CN205971839U - Many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane - Google Patents
Many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane Download PDFInfo
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- CN205971839U CN205971839U CN201620981891.8U CN201620981891U CN205971839U CN 205971839 U CN205971839 U CN 205971839U CN 201620981891 U CN201620981891 U CN 201620981891U CN 205971839 U CN205971839 U CN 205971839U
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Abstract
The utility model relates to a many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane, the airborne vehicle stationary vane, does is the rear side of stationary vane leading edge equipped with and expand including inflexible stationary vane leading edge return the wing gasbag of the action of contracting, the wing gasbag formation that the inflation was opened and the gasbag machine wing part of stationary vane leading edge joint. The utility model provides an in the airborne vehicle stationary vane, including setting up in the wing gasbag of the rear side of stationary vane leading edge, the inflation can be aerifyd to this wing gasbag, also can exhaust back and contract, forms gasbag machine wing part and combine with the stationary vane leading edge when wing air bag inflation opens, improves the airfoil area of whole stationary vane, improves the power appearance of whole stationary vane. In the time of on using many gyroplane of vertical lift with it, can make the wing gasbag be in retraction state in the lift stage, reduce stationary vane lateral force area, effectively reduce the influence of latasuture to many gyroplane of vertical lift.
Description
Technical field
This utility model is related to a kind of airborne vehicle fixed-wing and the many gyroplanes using fixed-wing and fixed wing airplane.
Background technology
Airborne vehicle includes the gyroplane of the sliding fixed wing airplane running lifting of level and vertical lifting, comes for fixed wing airplane
Say, change its aerodynamic characteristics by changing aircraft configuration.The general mode changing profile include arranging wing flap, the secondary side of a ship wing,
Elevator, rudder etc., the part that these modes are related to is all generally to be made by rigid material, needs hydraulic actuating mechanism etc.
The mechanism controls of type change, and overall structure and control are all complex, involve great expense.Gyroplane includes helicopter and many rotors
Machine, wherein, many gyroplanes refer to the airborne vehicle with the rotary shaft of the parallel arrangement of two or more, and many gyroplanes can be by changing
The flight characteristics to change gyroplane for the method for operation of change rotor.
The advantage of fixed wing airplane is that level speed is fast, and shortcoming is higher for landing-strip requirement；And gyroplane
Advantage be vertical lifting, relatively low to the Platform Requirements that rise and fall, defect is that level speed is slower, high energy consumption.In conjunction with two
Person's advantage, overcomes both shortcomings, develops tiltrotor, such as " osprey " V22 tiltrotor of the U.S., tiltrotor
Rotorshaft can be rotated between vertical and horizontal, thus realizing the requirement of vertical lifting and horizontal flight.But it is this
The overall structure of tiltrotor is complex, and flight control is extremely difficult, and fault rate is higher.
A kind of multi-rotor aerocraft with fixed-wing is there is also, such as application publication number is in prior art
VTOL craft disclosed in the Chinese invention patent application of CN105283384A, it includes two rotor crafts and four
Rotor craft, two rotor crafts include the port and starboard wing, and each side of a ship wing has rotor, rotor by swash plate connection respectively
By rotor motor-driven rotation, the port and starboard wing herein is equivalent to fixed-wing, the center of rotation axis of rotor and the wing of fixed-wing
Chord line is parallel, controls two rotor crafts in vertical lifting by controlling the rotating speed of two rotors and the incline direction of swash plate
Conversion and horizontal flight between, quadrotor then includes two larboard wings and two starboard wings, on each side of a ship wing respectively
Being rotated by swash plate has a rotor, and four side of a ship wings are symmetrically arranged, by controlling the rotating speed of four rotors and rotating tiltedly
The incline direction of plate controls conversion between vertical lifting and horizontal flight for the aircraft.Similar, such as application publication number is
High speed many rotors vertical lifting aircraft disclosed in the Chinese invention patent application of CN105620735A, it is likewise supplied with multiple
Fixed-wing, is respectively equipped with rotor on each fixed-wing, and the chordwise of each fixed-wing is parallel to each other, the rotary middle spindle of each rotor
Line is also parallel to each other with the chordwise of each fixed-wing, equally can realize aircraft vertical by controlling the rotating speed of each rotor
Conversion between lifting and horizontal flight.
In the above-mentioned multi-rotor aerocraft with fixed-wing, chordwise in actual lifting process for the fixed-wing is vertical,
Make fixed-wing lateral force area larger, whole rotor craft is during vertical lifting because fixed-wing crosswind affects relatively
Greatly, control more difficult, or even aviation accident can be caused, more dangerous.
Utility model content
The purpose of this utility model is to provide a kind of airborne vehicle fixed-wing, many with fixed-wing in prior art to solve
Rotor craft vertical fixed-wing during vertical lifting leads to aircraft to be affected larger technical problem by crosswind；Meanwhile,
This utility model also provides a kind of many gyroplanes using above-mentioned fixed-wing and fixed wing airplane.
For achieving the above object, the technical scheme of airborne vehicle fixed-wing provided by the utility model is：Airborne vehicle is fixed
The wing, including the fixing nose of wing of rigidity, the rear side of fixation nose of wing is provided with and can carry out expanding-wing the air bag of retracting action, swollen
The swollen wing air bag opened forms the air bag wing section engaging with fixing nose of wing.
Described wing air bag includes the utricule being made up of elastomeric material.
Described wing air bag expands along the spanwise of fixed-wing or chordwise, retraction.
The rear side of described fixing nose of wing is installed with for guiding wing air bag along the spanwise of fixed-wing or wing chord side
To carrying out the guide structure that expands, bounce back.
Described wing air bag is collapsible air bag, and collapsible air bag includes the support being alternately arranged successively and accordingly connecting even
Socket part and flexible fold.
Described wing air bag is disposed with least two in the spanwise or chordwise of fixed-wing.
Described wing air bag is provided with the retraction resetting means for driving described wing air bag retraction, and this retraction resets and fills
Put including the elastical retraction outer wrapping structure being wrapped in outside wing air bag and/or extend along the expansion-retraction direction of wing air bag
Back-moving spring, elastical retraction outer wrapping structure includes elastic network(s) or elastica.
