CN209366454U - A kind of culvert type aircraft - Google Patents
A kind of culvert type aircraft Download PDFInfo
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- CN209366454U CN209366454U CN201822129755.8U CN201822129755U CN209366454U CN 209366454 U CN209366454 U CN 209366454U CN 201822129755 U CN201822129755 U CN 201822129755U CN 209366454 U CN209366454 U CN 209366454U
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- culvert type
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- wing
- culvert
- mould group
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Abstract
The utility model discloses a kind of culvert type aircraft comprising fuselage, wing and the culvert type lift mould group that the fuselage two sides are arranged in provide the propeller of forward propulsion when further including rotation；Each culvert type lift mould group includes at least one ducted fan, and the pivot center of the ducted fan is fixedly installed relative to the fuselage.Since aircraft provided by the utility model has propeller and for providing the duct of lift, it tilts without ducted fan to generate forward component, that is, the duct lift mould group that the application is fixed on vehicle body two sides does not need to vert to cooperate and move ahead, the energy consumption of ducted fan is effectively reduced, to extend the flight time.In addition, due to eliminating duct inclining rotary mechanism, and do not need that movable rudder face is arranged on wing or empennage, accordingly reduce rudder face servo-actuating device, enormously simplify the structure of culvert type aircraft, while reducing the weight of culvert type aircraft.
Description
Technical field
The utility model relates to air material technical field, more specifically to a kind of culvert type aircraft.
Background technique
With the development of science and technology, the application field of culvert type aircraft becomes more and more extensive, it can be used for taking photo by plane, survey
The every field such as draw, transport.
Currently, being typically provided with tilting type duct, tilting type during aircraft flight in the structure of culvert type aircraft
Duct can turn to erected state, to provide propulsive force to aircraft.When above-mentioned tilting type duct turns to erected state with
Propeller function is identical, but also needs the driving mechanism of setting driving tilting type duct rotation and the control mode of driving mechanism,
So causes the structure of aircraft more complicated and increase the weight of aircraft.
Utility model content
In view of this, the purpose of this utility model is to provide a kind of culvert type aircraft, the knot of the culvert type aircraft
Structure design can effectively simplify structure.
In order to reach above-mentioned first purpose, the utility model is provided the following technical solutions:
A kind of culvert type aircraft, including fuselage, wing and the culvert type lift mould group that the fuselage two sides are arranged in, also
Including providing the propeller of forward propulsion when rotation；
Each culvert type lift mould group includes at least one ducted fan, and the pivot center of the ducted fan is opposite
It is fixedly installed in the fuselage.
Preferably, in above-mentioned culvert type aircraft, the propeller includes shaft and the blade that is arranged in the shaft,
The front end of culvert type aircraft shaft when being placed on level ground is towards heading；
The blade root of the blade is connect with the shaft, and the blade can be rotated relative to the shaft so that the paddle
Axis of the blade tip of leaf close to or far from the shaft.
It preferably, further include vertical tail and the water that is fixedly connected with the vertical tail in above-mentioned culvert type aircraft
The horizontal tail wing；
The propeller is arranged on the tailplane.
Preferably, in above-mentioned culvert type aircraft, the fuselage two sides are respectively arranged at least one set of culvert type liter
Power mould group, the multiple groups culvert type lift mould group ipsilateral positioned at the fuselage are successively arranged from front to back.
Preferably, in above-mentioned culvert type aircraft, the wing includes along the symmetrically arranged two points of wings of the fuselage, institute
Stating point wing includes the telescopic segment that multistage is capable of successively intussusception；
It further include driving device, the driving device can drive the stretching, extension of telescopic segment described in multistage or intussusception so that described point
The wing elongates or shortens.
Preferably, in above-mentioned culvert type aircraft, telescopic segment described in multistage covers poststack, described to divide the wing farthest away from the fuselage
Edge be located at the culvert type lift mould group farthest away from the edge of the fuselage close fuselage side.
Preferably, in above-mentioned culvert type aircraft, the driving device includes:
Expansion bracket, the expansion bracket include the multiple X-type bars arranged along its telescopic direction, and X-type bar includes arranged in a crossed manner
And the first connecting rod and second connecting rod being hinged, the end of two adjacent X-type bars is hinged, the end of the expansion bracket with most
The telescopic segment in outside is fixedly connected；
Driving assembly, for driving the first connecting rod end of same X-type bar to be located remotely from each other with second connecting rod end or close.
