CN107226207A - A kind of compound rudder face on vertically taking off and landing flyer - Google Patents
A kind of compound rudder face on vertically taking off and landing flyer Download PDFInfo
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- CN107226207A CN107226207A CN201710539397.5A CN201710539397A CN107226207A CN 107226207 A CN107226207 A CN 107226207A CN 201710539397 A CN201710539397 A CN 201710539397A CN 107226207 A CN107226207 A CN 107226207A
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- 150000001875 compounds Chemical class 0.000 title claims abstract description 61
- 230000007246 mechanism Effects 0.000 claims abstract description 18
- 230000004044 response Effects 0.000 abstract description 5
- 238000010276 construction Methods 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 15
- 230000007423 decrease Effects 0.000 description 9
- 230000007704 transition Effects 0.000 description 9
- 230000006870 function Effects 0.000 description 7
- 230000033001 locomotion Effects 0.000 description 4
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- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
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- LFYJSSARVMHQJB-QIXNEVBVSA-N bakuchiol Chemical compound CC(C)=CCC[C@@](C)(C=C)\C=C\C1=CC=C(O)C=C1 LFYJSSARVMHQJB-QIXNEVBVSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
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Abstract
A kind of of the invention and compound rudder face on vertically taking off and landing flyer, including being combined rudder face body, the compound rudder face body is divided into rudder face and lower rudder face, the compound rudder face body is arranged on wing end, the wing side is provided with engine nacelle, and the engine nacelle tail end is provided with propeller；The wing includes front wing and rear wing, and the wing wing root is provided with wing inclining rotary mechanism；The engine nacelle is fixedly connected with wing, and engine nacelle can vert with wing under inclining rotary mechanism driving around tiliting axis.It is an advantage of the invention that vertically taking off and landing flyer is realized in hovering by adjusting the angle of release amount for the compound rudder face being arranged on wing, put down compound rudder face when flying and play common multiaspect function, control system is simple and easy to apply, simple in construction, and response is rapid.
Description
Technical field
Of the invention and a kind of aircraft is combined rudder face, and in particular to a kind of compound rudder on vertically taking off and landing flyer
Face.
Background technology
The development of tiltrotor starts from the forties in last century, is taken the lead in being developed by American Bell Incorporated, tilting rotor
The success of machine development, which is that aircraft is historical, once to be leaped, but its security has just endured query to the fullest extent since emerge.In order to
The longitudinal stability of tiltrotor is improved, while increasing loading capacity, the plan for the quadrotor that verts is proposed out.Incline
The imagination for turning quadrotor was proposed by Bell Co. researcher in 1979 earliest.It is using two pairs of wings, each pair machine
Wing both sides are respectively equipped with a propeller, this not only adds lifting capacity during VTOL, while when also making horizontal flight
Thrust is greatly increased, and 2 months 2012, Korea Aerospace Res Inst subscribed to the agreement with Korean air, determines common develop
" TR-6X " tiltrotor aircraft.This is that in addition to the U.S., the whole world determines to include tiltrotor aircraft first that official is actual to be made
Motion.For four gyroplanes that vert, in addition to Bell Co., research institution is in basic research mostly at present or model machine is set
In the meter stage, wherein more representational is the quadrotor that verts of Chiba, Japan university design, the aircraft is employed
The scheme that wing together verts with nacelle.Wing is to the anti-of rotor air-flow during this scheme can significantly mitigate VTOL
Bullet, while the loading capacity of VTOL process can also be increased to a certain extent.Current tiltrotor aircraft hangs in the air
Stopping time needs regulation pitch or periodicity displacement, control rotor rotating speed etc. to change lift size, control system and complicated,
Response is slow.
The existing A of unauthorized patent document CN 105150558 that announced disclose a kind of part integral forming method and flown
The rudder face and aircraft of row device, the problem of it is mainly solved be mechanically connect in the prior art composite material parts processing when produce
Raw part performance reduction, frock is larger, and the problems such as cost is higher, the problem of being solved from the present invention is different.
The content of the invention
Simple in construction present invention aim to address above mentioned problem there is provided a kind of control system is simple and easy to apply, response is rapid
Be used for vertically taking off and landing flyer on compound rudder face.
