CN101041380A - Inclined wing airplane and application thereof - Google Patents
Inclined wing airplane and application thereof Download PDFInfo
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- CN101041380A CN101041380A CN 200610049963 CN200610049963A CN101041380A CN 101041380 A CN101041380 A CN 101041380A CN 200610049963 CN200610049963 CN 200610049963 CN 200610049963 A CN200610049963 A CN 200610049963A CN 101041380 A CN101041380 A CN 101041380A
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Abstract
The invention relates to an inclined-wing airplane, comprising body and the part, inclined wing swinging obliquely correspondingly to the body, propeller and control servo device fixed on the inclined wing. Under the condition that it like common airplane can fly horizontally in larger flying speed, it adds vertical lifting performance to airplane and the aerodynamic force distribution is reasonable. The inclined-wing plane can be applied in commercial loading aircraft, motion aircraft and scientific experiment aircraft and it can be applied in unmanned inclined-wing airplane, inclined-wing airplane model and toy with various usages. It also can be used in other relative usages. It is especially suitable for regional airplane. In underdeveloped area there is no need to build special runway and only a space with the size of medium bus station or a basketball area is needed to rise airplane, land airplane and open airline. By this way, a great deal of ground, invest fund, building period and operating cost are saved.
Description
Affiliated technical field
Inclined wing airplane and application thereof belong to the improvement of vertically taking off and landing flyer and application thereof.
Background technology
The aircraft that has the vertical takeoff and landing function at present mainly contains helicopter and autogyro; Common autogyro has vertically/STOL aircraft and tiltrotor aircraft etc.They respectively have merits and faults:
Helicopter has the characteristics of maneuverability, but its horizontal flight speed is slower;
Vertically/and STOL aircraft is applied to jet opportunity of combat usually, and it requires very high to the manufacturing of aircraft power and control thereof, also there is very high requirement in landing site, and manufacturing cost is high;
Present tiltrotor aircraft development cost is high, the accident rate height, and aerodynamic configu ration layout is unreasonable.
Summary of the invention
In order to overcome many weak points of existing vertically taking off and landing flyer, the present invention proposes a kind of novel autogyro---inclined wing airplane, also can be referred to as " dumper wing aircraft ".
The present invention is by fuselage and parts thereof, the fuselage wing of (swing) that can tilt relatively---and tiltwing, be fixed on the propelling unit on the tiltwing and control actuating device and formed.Wherein, fuselage and parts thereof have comprised instrument and equipment in cabin body, horizontal tail, the direction wing (rudder), alighting gear, the cabin, have taken facility etc., and tiltwing also comprises main wing and aileron.The present invention can keep common aircraft have on the basis of bigger horizontal flying speed characteristic, make aircraft increase the function of vertical takeoff and landing, and aerodynamic configu ration layout is reasonable.
The present invention is achieved in that
As shown in Figure 4, fuselage (1) can connect by connecting rod (6-2) by bevelled wing (2) relatively, is regulated the pivot angle α of connecting rod (6-2) by the hydraulic part (6-1) of level indicator control; Regulate tiltwing and angle of rake pivot angle β by control of flight instrument or the manual hydraulic part of aviator (6-3), thus the horizontal flight direction and the attitude of decision aircraft.When fuselage is in horizontality, pivot angle β is 0 when spending, and the present invention makes level and flies forward; Pivot angle is about 90 when spending, and the present invention makes vertical takeoff and landing and floating state; When pivot angle was spent greater than 90, the present invention walked or drive slowly backward; Pivot angle β maximum should not be greater than 120 degree.
