CN206914634U - 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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- CN206914634U CN206914634U CN201720801288.1U CN201720801288U CN206914634U CN 206914634 U CN206914634 U CN 206914634U CN 201720801288 U CN201720801288 U CN 201720801288U CN 206914634 U CN206914634 U CN 206914634U
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Abstract
It the utility model is related to a kind of compound rudder face on vertically taking off and landing flyer, including compound 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.The utility model has the advantages 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, simple in construction, and response is rapid.
Description
Technical field
It the utility model is related to a kind of compound rudder face of aircraft, and in particular to a kind of for answering on vertically taking off and landing flyer
Close rudder face.
Background technology
The development of tiltrotor starts from the forties in last century, takes 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 emerging.In order to
The longitudinal stability of tiltrotor is improved, while increases 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 uses 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 greatly increases, and 2 months 2012, Korea Aerospace Res Inst subscribed to the agreement with Korean air, determines common develop
" TR-6X " tiltrotor aircraft.This is in addition to the U.S., and 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 employs
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.Tiltrotor aircraft hangs in the air at present
Stopping time needs to adjust pitch or periodicity displacement, control rotor rotating speed etc. to change lift size, control system and complicated,
It is slow to respond.
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, its mainly solve the problems, such as be mechanically connect in the prior art composite material parts processing when produce
The problems such as raw part performance reduces, and frock is larger, and cost is higher, solves the problems, such as different from the utility model.
Utility model content
The purpose of this utility model is to solve the above problems, there is provided a kind of control system is simple and easy, simple in construction, response
Rapidly for the compound rudder face on vertically taking off and landing flyer.
To achieve the above object, the utility model 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 hovering when, 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 kind of optimal technical scheme of the present utility model, 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 mainly by five front wing, rear wing, fuselage, power set and undercarriage portions
It is grouped into.
The aircraft is mainly characterized in that：
(1) aircraft has the advantages 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 uses compound rudder face, and each compound rudder face separates from centre, is divided into two up and down
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 is perpendicular to aircraft longitudinal axis, by controlling compound rudder face
Folding angle changes air flow direction and flow velocity, so as to the lift of change of flight device, aircraft is hovered.
(4) during cruising flight, wing inclining rotary mechanism drives four wings and engine nacelle to rotate to engine nacelle and put down
Row turns into common fixed-wing configuration, energy consumption is relatively small, and has higher flying speed and larger flight half in aircraft longitudinal axis
Footpath.
The Attitude Control Strategies to hover 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, pitching/rolling moment is produced, so as to change posture；Controlled for driftage, by changing four
The deflection angle of compound rudder face, torsional moment is produced, drive 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 as to the lift of change of flight device.
During aircraft transition flight, first parallel to aircraft longitudinal axis, wing and engine nacelle vert machine engine nacelle
Structure drives wing and nacelle to rotate, while increases 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, controls posture.
When aircraft vertical landing process stage needs altitude dash/decline, compound rudder face opening and closing movement is driven to expire
When sufficient aircraft altitude dash/decline requires, now compound rudder face folding is coordinated to realize aircraft by adjusting revolution speed of propeller
Altitude dash/decline.
The beneficial effects of the utility model are：
The wing inclining rotary mechanism of wing wing root installation so that engine nacelle and wing can be around under inclining rotary mechanism driving
Tiliting axis verts, there is provided upward lift, gram aircraft self gravitation and air drag move 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 to advance is provided for aircraft；Controlled for driftage, by changing the deflection angle of four compound rudder faces,
Torsional moment is produced, drives vehicle yaw.Vertically taking off and landing flyer is compound on wing by adjusting in hovering
The angle of release amount of rudder face is realized, is put down compound rudder face when flying and is played common multiaspect function, and control system is simple and easy, simple in construction,
Response is rapid.
Brief description of the drawings
In order to illustrate more clearly of the utility model embodiment technical scheme, make required in being described below to embodiment
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only the utility model in order to more clearly
Illustrate the utility model embodiment or technical scheme of the prior art, below will be to needed for embodiment or description of the prior art
The accompanying drawing to be used is briefly described, and for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is compound rudder face partial structural diagram of the present utility model；
Fig. 2 is vertically taking off and landing flyer structural representation of the present utility model；
Fig. 3 is vertically taking off and landing flyer VTOL schematic diagram of the present utility model.