Preferably, in above-mentioned culvert type aircraft, the driving component includes:
Lead screw motor and the screw rod being fixedly connected with the output end of the lead screw motor；
With the sliding block of wire rod thread cooperation, end and the sliding block positioned at the first connecting rod of the expansion bracket head end
Relatively fixed and second connecting rod end and the fuselage are relatively fixed.
It preferably, further include the frame that the fuselage interior is set, the lead screw motor in above-mentioned culvert type aircraft
It is each attached on the frame with the end for the second connecting rod for being located at the expansion bracket head end, the screw rod and the frame member
Connection；
Sliding slot is also provided on the frame, the sliding block can be slided along the sliding slot.
It preferably, further include Power Component, clutch and wheel undercarriage, the clutch in above-mentioned culvert type aircraft
Device is for switching the Power Component to culvert type lift mould group transmitting power or the Power Component to described wheeled
Fall frame transmitting power.
When using culvert type aircraft provided by the above embodiment, when culvert type aircraft needs to rise, duct is utilized
The ducted fan of formula lift mould group provides lift, forward using propeller offer when culvert type aircraft needs to move forward
Propulsive force.Since aircraft provided by the utility model has propeller and for providing the duct of lift, is not necessarily to ducted fan
Inclination is to generate forward component, that is to say, that the duct lift mould group that the application is fixed on vehicle body two sides do not need to vert with
Cooperation moves ahead, and the energy consumption of ducted fan is effectively reduced, to extend the flight time.In addition, verting due to eliminating duct
Mechanism, and do not need that movable rudder face is arranged on wing or empennage, accordingly reduce rudder face servo-actuating device, greatly simplifies
The structure of culvert type aircraft, while reducing the weight of culvert type aircraft.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the structural representation of contraction state
Figure；
Fig. 2 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the main view of contraction state；
Fig. 3 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the side view of contraction state；
Fig. 4 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the top view of contraction state；
Fig. 5 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the structural representation of extended state
Figure；
Fig. 6 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the top view of extended state；
The structure that the wing for the culvert type aircraft that Fig. 7 provides for another embodiment of the utility model is in contraction state is shown
It is intended to；
Fig. 8 is that the wing for the culvert type aircraft that another embodiment of the utility model provides is in the vertical view of contraction state
Figure；
Fig. 9 is that the wing for the culvert type aircraft that another embodiment of the utility model provides is in the vertical view of extended state
Figure；
Figure 10 is that the wing for the culvert type aircraft that another embodiment of the utility model provides is in the structure of extended state
Schematic diagram；
Figure 11 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the structural representation of extended state
Figure；
Figure 12 is that the wing of culvert type aircraft provided by the embodiment of the utility model is in the structural representation of contraction state
Figure；
Figure 13 is the structural schematic diagram of driving device provided by the embodiment of the utility model.
In Fig. 1-13:
1- culvert type lift mould group, 1a- ducted fan, 2- fuselage, 3- propeller, 4- vertical tail, 5- tailplane, 6-
Wheel undercarriage, 7- divide the wing, 7a- telescopic segment, 8- front wing, 9- expansion bracket, 10- lead screw motor, 11- frame, 11a- sliding slot, 12-
Screw rod, 13- sliding block.
Specific embodiment
The purpose of this utility model is to provide a kind of culvert type aircraft, the structure design of the culvert type aircraft can be with
Effectively simplify structure.
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Fig. 1-Figure 13 is please referred to, culvert type aircraft provided by the utility model includes fuselage 2, wing, culvert type lift
Mould group 1 and propeller 3.Wherein, culvert type lift mould group 1 is arranged in 2 two sides of fuselage, and 2 two sides of fuselage are provided with culvert type liter
Power mould group 1, and the culvert type lift mould group 1 of 2 two sides of fuselage is symmetrical arranged.Propeller 3 can fly when rotating to the culvert type
Row device provides forward propulsive force, i.e., when the culvert type aircraft is mobile, the blade rotation of propeller 3, so that culvert type flies
Device moves forward.
Each culvert type lift mould group 1 includes at least one ducted fan 1a, and ducted fan 1a can give the culvert when rotating
Road formula aircraft provides upward lift, so that the culvert type aircraft rises.Wherein, the duct circle of ducted fan 1a relative to
Fuselage 2 is fixedly installed, i.e., the pivot center of all ducted fan 1a flabellums of culvert type lift mould group 1 is solid both with respect to fuselage 2
It is fixed to be arranged and vert relative to fuselage 2.
