CN2306952Y - Double-wing aircraft capable of landing or taking-off vertically - Google Patents
Double-wing aircraft capable of landing or taking-off vertically Download PDFInfo
- Publication number
- CN2306952Y CN2306952Y CN 97202712 CN97202712U CN2306952Y CN 2306952 Y CN2306952 Y CN 2306952Y CN 97202712 CN97202712 CN 97202712 CN 97202712 U CN97202712 U CN 97202712U CN 2306952 Y CN2306952 Y CN 2306952Y
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- wing
- hydraulic pressure
- shift calibrating
- backward
- pressure shift
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Abstract
The utility model relates to a double-wing aircraft capable of landing or taking-off vertically. The double-wing aircraft capable of landing or taking-off vertically is characterized in that two sets of wings comprising the front wing and the back wing are arranged on the aircraft body, wherein, the front wing is a short wing and the back wing is a long wing; two sets of hydraulic pressure pushing devices are connected and arranged on the lower part of the front wing and the back wing respectively; a pushing rod can push the wing to rotate clockwise along with a shaft; two sets of hydraulic pressure moving correcting devices are arranged on the lower part of the hydraulic pushing devices which are arranged on the lower part of the front wing and the back wing; a group of perpendicular hydraulic pressure manifolding devices and a jacket tube are arranged on the bottom of the hydraulic pressure moving correcting device under the front wing and the back wing respectively. The utility model is creative and has a novel structure. The double-wing aircraft capable of landing or taking-off vertically is a new technical proposal which has a prospect of practical application.
Description
But the utility model is a kind of biplane of vertical takeoff and landing (VTOL), and it has carried out new design in conjunction with control theory to the version of existing aircraft, has proposed a kind of new technical scheme.
The aircraft kind and the model of international airline field manufacturing at present and use are a lot, because its application target and environment difference separately, its version and performance characteristics are also different, this wherein, but the kind of the fixed wing aircraft of vertical takeoff and landing (VTOL) also seldom, finds according to present technology and equipment thereof, further develop the control that vertical takeoff and landing (VTOL) fixed-wing aircraft need solve its flight attitude better, it comprises two basic performance requriementss, the first, and the stagnant empty ability of aircraft zero-speed; The second, aircraft is from the zero-speed empty stable conversion to horizontal flight that stagnates, and the technical performance of resolving these two keys requires the important topic that will become in the vertical takeoff and landing (VTOL) fixed-wing aircraft evolution from now on.
The purpose of this utility model is just at above-mentioned imagination, through my a large amount of in recent years research and experiment, provide a kind of later-model vertical takeoff and landing (VTOL) biplane in conjunction with the control theory design, it relates to the bold improvement to prior art and structure, focuses on to be good at above-mentioned two gordian technique performance institute requirements.
The purpose of this utility model reaches by following design:
This kind vertical takeoff and landing (VTOL) biplane comprises airframe, wing, empennage, aero-engine, alighting gear and other equipment, and is consistent with existing aircraft, on this basis,, be specially in conjunction with structure design of the present utility model,
1.. forward and backward two groups of wings are installed on the fuselage, and wherein, preceding wing is short wing, and back wing is the lead aircraft wing, an aero-engine respectively is installed below the long and short wing left and right sides; Wherein, short wing is installed in from head to 1/5th of tail length, and the lead aircraft wing is installed in from head to 3/5ths of tail length.In addition, a stabilizer also is set below long and short wing.
2.. connection one cover hydraulic top pushing device all below forward and backward wing, but its propulsion arm pushing tow wing along the axle clickwise, angular range is 0-100 °, and can be fixed on any angular position.
3.. a cover hydraulic pressure shift calibrating device all is installed below the hydraulic top pushing device below being installed on forward and backward wing or a cover hydraulic pressure shift calibrating only is installed be installed on before below wing or the back wing, control the center of gravity of total system by the position of moving institute's erecting equipment on it; The correction ultimate range of hydraulic pressure shift calibrating device is 50 centimetres.
4.. one group of vertical hydraulic manifolding and a sleeve pipe are respectively installed in the bottom of hydraulic top pushing device below forward and backward wing and hydraulic pressure shift calibrating device, and arm quantity is 4, like this can be with forward and backward wing jacking simultaneously certain altitude.Dress oil line and cable provide oil plant to driving engine and miscellaneous equipment special use in the sleeve pipe.