Embodiment
A kind of compound rudder face on vertically taking off and landing flyer as Figure 1-3, including compound rudder face body 10, institute
State compound rudder face body 10 and divide and be arranged on the end of wing 4, the machine for upper rudder face 1 and lower rudder face 2, the compound rudder face body 10
The side of the 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 rotate, 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 kind of optimal technical scheme of the present utility model, 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 mainly by front wing 5,6, rear wing 7,8, fuselage, power set and undercarriage
Five parts form.
The aircraft is mainly characterized in that：
(1) aircraft has the advantages 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 the rudder face of rear wing 7,8 use compound rudder face, each compound rudder face separates 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 is perpendicular to aircraft longitudinal axis, by controlling compound rudder face
Folding angle change air flow direction and flow velocity, so as to the lift of change of flight device, aircraft is hovered.
(4) during cruising flight, wing inclining rotary mechanism drives four wings and engine nacelle to rotate to engine nacelle and put down
Row turns into common fixed-wing configuration, energy consumption is relatively small, and has higher flying speed and larger flight half in aircraft longitudinal axis
Footpath.
The Attitude Control Strategies to hover 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, pitching/rolling moment is produced, so as to change posture；Controlled for driftage, by changing four
The deflection angle of compound rudder face, torsional moment is produced, drive 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 as to 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 increases 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, compound rudder face opening and closing movement is driven to expire
When sufficient aircraft altitude dash/decline requires, 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, the design that rear wing 7,8 is the straight wing.The wing root of wing 4 is installed
Have 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, hair
Motivation nacelle 9 starts engine, engine driving propeller 3 rotates, and front wing 5,6 provides lift T perpendicular to aircraft longitudinal axisf,
Rear wing 7,8 provides lift Tr, lift TfAnd TrAircraft self gravitation and air drag is overcome to move up and down.Aircraft climb arrives
During a certain certain height, wing inclining rotary mechanism driving wing 4 and engine nacelle 9 vert to nacelle parallel to aircraft longitudinal axis,
The wing 4 and nacelle rotor 9 provide the power to advance for aircraft.
The Attitude Control Strategies to hover under configuration：For bowing/facing upward, control of sideward roll, the rotating speed of propeller 3 on four wings is not
Become, realized by changing the folding angle of four compound rudder faces.Rudder face up and down 1,2 folding angle δ on rear wingkReduction/increase,
Generation bows/face upward torque.The folding angle δ of left side rudder face 1,2kIncrease, the folding angle δ of the compound rudder face in right sidekReduce, generation is turned over
Torque is rolled, so as to change posture；Controlled for driftage, by the deflection angle δ for changing four compound rudder facesp, produce twisting resistance
Square, drive 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 that flow 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, changes the aircraft
Lift.
During aircraft transition flight, engine nacelle 9 first verts parallel to aircraft longitudinal axis, front and rear wing 5,6,7,8
Wing 5,6,7,8 and engine nacelle 9 rotate before and after mechanism driving, while increase compound rudder face folding angle δk, 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), control 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 meet aircraft altitude dash/decline requirement, it is compound now to adjust the cooperation of the rotating speed of propeller 3
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, simple in construction, and response is rapid.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Within the spirit and principle of utility model, any modification, equivalent substitution and improvements made etc., the utility model should be included in
Protection domain within.
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 are 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
State engine nacelle (9) 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。
A kind of 2. 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) rotates, 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 exist
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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| CN201720801288.1U CN206914634U (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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107226207A (en) * | 2017-07-04 | 2017-10-03 | 西安君晖航空科技有限公司 | A kind of compound rudder face on vertically taking off and landing flyer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107226207A (en) * | 2017-07-04 | 2017-10-03 | 西安君晖航空科技有限公司 | A kind of compound rudder face on vertically taking off and landing flyer |
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