When using culvert type aircraft provided by the above embodiment, when culvert type aircraft needs to rise, duct is utilized
The ducted fan 1a of formula lift mould group 1 provides lift, when culvert type aircraft needs to move forward using propeller 3 provide to
Preceding propulsive force.Since aircraft provided by the utility model has propeller 3 and for providing the duct of lift, is not necessarily to duct
Fan 1a is tilted to generate forward component, that is to say, that the duct lift mould group that the application is fixed on vehicle body two sides does not need
It verts to cooperate and move ahead, the energy consumption of ducted fan is effectively reduced, to extend the flight time.In addition, containing due to eliminating
Road inclining rotary mechanism, and do not need that movable rudder face is arranged on wing or empennage, accordingly reduce rudder face servo-actuating device, greatly
The structure of culvert type aircraft is simplified greatly, while reducing the weight of culvert type aircraft.
As shown in Figure 1 and Figure 5, in one embodiment, propeller 3 includes shaft and blade, wherein the quantity of blade
To be multiple, multiple blades are arranged in shaft and are uniformly distributed along the circumferential direction of shaft.The culvert type aircraft is placed in horizontally
The front end of shaft is towards heading when on face, i.e., the culvert type aircraft is in horizontal plane walking or horizontal flight, shaft
Front end towards heading, shaft can be horizontal or has small angle between horizontal plane at this time.
Forward propulsive force is provided to the culvert type aircraft when shaft drives axis rotation of multiple blades around shaft.
The blade root of blade is connect with shaft, and the blade tip of blade is stretched out to the direction far from shaft.Blade can relative to shaft rotate with
Make the blade tip of blade close to or far from the axis of shaft, and then realizes the gathering or expansion of propeller 3.
As shown in Figure 1, making the blade tip of multiple blades be close to the axis of shaft, finally when blade is rotated relative to shaft
Realize the gathering of propeller 3.As shown in figure 5, making the blade tip of multiple blades far from shaft when blade is rotated relative to shaft
Axis, the final expansion for realizing propeller 3.So set, when not needing the offer propulsive force of propeller 3, it can be by propeller 3
It collapses, in case propeller 3 increases windage.
Specifically, can be hinged by articulated shaft between the blade tip and shaft of blade, the axis of articulated shaft and the axis of shaft
Line is arranged in a mutually vertical manner.In order to realize the expansion and gathering of blade, torque spring can be set, when needing to hover in the sky or
When landing, control shaft stops operating, and blade collapses under the action of torque spring；When needing flight forward, shaft is controlled
Rotation, blade are unfolded under the influence of centrifugal force.
Drive the blade motor that rotates relative to shaft of blade alternatively, can also be arranged, with realize propeller 3 gathering or
Expansion.It can be realized and be driven by gear mechanism between blade motor and blade, is not limited thereto.
As shown in Figure 1, the culvert type aircraft further includes vertical tail 4 and tailplane 5, the lower end of vertical tail 4 with
Fuselage 2 is fixedly connected, and the upper end of vertical tail 4 is fixedly connected with tailplane 5, and it is stable that the side of vertical tail 4 forms course
Face.
Propeller 3 can be set on tailplane 5.Specifically, in the installation of the front side of tailplane 5 setting protrusion
Seat, propeller 3 are directly installed in above-mentioned mounting base, and 3 shaft of propeller and above-mentioned mounting base are rotatablely connected.In this way,
The mounting base of the front side setting protrusion of tailplane 5, provides to propeller 3 and collapses space, when propeller 3 collapses, blade
It collapses to and is bonded with the outer wall of mounting base, it is therefore prevented that the gathering of the influence propeller 3 of tailplane 5.It should be noted that the duct
Formula aircraft interior needs to be arranged propeller motor to drive the shaft of propeller 3 to rotate.
As shown in Figure 1 and Figure 7,2 two sides of fuselage are respectively arranged at least one set of culvert type lift mould group 1.That is a left side for fuselage 2
Side and right side are provided at least one set of culvert type lift mould group 1.Also, it is located at the ipsilateral multiple groups culvert type lift mould of fuselage 2
Group 1 is successively arranged from front to back.If the left and right side of fuselage 2 is respectively provided with multiple groups culvert type lift mould group 1,2 left side of fuselage
Multiple groups culvert type lift mould group 1 is successively arranged from front to back, the multiple groups culvert type lift mould group 1 on the right side of fuselage 2 from front to back according to
Secondary arrangement.Above-mentioned front side to the direction of rear side referred to from front to back by culvert type aircraft.The culvert type lift in 2 left side of fuselage
The culvert type lift mould group 1 on 2 right side of mould group 1 and fuselage is symmetrical arranged.