To achieve the above object, the present invention provides following technical scheme：
A kind of compound rudder face on vertically taking off and landing flyer, including compound rudder face body, the compound rudder face body
It is divided into rudder face and lower rudder face, the compound rudder face body is arranged on wing end, and the wing side is provided with engine nacelle,
The engine nacelle tail end is provided with propeller；
Further, the wing includes front wing and rear wing, and the wing wing root is provided with wing inclining rotary mechanism；The hair
Motivation nacelle is fixedly connected with wing, and engine nacelle can vert with wing under inclining rotary mechanism driving around tiliting axis；
Further, the front wing rotates around point c along arc AB, and rear wing rotates around point d along arc CD, on the front wing and rear wing
It is equipped with propeller；
Further, the deflection angle of the upper rudder face and lower rudder face along wing is δp, the upper rudder face and lower rudder face it
Between folding angle be δk, the angle of the upper rudder face and vertical direction is θ1, the angle of the lower rudder face and vertical direction is
θ2。
Further, aircraft vertical landing and during hovering, engine nacelle and wing vert to aircraft longitudinal axis and hung down
Directly, engine start, drives propeller rotational, and front wing provides lift Tf；When aircraft switchs to flat fly by VTOL, vert machine
Structure drives engine nacelle and the rich tiliting axis of wing to rotate to, rear wing offer lift T parallel with aircraft longitudinal axisr, to aircraft
Onward impulse is provided.
Further, the θ1And θ2It is δ with deflection anglepAnd folding angle is δkRelation it is as follows：
θ1=δp+δk
θ2=δp-δk。
As a preferred technical solution of the present invention, the front wing and rear wing are the straight wing.
Vertically taking off and landing flyer of the present invention, Fixed Wing AirVehicle and gyroplane are combined, and vertical rise can be achieved
Drop, hovering and fixed-wing mode are cruised.Aircraft is main by front wing, rear wing, fuselage, five portions of power set and undercarriage
It is grouped into.
The aircraft is mainly characterized in that：
(1) aircraft has the advantage of gyroplane and Fixed Wing AirVehicle concurrently.VTOL and hovering can either be realized, again may be used
The Fixed Wing AirVehicle that can be flown the long period is deformed into, can be changed as needed between both.
(2) rudder face of front wing and rear wing is using compound rudder face, and each compound rudder face is separated from centre, be divided into above and below two
Point, the rudder face up and down of described compound rudder face can link deflection in the same direction, realize the function of common rudder face, can also independent folding
Action, and the rudder face compound action on other wings, to control aircraft flight attitude.
(3) when aircraft is in floating state, engine nacelle passes through the compound rudder face of control perpendicular to aircraft longitudinal axis
Folding angle changes air flow direction and flow velocity, so that the lift of change of flight device, makes aircraft hover.
(4) during cruising flight, it is flat to engine nacelle that wing inclining rotary mechanism drives four wings and engine nacelle to rotate
Row is in aircraft longitudinal axis, and as common fixed-wing configuration, energy consumption is relatively small, and with higher flying speed and larger flight half
Footpath.
The Attitude Control Strategies hovered under configuration：For pitching/control of sideward roll, revolution speed of propeller is constant, by changing four
The folding angle of individual compound rudder face, produces pitching/rolling moment, so as to change posture；For driftage control, by changing four
The deflection angle of compound rudder face, produces torsional moment, drives vehicle yaw.
Height control during aircraft hovering, changes compound rudder face folding angle, now flows through aerofoil surface and compound
The air flow direction and flow velocity of rudder face change, and it can be seen from Bernoulli equation, airflow function is on aerofoil surface and rudder face
Pressure and active force change, the compound rudder face co-operating on four wings, so that the lift of change of flight device.
During aircraft transition flight, engine nacelle is first parallel to aircraft longitudinal axis, and wing and engine nacelle vert machine
Structure drives wing and nacelle to rotate, while increasing compound rudder face folding angle, increases flight resistance, quick reduction of speed.It is multiple by changing
Control surface deflection angle (transition leading portion) or folding angle (transition back segment) are closed, posture is controlled.
When aircraft vertical landing process stage needs altitude dash/decline, the compound rudder face opening and closing movement of driving can not expire
When sufficient aircraft altitude dash/decline is required, now compound rudder face folding is coordinated to realize aircraft by adjusting revolution speed of propeller
Altitude dash/decline.