Described fixing nose of wing is arc wall construction or hollow tubular structure.
Airborne vehicle fixed-wing includes the connecting portion for being fixedly connected with aircraft fuselage, and described connecting portion is installed with use
The fixed-wing trailing edge of the rigidity engaging in the tailing edge with described air bag wing section, described fixing nose of wing can be to fixed-wing trailing edge
What direction swung is assemblied on described connecting portion, so that airborne vehicle fixed-wing forms variable angle of sweep wing.
It is provided between described fixing nose of wing and fixed-wing trailing edge for applying to hinder fixing nose of wing to fixing nose of wing
The swing resistance structure of the active force swinging towards fixed-wing trailing edge, this swing resistance structure is to be arranged in fixing nose of wing and consolidate
Determine compressive resistance spring and/or the hydraulic actuating mechanism between wing trailing edge.
The technical scheme of many gyroplanes of vertical lifting provided by the utility model is：Many rotors of vertical lifting fly
Machine, including fuselage and the side board wing being arranged at the fuselage left and right sides, two side board wings is respectively equipped with least one rotor, side board
The center of rotation axis of the chordwise of the wing and described rotor is arranged parallel, and using fixing wing structure, this fixes the described side board wing
Wing structure is airborne vehicle fixed-wing, and including the fixing nose of wing of rigidity, the rear side of fixing nose of wing is provided with and can carry out expanding-bouncing back
The wing air bag of action, is expanded the wing air bag opened and forms the air bag wing section being engaged with fixing nose of wing.
It is respectively equipped with vertical tail, the vertical cloth of plane that this vertical tail, is located with the described side board wing on described two side board wings
Put, the rotor being respectively arranged at two ends with described in of each vertical tail,.
Rotor on described two side board wings is both sides rotor, and described fuselage is provided with two middle part vertical tail,s, in the middle part of in the of two
The plane that vertical tail, is arranged symmetrically with regard to fuselage and is located perpendicular to the described side board wing, during vertical tail, in the middle part of each is respectively equipped with
Portion's rotor.
On described fuselage, empennage is provided with by connecting rod, empennage is provided with tailplane, vertical tail, rudder and lifting
Rudder.
Being arranged on rotor on the described side board wing is main rotor, and many gyroplanes also include the secondary side of a ship wing, this secondary side of a ship wing along
The direction perpendicular with the plane that the described side board wing is located parallel arranged for interval with the described side board wing, the described pair side of a ship wing adopts described
Fixing wing structure, described pair the side of a ship wing and two side board wings between support be provided with vertical tail, described pair the side of a ship wing be provided with described
The secondary rotor of the parallel arrangement of the central axis of rotation of main rotor.
Being arranged on rotor on the described side board wing is main rotor, and many gyroplanes also include the secondary side of a ship wing, this secondary side of a ship wing along
The perpendicular direction of plane being located with the described side board wing parallel arranged for interval with the described port and starboard wing, the described pair side of a ship wing and described
Support between fuselage and be provided with vertical tail, parallel with the central axis of rotation of described main rotor in being respectively arranged at two ends with of vertical tail,
The secondary rotor of arrangement.
The technical scheme of the fixed wing airplane of horizontal lifting provided by the utility model is：The fixed-wing of horizontal lifting flies
Machine, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side the horizontal side board wing, and it is equal that described level surveys the side of a ship wing
Using fixing wing structure, this fixing wing structure is airborne vehicle fixed-wing, including the fixing nose of wing of rigidity, after fixing nose of wing
Side is provided with and can carry out expanding-wing the air bag of retracting action, expands the wing air bag opened and is formed and engages with fixation nose of wing
Air bag wing section.
The fixed wing airplane of horizontal lifting, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side water
The flat side board wing, the outside of two horizontal side board wings is respectively equipped with fixing wing structure, and fixing wing structure passes through the horizontal side board wing and institute
State fuselage to connect, this fixing wing structure is airborne vehicle fixed-wing, including the fixing nose of wing of rigidity, the rear side of fixing nose of wing sets
Have and can carry out expanding-wing the air bag of retracting action, expand the wing air bag opened and form the air bag engaging with fixation nose of wing
Wing section.
The fixed wing airplane of horizontal lifting, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side water
The flat side board wing, the front side towards fuselage head of two horizontal side board wings is respectively equipped with fixing wing structure, fixes wing structure and institute
State fuselage to connect, this fixing wing structure is airborne vehicle fixed-wing, including the fixing nose of wing of rigidity, the rear side of fixing nose of wing sets
Have and can carry out expanding-wing the air bag of retracting action, expand the wing air bag opened and form the air bag engaging with fixation nose of wing
Wing section.
The beneficial effects of the utility model are：In airborne vehicle fixed-wing provided by the utility model, solid including being arranged at
Determine the wing air bag of the rear side of nose of wing, this wing air bag can be with inflation it is also possible to aerofluxuss bounce back, when wing airbag inflation
Form air bag wing section when opening to be combined with fixing nose of wing, improve the aerofoil area of whole fixed-wing, improve and entirely fix
The power profile of the wing.When on the many gyroplanes applying it to vertical lifting, can make wing air bag in the lifting stage
It is in retracted state, reduce fixed-wing lateral force area, effectively reduce the impact of many gyroplanes to vertical lifting for the latasuture.
Further, the utricule of wing air bag is made up of elastomeric material, so can be by controlling aeration quantity come control machine
The degrees of expansion of wing air bag, can effective control and the power profile adjusting fixed-wing.
Further, wing air bag expands, bounces back along the spanwise of fixed-wing or chordwise, is easy to design, system
Make, reduces cost.
Further, fixing the fixed guide structure of rear side of nose of wing to guide wing air bag along the span side of fixed-wing
To or chordwise carry out expanding, bounce back, be easy to control wing air bag expansion retraction direction, the power of effective specification fixed-wing
The adjustment of profile.