Specifically, the two sides of fuselage 2 are respectively set there are two culvert type lift mould group 1, i.e. the left and right side of fuselage 2 is divided
It She Zhi not be there are two culvert type lift mould group 1.Preferably, in two culvert type lift mould groups 1 in 2 left side of fuselage, a duct
Formula lift mould group 1 is located at the front side of wing and another culvert type lift mould group 1 is located at the rear side of wing.Similarly, fuselage 2 is right
In two culvert type lift mould groups 1 of side, a culvert type lift mould group 1 is located at front side and another culvert type lift of wing
Mould group 1 is located at the rear side of wing.
As shown in Figure 6 and Figure 7, each culvert type lift mould group 1 may include four ducted fan 1a, four ducted fans
1a is divided to two rows two column to be uniformly distributed.Alternatively, each culvert type lift mould group 1 can also only include a ducted fan 1a.Certainly,
The quantity for the ducted fan 1a that each culvert type lift mould group 1 includes can also be two or more, not make herein specific
It limits.
As is illustrated by figs. 11 and 12, wing includes along the symmetrically arranged two points of wings 7 of fuselage 2, and dividing the wing 7 to include multistage can
Successively intussusception telescopic segment 7a.Two points of wings 7 are separately positioned on the left and right side of fuselage 2, and two points of wings 7 are in the two sides of fuselage 2
It is symmetrical arranged.
Each dividing the wing 7 includes the telescopic segment 7a that multistage is capable of successively intussusception, as shown in figure 11, when dividing the multiple flexible of the wing 7
Section 7a successively arranges expansion, this time-division wing 7 is in extended state, divides that the length of the wing 7 is longer and area is larger, which flies
When the flying speed of device is higher, stretching, extension divides the wing 7 that can generate biggish aerodynamic lift, to mitigate culvert type lift mould group 1
Load.As shown in figure 12, after Multi-section telescopic section 7a is nested together, divide the length of the wing 7 shorter, avoid point wing 7 and increase wind
Resistance.
Each the wing 7 is divided to may include three sections of telescopic segment 7a, naturally it is also possible to including other quantity such as four sections, two sections, herein
It is not construed as limiting.
Above-mentioned Multi-section telescopic section 7a can successively intussusception, refer in two sections of adjacent telescopic segment 7a, positioned at the flexible of outside
Section 7a can be contracted to the inside of the telescopic segment 7a positioned inside.Wherein the distance of the telescopic segment 7a away from fuselage 2 in outside is greater than interior
The telescopic segment 7a of side is away from the distance of fuselage 2.In other words, in same point of 7 structure of the wing, the telescopic segment 7a in outside is located at lateral expansion section
The side away from fuselage of 7a.
As shown in Fig. 9-Figure 10, in two sections of adjacent telescopic segment 7a, positioned at the outer wall of lateral expansion section 7a and positioned inside
Be provided on one in the inner wall of telescopic segment 7a sliding slot and another on be provided with sliding rail, sliding rail is in sliding fit with the sliding chute.When
When the wing 7 being divided to carry out expansion or intussusception, sliding rail is slided along sliding slot to play guiding role.
It should be noted that being limited when dividing the wing 7 to be unfolded or set is stacked to appropriate length, to prevent point wing from stretching
Contracting is shaken on direction.Specifically, elastic slice can be set in sliding rail and sliding slot, and elastic slice divides the surface of the wing to push up remaining
It leans on, the perturbed force that air-flow generates when the damping force that elastic slice generates can resist flight makes a point span open or cover and is stacked to appropriate length
When telescopic segment will not shake, guarantee flight stability.
It is unfolded it is of course also possible to only all be reduced to innermost telescopic segment 7a and whole telescopic segment 7a to remaining telescopic segment 7a
The case where limited, be so only divided to the wing to be expanded to and longest and be contracted to most short two kinds of working conditions.Above-mentioned culvert type flight
Device further includes driving device, above-mentioned driving device can drive Multi-section telescopic section 7a stretch or intussusception so that divide the wing 7 elongation or
Shorten.I.e. driving device can drive outermost telescopic segment 7a to move closer to fuselage 2, so that Multi-section telescopic section 7a successively covers
It is folded, until telescopic segment 7a all in addition to innermost telescopic segment 7a is respectively positioned on inside innermost telescopic segment 7a, divided with realizing
The complete contraction (as shown in figure 12) of the wing 7.Driving device can drive outermost telescopic segment 7a to be gradually distance from fuselage 2, so that
Multi-section telescopic section 7a is successively unfolded, the expansion until all telescopic segment 7a successively arrange, and divides being fully extended for the wing 7 to realize
(as shown in figure 11).