The beneficial effects of the present invention are：
The wing inclining rotary mechanism that wing wing root is installed so that engine nacelle and wing can be around under inclining rotary mechanism driving
Tiliting axis is verted there is provided upward lift, and gram aircraft self gravitation and air drag are moved up and down；Aircraft climb to certain
During one certain height, wing inclining rotary mechanism driving wing and engine nacelle vert to nacelle parallel to aircraft longitudinal axis, wing
With nacelle rotor the power advanced is provided for aircraft；For driftage control, by changing the deflection angle of four compound rudder faces,
Torsional moment is produced, vehicle yaw is driven.Vertically taking off and landing flyer is arranged on compound on wing in hovering by adjusting
The angle of release amount of rudder face is put down and rudder face performance common multiaspect function is combined when flying to realize, control system is simple and easy to apply, simple in construction,
Response is rapid.
Brief description of the drawings
Technical scheme, is used required in being described below to embodiment in order to illustrate the embodiments of the present invention more clearly
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only the present invention in order to illustrate more clearly of this hair
Bright embodiment or technical scheme of the prior art, below by the required accompanying drawing used in embodiment or description of the prior art
It is briefly described, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
These accompanying drawings obtain other accompanying drawings.
Fig. 1 is compound rudder face partial structural diagram of the invention；
Fig. 2 is vertically taking off and landing flyer structural representation of the invention；
Fig. 3 is vertically taking off and landing flyer VTOL schematic diagram of the invention.
Embodiment
A kind of compound rudder face on vertically taking off and landing flyer as Figure 1-3, including compound rudder face body 10,
10 points of the compound rudder face body is upper rudder face 1 and lower rudder face 2, and the compound rudder face body 10 is arranged on the end of wing 4, described
The side of wing 4 is provided with engine nacelle 9, and the tail end of engine nacelle 9 is provided with propeller 3；
Further, the wing 4 includes front wing 5,6 and rear wing 7,8, and the wing root of wing 4 is provided with wing and verted machine
Structure；The engine nacelle 9 is fixedly connected with wing 4, and engine nacelle 9 and wing 4 can be around under inclining rotary mechanism driving
Tiliting axis verts；
Further, the front wing 5,6 rotates around point c along arc AB, and rear wing 7,8 rotates around point d along arc CD, the front wing
5,6 and rear wing 7,8 on be equipped with propeller 3；
Further, the deflection angle of the upper rudder face 1 and lower rudder face 2 along wing 4 is δp, the upper rudder face 1 and lower rudder
Folding angle between face 2 is δk, the upper rudder face 1 and the angle of vertical direction are θ1, the lower rudder face 2 and vertical direction
Angle is θ2。
Further, aircraft vertical landing and during hovering, engine nacelle 9 and wing 4 vert to aircraft longitudinal axis
Vertically, engine start, driving propeller 3 is rotated, and front wing 5,6 provides lift Tf；When aircraft switchs to flat fly by VTOL,
Inclining rotary mechanism drives engine nacelle 9 and wing 4 tiliting axis of having mercy on to rotate to parallel with aircraft longitudinal axis, and rear wing 7,8 provides lift
Tr, onward impulse is provided to aircraft.
Further, the θ1And θ2It is δ with deflection anglepAnd folding angle is δkRelation it is as follows：
θ1=δp+δk
θ2=δp-δk。
As a preferred technical solution of the present invention, the front wing 5,6 and rear wing 7,8 are the straight wing.
Vertically taking off and landing flyer of the present invention, Fixed Wing AirVehicle and gyroplane are combined, and vertical rise can be achieved
Drop, hovering and fixed-wing mode are cruised.Aircraft is main by front wing 5,6, rear wing 7,8, fuselage, power set and undercarriage
Five parts are constituted.
The aircraft is mainly characterized in that：
(1) aircraft has the advantage of gyroplane and Fixed Wing AirVehicle concurrently.VTOL and hovering can either be realized, again may be used
The Fixed Wing AirVehicle that can be flown the long period is deformed into, can be changed as needed between both.
(2) front wing 5,6 and rear wing 7,8 rudder face using compound rudder face, each compound rudder face is separated from centre, is divided into
Lower two parts, the rudder face up and down of described compound rudder face can link deflection in the same direction, realize the function of common rudder face, can also be only
Vertical opening and closing movement, and the rudder face compound action on other wings, to control aircraft flight attitude.
(3) when aircraft is in floating state, engine nacelle 9 passes through the compound rudder face of control perpendicular to aircraft longitudinal axis
Folding angle change air flow direction and flow velocity so that the lift of change of flight device, makes aircraft hover.
(4) during cruising flight, it is flat to engine nacelle that wing inclining rotary mechanism drives four wings and engine nacelle to rotate
Row is in aircraft longitudinal axis, and as common fixed-wing configuration, energy consumption is relatively small, and with higher flying speed and larger flight half
Footpath.