Further, wing air bag is provided with two or more, is on the one hand easy to design and produce, and on the other hand can control to certain
One or certain several wing air bag supply, thus adjusting the aerodynamic characteristics of fixed-wing, and, this multiple wing air bags are only
Vertical design can also avoid having influence on the normal work of other wing air bags when certain aerating gasbag breaks down.
Further, the retraction resetting means for driving described wing air bag retraction is provided with wing air bag, so
The degrees of expansion of wing air bag can preferably be controlled, improve the stability of wing air bag.
Further, because fixing nose of wing can be assemblied on described connecting portion to what fixed-wing trailing edge direction swung, and
And, the air bag wing section that wing air bag is formed is engaged with fixing nose of wing, so can be by changing in wing air bag
Gas pressure, controls the degrees of expansion of wing air bag, because air bag wing section is engaged, so, wing gas with fixed-wing trailing edge
The retraction of capsule will drive fixing nose of wing to swing to fixed-wing trailing edge direction, and then makes airborne vehicle fixed-wing form variable sweepback
Angle wing, and sweepback angle can by adjust wing air bag in pressure be adjusted.
Further, between fixing nose of wing and fixed-wing trailing edge, setting swings resistance structure, with to fixing nose of wing
Apply the active force hindering fixing nose of wing to swing towards fixed-wing trailing edge, the swing of fixing nose of wing so can be kept steady
Fixed, keep the pressure stability of wing air bag.
Brief description
Fig. 1 is the structural representation of the embodiment 1 of airborne vehicle fixed-wing provided by the utility model；
Fig. 2 is the structural representation of the embodiment 2 of airborne vehicle fixed-wing provided by the utility model；
Fig. 3 is the structural representation of the embodiment 3 of airborne vehicle fixed-wing provided by the utility model；
Fig. 4 is the structural representation of the embodiment 4 of airborne vehicle fixed-wing provided by the utility model；
Fig. 5 is the structural representation of the embodiment 5 of airborne vehicle fixed-wing provided by the utility model；
Fig. 6 is the structural representation of the embodiment 6 of airborne vehicle fixed-wing provided by the utility model；
Fig. 7 is the structural representation of the embodiment 7 of airborne vehicle fixed-wing provided by the utility model；
Fig. 8 is the structural representation of the embodiment 1 of many gyroplanes of vertical lifting provided by the utility model；
Fig. 9 is the structural representation of the embodiment 2 of many gyroplanes of vertical lifting provided by the utility model；
Figure 10 is the structural representation of the embodiment 3 of many gyroplanes of vertical lifting provided by the utility model；
Figure 11 is the structural representation of the embodiment 4 of many gyroplanes of vertical lifting provided by the utility model；
Figure 12 is the structural representation of the embodiment 5 of many gyroplanes of vertical lifting provided by the utility model；
Figure 13 is the structural representation of the embodiment 1 of the fixed wing airplane of horizontal lifting provided by the utility model；
Figure 14 is the structural representation of the embodiment 2 of the fixed wing airplane of horizontal lifting provided by the utility model；
Figure 15 is the structural representation of the embodiment 3 of the fixed wing airplane of horizontal lifting provided by the utility model；.
Specific embodiment
Below in conjunction with the accompanying drawings embodiment of the present utility model is described further.
Many rotors of airborne vehicle fixed-wing provided by the utility model, the fixed wing airplane of horizontal lifting and vertical lifting
The specific embodiment of aircraft, particular content is as follows：
Airborne vehicle fixed-wing embodiment 1：
Fig. 1（a）Represent that wing air bag 11 is in the folded state of retraction, Fig. 1（b）Represent that wing air bag 11 is in expansion and beats
Open state, Fig. 1（c）Represent that wing air bag 11 is in full open position.
As shown in figure 1, the airborne vehicle fixed-wing in this embodiment includes rigid fixing nose of wing 12, fixing nose of wing 12
Rear side be provided with and can carry out-wing the air bag 11 of retracting action, wing air bag is arranged in the air bag being arranged on fixing nose of wing
In installing rack, this air bag installing rack can be wholely set or split fixing assembling with fixing nose of wing, expand the wing opened
Air bag 11 forms the air bag wing section engaging with fixing nose of wing, and this wing air bag 11 is collapsible air bag, and it passes through to beat
Open-fold to realize the expansion-retraction of wing air bag, this collapsible air bag include being alternately arranged successively and accordingly connect
Support connecting portion 14 and flexible fold 15, support connecting portion 14 non-telescoping, and flexible fold 15 are scalable.
It should be noted that wing air bag 11 in the present embodiment is opened, is folded along the chordwise of fixed-wing.And,
Retraction resetting means for driving described wing air bag retraction is provided with wing air bag 11, this retraction resetting means includes edge
The back-moving spring 13 that the expansion of wing air bag-retraction direction extends, back-moving spring 13 herein can be traditional spring, also may be used
Think the flexible pull wire with larger elastic modelling quantity.
In the present embodiment, fixing nose of wing 12 is arc wall construction, and, fixing nose of wing 12 is by rigid material system
Become it is ensured that the in-flight strength and stiffness of fixed-wing, generally select light-weight high-strength material.
In the present embodiment, wing air bag 11 is disposed with one, and in other embodiments, wing air bag can also be provided with two
More than individual, each wing air bag is separate.By the cooperation adjustment of the blowing pressure of multiple independent air bags, thus it is possible to vary fixing
The profile of the wing, lift efficiency.And, when indivedual wing air bags do not work, the normal use of other air bags can't be affected.
In the present embodiment, retraction resetting means includes the back-moving spring 13 that the expansion-retraction direction along wing air bag extends,
In other embodiments, retraction resetting means may also be employed being wrapped in the elastical retraction outer wrapping structure outside wing air bag, should
Elastical retraction outer wrapping can be elastic network(s) or elastica.