Above-mentioned outermost telescopic segment 7a refers to that farthest apart from fuselage 2 telescopic segment 7a, innermost telescopic segment 7a refer to
The telescopic segment 7a nearest apart from fuselage 2.
The outer dimension for dividing the wing 7 to influence culvert type aircraft in order to prevent divides the wing 7 most when Multi-section telescopic section 7a set poststack
The edge of separate fuselage 2 is located at the side of close fuselage 2 of the culvert type lift mould group 1 farthest away from the edge of fuselage 2.I.e. multistage is stretched
When contracting section 7a is in fully collapsed condition, divide distance of the wing 7 farthest away from the edge of fuselage 2 far from 2 center line of fuselage no more than duct
Formula lift mould group 1 is farthest away from the edge of fuselage 2 far from the distance of 2 center line of fuselage.So set, working as Multi-section telescopic section 7a intussusception
Afterwards, it ensure that point wing 7 will not protrude culvert type lift mould group 1 farthest away from the edge of fuselage 2 farthest away from the edge of fuselage 2, divide the wing 7
Width can be similar to the width dimensions of culvert type lift mould group 1, it is relatively regular outer to ensure that the culvert type aircraft has
Shape size, and meet the current requirement in road surface.
Wing integrally can be generally oval for trapezoidal or wing in the present embodiment.Along by the side far from fuselage 2
To the width and thickness of wing is gradually reduced.Width of wing refers to extension of the wing along head to tail direction at this
Distance, the thickness of wing refer to wing along the extended distance of 2 short transverse of fuselage.So for single telescopic segment 7a,
Its inside is higher and wide, and outside is shorter and narrow, when between adjacent two telescopic segment 7a set poststack, the end of two telescopic segment 7a
Gap is certainly existed, which will increase the induced drag of wing.
Optionally, in order to which the induced drag for reducing wing acts on, each divide in 7 structure of the wing, remove innermost telescopic segment 7a
Outside, end plate is provided on the end outer wall of the separate fuselage 2 of remaining telescopic segment 7a.The end plate can be perpendicular to telescopic segment 7a's
Outer surface setting or end plate can also be slightly slanted setting relative to the outer surface of telescopic segment 7a.End plate and telescopic segment 7a can
To be an integral structure or end plate can be fixedly connected by screw etc. with telescopic segment 7a.When Multi-section telescopic section 7a successively covers
In two layers adjacent of telescopic segment 7a, two layers adjacent of telescopic segment 7a can be blocked positioned at the end plate of the telescopic segment 7a of internal layer for poststack
Between gap.
In addition, in order to avoid when Multi-section telescopic section 7a is successively unfolded resistance it is excessive, in two adjacent telescopic segment 7a, outside
The size of the inner end of telescopic segment 7a is less than the outer end of lateral expansion section 7a, and after adjacent two telescopic segment 7a expansion, two are stretched
Gap is certainly existed between the end of contracting section 7a, which also will increase the induced drag of wing.At this, the inner end of telescopic segment 7a
Refer to it close to the side of fuselage 2, the outer end of telescopic segment 7a refers to its side far from fuselage 2.
Optionally, in above-described embodiment, each divide in 7 structure of the wing, in addition to outermost telescopic segment 7a, remaining telescopic segment 7a
Separate fuselage 2 inner wall of end on be provided with baffle.I.e. in addition to outermost telescopic segment 7a, the outer end of remaining telescopic segment 7a
Baffle is respectively provided on inner wall.Baffle can be perpendicular to the setting of the inner wall of telescopic segment 7a or baffle or relative to telescopic segment
The inner wall of 7a is slightly slanted setting.Baffle can be an integral structure with telescopic segment 7a or baffle can by screw etc. with
Telescopic segment 7a is fixedly connected.After Multi-section telescopic section 7a is successively unfolded, in two adjacent telescopic segment 7a, the telescopic segment 7a of inside
Baffle can block the gap between two adjacent telescopic segment 7a, with reduce wing induced drag effect.
