CN204895837U - Small -size VTOL aircraft aerodynamic layout - Google Patents
Small -size VTOL aircraft aerodynamic layout Download PDFInfo
- Publication number
- CN204895837U CN204895837U CN201520616748.4U CN201520616748U CN204895837U CN 204895837 U CN204895837 U CN 204895837U CN 201520616748 U CN201520616748 U CN 201520616748U CN 204895837 U CN204895837 U CN 204895837U
- Authority
- CN
- China
- Prior art keywords
- small
- fuselage body
- vertically taking
- landing flyer
- landing
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to the technical field of the aircraft technique and specifically relates to a small -size VTOL aircraft aerodynamic layout is related to, including the fuselage body, front wing, main wing and fin have been laid in proper order along its self length direction on the fuselage body, the front wing with the quantity of main wing is two, the quantity of fin is four, the front wing with main wing mutually perpendicular sets up, still be provided with driving system on the fuselage body for a thrust that the power and the level flight of the VTOL of the small -size VTOL aircraft of is provided, the direction of small -size VTOL aircraft VTOL with the length direction of fuselage body is consistent. The utility model discloses having improved small -size VTOL aircraft level flight's speed greatly, when accomplishing various action, having had the characteristics that response speed is fast, the reliability is high, still convenient to use maintains in addition.
Description
Technical field
The utility model relates to vehicle technology field, especially relates to a kind of small-sized vertically taking off and landing flyer aerodynamic arrangement.
Background technology
Current small aircraft type mainly helicopter and many cyclogyros that can realize vertical takeoff and landing.
Helicopter includes single rotor and DCB Specimen two type.Single-rotor helicopter is by driving engine through actuator drives rotor and tail-rotor, produces lift, overcome the unbalanced moment of rotor wing rotation generation by the rotation of tail-rotor by the rotation of rotor.
Twin-rotor helicopter is divided into again coaxial double-rotor helicopter and split axle twin-rotor helicopter.Coaxial double-rotor helicopter i.e. two groups of rotors rotate relative to same axle center thus produce lift, but turn on the contrary to offset the unbalanced moment rotating generation each other.Split axle twin-rotor helicopter i.e. two groups of rotors separately, rotate around respective rotor shaft.Split axle twin-rotor helicopter also can be divided into column dual rotors helicopter and twin-rotor helicopter arranged side by side according to the relative position of two rotor shaft, but groundwork is all turn to rotation by rotor by contrary, produce lift on the one hand, overcome the unbalanced moment produced each other on the one hand.
The groundwork of many cyclogyros is identical with helicopter, and difference is that most many cyclogyros are by motor direct-drive screw propeller, and can only realize various action by the speed changing screw propeller.
Helicopter and many cyclogyros all can realize vertical takeoff and landing, but are limited to principle of work and aerodynamic arrangement after taking off, and the speed of both horizontal flights is all very slow.The principle of the horizontal flight of helicopter is that adjustment rotor makes it to turn forward, the lift that such rotor produces will produce component in working direction, helicopter is advanced, due to a part of power being used to provide horizontal flight of lift that rotor produces, therefore greatly limit the speed of its horizontal flight.The principle of the horizontal flight of many cyclogyros is identical with the principle of the horizontal flight of helicopter.In addition, the driving device of helicopter and many cyclogyros is all very complicated, and reliability is lower, higher to the requirement of working service.
Utility model content
The purpose of this utility model is to provide a kind of small-sized vertically taking off and landing flyer aerodynamic arrangement, with the Problem Technical problem that the flying speed solving the small-sized vertically taking off and landing flyer existed in prior art is slow.
Based on above-mentioned purpose, the utility model provides a kind of small-sized vertically taking off and landing flyer aerodynamic arrangement, comprises fuselage body; Described fuselage body is laid with front wing, main wing and empennage successively along the length direction of himself; The quantity of described front wing and described main wing is two panels, and the quantity of described empennage is four; Described front wing is arranged with described main wing is mutually vertical; Described fuselage body is also provided with power system, for providing the small-sized power of vertically taking off and landing flyer vertical takeoff and landing and the thrust of horizontal flight; The direction of described small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of described fuselage body.