The drawing of accompanying drawing is described as follows:
Fig. 1 is an integral structure scheme drawing of the present utility model
Structural representation when Fig. 2 is 45 ° of wing of the present utility model rotations
Fig. 3 is the structural representation of hydraulic pressure shift calibrating device of the present utility model
Fig. 4 is the structural representation of hydraulic top pushing device of the present utility model
Structural representation when Fig. 5 is wing half-twist of the present utility model and pushing tow rising
Below with reference to drawings and Examples the utility model is further described:
Referring to accompanying drawing 1,2,3,4, shown in 5, this kind vertical takeoff and landing (VTOL) biplane, it comprises airframe (7), wing, tailplane (5), vertical tail (6), aero-engine (3), the attached wing (7), alighting gear (8) and other equipment, with the structure and the device basically identical of existing aircraft, on this basis, the technical program has proposed new project organization, is characterized in
1.. forward and backward two groups of wings (1), (2) are installed on fuselage (7), and wherein, preceding wing (1) is short wing, and back wing (2) is the lead aircraft wing, an aero-engine (3) respectively is installed below the long and short wing left and right sides; Wherein, short wing (1) is installed in from head to 1/5th of tail length, and the lead aircraft wing is installed in from head to 3/5ths of tail length, and a stabilizer (12) is set below long and short wing.
2.. all hydraulic top pushing device (15) is overlapped in connection one below forward and backward wing, its propulsion arm (14) is connected with the wing bottom surface, airfoil trailing edge be connected with platform (16) and as axle make propulsion arm (14) but the pushing tow wing along the axle clickwise, angular range is 0-100 °, and can be fixed on any angular position; Push rod groove (13) is installed in the both sides of platform (16).
3.. a cover hydraulic pressure shift calibrating device (11) all is installed below the hydraulic top pushing device below being installed on forward and backward wing (15), is controlled the center of gravity of total system by the position of moving institute's erecting equipment on it; Wherein, hydraulic pressure shift calibrating device before and after install preceding wing below, then left and right sides hydraulic pressure shift calibrating device is installed in the wing below, and control operation is carried out in setting comparably like this.The correction ultimate range of hydraulic pressure shift calibrating device (11) is 50 centimetres.
4.. one a group of vertical hydraulic manifolding (9) and a sleeve pipe (10) are respectively installed in the bottom of hydraulic top pushing device below forward and backward wing (15) and hydraulic pressure shift calibrating device (11), arm quantity is 4, like this can be with forward and backward wing jacking simultaneously certain altitude, the maximum top lifting height of hydraulic pressure manifolding (9) is 3 meters.And being housed in the sleeve pipe, oil hose and cable use to driving engine and miscellaneous equipment so that oil plant and electric power to be provided.
The structure design purpose of the above-described vertical takeoff and landing (VTOL) biplane that is made of long and short wing is, stagnate empty and turn in the process of state of flight in the aircraft zero-speed, when running into strong air flow and sinuous flow, can keep the balance of the stable and flight attitude of body nodal point hanging, make the vertical lift flight freely in any situation and any environment of this biplane.
The utility model compared with prior art has certain pioneering, its structural design novelty, its control Its effect of the relatively easy performance of system part is a kind of new technical scheme with actual application prospect.
Claims (6)
1. vertical takeoff and landing (VTOL) biplane, it comprises airframe, wing, empennage, aero-engine, alighting gear and other equipment, it is characterized in that:
1.. forward and backward two groups of wings (1), (2) are installed on the fuselage (7), and wherein, preceding wing (1) is short wing, and back wing (2) is the lead aircraft wing, an aero-engine (3) respectively is installed below the long and short wing left and right sides;
2.. connection one cover hydraulic top pushing device (15) all below forward and backward wing, its propulsion arm (14) but the pushing tow wing along the axle clickwise, angular range is 0-100 °, and can be fixed on any angular position;
3.. a cover hydraulic pressure shift calibrating device (11) all is installed below the hydraulic top pushing device below being installed on forward and backward wing (15) or a cover hydraulic pressure shift calibrating only is installed be installed on before below wing or the back wing, control the center of gravity of total system by the position of moving institute's erecting equipment on it;
4.. one a group of vertical hydraulic manifolding (9) and a sleeve pipe (10) are respectively installed in the bottom of hydraulic top pushing device below forward and backward wing (15) and hydraulic pressure shift calibrating device (11), arm quantity is 4, like this can be with forward and backward wing jacking simultaneously certain altitude.