Optionally, can also each divide in 7 structure of the wing in above-described embodiment, in addition to innermost telescopic segment 7a, remaining is stretched
Baffle is provided on the end outer wall of the close fuselage 2 of contracting section 7a.Baffle can be arranged perpendicular to the outer wall of telescopic segment 7a, or
Person's baffle can also be slightly slanted setting relative to the inner wall of telescopic segment 7a.Baffle can be an integral structure with telescopic segment 7a,
Or baffle can be fixedly connected by screw etc. with telescopic segment 7a.After Multi-section telescopic section 7a is successively unfolded, adjacent two
In telescopic segment 7a, the baffle of the telescopic segment 7a in outside can block the gap between two adjacent telescopic segment 7a, to reduce machine
The induced drag of the wing acts on.
Above-mentioned end plate and baffle can also play the role of sealing and dustproof when wing is unfolded and wing is shunk.
As shown in figure 13, in another embodiment, driving device includes expansion bracket 9 and driving assembly.Wherein, it stretches
Frame 9 includes the multiple X-type bars arranged along its telescopic direction, and each X-type bar includes the first company that is arranged in a crossed manner and being hinged
Bar and second connecting rod.The end of two adjacent X-type bars is hinged, i.e., in two adjacent X-type bars, one is the first X-type bar, separately
One is the second X-type bar.Wherein the end of the first connecting rod of the first X-type bar and the end of the second connecting rod of the second X-type bar are hinged,
The end of the second connecting rod of first X-type bar and the end of the first connecting rod of the second X-type bar are hinged.
Also, the end of expansion bracket 9 is fixedly connected with outermost telescopic segment 7a, its own length when expansion bracket 9 stretches
It elongates or shortens, expansion bracket 9 drives outermost telescopic segment 7a to be gradually distance from fuselage 2 when extending, and final realize divides the complete of the wing 7
It trails.Expansion bracket 9 drives outermost telescopic segment 7a to move closer to fuselage 2 when shortening, final to realize the complete receipts for dividing the wing 7
Contracting.
Driving assembly is located remotely from each other or close for driving the first connecting rod end of same X-type bar with second connecting rod end.
When driving assembly drives the first connecting rod end of same X-type bar and second connecting rod end is located remotely from each other, the length of single X-type bar
Shorten, and then realizes that the length of entire expansion bracket 9 shortens.When driving assembly drives the first connecting rod end of same X-type bar and the
When two interlinking lever ends are close to each other, the length elongation of single X-type bar, and then realize the length elongation of entire expansion bracket 9.
Further, driving assembly includes lead screw motor 10, screw rod 12 and sliding block 13, the output end and silk of lead screw motor 10
Bar 12 is fixedly connected.Sliding block 13 is threadedly engaged with screw rod 12.The output end of lead screw motor 10 drives screw rod 12 to rotate, 12 phase of screw rod
Sliding block 13 is rotated, sliding block 13 can be driven to move along the length direction of screw rod 12.
Expansion bracket 9 is arranged along the telescopic direction of wing, and the head end of telescopic machine is it close to one end of fuselage 2.Positioned at stretching
The end of the first connecting rod of the X-type bar of 9 head end of contracting frame and sliding block 13 are relatively fixed, positioned at the second connecting rod of expansion bracket 9 head end
End and fuselage 2 are relatively fixed.When i.e. sliding block 13 is moved along the length direction of screw rod 12, drives and be located at 9 head end of expansion bracket
The end of first connecting rod is mobile, so as to it is located at the first connecting rod end of 9 head end of expansion bracket far from or close to second connecting rod end, it is more
A X-type bar successively links, final to realize the flexible of expansion bracket 9.
It is of course also possible to which two sliding blocks 13 are arranged, two sliding blocks 13 drive the first connecting rod positioned at 9 head end of expansion bracket respectively
End and second connecting rod end it is mobile simultaneously so that the two is relatively distant from or close, be not limited thereto.
In order to improve the stability of driving assembly, above-mentioned culvert type aircraft can also include being arranged in inside fuselage 2
The end of frame 11, lead screw motor 10 and the second connecting rod positioned at 9 head end of expansion bracket is each attached on frame 11, screw rod 12 and frame
Frame 11 is rotatablely connected.Screw rod 12 can be arranged on the frame 11 by bearing.Sliding slot 11a is also provided in said frame 11, it is sliding
Block 13 passes through sliding slot 11a, and one end of sliding block 13 is fixedly connected with the end for the first connecting rod for being located at 9 head end of expansion bracket, screw rod 12
When rotating relative to sliding block 13, sliding block 13 is slided along sliding slot 11a.Sliding slot 11a can be strip-shaped hole, and the length of sliding slot 11a
Direction is parallel with the length direction of screw rod 12.