Further, described power system comprises two screw propellers; The hand of rotation of two described screw propellers is contrary.
Further, described fuselage body comprises forebody and rear body; Described in front wing described in two panels and two panels, main wing is all arranged on described forebody; Four described empennages and described power system are arranged on described rear body.
Further, described empennage can swing relative to described fuselage body, to adjust the flight attitude of described fuselage body.
Further, described forebody is rectangular-shaped.
Further, described rear body is cylindric.
Further, four described empennages are symmetrically distributed in the circumference of described rear body between two.
Further, the angle between adjacent two described empennages is 45 °; Angle between described empennage and described main wing is 45 °.
Further, transmitting support is also comprised; Described fuselage body is vertically set on described transmitting support.
Further, described transmitting support comprises base and canister launcher, and described canister launcher is fixedly connected with described base; Described fuselage body is inserted in described canister launcher.
Compared with prior art, the beneficial effects of the utility model are:
The small-sized vertically taking off and landing flyer aerodynamic arrangement that the utility model provides, comprises fuselage body; Fuselage body is laid with front wing, main wing and empennage successively along the length direction of himself; The quantity of front wing and main wing is two panels, and the quantity of empennage is four; Front wing and main wing are mutually vertical to be arranged; Fuselage body is also provided with power system, for providing the small-sized power of vertically taking off and landing flyer vertical takeoff and landing and the thrust of horizontal flight; The direction of small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of fuselage body.After aircraft vertical takes off, when the speed of aircraft with when highly arriving during certain value, by adjusting empennage, fuselage body being tilted, thus making length direction and the horizontal direction parallel of fuselage body, realizing horizontal flight; Because the direction of small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of fuselage body, when horizontal flight, main wing provides the lift of aircraft, the power that power system provides then all is used to provide the thrust of horizontal flight, makes aircraft level to flight, therefore, the utility model substantially increases the speed of small-sized vertically taking off and landing flyer horizontal flight, when completing various action, there is fast response time, feature that reliability is high, also maintenance easy to use in addition.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model detailed description of the invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in detailed description of the invention or description of the prior art below, apparently, accompanying drawing in the following describes is embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
The axonometric drawing (level flight condition) of the small-sized vertically taking off and landing flyer aerodynamic arrangement that Fig. 1 provides for the utility model embodiment;
Fig. 2 is the front view of the middle-size and small-size vertically taking off and landing flyer aerodynamic arrangement of the utility model embodiment;
Fig. 3 is the right elevation of the middle-size and small-size vertically taking off and landing flyer aerodynamic arrangement of the utility model embodiment;
Fig. 4 is the left view of the middle-size and small-size vertically taking off and landing flyer aerodynamic arrangement of the utility model embodiment;
Fig. 5 is the exploded view launching support in the utility model embodiment;
Fig. 6 is the assembly drowing launching support in the utility model embodiment;
Fig. 7 is the constitution diagram before the middle-size and small-size vertically taking off and landing flyer of the utility model embodiment takes off vertically;
Fig. 8 is the constitution diagram after the middle-size and small-size vertically taking off and landing flyer of the utility model embodiment takes off vertically.
Reference numeral:
101-front wing; 102-main wing; 103-empennage;
104-forebody; 105-rear body; 106-screw propeller;
107-canister launcher; 108-base; 109-leg; 110-opening.