Airborne vehicle fixed-wing embodiment 2：
It is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 1：As shown in Fig. 2 airborne vehicle fixed-wing is implemented
In example 2, wing air bag is disposed with two along fixed-wing spanwise, respectively inner side air bag 21 and outside air bag 22, two machines
The separate distribution of wing air bag, each wing air bag all by guide direction along fixed-wing chordwise guide frame 20 along solid
Fixed thriving chord line carries out expanding-retracting action.When being embodied as, can arrange on wing air bag slip ring 23 or bearing with
The corresponding assembling of guide frame, to ensure wing air bag along the normal slip of guide frame guide direction.
And, in the present embodiment, inner side air bag 21 and outside air bag 22 all include a utricule being made up of elastomeric material,
By being filled with the gas of different pressures in utricule, the degrees of expansion of utricule can be controlled.As shown in Figure 2 a, interior outside air bag
Degrees of expansion is identical, and shown in Fig. 2 b, inner side air bag 21 is different with the degrees of expansion of outside air bag 22, and then can make fixed-wing
Obtain different aerodynamic characteristics parameters.
Guide frame 20 in the present embodiment be along fixed-wing chordwise extend rail plate, air bag pass through slip ring or
The attachment structures such as bearing are connected with rail plate.The guide direction of wing airbag aeration tailing edge rail plate expands.Inflation
When, be equivalent to increase wing area, reduce aspect ratio, and then change fixed-wing aerodynamic characteristics.
In the present embodiment, wing air bag is provided with two along fixed-wing spanwise, in other embodiments, wing air bag
More than three can be arranged.
Airborne vehicle fixed-wing embodiment 3：
It is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 2：As shown in figure 3, airborne vehicle fixed-wing is implemented
In example 3, two independent wing air bags along fixed-wing spanwise arrangement all carry out expanding-bouncing back along fixed-wing spanwise
Action, in fact, the guide frame of respective guide wing airbag inflation-retraction is provided with fixing nose of wing, guide frame
Guide direction is fixed-wing spanwise.
In the present embodiment, include inner side air bag 31 and outside air bag 32 herein, two air bags along fixed-wing spanwise distribution,
And expand-retraction along fixed-wing spanwise, each wing air bag all includes a utricule being made up of elastomeric material, by
It is filled with the gas of different pressures in utricule, the degrees of expansion of utricule can be controlled.As Fig. 3（a）In outside air bag 32 expansion
Degree and 3（b）In outside air bag 32 degrees of expansion different, and then airborne vehicle fixed-wing can be made to obtain different air move
Force characteristic parameter.
Guide frame in the present embodiment is the rail plate extending along fixed-wing spanwise, two machines being arranged in juxtaposition
Wing air bag, the guide direction of wing airbag aeration tailing edge rail plate expands.During inflation, be equivalent to increase wing area,
Expand aspect ratio, and then change the aerodynamic characteristics of fixed-wing.
In the present embodiment, wing air bag is provided with two along fixed-wing spanwise, in other embodiments, wing air bag
More than three can be arranged.
In above-described embodiment 2 and embodiment 3, wing air bag has all been sequentially arranged multiple, at it along fixed-wing spanwise
In his embodiment, wing air bag can also be sequentially arranged two or more along fixed-wing chordwise.
Airborne vehicle fixed-wing embodiment 4：
As shown in figure 4, it is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 1：In embodiment 4, airborne vehicle
The fixing nose of wing 40 of fixed-wing adopts the hollow tubular structure of flat, the air bag wing section that wing air bag 41 is formed after expanding
Engage with fixing nose of wing 40.
Airborne vehicle fixed-wing embodiment 5：
As shown in figure 5, it is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 1：In embodiment 5, airborne vehicle
Fixing nose of wing 50 in fixed-wing is using circular hollow tubular structure, the air bag wing portion being formed after wing air bag 51 expansion
Divide and engage with fixing nose of wing 50.
Fixing nose of wing in embodiment 4 and embodiment 5 is equally made up of rigid material.And, consolidating in two embodiments
Determine nose of wing and be hollow tubular, so can enter walking line or stringing in the cavities, make full use of space.
Airborne vehicle fixed-wing embodiment 6：
It is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 1：Airborne vehicle fixed-wing include for aviation
The connecting portion 62 that device fuselage is fixedly connected, connecting portion 62 herein has the width extending along fixed-wing chordwise, connecting portion
It is installed with rigid fixed-wing trailing edge 61, this fixed-wing trailing edge 61 and the air bag wing being formed by the wing air bag 64 expanding on 62
Partial tailing edge engages, and fixing nose of wing 65 can be assemblied on connecting portion 62 to what fixed-wing trailing edge 61 direction swung, so that
Airborne vehicle fixed-wing forms variable angle of sweep wing, specifically can be by hinge page structure 63 and connecting portion 62 hinge mounted.
In the present embodiment, wing air bag 64 expands-retraction along fixed-wing chordwise.And, in fixing nose of wing 65 He
It is provided with the work for applying to hinder fixing nose of wing to swing towards fixed-wing trailing edge to fixing nose of wing between fixed-wing trailing edge 61
Swing resistance structure firmly, this swing resistance structure is the compressive resistance bullet being arranged between fixing nose of wing and fixed-wing trailing edge
Spring 66 and hydraulic actuating mechanism, hydraulic actuating mechanism herein can be used for keeping the position of fixing nose of wing and fixed-wing trailing edge
Put, so fixed-wing can be maintained the sweepback angular position of setting.
In fact, adaptive mode may also be employed being adjusted controlling, because in aircraft flight, fixed-wing is total
Be affected by gas pressure, now can suitably adjust the degrees of expansion of fixed-wing adapting to pressure that fixed-wing is born so that
Wing air bag is in steady statue.
When specifically used, such as Fig. 6（a）Shown, when wing air bag 64 is inflated and expanded completely, fixed-wing is in integrally tetragon
Structure, and as Fig. 6（b）, when the degrees of expansion of adjustment wing air bag, during wing air bag retraction, fixing nose of wing 65 swing backward
Form swept-back triangle, fixed-wing is integrally triangular in shape.
Compressive resistance spring 66 herein improves the stability of wing air bag 64, and can will be swung to using hydraulic actuating mechanism
The fixing nose of wing 65 of position is positioned, and keeps the angle between fixing nose of wing 65 and fixed-wing trailing edge 61.