It should be noted that the quantity of above-mentioned expansion bracket 9 is two, two expansion brackets 9 respectively drive the receipts of two points of wings 7
Contracting.The both ends of sliding block 13 are fixedly connected with the end of the first connecting rod of two 9 head ends of expansion bracket respectively, so realize a silk
Bar motor 10 drives two points of wings 7 flexible.Lead screw motor 10 can be servo motor, be not limited thereto.
Cylinder also can be set in driving assembly, and the telescopic end of cylinder drives the first of the X-type bar for being located at 9 head end of expansion bracket to connect
The end of bar and/or the end of second connecting rod are mobile, so that the two is relatively distant from or close, are not limited thereto.
In above-mentioned any one embodiment, which further includes Power Component, clutch and wheel undercarriage 6,
Clutch is dynamic to the transmitting of wheel undercarriage 6 to the transmitting power of culvert type lift mould group 1 or Power Component for switching Power Component
Power.Wheel undercarriage 6 may include two front-wheels and two rear-wheels, and two front-wheels can be set in culvert type aircraft front wing 8
On.
When culvert type aircraft is in mode motor, travelled as normal four-wheel automobile on road surface, this hour wheel
The front wheels and rear wheels of formula undercarriage 6 are in ground run.Clutch switches to Power Component and transmits power, tool to wheel undercarriage 6
Body Power Component is to rear wheel power.Two front-wheels can synchronize steering of the deflection control aircraft on ground, road surface row
Culvert type lift mould group 1 and propeller 3 under state is sailed not work.
When culvert type aircraft is in low-speed operations mode (speed is no more than 50 km/h), clutch switches to dynamic
Power component transmits power to culvert type lift mould group 1.The culvert type lift mould group 1 of 2 two sides of fuselage is started to work, ducted fan 1a
Rotation generates lift and drives that fuselage 2 is liftoff takes off, at this time can by control be located at the revolving speed of the ducted fan 1a of vehicle body two sides with
Control the flight attitude of vehicle.Power Component transmits power to propeller 3 simultaneously, and the rotation of propeller 3, which generates, pushes fuselage 2 forward
The propulsive force of flight.
When needing fair speed flight (speed is more than 50 km/h), clutch switches to Power Component to wheeled
It falls frame 6 and transmits power, specific Power Component is to rear wheel power.Lead screw motor 10 pushes machine by screw rod and expansion bracket 9
The span is opened, and wing has larger area after expansion, can produce biggish aerodynamic lift, reduces the load of duct lift mould group.This
When ducted fan 1a only need low-speed running, part lift and gesture stability torque are provided to culvert type aircraft, so as to effective
Energy consumption is reduced, the flight time is extended.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments can be realized professional and technical personnel in the field or using originally practical new
Type.Various modifications to these embodiments will be readily apparent to those skilled in the art, and determine herein
The General Principle of justice can be realized in other embodiments without departing from the spirit or scope of the present utility model.Cause
This, the present invention will not be limited to the embodiments shown herein, and is to fit to and principles disclosed herein
The widest scope consistent with features of novelty.
Claims (10)
1. a kind of culvert type aircraft, the culvert type lift mould including fuselage (2), wing and setting in the fuselage (2) two sides
Group (1), which is characterized in that the propeller (3) of forward propulsion is provided when further including rotation；
Each culvert type lift mould group (1) includes at least one ducted fan (1a), the rotation of the ducted fan (1a)
Axis is fixedly installed relative to the fuselage (2).
2. culvert type aircraft according to claim 1, which is characterized in that the propeller (3) includes shaft and setting
Blade in the shaft, the front end of culvert type aircraft shaft when being placed on level ground is towards heading；
The blade root of the blade is connect with the shaft, and the blade can be rotated relative to the shaft so that the blade
Axis of the blade tip close to or far from the shaft.
3. culvert type aircraft according to claim 1, which is characterized in that further include vertical tail (4) and hang down with described
The tailplane (5) that straight tail (4) is fixedly connected；
The propeller (3) is arranged on the tailplane (5).
4. culvert type aircraft according to claim 1, which is characterized in that fuselage (2) two sides be respectively arranged with to
Culvert type lift mould group (1) described in one group few is located at the fuselage (2) ipsilateral multiple groups culvert type lift mould group (1) You Qianzhi
It successively arranges afterwards.
