described dynamical system 7 includes motor or fuel engines.
Described class conical centrifuge air deflector 4 is for becoming centrifugal radiation air-flow downward air-flow.
Described annular cambered surface wing 5 is for guiding downwards centrifugal radiation air-flow thus producing lift.
The projection in the horizontal plane of the outermost edges of the described outermost edges of cylindric duct 3, the outermost edges of class conical centrifuge air deflector 4 and annular cambered surface wing 5 is circle, the circular diameter that the circular diameter that the projection in the horizontal plane of the outermost edges of cylindric duct 3 is formed is formed less than the outermost edges projection in the horizontal plane of class conical centrifuge air deflector 4.
As in figure 2 it is shown, the circular diameter that the circular diameter that formed of the projection that the outermost edges of class conical centrifuge air deflector 4 is in the horizontal plane is formed less than the outermost edges projection in the horizontal plane of annular cambered surface wing 5.
Described V-arrangement air deflector 6 includes two coaxial blades, by changing the deflection spin for controlling duct ring fixed-wing helicopter of this V-arrangement air deflector 6, and by the angle between two coaxial blades of this V-arrangement air deflector 6 of change thus controlling the air flow rate by this V-arrangement air deflector 6, and then control the heading of duct ring fixed-wing helicopter.As shown in Figures 3 and 4, the deflection of V-arrangement air deflector 6 refers to two coaxial blades of V-arrangement air deflector 6 as an integral-rotation, assuming that in Fig. 3, the orientation angles at V-arrangement air deflector 6 place is A, the air-flow F that now level blows out to the left is guided by two coaxial blades of V-arrangement air deflector 6 and blows to direction A1 and A2 respectively；When V-arrangement air deflector 6 rotates to position (orientation angles is B) shown in Fig. 4, the air-flow F that level blows out to the left is guided by two coaxial blades of V-arrangement air deflector 6 and blows to direction B1 and B2 respectively, say, that can realize guiding discrete air flow to blow to different directions by making V-arrangement air deflector 6 deflect different angles.When multiple V-arrangement air deflectors 6 deflect in predetermined angular time, it is possible to realize the direction guiding discrete air flow to blow to setting, and then realize the spin of duct ring fixed-wing helicopter.Because the duct ring fixed-wing helicopter that the effect of aerofoil fan 1 makes the present invention itself has the trend rotated, by the deflection of change V-arrangement air deflector 6 thus controlling the spin of duct ring fixed-wing helicopter, this spin can eliminate the trend of the duct ring fixed-wing helicopter own rotation that aerofoil fan 1 causes, thus maintaining stablizing of duct ring fixed-wing helicopter.
Be it desired to duct ring fixed-wing helicopter fly forward, make back region in helicopter V-arrangement air deflector 6 two coaxial blades between angle diminish, the air-flow that passes through becomes big, and the lift of the annular cambered surface wing 5 that this back region is corresponding becomes big.Angle between two coaxial blades of the V-arrangement air deflector 6 of front region becomes big simultaneously, and the air-flow passed through diminishes, and the lift of the annular cambered surface wing 5 that this front region is corresponding diminishes.Not waiting plus center of gravity of upwards lift before and after utilizing is to force whole duct ring fixed-wing helicopter flight forward at axle center, the lower section place of annular cambered surface wing 5.Flight theory on other directions is identical with flight forward.
Corner dimension between the deflection of V-arrangement air deflector 6 and two coaxial blades of V-arrangement air deflector 6 changes and is controlled by steering wheel 9.
Duct ring fixed-wing helicopter of the present invention be a kind of low cost, quiet safely, be prone to the vertically taking off and landing flyer of processing, namely its cylindric duct and cambered surface annular wing structural design itself add structural strength so that aircraft can be lighter；It is wrapped in the aerofoil fan (propeller) of inside even if encountering slight impact also can continue flight, therefore can in narrow place landing.Aircraft can use motor-driven that internal combustion engine can also be used to drive, so being no matter do unmanned plane or manned vehicle is all easily achieved, its duct air intake can not need the propeller of major diameter, and all movable parts are all wrapped in fuselage interior thus improve safety.
Principal character and the advantages of the present invention of the present invention have more than been shown and described.Skilled person will appreciate that; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.Claimed scope is defined by appending claims and equivalent thereof.
Claims (10)
1. a duct ring fixed-wing helicopter, it is characterized in that, this duct ring fixed-wing helicopter includes aerofoil fan, multiple connecting rod, cylindric duct, class conical centrifuge air deflector, annular cambered surface wing, V-arrangement air deflector, dynamical system, power transmission shaft and steering wheel, described aerofoil fan is arranged on cylindric top within duct, and this aerofoil fan power transmission shaft and dynamical system through class conical centrifuge air deflector connects；Class conical centrifuge air deflector is arranged on the position of the inside center of cylindric duct；Multiple connecting rods are fixed together class conical centrifuge air deflector and cylindric duct；Described annular cambered surface wing is connected to the bottom of cylindric duct sleekly；Multiple V-arrangement air deflectors are arranged between annular cambered surface wing and class conical centrifuge air deflector；Steering wheel is connected with V-arrangement air deflector.
2. duct ring fixed-wing helicopter according to claim 1, it is characterised in that multiple connecting rods are fixed together class conical centrifuge air deflector and cylindric duct；Described multiple connecting rods are radially uniformly arranged on a cylindric circular horizontal plane within duct, and the horizontal plane of this circle is in the central axis of cylindric duct.