Airborne vehicle fixed-wing embodiment 7：
It is essentially consisted in the difference of airborne vehicle fixed-wing embodiment 6：On airborne vehicle fixed-wing for aviation
The connecting portion that device fuselage is fixedly connected is connecting block structure 71, such as Fig. 7（a）Shown, when wing air bag 71 expands completely, fixing
The wing integrally structure triangular in shape, and as Fig. 7（b）Shown, when wing air bag 71 bounces back, fixed-wing is in integrally flat.
On airborne vehicle fixed-wing in embodiment 6 and embodiment 7, fixing nose of wing can be arranged on connection by articulated structure
In portion, so can control the pendulum angle of fixing nose of wing by controlling the degrees of expansion of wing air bag, and then control is fixed
The angle of sweep size of the wing.
In above-mentioned 6 airborne vehicle fixed-wings, the gas in wing air bag can be filled with lighter-than-air gas, can improve
Buoyancy.
One kind is to select nitrogen.Carry nitrogen with compression or liquid nitrogen bottle.When gasbag pressure needs to improve, air bag is carried out
Inflation；When needing to reduce, by regulating valve venting of exitting.Advantage is that nitrogen is relatively cheap, safety；Shortcoming be density of nitrogen only than
Air is lower slightly, and the buoyancy of generation is too small.According to gas tank mode, can directly to airbag aeration it is not necessary to setting compressor pump.
One kind is to select helium.Carry helium with compression or liquid helium bottle.When gasbag pressure needs to improve, air bag is carried out
Inflation；When needing to reduce, by regulating valve venting of exitting.If arranging the balloonet filling air as using dirigible, structure meeting
Become complicated.Advantage is helium safety；Helium density is little, produces buoyancy big.Shortcoming is that use cost is high.
One kind is to select hydrogen, carries hydrogen with compression or liquid hydrogen bottle.When gasbag pressure needs to improve, air bag is carried out
Inflation；When needing to reduce, by regulating valve venting of exitting.When using hydrogen-oxygen fuel cell, hydrogen drains into fuel cell.Select
, mainly there is safety problem in the difficulty of hydrogen.
Many rotary wing aircraft embodiment 1 of vertical lifting：
As shown in figure 8, many gyroplanes of vertical lifting include fuselage 83 and the side board wing being arranged at the fuselage left and right sides
81, two side board wings 81 are respectively equipped with a vertical tail, 82, the plane that this vertical tail, 82 is located with the side board wing 81 is arranged vertically,
And, each vertical tail, 82 be respectively arranged at two ends with rotor 85, rotor 85 is driven by rotor motor 86, the center of rotation of rotor 85
The chordwise of axis and the side board wing 81 is arranged parallel.
It should be noted that two side board wings 81 herein are all using fixing wing structure, and this fixation wing structure can adopt
Any one fixing wing structure in above-mentioned 6 embodiments of airborne vehicle fixed-wing, each side board wing all includes fixing nose of wing
811st, fixed-wing trailing edge 812 and be arranged in wing air bag 813 between fixing nose of wing 811 and fixed-wing trailing edge 812, so may be used
Control the area of the side board wing with the degrees of expansion by controlling wing air bag, reduce crosswind to many gyroplanes of vertical lifting
Impact, the structure of airborne vehicle fixed-wing to be described in above-mentioned airborne vehicle fixed-wing embodiment, no longer do and excessively go to live in the household of one's in-laws on getting married by here
State.
As many gyroplanes of vertical lifting, it is respectively arranged below with undercarriage 84 in each vertical tail,.
In fact, in the present embodiment, two side board wings 81, two vertical tail,s 82 and fuselage 83 have been monolithically fabricated H type structure, this
The control mode planting H type four gyroplane refers to existing quadrotor, application publication number is CN105283384A's
VTOL craft disclosed in Chinese utility model patent application and application publication number are the China of CN105620735A
The control mode of the high speed many rotors vertical lifting aircraft disclosed in utility application, by controlling turning of four rotors
Speed and direction, control the switching between the vertical lift of many gyroplanes and the horizontal flight in the present embodiment and other flights
The control of attitude.
In the present embodiment, a vertical tail, is respectively equipped with each side board wing, in other embodiments it is also possible to every
Two vertical tail,s are respectively provided with the individual side board wing.
Many rotary wing aircraft embodiment 2 of vertical lifting：
As shown in figure 9, it is essentially consisted in the difference of many rotary wing aircraft embodiment 1：Many rotors in embodiment 2 fly
On machine, the side board wing 91 of fuselage 92 both sides is directly installed with rotor 93 respectively, this rotor 93 is both sides rotor, both sides rotor
Center of rotation axis identical with the chordwise of the side board wing, and, fuselage 92 is provided with two middle part vertical tail,s 94, in two
The plane that portion's vertical tail, 94 is arranged symmetrically with regard to fuselage and is located perpendicular to the described side board wing, vertical tail, in the middle part of each sets respectively
There is middle part rotor 95.
Many gyroplanes in the present embodiment equally adopt four rotor forms, two side board wings, fuselage and two vertical tail,s
Cross-shaped configuration is integrally formed.
As a kind of preferred version, the power of the middle part rotor 95 at vertical tail, two ends can be less than both sides rotor 93.Many
Gyroplane is put down when flying, and the middle part rotor on vertical tail, can disable, so as to blade is along vertical tail, direction, to subtract during deactivation
Little air drag.
Vertical tail, herein is preferably by light high-intensity rigid material.Fuselage is longitudinally arranged in fixed-wing central authorities, its
Fuselage longitudinal direction vertical section is in wing shape.
Many rotary wing aircraft embodiment 3 of vertical lifting：
As shown in Figure 10, it is essentially consisted in the difference of many rotary wing aircraft embodiment 1：Many rotors in embodiment 3
On aircraft, the side board wing 102 of fuselage 101 both sides is respectively equipped with a rotor 103, fuselage 101 is along the span side of the side board wing 102
To being arranged in central authorities, the longitudinal vertical section of fuselage 101 is in wing shape.