As shown in Figure 6, the effect of being regulated the pivot angle α of connecting rod (6-2) by the hydraulic part (6-1) of level indicator control is: when the front and back of aircraft center of gravity partially during back (being positioned at W '), level indicator is controlled hydraulic part (6-1) point of connection (just propelling unit is to the hoist point of body) of connecting rod (6-2) and tiltwing (2) is adjusted to g ' when the aircraft vertical takeoff and landing; When the front and back of aircraft center of gravity partially before when (being positioned at W), level indicator control hydraulic part (6-1) point of connection (angle of rake hoist point) of connecting rod (6-2) and tiltwing is adjusted to the g point when the aircraft vertical takeoff and landing.Like this, the invention solves the anterior-posterior balance problem of aircraft in the vertical takeoff and landing stage.Since the present invention in the position of the tiltwing in horizontal flight stage in existing aircraft the same (shown in Fig. 2, Fig. 3 C, Fig. 4 B, Fig. 5 B), so the horizontal flight stage still rely on the horizontal tail on the body to control balance and flight attitude.The present invention also can regulate the position of hoist point with the mode of motion of slide block or chute.
The present invention is to rely on gyroscope auxiliary in the left and right sides in vertical takeoff and landing stage balance, and the difference of regulating left and right sides propeller thrust realizes balance; Simultaneously, can be by aviator's operation, the left and right displacement the when difference of adjusting left and right sides propeller thrust realizes the aircraft vertical takeoff and landing.And the horizontal flight stage also is the same with existing aircraft, relies on yaw rudder (wing) and control balance of the aileron on the tiltwing and flight attitude on the body.
The layout that the present invention puts wing on usually adopting, an and wing contract groove (1-2) is set at the fuselage top, the combining closely of tiltwing front end and fuselage when being used for the present invention and doing horizontal flight is to ensure flight safety and minimizing air resistance.By the effect of hydraulic part (6-1) and connecting rod (6-2), the front end of tiltwing (2) can be embedded forward in the contract groove (1-2).Be that convenient the present invention is taken off vertically center of gravity when preceding, tiltwing (2) can not directly rely on hydraulic part (6-3) to regulate the back that the β angle is modulated to its leading edge contract groove (1-2), then can pass through hydraulic part (6-1) with connecting rod (6-2) pusher, after treating that tiltwing can arrive the position that enters the contract groove, unite adjusting by hydraulic part (6-1), (6-3) and connecting rod (6-2) again tiltwing is embedded the contract groove.And the present invention has at this moment had cooresponding horizontal velocity, and its horizontal tail can play the function of regulating the present invention front and back level.And the present invention also was the adjusting of uniting by hydraulic part (6-1), (6-3) and connecting rod (6-2) before vertical landing, earlier tiltwing (2) is withdrawed from contract groove (1-2), and the point of connection of connecting rod (6-2) and tiltwing is adjusted to focus point by level indicator, regulate tiltwing and angle of rake pivot angle β by control of flight instrument or the manual hydraulic part of aviator (6-3) then, make the vertical or short range landing of the present invention.But, when the present invention recommends tiltwing (2) front end to embed contract groove (1-2), the point of connection of connecting rod (6-2) or slide block and tiltwing (2) is the proal preceding stop of this point, and like this, tiltwing when the present invention does horizontal flight (2) closely sticks together with fuselage (1).
The present invention can realize left-handed right-hand rotation of the present invention by the left and right sides aileron (2-2L) on the adjusting tiltwing and the pivot angle of (2-2R) in the vertical takeoff and landing process.
Propelling unit of the present invention recommends to be placed in the middle part (wing is at angle of rake axis lateral position) of wing, also can be placed in the top or the bottom of wing as Fig. 8.The present invention can also be on tiltwing a plurality of propelling units of symmetric configuration, to increase the carrying capacity of aircraft.
In sum, main points of the present invention are: inclination wing (2) fuselage (1) relatively can tilt (swing), and propelling unit (3) is fixed on the tiltable wing (2).It is that with the common maximum difference of aircraft its wing can swing; The maximum difference of it and tiltrotor aircraft is that propelling unit is bevelled along with the inclination of wing; The maximum difference of it and helicopter is that it has wing, and propelling unit is can swing with wing, and wing can be fixed.