2. omniplane according to claim 1 is characterized in that: short wing (1) is installed in from head to 1/5th of tail length, and the lead aircraft wing is installed in from head to 3/5ths of tail length.
3. omniplane according to claim 1 is characterized in that: a stabilizer (12) is set below long and short wing.
4. omniplane according to claim 1 is characterized in that: when two cover hydraulic pressure shift calibrating devices (11) are installed, and hydraulic pressure shift calibrating device before and after install preceding wing below, then left and right sides hydraulic pressure shift calibrating device is installed in the wing below.
5. according to claim 1 or 4 described omniplanes, it is characterized in that: the correction ultimate range of hydraulic pressure shift calibrating device (11) is 50 centimetres.
6. omniplane according to claim 1 is characterized in that: the maximum top lifting height of hydraulic pressure manifolding (9) is 3 meters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97202712 CN2306952Y (en) | 1997-03-27 | 1997-03-27 | Double-wing aircraft capable of landing or taking-off vertically |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97202712 CN2306952Y (en) | 1997-03-27 | 1997-03-27 | Double-wing aircraft capable of landing or taking-off vertically |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2306952Y true CN2306952Y (en) | 1999-02-10 |
Family
ID=33923795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97202712 Expired - Fee Related CN2306952Y (en) | 1997-03-27 | 1997-03-27 | Double-wing aircraft capable of landing or taking-off vertically |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2306952Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849211A (en) * | 2012-09-28 | 2013-01-02 | 宋新民 | Variable power vertical short-distance takeoff landing aircraft with fixed wings |
| CN103072691A (en) * | 2013-02-08 | 2013-05-01 | 郭建中 | Front-rear-rudder multiple-power-wing airplane |
| CN103419933A (en) * | 2013-07-24 | 2013-12-04 | 南京航空航天大学 | Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices |
| CN105197237A (en) * | 2015-09-29 | 2015-12-30 | 上海圣尧智能科技有限公司 | Vertical takeoff and landing unmanned aerial vehicle |
| CN105473443A (en) * | 2013-08-12 | 2016-04-06 | 第一装置有限公司 | Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable |
| CN106628168A (en) * | 2016-11-30 | 2017-05-10 | 北京天宇新超航空科技有限公司 | Novel tilt rotor aircraft |
| CN110979721A (en) * | 2019-12-24 | 2020-04-10 | 郑州航空工业管理学院 | Optimization method for double-wing layout time-limited carrying of air-drop aircraft |
| CN111762324A (en) * | 2020-07-17 | 2020-10-13 | 河南农业大学 | Integrative double-wing formula fixed wing plant protection unmanned aerial vehicle of pencil wing spar |
-
1997
- 1997-03-27 CN CN 97202712 patent/CN2306952Y/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849211A (en) * | 2012-09-28 | 2013-01-02 | 宋新民 | Variable power vertical short-distance takeoff landing aircraft with fixed wings |
| CN103072691A (en) * | 2013-02-08 | 2013-05-01 | 郭建中 | Front-rear-rudder multiple-power-wing airplane |
| CN103419933A (en) * | 2013-07-24 | 2013-12-04 | 南京航空航天大学 | Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices |
| CN105473443A (en) * | 2013-08-12 | 2016-04-06 | 第一装置有限公司 | Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable |
| CN105197237A (en) * | 2015-09-29 | 2015-12-30 | 上海圣尧智能科技有限公司 | Vertical takeoff and landing unmanned aerial vehicle |
| CN106628168A (en) * | 2016-11-30 | 2017-05-10 | 北京天宇新超航空科技有限公司 | Novel tilt rotor aircraft |
| CN110979721A (en) * | 2019-12-24 | 2020-04-10 | 郑州航空工业管理学院 | Optimization method for double-wing layout time-limited carrying of air-drop aircraft |
| CN110979721B (en) * | 2019-12-24 | 2021-06-08 | 郑州航空工业管理学院 | Optimization method for double-wing layout time-limited carrying of air-drop aircraft |
| CN111762324A (en) * | 2020-07-17 | 2020-10-13 | 河南农业大学 | Integrative double-wing formula fixed wing plant protection unmanned aerial vehicle of pencil wing spar |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| MM1K | Cease caused by non payment of annual fee |