For strengthening the control ability to aircraft, in fuselage 101 afterbody, empennage is provided with by connecting rod 105, empennage is provided with
Tailplane 106, vertical tail 108, rudder 109 and elevator 107.
Undercarriage 104 is arranged on below the side board wing 102, or can also be arranged at fuselage bottom.
In the present embodiment, it is respectively provided with a horizontal side board wing in the left and right sides of fuselage, in other embodiments, also can be
The both sides of fuselage are respectively provided with two horizontal side board wings being arranged in parallel, and pass through vertical links etc. between two side board wings of the same side
Structure connects to form bi-wing configuration.
Many rotary wing aircraft embodiment 4 of vertical lifting：
As shown in figure 11, it is with the something in common of many rotary wing aircraft embodiment 3：Set respectively in the both sides of fuselage 111
There is the side board wing 112, and, main rotor 110 is respectively equipped with the side board wing 112, difference essentially consists in：In the present embodiment,
On fuselage 111 and be not provided with empennage, but the secondary side of a ship wing 115 is had by vertical tail, 116 fixing assembling, this secondary side of a ship wing 115 along with
The perpendicular direction of plane and the parallel arranged for interval of the side board wing, the secondary side of a ship wing 115 and two side board wings 115 that the side board wing 112 is located
Between respectively support be provided with vertical tail, 116, this vertical tail, 116 preferably by light high-intensity rigid material, in the secondary side of a ship wing
The secondary rotor 114 of the 115 parallel arrangements of central axis of rotation being provided with the main rotor being provided with the described side board wing.
The secondary side of a ship wing herein is not joined directly together with fuselage, and it can be using in above-mentioned 6 airborne vehicle fixed-wing embodiments
Wing structure fixed by any one airborne vehicle, and concrete structure will not be described here.
When many gyroplanes are changed to horizontal flight, the secondary side of a ship wing herein is positioned at the top of the side board wing.Certainly, real at other
Apply in example, the secondary side of a ship wing also can be made to be located at the lower section of the side board wing.
The spanwise length of the secondary side of a ship wing 115 be equal to or less than two side board wings 112 spanwise length and fuselage 111 width it
With.
In the present embodiment, two side board wings 112,111, two vertical tail,s 116 of fuselage and the secondary side of a ship wing 115 constitute well on the whole
Font structure.Undercarriage 113 is set below two vertical tail,s 116.
Many rotary wing aircraft embodiment 5 of vertical lifting：
As shown in figure 12, its compared with many rotary wing aircraft embodiment 4 of vertical lifting, something in common is：In fuselage 123
Be respectively provided on two sides with the side board wing 121, and, main rotor 122 is respectively equipped with the side board wing 121, essentially consists in place of difference：
The secondary side of a ship wing 127 is connected with fuselage 123 by vertical tail, 126, and one end of vertical tail, 126 is connected directly between on fuselage 123, and,
The length of the secondary side of a ship wing 127 is less than the spanwise length of two side board wings, and herein, the secondary side of a ship wing 127 spanwise length is shorter, and it is general
Fixed-wing, be configured without wing air bag, be respectively arranged at two ends with secondary rotor 125 in the secondary side of a ship wing 127.
It should be noted that when this many gyroplanes are changed to horizontal flight, the length less pair side of a ship wing 127 is located at machine
Side with it, the secondary rotor power on the secondary side of a ship wing is less, when many gyroplanes are changed to horizontal flight, lower-powered pair rotor
125 can disable, and during deactivation, its blade is arranged along the spanwise of the secondary side of a ship wing, so can reduce windage.
The side board wing in many gyroplanes of above-mentioned vertical lifting is respectively adopted above-mentioned airborne vehicle fixed-wing, so, makees
The side board wing for fixed-wing has wing air bag, and this wing air bag can form air bag wing section in inflation, revolves when more
During wing aircraft vertical lifting, controllable wing air bag deflation retraction, it is to avoid crosswind is to many gyroplanes of vertical lifting
Impact, and after many gyroplanes liter gets up, controllable wing airbag aeration expands to form air bag wing section, expands and fixes
The lifting surface area of the wing, is effectively improved the performance during horizontal flight of many gyroplanes.
The vertical lifting of many gyroplanes of above-mentioned several vertical lifting, horizontal flight, the flight attitude such as spiral, turn
Control, switching all can be using the control mode in the vertical translation aircraft with fixed-wing of the prior art.
The fixed wing airplane embodiment 1 of horizontal lifting：
The structure of above-mentioned airborne vehicle fixed-wing is also applicable on the fixed wing airplane of traditional horizontal lifting, as Figure 13 institute
Show, this fixed wing airplane adopts two rotor forms, and using yi word pattern structure, fuselage 134 afterbody of aircraft is provided with empennage 131,
Fuselage is respectively arranged on the left side and the right side the horizontal side board wing 132, and two horizontal side board wings 132 are respectively equipped with a rotor 133, level
The center of rotation axis of the chordwise of the side board wing 132 and described rotor 133 is arranged parallel.And, fuselage is wheeled using 3 points
Undercarriage, is respectively arranged below with undercarriage 135, so that fixed wing airplane is in phase in fuselage 134 and two horizontal side board wings 132
On the runway answered, sliding race lifts.The empennage 131 of fuselage includes vertical tail and rudder, tailplane and elevator.
All using fixing wing structure, this fixing wing structure can adopt above-mentioned airborne vehicle to two horizontal side board wings 132 herein
The structure of fixed-wing, the structure here of airborne vehicle fixed-wing no longer excessively repeats.
In the takeoff and landing stage, for increasing the lift of aircraft, generally the wing air bag in airborne vehicle fixed-wing is filled
Full gas.Fill in the case of being lighter than air gas, provide buoyancy for aircraft.Fly the stage flat, for reducing air drag, generally drop
The pressure of low wing air bag, reduces area and the volume of fixed-wing, and then reduces lift and the buoyancy of aircraft.