Detailed description of the invention
Be clearly and completely described the technical solution of the utility model below in conjunction with accompanying drawing, obviously, described embodiment is the utility model part embodiment, instead of whole embodiments.The assembly of the utility model embodiment describing and illustrate in usual accompanying drawing herein can be arranged with various different configuration and design.Therefore, below to the detailed description of the embodiment of the present utility model provided in the accompanying drawings and the claimed scope of the present utility model of not intended to be limiting, but selected embodiment of the present utility model is only represented.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
In description of the present utility model, it should be noted that, orientation or the position relationship of the instruction such as term " " center ", " on ", D score, "left", "right", " vertically ", " level ", " interior ", " outward " they be based on orientation shown in the drawings or position relationship; be only the utility model and simplified characterization for convenience of description; instead of instruction or imply the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.In addition, term " first ", " second ", " the 3rd " only for describing object, and can not be interpreted as instruction or hint relative importance.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, particular case the concrete meaning of above-mentioned term in the utility model can be understood.
Embodiment
See shown in Fig. 1 to Fig. 8, the utility model embodiment provides a kind of small-sized vertically taking off and landing flyer aerodynamic arrangement, comprises fuselage body; Fuselage body entirety linearly type; Fuselage body is laid with front wing 101, main wing 102 and empennage 103 successively along the length direction of himself; The quantity of front wing 101 and main wing 102 is two panels, and the quantity of empennage 103 is four; Front wing 101 is arranged with main wing 102 is mutually vertical; Fuselage body is also provided with power system, for providing the small-sized power of vertically taking off and landing flyer vertical takeoff and landing and the thrust of horizontal flight; The direction of small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of fuselage body.After aircraft vertical takes off, when the speed of aircraft with when highly arriving during certain value, by adjusting empennage 103, fuselage body being tilted, thus making length direction and the horizontal direction parallel of fuselage body, realizing horizontal flight; Because the direction of small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of fuselage body, when horizontal flight, main wing 102 provides the lift of aircraft, the power that power system provides then all is used to provide the thrust of horizontal flight, makes aircraft level to flight, therefore, the utility model substantially increases the speed of small-sized vertically taking off and landing flyer horizontal flight, when completing various action, there is fast response time, feature that reliability is high, also maintenance easy to use in addition.
In the present embodiment, fuselage body comprises forebody 104 and rear body 105; Forebody 104 is connected with rear body 105.Specifically, forebody 104 is in rectangular-shaped, the cross-sectional plane of forebody 104 is the rectangle of band fillet, that is, four angles of rectangle are fillet, and the long limit of rectangle is vertical with main wing 102, the minor face of rectangle is parallel with main wing 102, the installation of equipment is convenient in such design on the one hand, also can produce certain transverse force on the other hand, is conducive to the crossrange maneuvering ability improving aircraft entirety; Rear body 105 is in cylindric.
In the present embodiment, two panels front wing 101 and two panels main wing 102 are all arranged on forebody 104; Four empennages 103 and power system are arranged on rear body 105; Power system is arranged between main wing 102 and empennage 103.
In the present embodiment, power system comprises two screw propellers 106, and each screw propeller 106 is driven by motor; Two screw propeller 106 coaxial lines, in addition, the hand of rotation of two screw propellers 106 is contrary.Due to when flying, the blade tip of the blade of screw propeller 106 can form tangential airstream eddy current, and air vortex fails to be convened for lack of a quorum and causes certain degradation of energy, by at design two screw propellers 106, and their hand of rotation is contrary, the airstream eddy current produced during the blade rotation of such two screw propellers 106 will cancel each other, and the degradation of energy caused by airstream eddy current drops to minimum, thus can improve the capacity usage ratio of power system.In addition, due to antagonistic force principle, when a screw propeller 106 rotates, air can produce the contrary power of a cireular frequency to motor, i.e. moment of torsion by blade.This power can cause aircraft to roll along torque direction.After designing the contrary screw propeller 106 of two hand of rotation, the moment of torsion that the blade of the screw propeller 106 of contrarotation produces just can be cancelled out each other.Thus effectively overcome the unbalanced moment rotating generation each other, considerably increase stability during aircraft flight.
In the present embodiment, the aspect of main wing 102 is rectangular; Main wing 102 is lower single-blade, and that is, main wing 102 is arranged on the bottom of fuselage body.
