CN209427023U - Rotor wing drop pitch-changing mechanism - Google Patents
Rotor wing drop pitch-changing mechanism Download PDFInfo
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- CN209427023U CN209427023U CN201822212958.3U CN201822212958U CN209427023U CN 209427023 U CN209427023 U CN 209427023U CN 201822212958 U CN201822212958 U CN 201822212958U CN 209427023 U CN209427023 U CN 209427023U
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- wing drop
- drop portion
- steering engine
- rotor
- central axis
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Abstract
The utility model discloses a kind of rotor wing drop pitch-changing mechanisms, including upper wing drop portion, lower wing drop portion and synchronising (connecting) rod.Upper wing drop portion and lower wing drop portion are movably arranged on central axis, and upper wing drop portion can be tilted with lower wing drop portion relative to the axis of central axis, and be moved along the axis direction of central axis；Upper wing drop portion is connect with lower wing drop portion by synchronising (connecting) rod, and upper wing drop portion can be tilted relative to the axis of central axis simultaneously with lower wing drop portion, and be moved along the axis direction of central axis.The rotor wing drop pitch-changing mechanism of the utility model, the rotor mechanism in upper wing drop portion, lower wing drop portion and aircraft is correspondingly connected with, the spacing of two rotor mechanisms setting up and down relative to two rotor mechanisms of the expansion amplitude of central axis and change can be changed, the flight attitude of aircraft is adjusted, has effectively ensured the flight stability of aircraft.
Description
Technical field
The utility model relates to vehicle technology fields, more particularly to a kind of rotor wing drop pitch-changing mechanism.
Background technique
In recent years, small-sized unmanned aircraft plays remarkable effect in military, civil field.In military field, small in size,
Light-weight small aircraft has very strong stealthy effect in various aspects such as vision, noise and radar reflection sections, can mention significantly
It is horizontal to rise battle field informationization.In civil field, small-sized unmanned aircraft also can be using exploration outdoors, power-line patrolling, fire prison
In the dangerous situations such as survey.
Currently, small-sized unmanned aircraft often shows certain limitation when coping with a variety of different task demands.Example
Such as, conventional Fixed Wing AirVehicle, forward flight speed is fast, task radius is big, but sliding race or ejection is needed to take off, and needs to block
Land, and a hovering investigation can not be carried out away to target；Rotor class aircraft, further as helicopter, more rotors fly
Row device etc., can VTOL, hovering, show excellent low-speed performance, but rotor class aircraft forward flight speed is low, task
Radius is small, can not cope with quick response, remote mission requirements.
In particular, individual soldier and level of platoon leader combat unit are different to the performance requirement of aircraft under different operational environments, for example,
In military operations in urban terrain, have it is vertical rise battle array, ability of hovering unmanned vehicle can between building, on roof, on windowsill observation exist
The enemy in shelter promotes soldier's situation of battlefield sensing capability；In Field Operational, often need flying speed fast, combat radius
Big aircraft is to obtain rapidly the large-scale reconnaissance in periphery.It is limited by load capacity, individual soldier and level of platoon leader combat unit are difficult
Different combat duty demands are coped with to carry a variety of aircraft simultaneously, a kind of flight stability is researched and developed, is not easy to be affected by the wind, it is empty
Between occupy small, be convenient for carrying, be suitble to individual equipment, be able to satisfy friction speed, different combat radiuses, can vertically play the small-sized nothing of battle array
People's aircraft is particularly important.
Utility model content
The purpose of this utility model is to provide a kind of rotor wing drop pitch-changing mechanisms, to solve to exist in the prior art
Unmanned vehicle fly unstable technical problem.
To achieve the goals above, the utility model uses following technical scheme:
A kind of rotor wing drop pitch-changing mechanism provided by the utility model, including upper wing drop portion, lower wing drop
Portion and synchronising (connecting) rod；
The upper wing drop portion and the lower wing drop portion are movably arranged on central axis, the upper wing drop
Portion can be tilted with the lower wing drop portion relative to the axis of central axis, and be moved along the axis direction of central axis
It is dynamic；
The upper wing drop portion is connect with the lower wing drop portion by the synchronising (connecting) rod, the upper wing drop
Portion can be tilted relative to the axis of central axis simultaneously with the lower wing drop portion, and along the axis side of the central axis
To movement.
It further, further include leaning device steering engine and leaning device steering engine bracket；
On center shaft, the leaning device steering engine is arranged in the inclination for the leaning device steering engine bracket fixed setting
On mechanism steering engine bracket；
The upper wing drop portion is connect by steering engine transmission component with the leaning device steering engine；
The upper wing drop portion and the lower wing drop portion are located at the upper and lower of the leaning device steering engine bracket
Two sides.
Further, the steering engine transmission component includes sequentially connected steering engine kinematic link and steering engine driving rocker；
The upper wing drop portion is connect with the steering engine kinematic link, the steering engine driving rocker and the leaning device
Steering engine connection.
Further, the upper wing drop portion includes rake inner ring and rake outer ring；
The rake inner ring is arranged on center shaft by oscillating bearing, and the rake inner ring can be relative to central axis
Axis tilted to any direction；
The rake outer ring is set in the rake inner ring；
The rake inner ring is connect by the steering engine transmission component with the leaning device steering engine；
The rake outer ring with upper rotor mechanism for connecting.
Further, rake connecting rod is provided in the rake inner ring；
The rake inner ring is connect by the rake connecting rod with the steering engine transmission component.
Further, the lower wing drop portion is identical as the upper wing drop portion structure；
The rake inner ring in the upper wing drop portion and the rake inner ring in the lower wing drop portion are logical
Cross the synchronising (connecting) rod connection；
The rake outer ring in the upper wing drop portion is described lower automatic for connecting with the propeller hub of upper rotor mechanism
The rake outer ring of rake with the propeller hub of lower rotor mechanism for connecting.
It further, further include anti-torsion link assembly；
The lower wing drop portion passes through the anti-torsion link assembly and center axis connection.
Further, the anti-torsion link assembly includes the sequentially connected first anti-torsion connecting rod and the second anti-torsion connecting rod；
The first anti-torsion connecting rod is connect with the described second anti-torsion connecting rod at angle.
Further, the described first anti-torsion connecting rod is connect with the described second anti-torsion connecting rod by pin shaft；
Axis of the axis of the pin shaft perpendicular to central axis.
Further, described anti-one end for turning round link assembly is connect with the lower wing drop portion, the anti-torsion connection rod set
The other end of part is connect with the leaning device steering engine bracket.
Rotor wing drop pitch-changing mechanism provided by the utility model, upper wing drop portion, lower wing drop portion and flight
The rotor mechanism of device is correspondingly connected with, and upper wing drop portion can be tilted with lower wing drop portion relative to the axis of central axis
And moved along the axis direction of central axis, and upper wing drop portion is connect with lower wing drop portion by synchronising (connecting) rod, it can be same
When carry out inclination relative to the axis of central axis and move along the axis direction of central axis, setting up and down two can be changed
Expansion amplitude and change two rotor mechanism the distance between of the rotor mechanism relative to central axis, so that the flight of aircraft
Posture can be adjusted, and significantly reduced influence of the wind-force to flight, effectively ensured the flight stability of aircraft,
It is unstable to solve the problems, such as that existing unmanned vehicle flies.
Detailed description of the invention
It, below will be right in order to illustrate more clearly of specific embodiment of the present invention or technical solution in the prior art
Specific embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, it is described below
In attached drawing be that some embodiments of the utility model are not paying creativeness for those of ordinary skill in the art
Under the premise of labour, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of structural schematic diagram for rotor wing drop pitch-changing mechanism that the utility model embodiment one provides；
Fig. 2 is a kind of structural schematic diagram for rotor wing drop pitch-changing mechanism that the utility model embodiment one provides；
Fig. 3 is a kind of sectional structure signal for rotor wing drop pitch-changing mechanism that the utility model embodiment one provides
Figure；
Fig. 4 is the upper wing drop portion in a kind of rotor wing drop pitch-changing mechanism that the utility model embodiment one provides
Structural schematic diagram；
Fig. 5 is a kind of overall structure diagram for portable aircraft that the utility model embodiment two provides；
Fig. 6 is a kind of overall structure diagram for portable aircraft that the utility model embodiment two provides；
Fig. 7 is the structural representation of the bispin swing device in a kind of portable aircraft that the utility model embodiment two provides
Figure；
Fig. 8 is the structural representation of the bispin swing device in a kind of portable aircraft that the utility model embodiment two provides
Figure；
Fig. 9 is the structural representation of the upper rotor mechanism in a kind of portable aircraft that the utility model embodiment two provides
Figure；
Figure 10 is that the structure of the upper rotor mechanism in a kind of portable aircraft that the utility model embodiment two provides is shown
It is intended to；
Figure 11 is the section view knot of the upper rotor mechanism in a kind of portable aircraft that the utility model embodiment two provides
Structure schematic diagram；
Figure 12 is the knot in the blade pose adjustment portion in a kind of portable aircraft that the utility model embodiment two provides
Structure schematic diagram；
Figure 13 is cuing open for the blade pose adjustment portion in a kind of portable aircraft that the utility model embodiment two provides
Depending on structural schematic diagram；
Figure 14 is that the structure of the rotor holder in a kind of portable aircraft that the utility model embodiment two provides is shown
It is intended to；
Figure 15 is the structure of the folding and unfolding take-off and landing device in a kind of portable aircraft that the utility model embodiment two provides
Schematic diagram.
Appended drawing reference:
The upper wing drop portion 131-；Wing drop portion under 132-；133- synchronising (connecting) rod；The anti-torsion link assembly of 134-；135-
Leaning device steering engine；136- steering engine kinematic link；137- steering engine driving rocker；138- leaning device steering engine bracket；139- inclination
Portion's connecting rod；
1311- rake inner ring；1312- rake outer ring；
000- fuselage；100- bispin swing device；200- folding and unfolding take-off and landing device；
The upper rotor mechanism of 110-；Rotor mechanism under 120-；130- rotor wing drop pitch-changing mechanism；140- central axis；
111- propeller hub；112- rotor blade；113- blade pose adjustment portion；114- rotor connecting rod；115- brushless motor；
116- motor cabinet；
1131- limiting fixed seat；1132- rotor holder；1133- connection horizontal axis；1134- sliding bearing；1135- positioning
Spring；
11321- limiting slot；11322- rotating base；11323- position limit arm；
230- buffers foot mechanism；
211- telescoping mechanism steering engine fixing seat；212- telescoping mechanism steering engine；213- sliding connector；214- sliding bearing；
221- first connecting rod；222- second connecting rod；223- third connecting rod；224- fourth link；The 5th connecting rod of 225-；226-
Six-bar linkage.
Specific embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, originally
Field those of ordinary skill every other embodiment obtained without making creative work belongs to practical
Novel protected range.
It is in the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is only
For ease of description the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have it is specific
Orientation, be constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.In addition, term " the
One ", " second ", " third " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Embodiment one:
In the optinal plan of the present embodiment, as shown in Figures 1 to 4, a kind of rotor wing drop provided in this embodiment
Pitch-changing mechanism, including upper wing drop portion 131, lower wing drop portion 132 and synchronising (connecting) rod 133；Upper wing drop portion 131 is under
Wing drop portion 132 is movably arranged on central axis 140, and upper wing drop portion 131 can be opposite with lower wing drop portion 132
It is tilted in the axis of central axis 140, and is moved along the axis direction of central axis 140；Upper wing drop portion 131 with it is lower from
Dynamic rake 132 is connected by synchronising (connecting) rod 133, and upper wing drop portion 131 can be simultaneously relative in lower wing drop portion 132
The axis of mandrel 140 is tilted, and is moved along the axis direction of central axis 140.
In the present embodiment, upper wing drop portion 131, company corresponding with the rotor mechanism of aircraft, lower wing drop portion 132
It connects, upper wing drop portion 131 can carry out tilting and in relative to the axis of central axis 140 with lower wing drop portion 132
The axis direction of mandrel 140 is mobile, and upper wing drop portion 131 is connect with lower wing drop portion 132 by synchronising (connecting) rod 133,
Inclination can be carried out relative to the axis of central axis 140 simultaneously and moved along the axis direction of central axis 140, can change up and down
Expansion amplitude and change two rotor mechanism the distance between of two rotor mechanisms being arranged relative to central axis 140, makes
The flight attitude for obtaining aircraft can be adjusted, and significantly reduced influence of the wind-force to flight, effectively ensured flight
The flight stability of device.
It further include leaning device steering engine 135 and leaning device steering engine bracket 138 in the optinal plan of the present embodiment；Incline
Oblique mechanism steering engine bracket 138 is fixed on central axis 140, and leaning device steering engine 135 is arranged in leaning device steering engine bracket
On 138；Upper wing drop portion 131 is connect by steering engine transmission component with leaning device steering engine 135；Upper wing drop portion 131 with
Lower wing drop portion 132 is located at the two sides up and down of leaning device steering engine bracket 138.
In the optinal plan of the present embodiment, steering engine transmission component includes sequentially connected steering engine kinematic link 136 and rudder
Machine driving rocker 137；Upper wing drop portion 131 is connect with steering engine kinematic link 136, steering engine driving rocker 137 and leaning device
Steering engine 135 connects.
In the present embodiment, leaning device steering engine 135 is driven by steering engine kinematic link 136 and steering engine driving rocker 137
Axis run-off the straight of the upper wing drop portion 131 relative to central axis 140, and moved along the axis direction of central axis 140, it is real
Now feathering between upper rotor mechanism 110 and lower rotor mechanism 120.
Preferably, leaning device steering engine 135 is arranged on leaning device steering engine bracket 138 by bolt.
In the optinal plan of the present embodiment, upper wing drop portion 131 includes rake inner ring 1311 and rake outer ring
1312；Rake inner ring 1311 is set on central axis 140 by oscillating bearing, and rake inner ring 1311 can be relative to central axis
140 axis is tilted to any direction；Rake outer ring 1312 is set in rake inner ring 1311；Rake inner ring
1311 are connect by steering engine transmission component with leaning device steering engine 135；Rake outer ring 1312 is used to connect with upper rotor mechanism 110
It connects.
In the present embodiment, oscillating bearing can be moved up and down along central axis 140, thus upper wing drop portion 131 and under
Wing drop portion 132 can be moved up and down along central axis 140.
Preferably, rake outer ring 1312 is set in rake inner ring 1311 by ball bearing.
In the present embodiment, rake inner ring 1311 is connect by steering engine kinematic link 136 with steering engine driving rocker 137,
And then it is connect with leaning device steering engine 135, that is to say, that rake inner ring 1311 is connect with leaning device steering engine 135.
In the optinal plan of the present embodiment, rake connecting rod 139 is provided in rake inner ring 1311；Rake inner ring
1311 are connect by rake connecting rod 139 with steering engine transmission component.
In the optinal plan of the present embodiment, lower wing drop portion 132 is identical as upper 131 structure of wing drop portion；Above certainly
The rake inner ring 1311 of dynamic rake 131 is connected with the rake inner ring 1311 in lower wing drop portion 132 by synchronising (connecting) rod 133
It connects；The rake outer ring 1312 in upper wing drop portion 131 with the propeller hub 111 of upper rotor mechanism 110 for connecting, lower wing drop
The rake outer ring 1312 in portion 132 with the propeller hub 111 of lower rotor mechanism 120 for connecting.
It further include anti-torsion link assembly 134 in the optinal plan of the present embodiment；Lower wing drop portion 132 passes through anti-torsion
Link assembly 134 is connect with central axis 140.
In the optinal plan of the present embodiment, anti-torsion link assembly 134 includes the sequentially connected first anti-torsion connecting rod and the
Two anti-torsion connecting rods；First anti-torsion connecting rod is connect with the second anti-torsion connecting rod at angle.
In the optinal plan of the present embodiment, the first anti-torsion connecting rod is connect with the second anti-torsion connecting rod by pin shaft；Pin shaft
Axis of the axis perpendicular to central axis 140.
In the optinal plan of the present embodiment, anti-one end for turning round link assembly 134 is connect with lower wing drop portion 132, is prevented
The other end for turning round link assembly 134 is connect with leaning device steering engine bracket 138.
In the present embodiment, the rake inner ring 1311 in anti-one end for turning round link assembly 134 and lower wing drop portion 132 connects
It connects, the anti-other end for turning round link assembly 134 is connect with leaning device steering engine bracket 138.
Embodiment two:
In the optinal plan of the present embodiment, as shown in Fig. 5 to Figure 15, a kind of portable flight provided in this embodiment
Device, including fuselage 000, bispin swing device 100 and folding and unfolding take-off and landing device 200:
Wherein, bispin swing device 100 includes upper rotor mechanism 110, lower rotor mechanism 120, central axis 140；
Bispin swing device 100 further includes the rotor wing drop pitch-changing mechanism 130 as described in embodiment one；
Upper rotor mechanism 110 is arranged on fuselage 000 by central axis 140 with lower rotor mechanism 120, upper rotor mechanism
110 can coaxially rotate backward with lower rotor mechanism 120 relative to central axis 140, so that this aircraft can be realized lifting, and on
Rotor mechanism 110 and lower rotor mechanism 120 can collapse and be unfolded, upper rotor mechanism 110, lower gyroplane relative to fuselage 000
Structure 120 can be inserted into the seam of fuselage 000 after collapsing, and improve the portability and ease for use of this aircraft；
On the centrally disposed axis 140 of rotor wing drop pitch-changing mechanism 130, rotor wing drop pitch-changing mechanism 130 is located at
Between upper rotor mechanism 110 and lower rotor mechanism 120, rotor wing drop pitch-changing mechanism 130 is for changing upper rotor mechanism 110
Expansion amplitude with lower rotor mechanism 120 relative to fuselage 000, and for changing upper rotor mechanism 110 and lower rotor mechanism
The distance between 120, this aircraft is realized longitudinally, laterally and vertically and horizontally compound movement in three-dimensional space, also,
The flight attitude that this aircraft can be adjusted is effectively reduced influence of the wind-force to flight, so that this aircraft resists wind-force
Ability is stronger, flies more steady；
Folding and unfolding take-off and landing device 200 includes telescoping mechanism and buffering foot mechanism 230；The centrally disposed axis in one end of telescoping mechanism
On 140, the other end of telescoping mechanism is arranged in buffering foot mechanism 230, and telescoping mechanism can be unfolded and receive relative to fuselage 000
Hold together.
In the present embodiment, upper rotor mechanism 110 and lower 120 coaxial reverse of rotor mechanism, can eliminate from torque, make
It is more steady to obtain the work of bispin swing device 100, has ensured the flight stability of this aircraft.
In the optinal plan of the present embodiment, upper rotor mechanism 110 includes propeller hub 111, blade pose adjustment portion 113, rotation
Wing blade 112 and rotor connecting rod 114；Propeller hub 111 is rotatably arranged on central axis 140；Rotor blade 112 passes through blade posture tune
Whole 113 connect with propeller hub 111；Propeller hub 111 is connect by rotor connecting rod 114 with rotor wing drop pitch-changing mechanism 130.
Further, the quantity in rotor blade 112 and blade pose adjustment portion 113 is multiple, and the quantity phase of the two
Together, multiple blade pose adjustments portion 113 is uniformly arranged along the circumferential direction of propeller hub 111.
Preferably, propeller hub 111 is connect by bearing with central axis 140.
In the optinal plan of the present embodiment, upper rotor mechanism 110 further includes brushless motor 115 and motor cabinet 116；Motor
Seat 116 is fixed on central axis 140；The stator of brushless motor 115 is connect with motor cabinet 116, the rotor of brushless motor 115
It is connect with propeller hub 111.
In the optinal plan of the present embodiment, blade pose adjustment portion 113 includes that limiting fixed seat 1131 and rotor are pressed from both sides
Seat 1132；Limiting fixed seat 1131 is arranged on propeller hub 111；One end of rotor holder 1132 is arranged by connection horizontal axis 1133
On limiting fixed seat 1131, rotor holder 1132 can be relative to the radial rotating of propeller hub 111, and along the diameter of propeller hub 111
To movement；The foldable other end that rotor holder 1132 is set of rotor blade 112.
In the present embodiment, for the foldable setting of rotor blade 112 on rotor holder 1132, rotor blade 112 can
It is folded relative to fuselage 000, rotor blade 112 is inserted into the seam of fuselage 000 after folding, and reduces this aircraft when not in use
Space hold, convenient for storage and transport etc., improve the portability and ease for use of this aircraft.
Further, rotor holder 1132 is socketed on connection horizontal axis 1133 by sliding bearing 1134, connection structure
Simply, the operation is stable.
Also, retaining spring 1135, one end of retaining spring 1135 and limiting fixed seat are arranged on connection horizontal axis 1133
1131 connections, the other end of retaining spring 1135 are connect with rotor holder 1132, and retaining spring 1135 is for limiting rotor
The relative position of holder 1132 and limiting fixed seat 1131.
Still further, rotor holder 1132 includes rotating base 11322 and limiting slot 11321；Rotating base 11322
One end be socketed on limiting fixed seat 1131；The other end of rotating base 11322 is arranged in limiting slot 11321.Rotating base
11322 are socketed on sliding bearing 1134, and rotating base 11322 can be slided and be rotated relative to limiting fixed seat 1131.
Also, rotor holder 1132 further includes position limit arm 11323；Rotating base 11322 is arranged in position limit arm 11323
One end, position limit arm 11323 is for limiting range of the rotating base 11322 on limiting fixed seat 1131.
Preferably, rotor blade 112 passes through the foldable other end that rotor holder 1132 is arranged in of shaft；Also, it revolves
The quantity of wing blade 112 is preferably 3, i.e., the sum of the blade of this aircraft is 6.
In the present embodiment, rotor blade 112 is unfolded, and adjusts posture, and retaining spring 1135 is matched with sliding bearing 1134
Cooperation is used, and rotor blade 112 and the relative position of limiting fixed seat 1131 are locked, and guaranteeing will not be because of rotor in flight course
112 position of leaf is unstable and safety accident occurs.
It should be noted that lower rotor mechanism 120 is identical as upper 110 structure of rotor mechanism, the diameter relative to central axis 140
To being symmetricly set on central axis 140.
In the optinal plan of the present embodiment, rotor wing drop pitch-changing mechanism 130 include upper wing drop portion 131, under
Wing drop portion 132 and synchronising (connecting) rod 133；Upper wing drop portion 131 is movably arranged on central axis with lower wing drop portion 132
On 140, upper wing drop portion 131 can be tilted with lower wing drop portion 132 relative to the axis of central axis 140, and
Axis direction along central axis 140 moves；Upper wing drop portion 131 is connected with lower wing drop portion 132 by synchronising (connecting) rod 133
Connect, upper wing drop portion 131 and lower wing drop portion 132 can the axis simultaneously relative to central axis 140 tilted, Yi Jiyan
The axis direction of central axis 140 is mobile；Upper rotor mechanism 110 is connect with upper wing drop portion 131, and lower rotor mechanism 120 is under
Wing drop portion 132 connects.
In the optinal plan of the present embodiment, rotor wing drop pitch-changing mechanism 130 further includes anti-torsion link assembly 134；
Lower wing drop portion 132 is connect by anti-torsion link assembly 134 with central axis 140.
Further, anti-torsion link assembly 134 includes the sequentially connected first anti-torsion connecting rod and the second anti-torsion connecting rod；First
Anti- torsion connecting rod and the second anti-torsion connecting rod are at angle；First anti-torsion connecting rod is connect with the second anti-torsion connecting rod by pin shaft, the axis of pin shaft
Axis of the line perpendicular to central axis 140.
In the optinal plan of the present embodiment, rotor wing drop pitch-changing mechanism 130 further include leaning device steering engine 135 and
Leaning device steering engine bracket 138；Leaning device steering engine bracket 138 is fixed on central axis 140, leaning device steering engine 135
It is arranged on leaning device steering engine bracket 138；Upper wing drop portion 131 passes through sequentially connected steering engine kinematic link 136 and rudder
Machine driving rocker 137 is connect with leaning device steering engine 135；Upper wing drop portion 131 is located at lower wing drop portion 132 to incline
The two sides up and down of oblique mechanism steering engine bracket 138.
In the present embodiment, leaning device steering engine 135 is driven by steering engine kinematic link 136 and steering engine driving rocker 137
Axis run-off the straight of the upper wing drop portion 131 relative to central axis 140, and moved along the axis direction of central axis 140, it is real
Existing 100 feathering of bispin swing device, that is, realize feathering between upper rotor mechanism 110 and lower rotor mechanism 120.
Preferably, leaning device steering engine 135 is arranged on leaning device steering engine bracket 138 by bolt.
Wherein, anti-one end for turning round link assembly 134 is connect with lower wing drop portion 132, anti-to turn round the another of link assembly 134
End is connect with leaning device steering engine bracket 138.
In the optinal plan of the present embodiment, upper wing drop portion 131 includes rake inner ring 1311 and rake outer ring
1312；Rake inner ring 1311 is set on central axis 140 by oscillating bearing, and rake inner ring 1311 can be relative to central axis
140 axis is tilted to any direction；Rake outer ring 1312 is set in rake inner ring 1311；Rake inner ring
1311 are connect by steering engine kinematic link 136 with steering engine driving rocker 137；Rake outer ring 1312 and upper rotor mechanism 110 connect
It connects.
In the present embodiment, oscillating bearing can be moved up and down along central axis 140, thus upper wing drop portion 131 and under
Wing drop portion 132 can be moved up and down along central axis 140.
Preferably, rake outer ring 1312 is set in rake inner ring 1311 by ball bearing.
Wherein, rake inner ring 1311 is connect by steering engine kinematic link 136 with steering engine driving rocker 137, so with incline
Oblique mechanism steering engine 135 connects, that is to say, that rake inner ring 1311 is connect with leaning device steering engine 135.
Further, rake connecting rod 139 is provided in rake inner ring 1311；Rake inner ring 1311 passes through rake
Connecting rod 139 is connect with steering engine kinematic link 136.
It should be noted that lower wing drop portion 132 is identical as upper 131 structure of wing drop portion；Upper wing drop portion 131
Rake inner ring 1311 and the rake inner ring 1311 in lower wing drop portion 132 connect by synchronising (connecting) rod 133；On incline automatically
The rake outer ring 1312 of inclined portion 131 is connect by rotor connecting rod 114 with the propeller hub 111 of upper rotor mechanism 110, lower wing drop
The rake outer ring 1312 in portion 132 is connect by rotor connecting rod 114 with the propeller hub 111 of lower rotor mechanism 120.
Also, anti-one end for turning round link assembly 134 is connect with the rake inner ring 1311 in lower wing drop portion 132, anti-torsion
The other end of link assembly 134 is connect with leaning device steering engine bracket 138.
Further, upper wing drop portion 131 further includes bulb mouth.
In the optinal plan of the present embodiment, telescoping mechanism includes sequentially connected second connecting rod 222, third connecting rod 223
And the 5th connecting rod 225；Second connecting rod 222 is connected on central axis 140, second connecting rod 222 can relative to fuselage 000 be unfolded and
It collapses；Buffering foot mechanism 230 is connected on the 5th connecting rod 225；Telescoping mechanism further include first connecting rod 221, fourth link 224 and
Six-bar linkage 226；One end of first connecting rod 221 is connected on second connecting rod 222, and the other end of first connecting rod 221 is connected to
On double leval jib 224, one end of fourth link 224 is connected on third connecting rod 223, and the other end of fourth link 224 is connected to
One end of six-bar linkage 226, the other end of six-bar linkage 226 are connected on the 5th connecting rod 225.
In the present embodiment, six hinged connecting rods constitute two parallelogram stretching structures；Also, it is interconnected
Connecting rod is realized by the structure type of pin shaft and shaft hole matching and is connected.
In the optinal plan of the present embodiment, buffering foot mechanism 230 includes buffering foot prop；Buffering foot prop is rotatably connected on the
On five connecting rods 225.
In the present embodiment, when this aircraft lands, buffering foot prop plays the role of bumper and absorbing shock.
Further, buffering foot prop is connect with the 5th connecting rod 225 by pin shaft；Torque spring, torsion are arranged on pin shaft
One end of spring is connect with buffering foot prop, and the other end of torque spring is connect with the 5th connecting rod 225.
In the present embodiment, buffering foot prop can be rotated relative to the 5th connecting rod 225, and be resetted after rotation.
Still further, folding and unfolding take-off and landing device 200 further includes Power Component, Power Component is used to provide it to telescoping mechanism
The power for being unfolded relative to fuselage 000 and collapsing.
Also, Power Component include telescoping mechanism steering engine 212, telescoping mechanism steering engine fixing seat 211, sliding bearing 214 and
Sliding connector 213；Telescoping mechanism steering engine fixing seat 211 is fixed on central axis 140；The one of telescoping mechanism steering engine 212
End is arranged in telescoping mechanism steering engine fixing seat 211, and telescoping mechanism steering engine 212 can provide the axis side for being parallel to central axis 140
To power；Sliding bearing 214 is set on central axis 140, and sliding bearing 214 is another with telescoping mechanism steering engine 212 simultaneously
End connection, sliding bearing 214 can be under the drives of telescoping mechanism steering engine 212 along the axial direction up and down motion of central axis 140；Sliding connects
One end of fitting 213 is movably arranged on sliding bearing 214, and the other end of sliding connector 213 is connected on telescoping mechanism, sliding
Follower link 213 is moved with sliding bearing 214 to drive telescoping mechanism to be unfolded and collapse relative to fuselage 000.
Wherein, one end of second connecting rod 222 and telescoping mechanism steering engine fixing seat 211 are rotatablely connected, second connecting rod 222 it is another
One end and third connecting rod 223 and first connecting rod 221 are rotatablely connected.
Also, one end of sliding connector 213 and sliding bearing 214 are rotatablely connected, the other end of sliding connector 213 with
First connecting rod 221 is rotatablely connected.
In the present embodiment, sliding bearing 214 is under the drive of telescoping mechanism steering engine 212 in the axial direction of central axis 140
Lower movement, then drive telescoping mechanism to be unfolded and collapse relative to fuselage 000 by sliding connector 213.
After this aircraft takeoff, the telescoping mechanism steering engine 212 of Power Component is moved down, so that sliding connector 213
The slide downward on central axis 140, so that first connecting rod 221 is moved down with sliding connector 213, so that first
Connecting rod 221 rotates, and the other end of first connecting rod 221 moves up, i.e., the other end of first connecting rod 221 tilts, first connecting rod
221 pull the one of one end of second connecting rod 222 and the connection of third connecting rod 223 and fourth link 224 and the connection of the 5th connecting rod 225
End moves up, and the distance that fourth link 224 moves up connects less than the distance that the 5th connecting rod 225 moves up, the 6th
The other end of bar 226 tilts, and in the horizontal direction upwards, first connecting rod 221, second connecting rod 222, third connecting rod the 223, the 4th
Connecting rod 224, the 5th connecting rod 225 are mobile to fuselage 000, and final folding and unfolding take-off and landing device 200 is folded in the seam of fuselage 000,
During aircraft is taken photo by plane, the visual field of taking photo by plane will not be blocked.When the landing of this aircraft, the telescoping mechanism steering engine of Power Component
212 move up, so that the upward sliding on central axis 140 of sliding connector 213, so that first connecting rod 221 and sliding
Connector 213 moves up, so that first connecting rod 221 rotates, and the other end of first connecting rod 221 is moved down, i.e., and the
The other end of one connecting rod 221 is sagging, one end that first connecting rod 221 pulls second connecting rod 222 and third connecting rod 223 to connect and the
One end of double leval jib 224 and the connection of the 5th connecting rod 225 moves down, and the distance that moves down of fourth link 224 is less than the
The distance that five connecting rods 225 move down, six-bar linkage 226 and buffer foot mechanism 230 one end it is sagging, and in the horizontal direction to
On, first connecting rod 221, second connecting rod 222, third connecting rod 223, fourth link 224, the 5th connecting rod 225 are towards far from fuselage 000
Direction it is mobile, buffering foot mechanism 230 becomes the minimum point of aircraft, in aircraft landing with ground face contact, bumper and absorbing shock.
It should be noted that being provided with mission payload, flight control system, smart battery system on fuselage 000；Task carries
Lotus is mounted on the lower end of fuselage 000, and according to the needs of task, mission payload can be changed the outfit as photoelectric nacelle, first-aid medicine packet, be answered
The load such as anxious communication equipment；Flight control system is used to control brushless motor 115, the rotor wing drop of bispin swing device 100
The leaning device steering engine 135 of pitch-changing mechanism 130 and the telescoping mechanism steering engine 212 of folding and unfolding take-off and landing device 200 work；Intelligent battery
The two sides up and down of bispin swing device 100 are set to symmetry system having symmetry, and are connect by central axis 140 with motor cabinet 116, for for
The brushless motor 115 of bispin swing device 100, the leaning device steering engine 135 of rotor wing drop pitch-changing mechanism 130 and folding and unfolding rise
The telescoping mechanism steering engine 212 of dropping control device 200 is powered, and smart battery system includes upper battery pack, lower battery pack and battery house keeper.This
Outside, this aircraft further includes mission payload installing mechanism, and mission payload installing mechanism includes load portion, and load portion is hung for mounting
Cabin is convenient for quick despatch, also, is equipped with SOS alarm on mission payload installing mechanism, makes a sound when beyond specified counterweight
And optical alert.
In conclusion the course of work of this portable aircraft is as follows:
Aircraft rises or falls, and folding and unfolding take-off and landing device 200 lands, and fuselage 000 is perpendicular to the ground, bispin swing device
100 two groups of brushless motors 115 drive two groups of coaxial reverse rotations of rotor blade 112, and pushing air to generate thrust makes this flight
Device takes off vertically；Change thrust size by adjusting the revolving speed of two groups of brushless motors 115, control aircraft rises or falls winged
Row；
Aircraft changes course, and controls two groups of rotor blades 112 by two groups of brushless motors 115 and carries out differential speed rotation,
Yawing, the heading of change of flight device are provided using the reaction torque difference of two groups of rotor blades 112 for this aircraft；
The longitudinal direction of aircraft or/and horizontal flight adjust three steering engine kinematic links by three leaning device steering engines 135
136 relative position, such as a steering engine kinematic link 136 moves downward, other two steering engine kinematic link 136 is transported upwards
It is dynamic, so that upper wing drop portion 131, lower wing drop portion 132 synchronize inclination in the same direction, remain parastate, rotor connecting rod
114 drive upper rotor mechanism 110, lower rotor mechanism 120 therewith, so that the rotor of upper rotor mechanism 110, lower rotor mechanism 120
Blade 112 changes different angle in each swing circle, realizes the longitudinal direction or/and transverse shifting of this aircraft.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should
Understand: it is still possible to modify the technical solutions described in the foregoing embodiments, or to some or all of
Technical characteristic is equivalently replaced；And these are modified or replaceed, it does not separate the essence of the corresponding technical solution, and this is practical new
The range of each embodiment technical solution of type.
Claims (10)
1. a kind of rotor wing drop pitch-changing mechanism, which is characterized in that including upper wing drop portion (131), lower wing drop portion
(132) and synchronising (connecting) rod (133)；
The upper wing drop portion (131) and the lower wing drop portion (132) are movably arranged on central axis (140), institute
Stating wing drop portion (131) can incline with the lower wing drop portion (132) relative to the axis of central axis (140)
Tiltedly, and it is mobile along the axis direction of central axis (140)；
The upper wing drop portion (131) is connect with the lower wing drop portion (132) by the synchronising (connecting) rod (133), institute
Stating wing drop portion (131) and the lower wing drop portion (132) can incline relative to the axis of central axis (140) simultaneously
Tiltedly, and it is mobile along the axis direction of the central axis (140).
2. rotor wing drop pitch-changing mechanism according to claim 1, which is characterized in that further include leaning device steering engine
(135) and leaning device steering engine bracket (138)；
The leaning device steering engine bracket (138) is fixed on central axis (140), and the leaning device steering engine (135) sets
It sets on the leaning device steering engine bracket (138)；
The upper wing drop portion (131) is connect by steering engine transmission component with the leaning device steering engine (135)；
The upper wing drop portion (131) and the lower wing drop portion (132) are located at the leaning device steering engine bracket
(138) two sides up and down.
3. rotor wing drop pitch-changing mechanism according to claim 2, which is characterized in that the steering engine transmission component includes
Sequentially connected steering engine kinematic link (136) and steering engine driving rocker (137)；
The upper wing drop portion (131) connect with the steering engine kinematic link (136), the steering engine driving rocker (137) with
Leaning device steering engine (135) connection.
4. rotor wing drop pitch-changing mechanism according to claim 2, which is characterized in that the upper wing drop portion
It (131) include rake inner ring (1311) and rake outer ring (1312)；
The rake inner ring (1311) is set on central axis (140) by oscillating bearing, the rake inner ring (1311)
It can be tilted relative to the axis of central axis (140) to any direction；
The rake outer ring (1312) is set on the rake inner ring (1311)；
The rake inner ring (1311) is connect by the steering engine transmission component with the leaning device steering engine (135)；
The rake outer ring (1312) with upper rotor mechanism (110) for connecting.
5. rotor wing drop pitch-changing mechanism according to claim 4, which is characterized in that the rake inner ring (1311)
On be provided with rake connecting rod (139)；
The rake inner ring (1311) is connect by the rake connecting rod (139) with the steering engine transmission component.
6. rotor wing drop pitch-changing mechanism according to claim 4 or 5, which is characterized in that the lower wing drop portion
(132) identical as upper wing drop portion (131) structure；
The rake inner ring (1311) of the upper wing drop portion (131) is described with the lower wing drop portion (132)
Rake inner ring (1311) is connected by the synchronising (connecting) rod (133)；
The rake outer ring (1312) of the upper wing drop portion (131) is for the propeller hub with upper rotor mechanism (110)
(111) it connects, the rake outer ring (1312) of the lower wing drop portion (132) is used for and lower rotor mechanism (120)
Propeller hub (111) connection.
7. rotor wing drop pitch-changing mechanism according to claim 2, which is characterized in that further include anti-torsion link assembly
(134)；
The lower wing drop portion (132) is connect by the anti-torsion link assembly (134) with central axis (140).
8. rotor wing drop pitch-changing mechanism according to claim 7, which is characterized in that the anti-torsion link assembly
It (134) include the sequentially connected first anti-torsion connecting rod and the second anti-torsion connecting rod；
The first anti-torsion connecting rod is connect with the described second anti-torsion connecting rod at angle.
9. rotor wing drop pitch-changing mechanism according to claim 8, which is characterized in that the first anti-torsion connecting rod and institute
The second anti-torsion connecting rod is stated to connect by pin shaft；
Axis of the axis of the pin shaft perpendicular to central axis (140).
10. rotor wing drop pitch-changing mechanism according to claim 7, which is characterized in that the anti-torsion link assembly
(134) one end is connect with the lower wing drop portion (132), and the anti-other end for turning round link assembly (134) inclines with described
Oblique mechanism steering engine bracket (138) connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822212958.3U CN209427023U (en) | 2018-12-26 | 2018-12-26 | Rotor wing drop pitch-changing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822212958.3U CN209427023U (en) | 2018-12-26 | 2018-12-26 | Rotor wing drop pitch-changing mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN209427023U true CN209427023U (en) | 2019-09-24 |
Family
ID=67974034
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822212958.3U Expired - Fee Related CN209427023U (en) | 2018-12-26 | 2018-12-26 | Rotor wing drop pitch-changing mechanism |
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| Country | Link |
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| CN (1) | CN209427023U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979652A (en) * | 2019-12-26 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Two-steering engine direct-drive coaxial rotor system and control strategy |
| CN110979653A (en) * | 2019-12-28 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Three-steering-engine coaxial dual-rotor system and control strategy thereof |
| CN111003167A (en) * | 2019-12-28 | 2020-04-14 | 湖南韬讯航空科技有限公司 | Two-steering engine coaxial dual-rotor system and control strategy |
-
2018
- 2018-12-26 CN CN201822212958.3U patent/CN209427023U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979652A (en) * | 2019-12-26 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Two-steering engine direct-drive coaxial rotor system and control strategy |
| CN110979652B (en) * | 2019-12-26 | 2021-06-08 | 苏州韬讯航空科技有限公司 | Two-steering engine direct-drive coaxial rotor system and control strategy |
| CN110979653A (en) * | 2019-12-28 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Three-steering-engine coaxial dual-rotor system and control strategy thereof |
| CN111003167A (en) * | 2019-12-28 | 2020-04-14 | 湖南韬讯航空科技有限公司 | Two-steering engine coaxial dual-rotor system and control strategy |
| CN111003167B (en) * | 2019-12-28 | 2021-09-28 | 湖南韬讯航空科技有限公司 | Two-steering engine coaxial dual-rotor system and control strategy |
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