Be respectively equipped with rotor to provide thrust on the horizontal side board wing in the present embodiment, in other embodiments it is also possible to
Jet engine is arranged on fuselage to provide thrust, at this point it is possible to save rotor.
The fixed wing airplane embodiment 2 of horizontal lifting：
As shown in figure 14, the fixed wing airplane of the horizontal lifting in this embodiment, including fuselage 144, fuselage 144 afterbody sets
There is empennage 146, fuselage 144 is respectively arranged on the left side and the right side the horizontal side board wing 145, the horizontal side board wing 145 is and rigidly fixes the wing, two
One rotor, the chordwise of the horizontal side board wing 145 and the center of rotation of described rotor are respectively equipped with the individual horizontal side board wing 145
Axis is arranged parallel, and the outside of two horizontal side board wings 145 is respectively equipped with fixing wing structure, and fixing wing structure passes through horizontal side board
The wing 145 is connected with fuselage, fixing wing structure herein can using the fixing wing structure in above-mentioned airborne vehicle fixed-wing embodiment 6,
Include fixing nose of wing 142, fixed-wing trailing edge and wing air bag 141 respectively, fixing wing structure passes through connecting portion 143 and horizontal side
The side of a ship wing 145 is linked and packed, and fixing wing structure can be found in the fixing wing structure in above-mentioned airborne vehicle fixed-wing embodiment 6, and here is not
After repeating more.
This kind of mode is relatively specific for the relatively low Fixed Wing AirVehicle of cruising speed.
In fact, the fixing wing structure outside two horizontal side board wings herein may also be employed other airborne vehicle fixed-wings in fact
Apply the structure of example, as long as can be installed on the side board wing of fuselage both sides, can be by controlling filling of wing air bag
Gas degrees of expansion obtains different power profiles.
As Figure 14（a）Shown, wing air bag 141 is in full state, and as Figure 14（b）Shown, wing air bag 141 is in
Venting retracted state, can get visibly different wing power profile.
Be respectively equipped with rotor to provide thrust on the horizontal side board wing in the present embodiment, in other embodiments it is also possible to
Jet engine is arranged on fuselage to provide thrust, at this point it is possible to save rotor.
The fixed wing airplane embodiment 3 of horizontal lifting：
As shown in figure 15, the fixed wing airplane of the horizontal lifting in this embodiment, including fuselage 154, fuselage 154 tail
Portion is provided with empennage, and fuselage 154 is respectively arranged on the left side and the right side the horizontal side board wing 155, and the horizontal side board wing 155 is and rigidly fixes the wing,
The front side towards fuselage head of two side board wings 155 is respectively equipped with fixing wing structure, fixing wing structure directly with described fuselage
Connect, fixing wing structure includes fixing nose of wing 152, fixed-wing trailing edge and wing air bag 151 respectively, fixing wing structure passes through even
Socket part 153 is linked and packed with the horizontal side board wing 155, and fixing wing structure can be found in consolidating in above-mentioned airborne vehicle fixed-wing embodiment 7
Determine wing structure, here no longer excessively repeats.
And, connecting portion 153 represents that fixing nose of wing can swing to adjust after wing towards after horizontal side board flapwise
Sweep angle degree.
It should be noted that work as that the fixed-wing in above-mentioned airborne vehicle embodiment 7 embodiment is applied consolidating in the present embodiment
When determining on wing aircraft, by the fixed-wing trailing edge of two airborne vehicle fixed-wings and side board nose of wing fixing assembling or can be wholely set.
As Figure 15（a）Shown, wing air bag 151 is in full state, and as Figure 15（b）Shown, wing air bag 151 is in
Venting retracted state, can get visibly different power profile.
This kind of mode is relatively specific for the higher Fixed Wing AirVehicle of cruising speed.
In fact, the fixing wing structure of two side board wings front portions herein may also be employed other airborne vehicle fixed-wing embodiments
Structure, as long as fuselage both sides can be installed in, can by control wing air bag inflation degree obtain
Different power profiles.
It should be noted that jet engine can be arranged on fuselage to provide thrust.
In above-mentioned 3 fixed wing airplane embodiments, mainly make use of the degree of inflation of control wing air bag whole to adjust
The formal parameter of the both sides wing of fuselage, and then can effectively adjust the flight parameter of whole fixed wing airplane.
Claims (19)
1. airborne vehicle fixed-wing it is characterised in that：Including the fixing nose of wing of rigidity, the rear side of fixing nose of wing is provided with and can carry out
The wing air bag of expansion-retracting action, is expanded the wing air bag opened and forms the air bag wing section being engaged with fixing nose of wing.
2. airborne vehicle fixed-wing according to claim 1 it is characterised in that：Described wing air bag is included by elastomeric material system
The utricule becoming.
3. airborne vehicle fixed-wing according to claim 1 it is characterised in that：Described wing air bag is along the span side of fixed-wing
To or chordwise expand, retraction.
4. airborne vehicle fixed-wing according to claim 3 it is characterised in that：The rear side of described fixing nose of wing is installed with use
Carry out the guide structure expanding, bouncing back in guiding wing air bag along the spanwise of fixed-wing or chordwise.
5. airborne vehicle fixed-wing according to claim 3 it is characterised in that：Described wing air bag is collapsible air bag, folding
Stacked air bag includes support connecting portion and the flexible fold being alternately arranged successively and accordingly connecting.
6. airborne vehicle fixed-wing according to claim 1 it is characterised in that：Described wing air bag is in the span side of fixed-wing
To or chordwise on be disposed with least two.
7. airborne vehicle fixed-wing as claimed in any of claims 1 to 6 it is characterised in that：On described wing air bag
It is provided with the retraction resetting means for driving described wing air bag retraction, this retraction resetting means includes being wrapped in outside wing air bag
The elastical retraction outer wrapping structure in portion and/or the back-moving spring of the expansion-retraction direction extension along wing air bag, outside elastical retraction
Package structure includes elastic network(s) or elastica.
8. airborne vehicle fixed-wing as claimed in any of claims 1 to 6 it is characterised in that：Described fixing nose of wing
For arc wall construction or hollow tubular structure.