5. culvert type aircraft described in any one of -4 according to claim 1, which is characterized in that the wing includes along described
The symmetrically arranged two points of wings (7) of fuselage (2) are described that the wing (7) is divided to include the telescopic segment (7a) that multistage is capable of successively intussusception；
It further include driving device, telescopic segment described in multistage (7a) can be driven to stretch for the driving device or intussusception is so that described point
The wing (7) elongate or shorten.
6. culvert type aircraft according to claim 5, which is characterized in that telescopic segment described in multistage (7a) covers poststack, institute
It states a point wing (7) and is located at the culvert type lift mould group (1) farthest away from the fuselage (2) farthest away from the edge of the fuselage (2)
The side of the close fuselage (2) at edge.
7. culvert type aircraft according to claim 5, which is characterized in that the driving device includes:
Expansion bracket (9), the expansion bracket (9) include the multiple X-type bars arranged along its telescopic direction, and X-type bar includes intersecting to set
The end of the first connecting rod and second connecting rod set and be hinged, two adjacent X-type bars is hinged, the end of the expansion bracket (9)
End is fixedly connected with outermost telescopic segment (7a)；
Driving assembly, for driving the first connecting rod end of same X-type bar to be located remotely from each other with second connecting rod end or close.
8. culvert type aircraft according to claim 7, which is characterized in that the driving component includes:
Lead screw motor (10) and the screw rod (12) being fixedly connected with the output end of the lead screw motor (10)；
The sliding block (13) being threadedly engaged with the screw rod (12) is located at the first connecting rod of the X-type bar of the expansion bracket (9) head end
Relatively fixed and second connecting rod end and the fuselage (2) are relatively fixed with the sliding block (13) for end.
9. culvert type aircraft according to claim 8, which is characterized in that further include that setting is internal in the fuselage (2)
Frame (11), the lead screw motor (10) and be located at the expansion bracket (9) head end X-type bar second connecting rod end it is solid
It is scheduled on the frame (11), the screw rod (12) and the frame (11) are rotatablely connected；
It is also provided with sliding slot (11a) on the frame (11), the sliding block (13) can be slided along the sliding slot (11a).
10. culvert type aircraft described in any one of -4 according to claim 1, which is characterized in that further include Power Component, from
Clutch and wheel undercarriage (6), the clutch are transmitted for switching the Power Component to the culvert type lift mould group (1)
Power or the Power Component give the wheel undercarriage (6) transmitting power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822129755.8U CN209366454U (en) | 2018-12-18 | 2018-12-18 | A kind of culvert type aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822129755.8U CN209366454U (en) | 2018-12-18 | 2018-12-18 | A kind of culvert type aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN209366454U true CN209366454U (en) | 2019-09-10 |
Family
ID=67831364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822129755.8U Active CN209366454U (en) | 2018-12-18 | 2018-12-18 | A kind of culvert type aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN209366454U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484634A (en) * | 2018-12-18 | 2019-03-19 | 酷黑科技（北京）有限公司 | A kind of culvert type aircraft |
| CN112722247A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Power take-up and pay-off device applied to vertical/short-distance take-off and landing aircraft |
| RU2777564C1 (en) * | 2021-06-01 | 2022-08-08 | Александр Викторович Атаманов | Method for vertical takeoff/landing and horizontal rectilinear flight of an aerial vehicle (av) and aerial vehicle (av) for implementation thereof |
| CN115476885A (en) * | 2022-09-27 | 2022-12-16 | 兰州交通大学 | High-speed train flank lift regulation and control device |
-
2018
- 2018-12-18 CN CN201822129755.8U patent/CN209366454U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484634A (en) * | 2018-12-18 | 2019-03-19 | 酷黑科技（北京）有限公司 | A kind of culvert type aircraft |
| CN112722247A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Power take-up and pay-off device applied to vertical/short-distance take-off and landing aircraft |
| CN112722247B (en) * | 2021-01-19 | 2022-09-06 | 西北工业大学 | Power take-up and pay-off device applied to vertical/short-distance take-off and landing aircraft |
| RU2777564C1 (en) * | 2021-06-01 | 2022-08-08 | Александр Викторович Атаманов | Method for vertical takeoff/landing and horizontal rectilinear flight of an aerial vehicle (av) and aerial vehicle (av) for implementation thereof |
| CN115476885A (en) * | 2022-09-27 | 2022-12-16 | 兰州交通大学 | High-speed train flank lift regulation and control device |
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