3. duct ring fixed-wing helicopter according to claim 2, it is characterised in that described dynamical system drives aerofoil fan to rotate by power transmission shaft, the air-flow that aerofoil fan rotation produces is guided by cylindric duct and blows to downwards class conical centrifuge air deflector.
4. duct ring fixed-wing helicopter according to claim 3, it is characterised in that described dynamical system includes motor or fuel engines.
5. duct ring fixed-wing helicopter according to claim 4, it is characterised in that described class conical centrifuge air deflector is for becoming centrifugal radiation air-flow downward air-flow.
6. duct ring fixed-wing helicopter according to claim 5, it is characterised in that described annular cambered surface wing is for guiding downwards centrifugal radiation air-flow thus producing lift.
7. duct ring fixed-wing helicopter according to claim 6, it is characterized in that, the projection in the horizontal plane of the outermost edges of the described outermost edges of cylindric duct, the outermost edges of class conical centrifuge air deflector and annular cambered surface wing is circle, the circular diameter that the circular diameter that the projection in the horizontal plane of the outermost edges of cylindric duct is formed is formed less than the outermost edges projection in the horizontal plane of class conical centrifuge air deflector.
8. duct ring fixed-wing helicopter according to claim 7, it is characterized in that, the circular diameter that the circular diameter that the projection in the horizontal plane of the outermost edges of class conical centrifuge air deflector is formed is formed less than the outermost edges projection in the horizontal plane of annular cambered surface wing.
9. duct ring fixed-wing helicopter according to claim 8, it is characterized in that, described V-arrangement air deflector includes two coaxial blades, by changing the deflection spin for controlling duct ring fixed-wing helicopter of this V-arrangement air deflector, and by the angle between two coaxial blades of this V-arrangement air deflector of change thus controlling the air flow rate by this V-arrangement air deflector, and then control the heading of duct ring fixed-wing helicopter.
10. duct ring fixed-wing helicopter according to claim 9, it is characterised in that the deflection of V-arrangement air deflector and the corner dimension between two coaxial blades of V-arrangement air deflector change by servos control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610152990.XA CN105799927A (en) | 2016-03-17 | 2016-03-17 | Ducted ring fixed wing helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610152990.XA CN105799927A (en) | 2016-03-17 | 2016-03-17 | Ducted ring fixed wing helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105799927A true CN105799927A (en) | 2016-07-27 |
Family
ID=56453181
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610152990.XA Pending CN105799927A (en) | 2016-03-17 | 2016-03-17 | Ducted ring fixed wing helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105799927A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017121116A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Engine for vertically taking off or landing with airfoil lift |
| CN108248851A (en) * | 2018-02-02 | 2018-07-06 | 郑州轻工业学院 | Aircraft for the device for protecting aircraft rotor and with the device |
| US20200317337A1 (en) * | 2019-04-07 | 2020-10-08 | Donald Lee Chalker | Unmanned Aerial Vehicle With Ducted Rotors |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3630470A (en) * | 1970-02-13 | 1971-12-28 | Frederick Thomas Elliott | Vertical takeoff and landing vehicle |
| US3785592A (en) * | 1971-10-04 | 1974-01-15 | K Kerruish | Vtol aircraft |
| CN101092167A (en) * | 2007-07-24 | 2007-12-26 | 沈阳航空工业学院 | Dished aircraft |
| CN101704415A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨盛世特种飞行器有限公司 | Ducted single-propeller saucer-shaped unmanned aerial vehicle |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
| CN103803078A (en) * | 2012-11-12 | 2014-05-21 | 余彦武 | Flying saucer type helicopter utilizing active airflow to generate lifting power |
| CN205418101U (en) * | 2016-03-17 | 2016-08-03 | 高大勇 | Duct ring stationary vane helicopter |
-
2016
- 2016-03-17 CN CN201610152990.XA patent/CN105799927A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3630470A (en) * | 1970-02-13 | 1971-12-28 | Frederick Thomas Elliott | Vertical takeoff and landing vehicle |
| US3785592A (en) * | 1971-10-04 | 1974-01-15 | K Kerruish | Vtol aircraft |
| CN101092167A (en) * | 2007-07-24 | 2007-12-26 | 沈阳航空工业学院 | Dished aircraft |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
| CN101704415A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨盛世特种飞行器有限公司 | Ducted single-propeller saucer-shaped unmanned aerial vehicle |
| CN103803078A (en) * | 2012-11-12 | 2014-05-21 | 余彦武 | Flying saucer type helicopter utilizing active airflow to generate lifting power |
| CN205418101U (en) * | 2016-03-17 | 2016-08-03 | 高大勇 | Duct ring stationary vane helicopter |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017121116A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Engine for vertically taking off or landing with airfoil lift |
| CN108248851A (en) * | 2018-02-02 | 2018-07-06 | 郑州轻工业学院 | Aircraft for the device for protecting aircraft rotor and with the device |
| US20200317337A1 (en) * | 2019-04-07 | 2020-10-08 | Donald Lee Chalker | Unmanned Aerial Vehicle With Ducted Rotors |
| US11591087B2 (en) * | 2019-04-07 | 2023-02-28 | Donald Lee Chalker | Unmanned aerial vehicle with ducted rotors |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20160727 |