The invention has the beneficial effects as follows: keeping common aircraft to have on the basis of bigger horizontal flying speed characteristic, make aircraft increase the function of vertical takeoff and landing, and aerodynamic configu ration layout is being reasonable.
The rational embodiment of aerodynamic configu ration layout of the present invention: as shown in Figure 8, the A among the figure, B, C are respectively tiltrotor aircraft in the effect signal to wing of vertical takeoff and landing state A and level flight condition C and transition period B air-flow thereof; A ' among the figure, B ', C ' are respectively the present invention at the effect signal to wing of vertical takeoff and landing state A ' and level flight condition C ' and transition period B ' air-flow thereof, the arrow among the figure → expression air motion direction.Can see significantly from figure: tiltrotor aircraft is very big at vertical takeoff and landing state and transition period air-flow resistance, between propelling unit and the wing mutually loss very big lift and energy; The present invention does not then have this loss.
The present invention is particularly suitable for secondary-line-aircraft.Do not need to build private track in the under-developed area, the space that only needs compact car stations (even a basketball court) size just can the landing aircraft, opens the course line.Like this, can save a large amount of soils, capital fund and completion time of project, cut operating costs.
The present invention also is particularly suitable for the unmanned plane of scientific experiment and military use, and it does not need special-purpose landing site, almost can take off whenever and wherever possible and reclaim.
Description of drawings
Three-view diagram when Fig. 1 is a vertical takeoff and landing of the present invention.
Three-view diagram when parking when Fig. 2 is horizontal flight of the present invention or after the landing.
Fig. 3 is the block diagram of vertical takeoff and landing of the present invention, horizontal flight and transition thereof;
Block diagram when Fig. 3 A is a vertical takeoff and landing of the present invention,
Block diagram when Fig. 3 B is vertical takeoff and landing of the present invention and horizontal flight transition,
Block diagram when Fig. 3 C is horizontal flight of the present invention,
Fig. 4 is the cutaway view of tiltwing control position of the present invention and hydraulic servo mechanism mode of operation thereof;
When Fig. 4 A is vertical takeoff and landing of the present invention (about 90 degree in β angle), the cutaway view of its tiltwing control position and hydraulic servo mechanism mode of operation thereof,
When Fig. 4 B is horizontal flight of the present invention (the β angle is 0 degree), the cutaway view of its tiltwing control position (the tiltwing front end embeds the contract groove) and hydraulic servo mechanism mode of operation thereof.
Fig. 5 is tiltwing control position of the present invention and gear transmission servomechanism mode of operation cutaway view thereof;
When Fig. 5 A is vertical takeoff and landing of the present invention (about 90 degree in β angle), the cutaway view of its tiltwing control position and gear transmission servomechanism mode of operation thereof,
When Fig. 5 B is horizontal flight of the present invention (the β angle is 0 degree), the cutaway view of its tiltwing control position (the tiltwing front end embeds the contract groove) and gear transmission servomechanism mode of operation thereof.
When Fig. 6 is a vertical takeoff and landing of the present invention because of the center-of-gravity position difference, the signal of the position of angle of rake hoist point;
Fig. 6 A is center of gravity of the present invention when back relatively partially, the position of the point of connection of connecting rod and tiltwing (just propelling unit is to the hoist point of body),
Fig. 6 B be center of gravity of the present invention relatively partially before the time, the position of the point of connection of connecting rod and tiltwing (propelling unit hoist point),
Fig. 6 C is the connecting rod pivot angle α of tiltwing servomechanism of the present invention and the signal of propelling unit hoist point position relation.
Fig. 7 is the signal that the present invention adopts different propeller form and installation position;
Fig. 7 A is the signal that whirlpool slurry propelling unit places wing top,
Fig. 7 B is the signal that the turbofan propelling unit places the wing bottom,
Fig. 7 C is the signal that the turbofan propelling unit places wing top.
Fig. 8 is that tiltrotor aircraft is in the rational contrast signal of aerodynamic configu ration layout of the present invention;
A among Fig. 8, B, C are respectively: tiltrotor aircraft is in the effect signal to wing of vertical takeoff and landing state A and level flight condition C and transition period B air-flow thereof,
A ' among Fig. 8, B ', C ' are respectively: the present invention is in the effect signal to wing of vertical takeoff and landing state A ' and level flight condition C ' and transition period B ' air-flow thereof,
Arrow among Fig. 8 → expression air motion direction.
Fig. 9 is the three-view diagram that middle part (wing is at angle of rake axis lateral position) that propelling unit of the present invention is placed in wing is in the vertical takeoff and landing state.
In the accompanying drawing:
The 1st, fuselage (body), 1-2 are the contract grooves
The 2nd, tiltwing (inclination wing), 2-2 are aileron (ailerons of inclination wing)
The 3rd, propelling unit
The 4th, vertical tail (the direction wing or yaw rudder)
The 5th, tailplane (horizontal tail)
The 6th, the servomechanism of tiltwing
6-1 is hydraulic actuating cylinder and the hydraulic stem that connects body 1 and connecting rod 6-2
6-2 is the connecting rod (fork) that is placed on the body 1 and connects tiltwing 2
6-3 is hydraulic actuating cylinder and the hydraulic stem that connects connecting rod 6-2 and tiltwing 2
6-1 ' is the servo driving gear that is placed on the body
6-2 ' is connecting rod (fork) and the driven quadrant gear of siamesed thereof that is placed on the body and connects tiltwing
6-3 ' is the servo driving gear that is placed on the connecting rod 6-2 '
6-4 ' is the driven quadrant gear that is fixed on the tiltwing 2
α is the pivot angle of connecting rod
β is the leaning angle of tiltwing and body
W is relative connecting rod 6-2 and the forward center of gravity of body 1 point of connection
W ' is the center of gravity after relative connecting rod 6-2 and body 1 point of connection lean on
G is the hoist point to corresponding center of gravity W
G ' is the hoist point to corresponding center of gravity w '
The specific embodiment
In the embodiment of Fig. 9, fuselage and parts thereof all adopt the aircraft technology of ripe model, adopt on the tiltwing on this basis and put, and propelling unit is mid-; Adopt hydraulic servo mechanism shown in Figure 4, tiltwing pivot angle 0 degree≤β≤110 degree are adjustable.In the aircraft vertical takeoff and landing or when hovering, with the front and back level of level indicator control fuselage, with the left and right sides balance of gyroscope aux. controls fuselage.
The present invention can be applied to various commercial transport aircraft, motion aircraft, Research Test Vehicle, can also be applied to driverless operation inclined wing airplane and the inclined wing airplane model and the toy thereof of various uses, also can be as other associated uses.
Only be case of the present invention below, be not limited to this.
Claims (10)
1, inclined wing airplane is made up of fuselage and parts, propelling unit, tiltwing and control actuating device thereof, it is characterized in that: its wing (tiltwing) is fuselage can tilt (swing) relatively, propelling unit is fixed on the tiltwing, and swings with tiltwing.
2, inclined wing airplane as claimed in claim 1, it is characterized in that: in the aircraft vertical takeoff and landing and the process of hovering, control and adjust the mode of the propelling unit hoist point of tiltwing actuating device with level indicator and come the anterior-posterior balance of controlling aircraft, actuating device recommends to adopt hydraulic connecting rod mechanism.
3, inclined wing airplane as claimed in claim 1 is characterized in that: in aircraft vertical takeoff and landing process, control seesaw direction and speed by the pivot angle of regulating tiltwing and fuselage.
4, inclined wing airplane as claimed in claim 1 is characterized in that: in the aircraft vertical takeoff and landing and the process of hovering, by gyroscope aux. controls left and right sides balance.
5, inclined wing airplane as claimed in claim 1 is characterized in that: in the aircraft vertical takeoff and landing and the process of hovering, by regulating the difference control sideway movement of left and right sides lift of propeller.
6, inclined wing airplane as claimed in claim 1 is characterized in that: the left rotation and right rotation (turning to) of controlling the vertical takeoff and landing and the process of hovering by the pivot angle of regulating the tiltwing aileron.
7, inclined wing airplane as claimed in claim 1 is characterized in that: be equipped with the contract groove at the top of fuselage, in the aircraft horizontal flight or make the usefulness of the auxiliary constant tilt wing when parking; When the tiltwing front end embedded the contract groove, the point of connection of connecting rod and tiltwing was the proal preceding stop of connecting rod mechanism.
8, inclined wing airplane as claimed in claim 1 is characterized in that: propelling unit is placed in the middle part (wing is at angle of rake axis lateral position) of wing.
9, inclined wing airplane as claimed in claim 1 is characterized in that: the leaning angle of the relative fuselage of its inclination wing scalable in 0～110 degree scope, maximum are no more than 120 degree.
10, inclined wing airplane as claimed in claim 1 can be applied to various commercial transport aircraft, motion aircraft, Research Test Vehicle, can also be applied to driverless operation inclined wing airplane and the inclined wing airplane model and the toy thereof of various uses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610049963 CN101041380A (en) | 2006-03-23 | 2006-03-23 | Inclined wing airplane and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610049963 CN101041380A (en) | 2006-03-23 | 2006-03-23 | Inclined wing airplane and application thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101041380A true CN101041380A (en) | 2007-09-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610049963 Pending CN101041380A (en) | 2006-03-23 | 2006-03-23 | Inclined wing airplane and application thereof |
Country Status (1)
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| CN (1) | CN101041380A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| CN101870355A (en) * | 2010-06-03 | 2010-10-27 | 杨茂亮 | Coaxial double-rotary wing and tilt wing aircraft |
| CN101939219A (en) * | 2008-02-13 | 2011-01-05 | 贝尔直升机泰克斯特龙公司 | Rotor craft with variable incidence wing |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN104925254A (en) * | 2015-06-24 | 2015-09-23 | 吴畏 | Vertical take-off and landing aircraft |
| CN106114847A (en) * | 2016-06-27 | 2016-11-16 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN107651164A (en) * | 2017-08-28 | 2018-02-02 | 北京航空航天大学 | A kind of wing wide-angle inclining rotary mechanism for small-sized tilting wing formula aircraft |
| CN108382589A (en) * | 2018-02-05 | 2018-08-10 | 中国航空工业集团公司成都飞机设计研究所 | A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method |
-
2006
- 2006-03-23 CN CN 200610049963 patent/CN101041380A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| CN101939219A (en) * | 2008-02-13 | 2011-01-05 | 贝尔直升机泰克斯特龙公司 | Rotor craft with variable incidence wing |
| US8567709B2 (en) | 2008-02-13 | 2013-10-29 | Textron Innovations Inc. | Rotorcraft with variable incident wing |
| CN101939219B (en) * | 2008-02-13 | 2014-01-01 | 贝尔直升机泰克斯特龙公司 | Rotorcraft with variable incident wing |
| CN101870355A (en) * | 2010-06-03 | 2010-10-27 | 杨茂亮 | Coaxial double-rotary wing and tilt wing aircraft |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN104925254A (en) * | 2015-06-24 | 2015-09-23 | 吴畏 | Vertical take-off and landing aircraft |
| CN106114847A (en) * | 2016-06-27 | 2016-11-16 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106114847B (en) * | 2016-06-27 | 2018-10-09 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN107651164A (en) * | 2017-08-28 | 2018-02-02 | 北京航空航天大学 | A kind of wing wide-angle inclining rotary mechanism for small-sized tilting wing formula aircraft |
| CN108382589A (en) * | 2018-02-05 | 2018-08-10 | 中国航空工业集团公司成都飞机设计研究所 | A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method |
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Open date: 20070926 |