In this enforcement, two panels front wing 101 is symmetrically distributed on fuselage body, and specifically, a slice is positioned at the top of fuselage body, and another sheet is positioned at the bottom of fuselage body.
In the present embodiment, empennage 103 can swing relative to fuselage body, to adjust the flight attitude of fuselage body, that is, after aircraft vertical takes off, when aircraft speed and highly arrive time certain value time, by adjustment empennage 103 pivot angle fuselage body can be made to tilt, thus make length direction and the horizontal direction parallel of fuselage body, realize horizontal flight; In addition when aircraft does various running, by adjusting the pivot angle of empennage 103, the heeling condition of conversion fuselage body can be made.
In the present embodiment, four empennages 103 are symmetrically distributed in the circumference of rear body 105 between two.Specifically, the angle between adjacent two empennages 103 is 45 °, can produce required motor-driven overload like this in all directions, and all has fast speed response characteristic in the normal force that all directions produce; Angle between empennage 103 and main wing 102 is 45 °.By such design, be conducive to the flight attitude being adjusted fuselage body by empennage 103.
Shown in Fig. 5 and Fig. 6, in the present embodiment, small-sized vertically taking off and landing flyer aerodynamic arrangement also comprises transmitting support; Fuselage body is vertically set on to be launched on support, and that is, when aircraft vertical takes off, fuselage body just can leave transmitting support gradually.In the preferred scheme of the present embodiment, launch support and comprise base 108 and canister launcher 107, canister launcher 107 is fixedly connected with base 108; Fuselage body is inserted in canister launcher 107.Specifically, one end that base 108 comprises three legs, 109, three legs 109 is fixed together; Canister launcher 107 is fixed on the point of connection of three legs 109; Canister launcher 107 offers four openings, 110, four positions of opening 110 on canister launcher 107 corresponding with four positions of empennage 103 on rear body 105.
The principle of work of the middle-size and small-size vertically taking off and landing flyer of the present embodiment is:
By the rotation of two screw propellers 106, produce lift, make aircraft gradually leave transmitting support, when aircraft speed and highly arrival time certain value time, by adjusting the pivot angle of empennage 103, and utilize the air-flow of screw propeller 106 to produce aerodynamic force, fuselage body is tilted, thus makes length direction and the horizontal direction parallel of fuselage body, after proceeding to horizontal flight, screw propeller 106 provides thrust, and main wing 102 provides lift, realizes horizontal flight.The descent of aircraft is exactly the inverse process of aircraft takeoff.
In sum, small-sized vertically taking off and landing flyer in the present embodiment, when taking off vertically, screw propeller 106 provides lift, when horizontal flight, the power that screw propeller 106 provides all is used to provide thrust during horizontal flight, and provide lift by main wing 102, thus improve the speed of horizontal flight, when completing various action, there is fast response time, feature that reliability is high, also maintenance easy to use in addition.
Last it is noted that above each embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to foregoing embodiments, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein some or all of technical characteristic; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the scope of each embodiment technical scheme of the utility model.
Claims (10)
1. a small-sized vertically taking off and landing flyer aerodynamic arrangement, is characterized in that, comprise fuselage body; Described fuselage body is laid with front wing, main wing and empennage successively along the length direction of himself; The quantity of described front wing and described main wing is two panels, and the quantity of described empennage is four; Described front wing is arranged with described main wing is mutually vertical; Described fuselage body is also provided with power system, for providing the small-sized power of vertically taking off and landing flyer vertical takeoff and landing and the thrust of horizontal flight; The direction of described small-sized vertically taking off and landing flyer vertical takeoff and landing is consistent with the length direction of described fuselage body.
2. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 1, is characterized in that, described power system comprises two screw propellers; The hand of rotation of two described screw propellers is contrary.
3. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 1 and 2, it is characterized in that, described fuselage body comprises forebody and rear body; Described in front wing described in two panels and two panels, main wing is all arranged on described forebody; Four described empennages and described power system are arranged on described rear body.
4. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 1 and 2, is characterized in that, described empennage can swing relative to described fuselage body, to adjust the flight attitude of described fuselage body.
5. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 3, it is characterized in that, described forebody is rectangular-shaped.
6. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 3, it is characterized in that, described rear body is cylindric.
7. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 6, it is characterized in that, four described empennages are symmetrically distributed in the circumference of described rear body between two.
8. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 7, is characterized in that, the angle between adjacent two described empennages is 45 °; Angle between described empennage and described main wing is 45 °.
9. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 1 and 2, is characterized in that, also comprise transmitting support; Described fuselage body is vertically set on described transmitting support.
10. small-sized vertically taking off and landing flyer aerodynamic arrangement according to claim 9, is characterized in that, described transmitting support comprises base and canister launcher, and described canister launcher is fixedly connected with described base; Described fuselage body is inserted in described canister launcher.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520616748.4U CN204895837U (en) | 2015-08-14 | 2015-08-14 | Small -size VTOL aircraft aerodynamic layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520616748.4U CN204895837U (en) | 2015-08-14 | 2015-08-14 | Small -size VTOL aircraft aerodynamic layout |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204895837U true CN204895837U (en) | 2015-12-23 |
Family
ID=54918035
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520616748.4U Expired - Fee Related CN204895837U (en) | 2015-08-14 | 2015-08-14 | Small -size VTOL aircraft aerodynamic layout |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204895837U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059525A (en) * | 2015-08-14 | 2015-11-18 | 北京贯中精仪科技有限公司 | Aerodynamic layout of small-sized vertical takeoff and landing aircraft |
-
2015
- 2015-08-14 CN CN201520616748.4U patent/CN204895837U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059525A (en) * | 2015-08-14 | 2015-11-18 | 北京贯中精仪科技有限公司 | Aerodynamic layout of small-sized vertical takeoff and landing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206125423U (en) | VTOL fixed wing uavs with power device verts | |
| US20110177748A1 (en) | Vtol model aircraft | |
| CN205098474U (en) | Duct formula aircraft that verts with VTOL function | |
| CN102001446B (en) | Structure of vertical take-off and landing rotor aircraft | |
| CN204674831U (en) | Many fan arms aircraft | |
| EP3261925B1 (en) | Tiltrotor with double mobile wing | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN204250356U (en) | New fan wing aircraft | |
| CN107672802A (en) | Fluting culvert type plume rotor craft | |
| CN205418102U (en) | All -wing aircraft formula rotor craft that verts | |
| CN106915459A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN105059536A (en) | Rotor wing device with variable pitch and multi-rotor-wing aircraft | |
| CN105059525A (en) | Aerodynamic layout of small-sized vertical takeoff and landing aircraft | |
| CN103072690A (en) | Single-ducted coaxial rotor/propeller saucer-shaped aircraft | |
| CN109515704B (en) | Ducted plume rotorcraft based on cycloidal propeller technology | |
| CN203199178U (en) | Single-duct coaxial rotor/propeller saucer-shaped aircraft | |
| CN103754360B (en) | One kind flying disc type gyroplane | |
| CN204507261U (en) | A kind of coaxial many in the same way helighros | |
| CN104973241A (en) | Unmanned aerial vehicle with main and auxiliary multi-rotor structure | |
| CN204776020U (en) | Unmanned vehicles with many rotors of major -minor structure | |
| CN204916174U (en) | Variable -pitch rotor device and many rotor crafts | |
| CN208915439U (en) | Adjustable wing swallow shape simulation type unmanned plane | |
| CN204895837U (en) | Small -size VTOL aircraft aerodynamic layout | |
| CN106275415B (en) | The aircraft that a kind of fixed-wing and more rotors can automatically switch | |
| KR20160072522A (en) | Tilt-rotor aircraft wing |
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: 20151223 Termination date: 20170814 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |