CN205418101U - Duct ring stationary vane helicopter - Google Patents
Duct ring stationary vane helicopter Download PDFInfo
- Publication number
- CN205418101U CN205418101U CN201620214022.2U CN201620214022U CN205418101U CN 205418101 U CN205418101 U CN 205418101U CN 201620214022 U CN201620214022 U CN 201620214022U CN 205418101 U CN205418101 U CN 205418101U
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- Prior art keywords
- duct
- air deflector
- wing
- cylindric
- ring fixed
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Abstract
The utility model relates to a duct ring stationary vane helicopter, including axial fan, a plurality of connecting rod, cylindric duct, type toper centrifugation divertor, annular cambered surface wing, V -arrangement divertor, driving system, transmission shaft and steering wheel, axial fan sets up in the inside of cylindric duct, and axial fan connects through the transmission shaft and the driving system of type of running through toper centrifugation divertor, the setting of class toper centrifugation divertor is in the position at the inside center of cylindric duct, a plurality of connecting rods are in the same place a type toper centrifugation divertor with cylindric duct fixed connection, annular cambered surface wing be connected to the bottom of cylindric duct slick and slyly, a plurality of V -arrangement divertors are installed between annular cambered surface wing and type toper centrifugation divertor, the steering wheel is connected with the V -arrangement divertor. This duct ring stationary vane helicopter is with low costs, quiet safe, easily processing, thereby all movable parts all wrap up and have improved the security in that the fuselage is inside.
Description
Technical field
This utility model belongs to vehicle technology field, is 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.The shortcoming of helicopter is: movable part is many, and noise is big, and the huge rotor of exposure is more fragile, there are certain requirements landing site.And the shortcoming of Multi-axis aircraft includes: multiple propellers are exposed to surrounding and easily get to thing and people, being difficult to realize manned and maximize, continue 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 relatively can spin upside down.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, the circular arc end face being allowed to distance fuselage has a certain distance, and 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, the drive system 20 including support 10 and being installed 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 first side lever 11 and centre position of 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 that four the first supports 14, four the first supports 14 are respectively arranged in the first side lever 11 and four ends of 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 drive shaft the 31, first synchronous pulley the 32, first fin the 331, second fin 332, propeller hub 34 and drive division.
Utility model content
This utility model is for 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 described in the utility model 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 is rotated by power transmission shaft drive shaft flow fan, 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 produces lift for centrifugal radiation air-flow is guided downwards.
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 of this V-arrangement air deflector for the spin controlling duct ring fixed-wing helicopter, and control the air flow rate by this V-arrangement air deflector by changing the angle between two coaxial blades of 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 described in the utility model: duct ring fixed-wing helicopter low cost of the present utility model, quiet safety 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 be in narrow place landing.Aircraft can use motor-driven that internal combustion engine can also be used to drive, so being no matter to do unmanned plane or manned vehicle is all easily achieved, its duct air intake can need not 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 duct ring fixed-wing helicopter of the present utility model.
Fig. 2 is the top view of duct ring fixed-wing helicopter of the present utility model.
Fig. 3 and 4 is the schematic diagram of V-arrangement air deflector of the present utility model deflection.
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 are obtained on the premise of not making creative work, broadly fall into the scope of the application protection.
Fig. 1 shows the structure of duct ring fixed-wing helicopter of the present utility model, as shown in Figure 1, duct ring fixed-wing helicopter described in the utility model 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 is rotated by power transmission shaft 8 drive shaft flow fan 1, 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 produces lift for centrifugal radiation air-flow is guided downwards.
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 of this V-arrangement air deflector 6 for the spin controlling duct ring fixed-wing helicopter, and control the air flow rate by this V-arrangement air deflector 6 by changing the angle between two coaxial blades of 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 when, it is possible to realize guiding discrete air flow to blow to the direction set, and then realize the spin of duct ring fixed-wing helicopter.Because the effect of aerofoil fan 1 makes duct ring fixed-wing helicopter of the present utility model itself have the trend rotated, the spin of duct ring fixed-wing helicopter is controlled by changing the deflection of V-arrangement air deflector 6, this spin can eliminate the trend of the duct ring fixed-wing helicopter own rotation that aerofoil fan 1 causes, thus maintains 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 utilization is to force whole duct ring fixed-wing helicopter flight forward at the axle center, lower section 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 described in the utility model be a kind of low cost, quiet safely, be prone to the vertically taking off and landing flyer of processing, its cylindric duct and cambered surface annular wing structure design itself i.e. 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 be in narrow place landing.Aircraft can use motor-driven that internal combustion engine can also be used to drive, so being no matter to do unmanned plane or manned vehicle is all easily achieved, its duct air intake can need not the propeller of major diameter, and all movable parts are all wrapped in fuselage interior thus improve safety.
Of the present utility model principal character and of the present utility model advantage have more than been shown and described.Those skilled in the art it should be recognized that; this utility model is not restricted to the described embodiments; described in above-described embodiment and description, principle of the present utility model is simply described; on the premise of without departing from this utility model spirit and scope; this utility model also has various changes and modifications, in the range of these changes and improvements both fall within claimed this utility model.This utility model claims scope and 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.
Duct ring fixed-wing helicopter the most 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.
Duct ring fixed-wing helicopter the most according to claim 2, it is characterised in that described dynamical system is rotated by power transmission shaft drive shaft flow fan, the air-flow that aerofoil fan rotation produces is guided by cylindric duct and blows to downwards class conical centrifuge air deflector.
Duct ring fixed-wing helicopter the most according to claim 3, it is characterised in that described dynamical system includes motor or fuel engines.
Duct ring fixed-wing helicopter the most 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.
Duct ring fixed-wing helicopter the most according to claim 5, it is characterised in that described annular cambered surface wing produces lift for centrifugal radiation air-flow is guided downwards.
Duct ring fixed-wing helicopter the most 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.
Duct ring fixed-wing helicopter the most 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.
Duct ring fixed-wing helicopter the most according to claim 8, it is characterized in that, described V-arrangement air deflector includes two coaxial blades, by changing the deflection of this V-arrangement air deflector for the spin controlling duct ring fixed-wing helicopter, and control the air flow rate by this V-arrangement air deflector by changing the angle between two coaxial blades of this V-arrangement air deflector, and then control the heading of duct ring fixed-wing helicopter.
Duct ring fixed-wing helicopter the most according to claim 9, it is characterised in that the corner dimension between the deflection of V-arrangement air deflector and two coaxial blades of V-arrangement air deflector changes by servos control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620214022.2U CN205418101U (en) | 2016-03-17 | 2016-03-17 | Duct ring stationary vane helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620214022.2U CN205418101U (en) | 2016-03-17 | 2016-03-17 | Duct ring stationary vane helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205418101U true CN205418101U (en) | 2016-08-03 |
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ID=56519462
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620214022.2U Expired - Fee Related CN205418101U (en) | 2016-03-17 | 2016-03-17 | Duct ring stationary vane helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205418101U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799927A (en) * | 2016-03-17 | 2016-07-27 | 高大勇 | Ducted ring fixed wing helicopter |
-
2016
- 2016-03-17 CN CN201620214022.2U patent/CN205418101U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799927A (en) * | 2016-03-17 | 2016-07-27 | 高大勇 | Ducted ring fixed wing helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160803 Termination date: 20190317 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |