CN206374977U - Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system - Google Patents
Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system Download PDFInfo
- Publication number
- CN206374977U CN206374977U CN201621340569.3U CN201621340569U CN206374977U CN 206374977 U CN206374977 U CN 206374977U CN 201621340569 U CN201621340569 U CN 201621340569U CN 206374977 U CN206374977 U CN 206374977U
- Authority
- CN
- China
- Prior art keywords
- support arm
- connecting rod
- articulated section
- cantilever
- arm
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
- 230000008520 organization Effects 0.000 title claims abstract description 20
- 230000007246 mechanism Effects 0.000 claims description 25
- 239000000725 suspension Substances 0.000 claims description 13
- 230000009471 action Effects 0.000 abstract description 6
- 238000010276 construction Methods 0.000 abstract description 4
- 230000001360 synchronised effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000004069 differentiation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system, the unmanned plane rotor folding and unfolding controlling organization includes steering wheel, linkage pivoted arm, first connecting rod, second connecting rod；Steering wheel has rotating output shaft, linkage pivoted arm has affixed first support arm and second support arm, first support arm has pivot with second support arm joint, rotating output shaft is fixed on pivot, the outer end of first support arm and second support arm has the first articulated section, the second articulated section respectively, first connecting rod, the first end of second connecting rod are hinged with the first articulated section, the second articulated section respectively, and first connecting rod, the second end of second connecting rod have the 3rd articulated section, the 4th articulated section respectively.Of the present utility model simple in construction, uniform force, action is smooth, reduces the jam during folding and unfolding.
Description
Technical field
The utility model belongs to unmanned plane field, and in particular to unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor are received
Place system.
Background technology
A kind of higher VTOL fixed-wing unmanned plane solution of energy ecology has been occurred in that, has passed through rotor
Folding and unfolding controlling organization control rotor deploys and packed up, when rotor deploys, and rotor provides vertical in the both sides rotation of fixed-wing fuselage
The power of landing, due to being exclusively used in low speed on these rotors, can optimize design in strict accordance with the requirement of low speed power, when
When aircraft enters fixed-wing state of flight, rotor is taken in fuselage interior by many rotor folding and unfolding controlling organizations, is reduced fixed-wing and is flown
Air drag during row, improves the energy ecology during fixed wing aircraft, but many rotor folding and unfolding control machines
Structure has the following disadvantages：
Complicated, part is excessive, and being converted into steering wheel rotating shaft in the linear motion of sliding block, starts
During folding and unfolding campaign, it is considered to the presence of static friction, and both sides force unbalance, easily occur jam, and latch and steering wheel connecting rod
Rub, be also easily damaged for a long time in the chute of sliding block, cause part service life not long.
The content of the invention
The purpose of this utility model is a kind of unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system, this
Simple in construction, the uniform force of utility model, action is smooth, reduces the jam during folding and unfolding.
Its technical scheme is as follows：
Unmanned plane rotor folding and unfolding controlling organization, including steering wheel, linkage pivoted arm, first connecting rod, second connecting rod；Steering wheel has rotation
Shaft is transferred, linkage pivoted arm has affixed first support arm and second support arm, and first support arm has rotation with second support arm joint
Turn center, rotating output shaft is fixed on pivot, the outer end of first support arm and second support arm have respectively the first articulated section,
Second articulated section, first connecting rod, the first end of second connecting rod are hinged with the first articulated section, the second articulated section respectively, and first connects
Bar, the second end of second connecting rod have the 3rd articulated section, the 4th articulated section respectively.
Unmanned plane rotor extension and retraction system, including outstanding wing supporting mechanism and folding and unfolding controlling organization, hanging wing supporting mechanism includes the
The stage casing of one cantilever, the second cantilever, the first cantilever and the second cantilever has the center that is hinged, and the first cantilever and the second cantilever pass through hinge
Connect central movable to be hinged and form X-shaped, there is the first force section, the second force section, first applies on the first cantilever, the second cantilever
Power portion, the second force section deviate from the center of being hinged；Folding and unfolding controlling organization includes steering wheel, linkage pivoted arm, first connecting rod, the second company
Bar；Steering wheel has rotating output shaft, and linkage pivoted arm has affixed first support arm and second support arm, first support arm and second support arm
Joint has pivot, and rotating output shaft is fixed on pivot, and the outer end of first support arm and second support arm has respectively
Have the first articulated section, the second articulated section, first connecting rod, second connecting rod first end respectively with the first articulated section, the second articulated section
It is hinged, first connecting rod, the second end of second connecting rod have the 3rd articulated section, the 4th articulated section respectively；3rd articulated section, the 4th
Articulated section is movably hinged with the first force section, the second force section respectively.
Further, the first articulated section, the second articulated section relative to the pivot equal length.
Further, " V " shape is formed between the first support arm and second support arm.
Further, the angle between the first support arm and second support arm is 30 degree to 150 degree.
Further, the plane perpendicular to the rotating output shaft is Plane of rotation, and first hinge point is in first
Plane of rotation, second hinge point is in the second Plane of rotation.
Further, the plane perpendicular to the rotating output shaft is Plane of rotation, and first articulated section, second are hinged
Portion is located at the first Plane of rotation, and first force section, the second force application part are in the second Plane of rotation.
Further, first cantilever, the two ends of the second cantilever have rotor installation position respectively.
Further, in the first support arm, second support arm near when being hinged center, the first support arm is relative to
For one articulated section, positioned at the extended line direction of the first connecting rod, and the first support arm and the extension of the first connecting rod
Angle between line is less than 5 degree；The second support arm is for the second articulated section, positioned at the extended line of the second connecting rod
Angle between direction, and the extended line of the second support arm and the second connecting rod is less than 5 degree；In the first support arm,
Two support arms are most away from when being hinged center, and the first support arm is for the first articulated section, positioned at the phase of the first connecting rod
It is equidirectional, and angle between the extended line of the first support arm and the first connecting rod is less than 5 degree；The second support arm is relative
For the second articulated section, positioned at the equidirectional of the second connecting rod, and the second support arm and the second connecting rod prolong
Angle between long line is less than 5 degree.
Further, in the first support arm, second support arm near when being hinged center, first connecting rod, second connecting rod phase
Tilt；When the first support arm, second support arm deviate from and be hinged center, first connecting rod, second connecting rod are tilted and intersected.
Further, suspension body and torque arm are included in first cantilever, the second cantilever, torque arm is located at cantilever master
The outside of body and relative to suspension body outside stretch out.
It should be noted that：
Foregoing " first, second ... " does not represent specific quantity and order, is only used for the differentiation to title.
Advantage of the present utility model or principle are illustrated below：
1st, the folding and unfolding controlling organization has steering wheel, linkage pivoted arm, first connecting rod, second connecting rod, first of linkage pivoted arm
Arm and the second support arm synchronous axial system in the presence of steering wheel, drive first connecting rod, second connecting rod movement, then connected by first respectively
Bar, second connecting rod control the first cantilever of outstanding wing supporting mechanism, the second cantilever to deploy with folding respectively.The folding and unfolding controlling organization will
The convert rotational motion of steering wheel is translational motion, is acted on successively by first support arm, first connecting rod, the first cantilever, simple in construction
Also it is more flexible；Simultaneously because using linkage pivoted arm, the active force point two-way of steering wheel is respectively acting on the first cantilever, the second cantilever,
And then the first cantilever, the second cantilever are controlled simultaneously, the first cantilever, the stress balance of the second cantilever, action is synchronous, is difficult
Generation jam.
2nd, the outstanding wing supporting mechanism includes the first cantilever, the second cantilever, and the first cantilever and the second cantilever are by being hinged center
It is movably hinged and forms X-shaped, the first cantilever and the second cantilever intersected in X-shaped connects with the first of folding and unfolding controlling organization respectively
Bar, second connecting rod connection, when the rotating output shaft of steering wheel is rotated, first support arm and second support arm synchronous axial system, first support arm and
Second support arm acts on the first cantilever, the second cantilever by first connecting rod, second connecting rod respectively, when first support arm, second support arm
Near when being hinged center, first support arm, second support arm are by first connecting rod, second connecting rod by the first cantilever, the second cross arm brace
Open, hang wing supporting mechanism and be in open mode, when first support arm, second support arm away from be hinged center when, first support arm, second
Arm is drawn over to one's side the first cantilever, the second cantilever by first connecting rod, second connecting rod, is hanged wing supporting mechanism and is in collapse state.
3rd, the first articulated section, the second articulated section are relative to the equal length of the pivot, the first support arm and
" V " shape is formed between two support arms.The first articulated section, the second articulated section position phase of first support arm and second support arm can so be made
Mutually deviate certain position, and the first cantilever, the second cantilever are in maximum open mode, maximum collapse state, can guarantee that first hangs
Arm, the second cantilever have identical angular displacement.It is preferred that, angle between the first support arm and second support arm for 30 degree extremely
At 150 degree, its effect is best.
4th, first hinge point is in the first Plane of rotation, and second hinge point is in the second Plane of rotation, first
Plane where articulated section, the second articulated section mutually staggers, linkage pivoted arm rotate during, can avoid first connecting rod,
Second connecting rod produces interference each other.
Similarly, first articulated section, the second hinge point are in the first Plane of rotation, and first force section, second are applied
Power portion is located at the second Plane of rotation.First connecting rod, second connecting rod can also be reduced and produce interference each other.
When the 5th, hanging wing supporting mechanism in collapse state, extended line of the first support arm generally within the first connecting rod
Direction and both angles are less than 5 degree；Extended line direction and both angles of the second support arm generally within the second connecting rod
Less than 5 degree；When outstanding wing supporting mechanism is in collapse state, the first support arm is overlapped with the first connecting rod substantially；Described
Two support arms are overlapped with the second connecting rod substantially.For outstanding wing supporting mechanism, its conventional two states is collapse state
And open mode, now need to ensure as far as possible the stabilization of its mechanism, reliable, said structure can ensure：In open mode
Or during collapse state, the first cantilever or/and the second cantilever are when by side force, and rotating output shaft is only by linkage pivoted arm
The pulling force or pressure of effect, without producing the moment of torsion for rotating it, therefore are " double dead point mechanisms ".
6th, in the first support arm, second support arm near when being hinged center, first connecting rod, second connecting rod are tilted；
The first support arm, second support arm are away from when being hinged center, and first connecting rod, second connecting rod are tilted and intersected.Due to foregoing
One Plane of rotation, the second Plane of rotation mutually stagger, and during linkage pivoted arm rotation, the generation effectively avoided interference with reduces card
Resistance；On the other hand, tilt and intersect by first connecting rod, second connecting rod, the first cantilever, the second cantilever is opened or is folded
When, rotated respectively by the different anglecs of rotation, it is to avoid the first cantilever, the second cantilever produce interference in same position.
7th, suspension body and torque arm are included in first cantilever, the second cantilever, torque arm is located at the outer of suspension body
Side and relative to suspension body outside stretch out；, can be with more flexible pair from the aspects of geometric layout due to being provided with torque arm
First cantilever, the second cantilever, first connecting rod, second connecting rod and first support arm, second support arm etc. are laid out；On the other hand, exist
When first cantilever, the second cantilever are in collapse state, angle between the two is minimum, now first connecting rod, second connecting rod effect
Most of power is had in the power of the first cantilever, the second cantilever to act on the center of being hinged and consume, and is reduced when opening or folding
Action accuracy and speed, there is provided after the torque arm stretched out laterally, when both the first cantilever, the second cantilever are in collapse state
(or during close to collapse state), first connecting rod, second connecting rod act on the first cantilever, the power of the second cantilever can be to different directions
Decomposed, reduce the first cantilever, the second cantilever and open or pulling force or pressure required when folding, more conducively the first cantilever, the
The opening of two cantilevers is with folding.
Brief description of the drawings
Fig. 1 is the structure chart of unmanned plane rotor extension and retraction system described in the utility model embodiment；
Fig. 2 is the disassembly diagram of unmanned plane rotor extension and retraction system described in the utility model embodiment；
Fig. 3 is the partial enlarged drawing of unmanned plane rotor extension and retraction system described in the utility model embodiment；
Fig. 4 is the structure chart of folding and unfolding controlling organization described in the utility model embodiment；
Fig. 5 is schematic diagram of the unmanned plane rotor extension and retraction system in open mode described in the utility model embodiment；
Fig. 6 is schematic diagram of the unmanned plane rotor extension and retraction system in the first collapse state described in the utility model embodiment；
Fig. 7 is schematic diagram of the unmanned plane rotor extension and retraction system in the second collapse state described in the utility model embodiment；
Fig. 8 is schematic diagram of the unmanned plane rotor extension and retraction system in complete collapse state described in the utility model embodiment；
Description of reference numerals：
10th, steering wheel, 11, rotating output shaft, 20, linkage pivoted arm, 21, first support arm, the 211, first articulated section, 22, second
Support arm, the 221, second articulated section, 31, first connecting rod, the 311, the 3rd articulated section, 32, second connecting rod, the 321, the 4th articulated section, 41,
First cantilever, the 42, second cantilever, 43, be hinged center, 44, rotor installation position, 45, suspension body, 46, torque arm, 47, rotor.
Embodiment
Embodiment of the present utility model is described in detail below.
As shown in Figures 1 to 8, unmanned plane rotor extension and retraction system, including outstanding wing supporting mechanism and folding and unfolding controlling organization, hang the wing
Supporting mechanism includes the first cantilever 41, the second cantilever 42, the stage casing of the first cantilever 41 and the second cantilever 42 with being hinged center 43,
First cantilever 41 and the second cantilever 42 are movably hinged by being hinged center 43 and form X-shaped, the first cantilever 41, the second cantilever 42
Upper to have the first force section, the second force section, the first force section, the second force section deviate from the center of being hinged 43；Folding and unfolding control machine
Structure includes steering wheel 10, linkage pivoted arm 20, first connecting rod 31, second connecting rod 32；Steering wheel 10 has rotating output shaft 11, and link pivoted arm
20 have affixed first support arm 21 and second support arm 22, and first support arm 21 has pivot with the joint of second support arm 22,
Rotating output shaft 11 is fixed on pivot, and the outer end of first support arm 21 and second support arm 22 has the first articulated section respectively
211st, the second articulated section 221, first connecting rod 31, second connecting rod 32 first end respectively with the first articulated section 211, the second articulated section
221 are hinged, and first connecting rod 31, the second end of second connecting rod 32 have the 3rd articulated section 311, the 4th articulated section 321 respectively；The
Three articulated sections 311, the 4th articulated section 321 are movably hinged with the first force section, the second force section respectively.
Wherein, " V " shape, the first support arm 21 and second support arm are formed between the first support arm 21 and second support arm 22
Angle between 22 is 70 degree, and the first articulated section 211, the second articulated section 221 relative to the pivot equal length；
The straight plane in the rotating output shaft 11 is Plane of rotation, and first articulated section 211 is located at the first Plane of rotation, described the
Two articulated sections 221 are located at the second Plane of rotation.
Include suspension body 45 and torque arm 46 in first cantilever 41, the second cantilever 42, torque arm 46 is located at cantilever
The outside of main body 45 and relative to suspension body 45 outside stretch out.
When the first support arm 21, second support arm 22 are near the center 43 of being hinged, (i.e. outstanding wing supporting mechanism, which is in, to be folded
During state), the first support arm 21 is overlapped with the extended line of the first connecting rod 31, and the second support arm 22 connects with described second
The extended line of bar 32 is overlapped；(wing supporting mechanism is hanged when the first support arm 21, second support arm 22 most deviate from and be hinged center 43
During in open mode), the first support arm 21 is overlapped with the first connecting rod 31, and the second support arm 22 connects with described second
Bar 32 is overlapped.
First cantilever 41, the two ends of the second cantilever 42 have rotor installation position 44 respectively, vertical for installing herein
The rotor 47 of lifting.
When the first support arm 21, second support arm 22 are near the center 43 of being hinged, first connecting rod 31, the phase of second connecting rod 32
Tilt；When the first support arm 21, second support arm 22 deviate from and be hinged center 43, first connecting rod 31, second connecting rod 32 are tilted
And intersect.
The present embodiment has the following advantages that：
1st, the folding and unfolding controlling organization has steering wheel 10, linkage pivoted arm 20, first connecting rod 31, second connecting rod 32, and link pivoted arm
20 first support arm 21 and second support arm 22 synchronous axial system in the presence of steering wheel 10, drives first connecting rod 31, second to connect respectively
Bar 32 is moved, then controls by first connecting rod 31, second connecting rod 32 the first cantilever 41, the second cantilever 42 of outstanding wing supporting mechanism respectively
Deploy and fold.The convert rotational motion of steering wheel 10 is translational motion by the folding and unfolding controlling organization, passes through first support arm 21, first
Connecting rod 31, the first cantilever 41 are acted on successively, simple in construction also more flexible；Simultaneously because using linkage pivoted arm 20, the work of steering wheel 10
Firmly divide two-way to be respectively acting on the first cantilever 41, the second cantilever 42, and then the first cantilever 41, the second cantilever 42 are carried out simultaneously
Control, the first cantilever 41, the stress balance of the second cantilever 42, action is synchronous, is not susceptible to jam.
2nd, the outstanding wing supporting mechanism includes the first cantilever 41, the second cantilever 42, and the first cantilever 41 passes through with the second cantilever 42
Center 43 is hinged to be movably hinged and form X-shaped, the first cantilever 41 and the second cantilever 42 intersected in X-shaped respectively with folding and unfolding control
First connecting rod 31, the second connecting rod 32 of mechanism processed are connected, when the rotating output shaft 11 of steering wheel 10 is rotated, first support arm 21 and second
The synchronous axial system of support arm 22, first support arm 21 and second support arm 22 act on first by first connecting rod 31, second connecting rod 32 respectively
Cantilever 41, the second cantilever 42, when first support arm 21, second support arm 22 are near the center 43 of being hinged, first support arm 21, second
Arm 22 is strutted the first cantilever 41, the second cantilever 42 by first connecting rod 31, second connecting rod 32, is hanged wing supporting mechanism and is in opening
State, when first support arm 21, second support arm 22, which deviate from, is hinged center 43, first support arm 21, second support arm 22 pass through first and connected
Bar 31, second connecting rod 32 draw the first cantilever 41, the second cantilever 42 over to one's side, hang wing supporting mechanism and are in collapse state.
3rd, the first articulated section 211, the second articulated section 221 relative to the pivot equal length, described first
" V " shape is formed between arm 21 and second support arm 22.The first articulated section of first support arm 21 and second support arm 22 can so be made
211st, the position of the second articulated section 221 deviates from each other certain position, and the first cantilever 41, the second cantilever 42 maximum open mode,
Maximum collapse state, can guarantee that the first cantilever 41, the second cantilever 42 have identical angular displacement.It is preferred that, described first
When angle between arm 21 and second support arm 22 is 30 degree to 150 degree, its effect is best.
4th, first articulated section 211 is located at the first Plane of rotation, and second articulated section 221 is located at the second rotary flat
Face, the plane where the first articulated section 211, the second articulated section 221 mutually staggers, can during linkage pivoted arm 20 is rotated
To avoid first connecting rod 31, second connecting rod 32 from producing interference each other.
Similarly, first articulated section 211, the second articulated section 221 be located at the first Plane of rotation, first force section,
Second force application part is in the second Plane of rotation.First connecting rod 31, second connecting rod 32 can also be reduced and produce interference each other.
5th, when outstanding wing supporting mechanism is in collapse state, the first support arm 21 and the extended line of the first connecting rod 31
Overlap, the second support arm 22 is overlapped with the extended line of the second connecting rod 32；When outstanding wing supporting mechanism is in open mode,
The first support arm 21 is overlapped with the first connecting rod 31, and the second support arm 22 is overlapped with the second connecting rod 32.For outstanding
For wing supporting mechanism, its conventional two states is collapse state and open mode, now needs to ensure its machine as far as possible
The stabilization of structure, reliable, said structure can ensure：In open mode or collapse state, the first cantilever 41 or/and the second cantilever
42 when by side force, pulling force or pressure that rotating output shaft 11 is only acted on by linkage pivoted arm 20, without producing
The moment of torsion for rotating it, therefore be " double dead point mechanisms ".
6th, when the first support arm 21, second support arm 22 are near the center 43 of being hinged, first connecting rod 31, second connecting rod 32
Tilt；When the first support arm 21, second support arm 22 deviate from and be hinged center 43, first connecting rod 31, second connecting rod 32 mutually incline
Oblique and intersection.Because foregoing first Plane of rotation, the second Plane of rotation mutually stagger, when linkage pivoted arm 20 rotates, effectively keep away
Exempt from the generation of interference, reduce jam；On the other hand, tilt and intersect by first connecting rod 31, second connecting rod 32, make first
When cantilever 41, the second cantilever 42 are opened or folded, rotated respectively by the different anglecs of rotation (as shown in Figure 6), it is to avoid
First cantilever 41, the second cantilever 42 produce interference in same position.
7th, suspension body 45 and torque arm 46 are included in first cantilever 41, the second cantilever 42, torque arm 46 is located at outstanding
The outside of arm main body 45 and relative to suspension body 45 outside stretch out；Due to being provided with torque arm 46, come in terms of geometric layout
Saying can be with more flexible to the first cantilever 41, the second cantilever 42, first connecting rod 31, second connecting rod 32 and first support arm 21, second
Support arm 22 etc. is laid out；On the other hand, when the first cantilever 41, the second cantilever 42 are in collapse state, folder between the two
Angle is minimum, and now first connecting rod 31, second connecting rod 32 act on the first cantilever 41, the power of the second cantilever 42 and have most of masterpiece
For being hinged center 43 and consuming, the action accuracy and speed when opening or folding are reduced, there is provided stretch out laterally
After torque arm 46, when both the first cantilever 41, the second cantilever 42 are in collapse state (or during close to collapse state), first connecting rod
31st, second connecting rod 32 acts on the first cantilever 41, the power of the second cantilever 42 can be decomposed to different directions, reduces first and hangs
Arm 41, the second cantilever 42 pulling force or pressure required when opening or folding, more conducively the first cantilever 41, the opening of the second cantilever 42
With folding.
Specific embodiment of the utility model is these are only, protection domain of the present utility model is not limited with this；Not
Any replacement made on the basis of the utility model design is violated with improving, belongs to protection domain of the present utility model.
Claims (10)
1. unmanned plane rotor folding and unfolding controlling organization, it is characterised in that including steering wheel, linkage pivoted arm, first connecting rod, second connecting rod；
Steering wheel has rotating output shaft, and linkage pivoted arm has affixed first support arm and second support arm, first support arm and second support arm phase
Meeting place has pivot, and rotating output shaft is fixed on pivot, and the outer end of first support arm and second support arm has respectively
First articulated section, the second articulated section, first connecting rod, second connecting rod first end respectively with the first articulated section, the second articulated section phase
It is hinged, first connecting rod, the second end of second connecting rod have the 3rd articulated section, the 4th articulated section respectively.
