CN106542088A - 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
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- CN106542088A CN106542088A CN201611121054.9A CN201611121054A CN106542088A CN 106542088 A CN106542088 A CN 106542088A CN 201611121054 A CN201611121054 A CN 201611121054A CN 106542088 A CN106542088 A CN 106542088A
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- 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
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000001360 synchronised effect 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
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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Abstract
The invention 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, link 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 center of rotation with second support arm joint, rotating output shaft is fixed on center of rotation, 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.The simple structure of the present invention, uniform force, action are smooth, reduce the jam during folding and unfolding.
Description
Technical field
The invention belongs to unmanned plane field, and in particular to unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor folding and unfolding system
System.
Background technology
A kind of higher VTOL fixed-wing unmanned plane solution of energy ecology is occurred in that, by rotor
Folding and unfolding controlling organization control rotor launches and packs up, and when rotor launches, 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 be optimized 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 airplane, but many rotor folding and unfolding control machines
Structure is suffered from the drawback that：
Complex structure, part are excessive, and being converted into steering wheel rotating shaft in the linear motion of slide block, start
During folding and unfolding campaign, it is considered to the presence of static friction, and both sides force unbalance, it is susceptible to jam, and latch and steering wheel connecting rod
Rubbed in the chute of slide block for a long time, be also easily damaged, cause part service life not long.
The content of the invention
It is an object of the invention to a kind of unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system, the present invention
Simple structure, uniform force, action be 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 center of rotation, 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, outstanding wing supporting mechanism include the
The stage casing of one cantilever, the second cantilever, the first cantilever and the second cantilever has the center that is hinged, the first cantilever and the second cantilever by hinge
Connect central movable and be hinged and formed X-shaped, there is on the first cantilever, the second cantilever the first force section, the second force section, first applies
Power portion, the second force section deviate from the center of being hinged；Folding and unfolding controlling organization includes that steering wheel, linkage pivoted arm, first connecting rod, second connect
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 center of rotation, and rotating output shaft is fixed on center of rotation, 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 center of rotation 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, the first support arm, second support arm near be hinged center when, the first support arm is relative to
For one articulated section, positioned at the extended line direction of the first connecting rod, and the prolongation of the first support arm and the first connecting rod
Angle between line is less than 5 degree；The second support arm 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；The first support arm,
Two support arms most away from be hinged center when, the first support arm for the first articulated section, positioned at the phase of the first connecting rod
It is equidirectional, and the 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, the first support arm, second support arm near be hinged center when, first connecting rod, second connecting rod phase
Incline；When the first support arm, second support arm deviate from and be hinged center, first connecting rod, second connecting rod are tilted and are 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 stretching out on the outside of suspension body.
It should be noted that：
Aforementioned " first, second ... " does not represent specific quantity and order, is only used for the differentiation to title.
Below advantages of the present invention or principle are illustrated：
1st, the folding and unfolding controlling organization has steering wheel, link pivoted arm, first connecting rod, second connecting rod, first of the pivoted arm that links
The arm and second support arm synchronous axial system in the presence of steering wheel, drives first connecting rod, second connecting rod movement respectively, then is connected by first
Bar, second connecting rod control the first cantilever of outstanding wing supporting mechanism, the second cantilever respectively to launch and folds.The folding and unfolding controlling organization will
The convert rotational motion of steering wheel is translational motion, is acted on by first support arm, first connecting rod, the first cantilever successively, simple structure
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 simultaneously the first cantilever, the second cantilever are controlled, the first cantilever, the stress balance of the second cantilever, action synchronization are difficult
Generation jam.
2nd, the outstanding wing supporting mechanism includes the first cantilever, the second cantilever, the first cantilever and the second cantilever by being hinged center
X-shaped is movably hinged and is formed, the first cantilever intersected in X-shaped and the second cantilever connect 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
When center is hinged, first support arm, second support arm pass through 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
First cantilever, the second cantilever are drawn over to one's side by arm by first connecting rod, second connecting rod, hang wing supporting mechanism and are in collapse state.
3rd, the first articulated section, the second articulated section relative to the center of rotation equal length, 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 in maximum open mode, maximum collapse state, can guarantee that first hangs
Arm, the second cantilever have identical angular displacement.Preferably, the angle between the first support arm and second support arm be 30 degree extremely
When 150 degree, its effect is best.
4th, first hinge point is in the first Plane of rotation, second hinge point in the second Plane of rotation, first
Articulated section, the second articulated section be located plane mutually stagger, linkage pivoted arm rotate during, can avoid first connecting rod,
Second connecting rod produces interference each other.
In the same manner, in the first Plane of rotation, first force section, second are applied for first articulated section, the second hinge point
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.
5th, when outstanding wing supporting mechanism is 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；The second support arm extended line direction and both angles 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 needing to ensure the stable, reliable of its mechanism as far as possible, said structure can ensure that：In open mode
Or during collapse state, when by side force, rotating output shaft is only subject to linkage pivoted arm for the first cantilever or/and the second cantilever
The pulling force or pressure of effect, without producing the moment of torsion for rotating which, therefore is " double dead point mechanisms ".
6th, the first support arm, second support arm near be hinged center when, first connecting rod, second connecting rod are tilted；
, away from when being hinged center, first connecting rod, second connecting rod are tilted and are intersected for the first support arm, second support arm.Due to aforementioned
One Plane of rotation, the second Plane of rotation mutually stagger, and when linkage pivoted arm rotates, the generation for effectively avoiding 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, respectively by the different anglecs of rotation being rotated, 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 stretching out on the outside of suspension body；Due to being provided with torque arm, can be with more flexible right from from the aspects of geometric layout
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, is reduced when opening or folding
Action accuracy and speed, after being provided with the torque arm stretched out laterally, when both the first cantilever, the second cantilever are in collapse state
(or when being 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 required pulling force when folding or pressure, more conducively the first cantilever, the
The opening of two cantilevers with fold.
Description of the drawings
Fig. 1 is the structure chart of unmanned plane rotor extension and retraction system described in the embodiment of the present invention；
Fig. 2 is the disassembly diagram of unmanned plane rotor extension and retraction system described in the embodiment of the present invention；
Fig. 3 is the partial enlarged drawing of unmanned plane rotor extension and retraction system described in the embodiment of the present invention；
Fig. 4 is the structure chart of folding and unfolding controlling organization described in the embodiment of the present invention；
Fig. 5 is schematic diagram of the unmanned plane rotor extension and retraction system in open mode described in the embodiment of the present invention；
Fig. 6 is schematic diagram of the unmanned plane rotor extension and retraction system in the first collapse state described in the embodiment of the present invention；
Fig. 7 is schematic diagram of the unmanned plane rotor extension and retraction system in the second collapse state described in the embodiment of the present invention；
Fig. 8 is schematic diagram of the unmanned plane rotor extension and retraction system in complete collapse state described in the embodiment of the present invention；
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.
Specific embodiment
Below embodiments of the invention are described in detail.
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 include the first cantilever 41, the second cantilever 42, the first cantilever 41 and the second cantilever 42 stage casing have be hinged center 43,
First cantilever 41 and the second cantilever 42 are movably hinged and are formed X-shaped, the first cantilever 41, the second cantilever 42 by being hinged center 43
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 center of rotation with 22 joint of second support arm,
Rotating output shaft 11 is fixed on center of rotation, 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 be 70 degree, and the first articulated section 211, the second articulated section 221 relative to the center of rotation 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.
Suspension body 45 and torque arm 46 are included in first cantilever 41, the second cantilever 42, torque arm 46 is located at cantilever
The outside of the main body 45 and outside relative to suspension body 45 is stretched 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 is in and folds
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 overlaps；Wing supporting mechanism is hanged (when the first support arm 21, second support arm 22 most deviate from and be hinged center 43
In open mode when), the first support arm 21 is overlapped with the first connecting rod 31, the second support arm 22 and described second connect
Bar 32 overlaps.
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 31,32 phase of second connecting rod
Incline；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 advantage 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 is controlled the first cantilever 41, second cantilever 42 of outstanding wing supporting mechanism by first connecting rod 31, second connecting rod 32 respectively
Launch and fold.The convert rotational motion of steering wheel 10 is translational motion by the folding and unfolding controlling organization, by first support arm 21, first
Connecting rod 31, the first cantilever 41 are acted on successively, and simple structure is 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 while the first cantilever 41, the second cantilever 42 are carried out
Control, the first cantilever 41, the stress balance of the second cantilever 42, action synchronization are not susceptible to jam.
2nd, the outstanding wing supporting mechanism includes the first cantilever 41, the second cantilever 42, and the first cantilever 41 is passed through with the second cantilever 42
Be hinged center 43 and be movably hinged and formed X-shaped, in X-shaped intersect the first cantilever 41 and the second cantilever 42 respectively with folding and unfolding control
The first connecting rod 31 of mechanism processed, second connecting rod 32 connect, when the rotating output shaft 11 of steering wheel 10 is rotated, first support arm 21 and second
22 synchronous axial system of support arm, 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
First cantilever 41, the second cantilever 42 are strutted by arm 22 by first connecting rod 31, second connecting rod 32, hang wing supporting mechanism in opening
State, when first support arm 21, second support arm 22 deviate from is hinged center 43, first support arm 21, second support arm 22 connect by first
First cantilever 41, the second cantilever 42 are drawn over to one's side by bar 31, second connecting rod 32, hang wing supporting mechanism and are in collapse state.
3rd, the first articulated section 211, the second articulated section 221 relative to the center of rotation 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, 221 position of the second articulated section 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.Preferably, 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 that the first articulated section 211, the second articulated section 221 are located mutually are staggered, during linkage pivoted arm 20 is rotated, can
To avoid first connecting rod 31, second connecting rod 32 from producing interference each other.
In the same manner, first articulated section 211, the second articulated section 221 are 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 extended line of the first support arm 21 and 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
Stable, the reliability of structure, said structure can ensure that：In open mode or collapse state, the first cantilever 41 or/and the second cantilever
42 when by side force, and rotating output shaft 11 is subject to the pulling force or pressure of the linkage effect of pivoted arm 20, without producing
The moment of torsion for rotating which, 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.As aforementioned first Plane of rotation, the second Plane of rotation mutually stagger, when linkage pivoted arm 20 rotates, effectively keep away
Exempt from the generation interfered, 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, respectively by the different anglecs of rotation being rotated (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 the arm main body 45 and outside relative to suspension body 45 is stretched 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 is reduced, is provided with what is stretched out laterally
After torque arm 46, when both the first cantilever 41, the second cantilever 42 are in collapse state (or when being 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 required when opening or folding or pressure, more conducively the first cantilever 41, the opening of the second cantilever 42
With fold.
The specific embodiment of the present invention is these are only, protection scope of the present invention is not limited with this；Do not violating this
Any replacement made on the basis of bright design and improvement, belong to protection scope of the present invention.
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
Place is met with center of rotation, rotating output shaft is fixed on center of rotation, 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 the wing and supports machine
Structure includes that the stage casing of the first cantilever, the second cantilever, the first cantilever and the second cantilever has the center that is hinged, and the first cantilever and second hangs
Arm is hinged and is formed X-shaped by being hinged central movable, 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 that steering wheel, linkage pivoted arm, first connect
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 center of rotation with second support arm joint, rotating output shaft is fixed on center of rotation, 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 center of rotation.
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 in the first Plane of rotation, second hinge point is in second for first hinge point
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
The first support arm, second support arm near be hinged center when, 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 little
In 5 degree；The second support arm 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 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
Near 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 are 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 relative to the outer of suspension body
Stretch out side.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016102779480 | 2016-04-29 | ||
| CN201610277948 | 2016-04-29 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106542088A true CN106542088A (en) | 2017-03-29 |
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| WO2018214124A1 (en) * | 2017-05-25 | 2018-11-29 | SZ DJI Technology Co., Ltd. | Rotational expansion of propulsion systems of a movable vehicle |
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| CN106542088B (en) | 2024-05-28 |
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