The Attitude Control Strategies hovered under configuration：For pitching/control of sideward roll, revolution speed of propeller is constant, by changing four
The folding angle of individual compound rudder face, produces pitching/rolling moment, so as to change posture；For driftage control, by changing four
The deflection angle of compound rudder face, produces torsional moment, drives vehicle yaw.
Height control during aircraft hovering, changes compound rudder face folding angle, now flows through aerofoil surface and compound
The air flow direction and flow velocity of rudder face change, according to Bernoulli equation：
Understand, pressure and active force of the airflow function on the aerofoil of wing 4 and rudder face change, answering on four wings
Rudder face co-operating is closed, so that the lift of change of flight device.
During aircraft transition flight, engine nacelle 9 first verts parallel to aircraft longitudinal axis, wing 4 and engine nacelle 9
Mechanism drives wing 4 and engine nacelle 9 to rotate, while increasing compound rudder face folding angle, increases flight resistance, quick reduction of speed.
By changing compound control surface deflection angle (transition leading portion) or folding angle (transition back segment), posture is controlled.
When aircraft vertical landing process stage needs altitude dash/decline, the compound rudder face opening and closing movement of driving can not expire
When sufficient aircraft altitude dash/decline is required, now compound rudder face folding is coordinated to realize aircraft by adjusting the rotating speed of propeller 3
Altitude dash/decline.
Embodiment：
Aircraft layout is as shown in Figure 2：Aircraft front wing 5,6, rear wing 7,8 are the design of the straight wing.The wing root of wing 4 is pacified
Equipped with wing can inclining rotary mechanism, as shown in figure 3, front wing around point c along arc AB rotate, rear wing around point d along arc CD rotate.Before taking off,
Engine nacelle 9 starts engine perpendicular to aircraft longitudinal axis, and engine driving propeller 3 is rotated, and front wing 5,6 provides lift
Tf, the offer lift of rear wing 7,8 Tr, lift TfAnd TrAircraft self gravitation and air drag is overcome to move up and down.Aircraft is climbed
When being raised to a certain certain height, wing inclining rotary mechanism driving wing 4 and engine nacelle 9 vert to nacelle and indulged parallel to aircraft
Axle, the wing 4 and nacelle rotor 9 provide the power advanced for aircraft.
The Attitude Control Strategies hovered under configuration：For bowing/facing upward, control of sideward roll, the rotating speed of propeller 3 on four wings
It is constant, realized by changing the folding angle of four compound rudder faces.Rudder face up and down 1,2 folding angle δ on rear wingkReduction/increasing
Plus, generation bow/face upward torque.The folding angle δ of left side rudder face 1,2kIncrease, right side is combined the folding angle δ of rudder facekReduce, produce
Rolling torque, so as to change posture；For driftage control, by the deflection angle δ for changing four compound rudder facesp, produce torsion
Torque, drives vehicle yaw.
Height control during aircraft hovering, changes rudder face 1,2 folding angle δk, the aerofoil of airflow passes wing 4 and rudder
During face 1,2, the flow velocity and direction for flowing through the air-flow on rudder face 1,2 change, and it can be seen from Bernoulli equation, airflow function exists
Power on compound rudder face 1,2 changes, and rudder face 1,2 co-operatings on front and rear wing 5,6,7,8 change the aircraft
Lift.
During aircraft transition flight, engine nacelle 9 is first parallel to aircraft longitudinal axis, and front and rear wing 5,6,7,8 verts
Wing 5,6,7,8 and engine nacelle 9 are rotated before and after mechanism driving, while the compound rudder face folding angle δ of increasek, increase flight resistance
Power, quick reduction of speed.By changing compound control surface deflection angle δp(transition leading portion) or folding angle δk(transition back segment), controls appearance
State.
When aircraft altitude dash/decline is needed during aircraft vertical landing, only adjust on each wing
The folding angle δ of rudder face 1,2k, it is impossible to aircraft altitude dash/decline requirement is met, the rotating speed of propeller 3 is now adjusted and coordinates compound
Rudder face 1,2 foldings realize aircraft altitude dash/decline.
Vertically taking off and landing flyer is realized in hovering by adjusting the angle of release amount for the compound rudder face being arranged on wing, is put down
Compound rudder face plays common multiaspect function when flying, and control system is simple and easy to apply, simple in construction, and response is rapid.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
God is with principle, and any modification, equivalent substitution and improvements made etc. should be included in the scope of the protection.