2. unmanned plane rotor extension and retraction system, it is characterised in that including outstanding wing supporting mechanism and folding and unfolding controlling organization, hangs wing support machine
Structure includes the first cantilever, the second cantilever, and the stage casing of the first cantilever and the second cantilever has the center that is hinged, and the first cantilever and second are hanged
Arm is hinged by being hinged central movable and forms X-shaped, has the first force section, the second force on the first cantilever, the second cantilever
Portion, the first force section, the second force section deviate from the center of being hinged；Folding and unfolding controlling organization includes steering wheel, linkage pivoted arm, the first company
Bar, second connecting rod；Steering wheel has rotating output shaft, and linkage pivoted arm has affixed first support arm and second support arm, first support arm
There is pivot with second support arm joint, rotating output shaft is fixed on pivot, first support arm and second support arm
Outer end respectively have the first articulated section, the second articulated section, first connecting rod, second connecting rod first end respectively with the first articulated section,
Second articulated section is hinged, and first connecting rod, the second end of second connecting rod have the 3rd articulated section, the 4th articulated section respectively；3rd
Articulated section, the 4th articulated section are movably hinged with the first force section, the second force section respectively.
3. unmanned plane rotor extension and retraction system as claimed in claim 2, it is characterised in that the first articulated section, the second articulated section are relative
In the equal length of the pivot.
4. unmanned plane rotor extension and retraction system as claimed in claim 2, it is characterised in that between the first support arm and second support arm
Form " V " shape.
5. unmanned plane rotor extension and retraction system as claimed in claim 4, it is characterised in that between the first support arm and second support arm
Angle be 30 degree to 150 degree.
6. the unmanned plane rotor extension and retraction system as any one of claim 2 to 5, it is characterised in that perpendicular to the rotation
The plane of output shaft is Plane of rotation, and first hinge point is in the first Plane of rotation, and second hinge point is in second
Plane of rotation.
7. the unmanned plane rotor extension and retraction system as any one of claim 2 to 5, it is characterised in that perpendicular to the rotation
The plane of output shaft is Plane of rotation, and first articulated section, the second hinge point are in the first Plane of rotation, first force
Portion, the second force application part are in the second Plane of rotation.
8. the unmanned plane rotor extension and retraction system as any one of claim 2 to 5, it is characterised in that
In the first support arm, second support arm near when being hinged center, the first support arm for the first articulated section,
Positioned at the extended line direction of the first connecting rod, and the angle between the extended line of the first support arm and the first connecting rod is small
In 5 degree；The second support arm is for the second articulated section, positioned at the extended line direction of the second connecting rod, and described
Angle between the extended line of two support arms and the second connecting rod is less than 5 degree；
The first support arm, second support arm most away from be hinged center when, the first support arm for the first articulated section,
Angle between the equidirectional of the first connecting rod, and the extended line of the first support arm and the first connecting rod is less than
5 degree；The second support arm is for the second articulated section, positioned at the equidirectional of the second connecting rod, and described second
Angle between the extended line of arm and the second connecting rod is less than 5 degree.
9. unmanned plane rotor extension and retraction system as claimed in claim 8, it is characterised in that in the first support arm, second support arm most
Close to when being hinged center, first connecting rod, second connecting rod are tilted；When the first support arm, second support arm deviate from and are hinged center,
First connecting rod, second connecting rod are tilted and intersected.