9. airborne vehicle fixed-wing as claimed in any of claims 1 to 6 it is characterised in that：Airborne vehicle fixed-wing bag
Include the connecting portion for being fixedly connected with aircraft fuselage, described connecting portion is installed with for described air bag wing section
The fixed-wing trailing edge of the rigidity that tailing edge engages, described fixing nose of wing can be assemblied in described company to what fixed-wing trailing edge direction swung
In socket part, so that airborne vehicle fixed-wing forms variable angle of sweep wing.
10. airborne vehicle fixed-wing according to claim 9 it is characterised in that：Described fixing nose of wing and fixed-wing trailing edge
Between be provided with the swing of the active force for applying to hinder fixing nose of wing to swing towards fixed-wing trailing edge to fixing nose of wing and hinder
Power structure, this swing resistance structure is the compressive resistance spring and/or hydraulic pressure being arranged between fixing nose of wing and fixed-wing trailing edge
Actuator.
Many gyroplanes of 11. vertical liftings, including fuselage and the side board wing being arranged at the fuselage left and right sides, on two side board wings
It is respectively equipped with least one rotor, the center of rotation axis of the chordwise of the side board wing and described rotor is arranged parallel, its feature
It is：, using fixing wing structure, this fixing wing structure is using as described in any one in claim 1 to 10 for the described side board wing
Airborne vehicle fixed-wing.
Many gyroplanes of 12. vertical liftings according to claim 11 it is characterised in that：Divide on described two side board wings
Be not provided with vertical tail, the plane that this vertical tail, is located with the described side board wing is arranged vertically, each vertical tail, be respectively arranged at two ends with one
Individual described rotor.
Many gyroplanes of 13. vertical liftings according to claim 11 it is characterised in that：On described two side board wings
Rotor is both sides rotor, and described fuselage is provided with two middle part vertical tail,s, and two middle part vertical tail,s are arranged symmetrically with regard to fuselage and hang down
The straight plane being located in the described side board wing, vertical tail, in the middle part of each is respectively equipped with middle part rotor.
Many gyroplanes of 14. vertical liftings according to claim 11 it is characterised in that：Pass through on described fuselage to connect
Bar is provided with empennage, and empennage is provided with tailplane, vertical tail, rudder and elevator.
Many gyroplanes of 15. vertical liftings according to claim 11 it is characterised in that：It is arranged on the described side board wing
Rotor be main rotor, many gyroplanes also include the secondary side of a ship wing, and this secondary side of a ship wing is vertical along the plane phase being located with the described side board wing
The straight direction parallel arranged for interval with the described side board wing, the described pair side of a ship wing adopts described fixing wing structure, the described pair side of a ship wing with
Support between two side board wings and be provided with vertical tail, the described pair side of a ship wing is provided with the parallel cloth with the central axis of rotation of described main rotor
The secondary rotor put.
Many gyroplanes of 16. vertical liftings according to claim 11 it is characterised in that：It is arranged on the described side board wing
Rotor be main rotor, many gyroplanes also include the secondary side of a ship wing, and this secondary side of a ship wing is vertical along the plane phase being located with the described side board wing
Straight direction parallel arranged for interval with the described port and starboard wing, supports between the described pair side of a ship wing and described fuselage and is provided with vertical tail,
The secondary rotor being respectively arranged at two ends with the parallel arrangement of the central axis of rotation of described main rotor in vertical tail,.
The fixed wing airplane of 17. horizontal liftings, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side water
The flat side board wing it is characterised in that：Described level surveys the side of a ship wing all using fixing wing structure, and this fixing wing structure is using as claim
Airborne vehicle fixed-wing described in any one in 1 to 10.
The fixed wing airplane of 18. horizontal liftings, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side water
The flat side board wing it is characterised in that：The outside of two horizontal side board wings is respectively equipped with fixing wing structure, and fixing wing structure passes through level
The side board wing is connected with described fuselage, and described fixing wing structure is using the airborne vehicle as described in any one in claim 1 to 10
Fixed-wing.
The fixed wing airplane of 19. horizontal liftings, including fuselage, afterbody is provided with empennage, and fuselage is respectively arranged on the left side and the right side water
The flat side board wing it is characterised in that：The front side towards fuselage head of two horizontal side board wings is respectively equipped with fixing wing structure, fixing
Wing structure is connected with described fuselage, and described fixing wing structure is using the airborne vehicle as described in any one in claim 1 to 10
Fixed-wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620981891.8U CN205971839U (en) | 2016-08-30 | 2016-08-30 | Many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620981891.8U CN205971839U (en) | 2016-08-30 | 2016-08-30 | Many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205971839U true CN205971839U (en) | 2017-02-22 |
Family
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620981891.8U Expired - Fee Related CN205971839U (en) | 2016-08-30 | 2016-08-30 | Many gyroplane and fixed -wing aircraft of airborne vehicle stationary vane and use stationary vane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081099A (en) * | 2016-08-30 | 2016-11-09 | 苏跃进 | Airborne vehicle fixed-wing and use many gyroplanes and the fixed wing airplane of this fixed-wing |
| WO2019119556A1 (en) * | 2017-12-20 | 2019-06-27 | 上海交通大学 | Fixed-wing sea-air amphibious aircraft and control method |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
-
2016
- 2016-08-30 CN CN201620981891.8U patent/CN205971839U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081099A (en) * | 2016-08-30 | 2016-11-09 | 苏跃进 | Airborne vehicle fixed-wing and use many gyroplanes and the fixed wing airplane of this fixed-wing |
| CN106081099B (en) * | 2016-08-30 | 2019-05-03 | 苏跃进 | More gyroplanes of vertical lifting and the fixed wing aircraft of horizontal lifting |
| WO2019119556A1 (en) * | 2017-12-20 | 2019-06-27 | 上海交通大学 | Fixed-wing sea-air amphibious aircraft and control method |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
| CN113022846B (en) * | 2021-05-27 | 2021-08-03 | 北京航空航天大学 | Mixed mode aircraft |
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Granted publication date: 20170222 Termination date: 20200830 |