Claims (4)
1. a kind of compound rudder face on vertically taking off and landing flyer, including compound rudder face body (10), it is characterised in that described
Compound rudder face body (10) is divided into rudder face (1) and lower rudder face (2), and the compound rudder face body (10) is arranged on wing (4) end
End, wing (4) side is provided with engine nacelle (9), and engine nacelle (9) tail end is provided with propeller (3)；
The wing (4) includes front wing (5,6) and rear wing (7,8), and wing (4) wing root is provided with wing inclining rotary mechanism；Institute
Engine nacelle (9) is stated to be fixedly connected with wing (4), and engine nacelle (9) and wing (4) can be with inclining rotary mechanism driving
Verted around tiliting axis；
The front wing (5,6) rotates around point c along arc AB, and rear wing (7,8) rotates around point d along arc CD, the front wing (5,6) and rear wing
Propeller (3) is equipped with (7,8)；
The deflection angle of the upper rudder face (1) and lower rudder face (2) along wing (4) is δp, the upper rudder face (1) and lower rudder face (2) it
Between folding angle be δk, the upper rudder face (1) and the angle of vertical direction are θ1, the folder of the lower rudder face (2) and vertical direction
Angle is θ2。
2. a kind of compound rudder face on vertically taking off and landing flyer according to claim 1, it is characterised in that aircraft
When VTOL and hovering, engine nacelle (9) and wing (4) vert to, engine start vertical with aircraft longitudinal axis, driving
Propeller (3) is rotated, and front wing (5,6) provides lift Tf；When aircraft switchs to flat fly by VTOL, inclining rotary mechanism driving is started
Machine nacelle (9) and the rich tiliting axis of wing (4) are rotated to, rear wing (7,8) offer lift T parallel with aircraft longitudinal axisr, to aircraft
Onward impulse is provided.
3. a kind of compound rudder face on vertically taking off and landing flyer according to claim 1, it is characterised in that before described
The wing (5,6) and rear wing (7,8) are the straight wing.
4. a kind of compound rudder face on vertically taking off and landing flyer according to any one of claims 1 to 3, its feature exists
In the θ1And θ2It is δ with deflection anglepAnd folding angle is δkRelation it is as follows：
θ1=δp+δk
θ2=δp-δk。
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710539397.5A CN107226207A (en) | 2017-07-04 | 2017-07-04 | A kind of compound rudder face on vertically taking off and landing flyer |
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| CN201710539397.5A CN107226207A (en) | 2017-07-04 | 2017-07-04 | A kind of compound rudder face on vertically taking off and landing flyer |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791816A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of tilting wing unmanned plane with complex pneumatic rudder face |
| CN110077586A (en) * | 2019-05-22 | 2019-08-02 | 福州大学 | A kind of combined type aircraft and its control method |
| CN113788139A (en) * | 2021-10-26 | 2021-12-14 | 上海磐拓航空科技服务有限公司 | Method for accurately controlling aircraft track through multifunctional pneumatic control surface |
| CN115071967A (en) * | 2022-07-14 | 2022-09-20 | 西南交通大学 | Vertical take-off and landing aircraft |
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| GB448703A (en) * | 1934-12-12 | 1936-06-12 | Audrey Gretchen Coats | Improvements in or relating to aircraft fuselages |
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| CN108791816A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of tilting wing unmanned plane with complex pneumatic rudder face |
| CN108791816B (en) * | 2018-07-16 | 2024-02-06 | 西安君晖航空科技有限公司 | Tilting wing unmanned aerial vehicle with compound pneumatic control surface |
| CN110077586A (en) * | 2019-05-22 | 2019-08-02 | 福州大学 | A kind of combined type aircraft and its control method |
| CN110077586B (en) * | 2019-05-22 | 2023-10-13 | 福州大学 | Composite aircraft and control method thereof |
| CN113788139A (en) * | 2021-10-26 | 2021-12-14 | 上海磐拓航空科技服务有限公司 | Method for accurately controlling aircraft track through multifunctional pneumatic control surface |
| CN113788139B (en) * | 2021-10-26 | 2024-05-24 | 上海磐拓航空科技服务有限公司 | Method for precisely controlling track of aircraft by using multifunctional pneumatic control surface |
| CN115071967A (en) * | 2022-07-14 | 2022-09-20 | 西南交通大学 | Vertical take-off and landing aircraft |
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Application publication date: 20171003 |