10. the unmanned plane rotor extension and retraction system as any one of claim 2 to 5, it is characterised in that outstanding described first
Arm, the second cantilever include suspension body and torque arm, and torque arm is located at the outside of suspension body and outer relative to suspension body
Side is stretched out.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620380045 | 2016-04-29 | ||
| CN2016203800450 | 2016-04-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206374977U true CN206374977U (en) | 2017-08-04 |
Family
ID=59406688
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621340569.3U Withdrawn - After Issue CN206374977U (en) | 2016-04-29 | 2016-12-08 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206374977U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542088A (en) * | 2016-04-29 | 2017-03-29 | 上海福昆航空科技有限公司 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
| CN109720545A (en) * | 2019-01-14 | 2019-05-07 | 珠海卡特瑞科农林航空装备研究所有限公司 | A kind of four axial crosses rotating mechanism and the quadrotor with the mechanism fold unmanned plane |
-
2016
- 2016-12-08 CN CN201621340569.3U patent/CN206374977U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542088A (en) * | 2016-04-29 | 2017-03-29 | 上海福昆航空科技有限公司 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
| CN106542088B (en) * | 2016-04-29 | 2024-05-28 | 中山福昆航空科技有限公司 | Unmanned aerial vehicle rotor wing retraction control mechanism and unmanned aerial vehicle rotor wing retraction system |
| CN109720545A (en) * | 2019-01-14 | 2019-05-07 | 珠海卡特瑞科农林航空装备研究所有限公司 | A kind of four axial crosses rotating mechanism and the quadrotor with the mechanism fold unmanned plane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2017025060A1 (en) | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor | |
| CN107972847A (en) | A kind of aircraft wing fold mechanism and the lid mechanism based on it | |
| US20090289148A1 (en) | Faired tether for wind power generation systems | |
| CN206374977U (en) | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system | |
| DE602008005164D1 (en) | AIR CONDITIONING WITH BUMPING WINGS | |
| CN105217025A (en) | A kind of aircraft coaxial double-rotary wing system | |
| WO2016062223A1 (en) | Vertical take-off and landing aircraft | |
| CN105197240B (en) | Differential luffing driving mechanism for flapping wing and driving method | |
| CN110294102A (en) | The composite-motion mechanism of integral type flaperon | |
| CN110371291A (en) | A kind of steady upper lower thread mechanism of high voltage transmission line flight crusing robot | |
| CN106542088A (en) | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system | |
| CN109606631A (en) | A kind of dual rotation of linear drives can the wingfold mechanism that folds of wide-angle | |
| CN206939051U (en) | A kind of wing of imitative beetle elytrum | |
| CN107933961A (en) | A kind of variable topological folding and unfolding mechanism of imitative sensitive plant flexible hinge connection | |
| EP2851288A1 (en) | Aerodynamic surface drive mechanism | |
| WO2018224033A1 (en) | Aircraft with imitation beetle elytron wings | |
| CN109606633A (en) | A kind of single axle wingfold mechanism | |
| CN107140181A (en) | A kind of wing of imitative beetle elytrum | |
| CN105539821A (en) | Deformable folding structure of multi-rotor type aircraft | |
| CN107719644A (en) | Flap retracting device | |
| CN216611596U (en) | Unmanned aerial vehicle | |
| CN115636086A (en) | Flapping wing aircraft and rolling flight method thereof | |
| CN108045556A (en) | A kind of aircraft flaperon motion | |
| CN205098477U (en) | Differential change width of cloth flapping wing actuating mechanism | |
| CN205186524U (en) | Coaxial two rotor system of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181130 Address after: 528467 315 cards on the third floor of No. 7 F Building, Xiaoyang Road, Tanzhou Town, Zhongshan City, Guangdong Province Patentee after: Zhongshan Fukun Aviation Technology Co.,Ltd. Address before: Room 710, No. 2, Lane 2388, Xiupu Road, Pudong New Area, Shanghai 200000 Patentee before: SHANGHAI FUKUN AVIATION TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170804 Effective date of abandoning: 20240528 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20170804 Effective date of abandoning: 20240528 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |