CN108438204A - Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying - Google Patents
Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying Download PDFInfo
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- CN108438204A CN108438204A CN201810486484.3A CN201810486484A CN108438204A CN 108438204 A CN108438204 A CN 108438204A CN 201810486484 A CN201810486484 A CN 201810486484A CN 108438204 A CN108438204 A CN 108438204A
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000007246 mechanism Effects 0.000 claims abstract description 36
- 238000011017 operating method Methods 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 4
- 238000003756 stirring Methods 0.000 claims description 4
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims 1
- 230000009471 action Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 14
- 238000009434 installation Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
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- 238000003032 molecular docking Methods 0.000 description 1
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Classifications
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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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses vertical take-off and landing drone rotor foldable structure and its folding and method of deploying, which includes：Head case, two head connecting rods, two tail portion connecting rods, head connecting rod and tail portion connecting rod are by connecting and self-locking mechanism connects, at least provided with a rotor above and below each head connecting rod and tail portion connecting rod.The method for folding includes step 1：Position rotor；Step 2：The tail end of tail portion connecting rod is removed, around connection and self-locking mechanism rotating tail connecting rod, it is made to be aligned with head connecting rod；Step 3：Connection and self-locking mechanism are removed, and connection and self-locking mechanism is close towards unmanned drive end unit.The method of deploying is opposite with method for folding.The present invention is folding structure, is carried after folding, and carrying, transportation cost are reduced, rotor provides upward motive force to vertical take-off and landing drone, the stationarity for improving vertical take-off and landing drone, increases the operability of vertical take-off and landing drone, and operable action is more.
Description
Technical field
The present invention relates to vertical take-off and landing drone rotor foldable structure and its folding and method of deploying, belong to VTOL without
Man-machine technical field.
Background technology
In the 16th Beijing international airline exhibition in 2015, the VD200 vertical take-off and landing drone that Air China puts on display causes common people
Greatly concern.It is said that VD200 possesses world-leading VTOL system, it can as helicopter VTOL and
High-speed horizontal flight is carried out in the way of fixed-wing.British media thinks to compare with an equal amount of unmanned helicopter, and Flying-wing sets
Meter enables VD200 in load and performance, all has advantage.
Currently, unmanned plane is the indispensable Intelligence, Surveillance, and Reconnaissance platform of army, the navy and the air force.For naval, due to
It is limited by earth curvature, general the shipborne radar only low latitude in detectable about 40 kilometers or sea-surface target, and farther place is low
Empty or sea-surface target, then completely by horizon（Also it is skyline）It is blocked, is hung down as VD200 so China can develop
Straight landing unmanned plane is significant.
But current vertical take-off and landing drone increases rotor using adding structural not yet, the rotor of unmanned plane is equal
It is integrally fixed on fuselage, alternatively, most of at present is all directly before and after wing plus to go out rotor, needs to change in rotor again
The structure and avionics system in portion bring significant limitation since the own form of fuselage is limited to research and development.
Invention content
Above-mentioned in order to solve the problems, such as, the invention discloses vertical take-off and landing drone rotor foldable structure and its foldings
And method of deploying, break Traditional Thinking, provide through adding structural, more rotors are provided to unmanned plane, to flying for unmanned plane
Row brings more operability, specific technical solution as follows：
Vertical take-off and landing drone rotor foldable structure, including：
For the head case mounted on vertical take-off and landing drone Handpiece Location；
Two head connecting rods, front end can rotationally be connected to the both sides of head case respectively；
Two tail portion connecting rods, front end can rotationally be connected to the tail end of head connecting rod respectively；One head connecting rod and a tail
Portion's connecting rod connection, and it is symmetrically positioned in the horizontal both sides of vertical take-off and landing drone；
Several rotors, at least provided with a rotor above and below each head connecting rod and tail portion connecting rod.
Every head connecting rod and tail portion connecting rod are respectively provided with there are two rotor, and the connection of close head connecting rod and tail portion connecting rod
The rotor at place is arranged at the lower section of head connecting rod and tail portion connecting rod, and other rotors are arranged in the upper of head connecting rod or tail portion connecting rod
Side.
The head connecting rod and tail portion connecting rod are connected by connection and self-locking mechanism, and the connection and self-locking mechanism include：
It is fixedly connected with framework, for connecting tail portion connecting rod；
Be rotatably connected framework, for connecting head connecting rod；
Rotary shaft, rotary shaft are fixedly connected with framework is fixedly connected with, and rotatable connection framework can rotate around the axis of rotation,
Postive stop baffle, is fixedly connected in framework and rotatable connection framework and is both provided with postive stop baffle, and postive stop baffle is solid for limiting
Surely connection framework and the framework that is rotatably connected can rotate the angle of arrival；
It is provided with from lock barrel below two middle part wings of vertical take-off and landing drone, the rotary shaft is inserted into self-locking
In sleeve, and it is locked with self-locking sleeve after directional-rotation.
The rotary shaft is relatively set with two radially-protruding lock pillars close to its top,
It is described from lock barrel towards rotary shaft one end setting there are two lock road, the lock road from the rim openings from lock barrel simultaneously
It is tilted towards self-locking circumference, the diameter of lock pillar is no more than the width for locking road, during rotary shaft is inserted from lock barrel, two
A lock pillar can enter lock road from the opening in lock road simultaneously, and the roads Bing Yusuo are locked.
Vertical take-off and landing drone is provided with tail portion connecting pole in the middle part of its empennage, and the tail end of described two tail portion connecting rods is equal
It is fixed with tail portion connecting pole.
The framework and the top for the framework that is rotatably connected of being fixedly connected is in circular arc curved shape, described to be fixedly connected with framework
With the top overlapping of rotatable connection framework, the rotary shaft runs through the lap, will be fixedly connected with framework and rotatable connection structure
Frame connects.
The framework that is fixedly connected includes two parallel connecting plates I, and the top of two connecting plates I connects with rotary shaft
It connects, tail portion is provided with support plate I, and described two connecting plates I fix parallel, described two connecting plates I with support plate I by rotary shaft
Between be provided with postive stop baffle I；
The rotatable connection framework includes two parallel connecting plates II, the tops of two connecting plates II with rotation axis connection,
Tail portion is provided with support plate II, and described two connecting plates II fix parallel, described two connecting plates with support plate II by rotary shaft
Postive stop baffle II is provided between II；
The outside of circular arc curved shape of the one end of the postive stop baffle I beyond connecting plate I, the other end is without departing from connecting plate I
The inside of circular arc curved shape；
The outside of circular arc curved shape of the one end of postive stop baffle II beyond connecting plate II, circle of the other end without departing from connecting plate II
The inside of arc curved shape；
The center of the support plate I and postive stop baffle I offers circular hole I, and tail portion connecting rod passes through circular hole I, and is secured to；
The center of the support plate II and postive stop baffle II offers circular hole II, and head connecting rod passes through circular hole II, and solid with it
It is fixed.
Shape, front end extend to the outside extension to the head connecting rod from itself and head case junction in obtuse angle, extend super
After crossing head case, the linear parallel with VTOL aircraft fuselage is bent, the tail portion connecting rod is linear.
Vertical take-off and landing drone is provided with tail portion connecting pole in the middle part of its empennage, and the tail end of described two tail portion connecting rods is equal
It is fixed with tail portion connecting pole..
The structure of the method for folding of vertical take-off and landing drone rotor, the vertical take-off and landing drone rotor is for example above-mentioned, including with
Lower operating procedure：
Step 1：Position rotor：Stir rotor so that rotor is parallel with corresponding head connecting rod and tail portion connecting rod, and rotor is consolidated
It is fixed, no longer rotate；
Step 2：Remove the tail end of tail portion connecting rod：The tail end of tail portion connecting rod is removed from the connecting pole of tail portion, and towards outside fuselage
Side rotating tail connecting rod, until tail portion connecting rod is aligned with head connecting rod；
Step 3：Remove connection and self-locking mechanism：The rotary shaft of connection and self-locking mechanism is rotated from from lock barrel and is removed, and
Towards airplane tail group pull connection and self-locking mechanism, until head connecting rod and tail portion connecting rod be adjacent to fuselage it is parallel；
Step 4：Step 2 and step 3 are repeated, the head connecting rod of the aircraft other side and tail portion connecting rod are removed.
The structure of the method for deploying of vertical take-off and landing drone rotor, the vertical take-off and landing drone rotor is for example above-mentioned, and uses
The method stated, which folds, to be completed, including following operating procedure：
Step（1）：Securement head case：By head cover valve jacket on the head of vertical take-off and landing drone so that two groups of heads connect root
The both sides of fuselage are symmetrically positioned in tail portion connecting rod, and positioned at the lower section of wing；
Step（2）：The head connecting rod and tail portion connecting rod of fuselage side are installed：The connection and self-locking of the side are pulled towards fuselage outer side
Mechanism, head connecting rod and tail portion connecting rod synchronous rotary, until connection and self-locking mechanism be moved to the side below the lock barrel, will
Connection and the lock pillar precession of self-locking mechanism are from the lock road of lock barrel, then tail portion connecting rod end annulus is pulled to fly towards VTOL
The tail portion of machine is moved, until the realization maximum angle limit of the lock pillar of connection and self-locking mechanism, at this point, the tail end of tail portion connecting rod is rigid
It is located at the lower section of airplane tail group well, tail portion connecting rod is fixed on the connecting pole of tail portion；
Step（3）：The head connecting rod and tail portion connecting rod of the fuselage other side are installed：Repeat step（2）By the head of the fuselage other side
Connecting rod and the expansion of tail portion connecting rod, and it is fixed.
The beneficial effects of the invention are as follows：
Structure of the invention is folding structure, is carried after folding, more convenient, easy to carry, substantially reduce carrying, transport at
This, and substantially reduce collsion damage of the rotor in carrying, transportational process..
Structure of the invention is respectively to increase by two rotors before and after the middle part wing of vertical take-off and landing drone, and close to middle part machine
The rotor of the wing is located at below wing, and upward motive force is provided to vertical take-off and landing drone, respectively has close to head and seat in the plane position
Two upward rotors, improve the stationarity of vertical take-off and landing drone.
The more traditional vertical take-off and landing drone of structure of the invention is additionally arranged eight rotors, increases vertical take-off and landing drone
Operability, can control more flexiblely vertical take-off and landing drone flying speed, flight turning and other flight skills
Can, operable action is more.
The present invention can be fitted in existing vertical take-off and landing drone, be made according to the specification of vertical take-off and landing drone
The structure of the invention of corresponding specification is made, it is applied widely.
Description of the drawings
Fig. 1 is the structural schematic diagram of structure of the invention folded state,
Fig. 2 is the vertical view state figure that structure of the invention is mounted in vertical take-off and landing drone,
Fig. 3 is that structure of the invention looks up state diagram in vertical take-off and landing drone,
Fig. 4 is the state diagram after Fig. 2 expansion,
Fig. 5 is the state diagram after Fig. 3 expansion,
Fig. 6 is usage state diagram of the present invention,
Fig. 7 is the structural schematic diagram of connection and self-locking mechanism,
Fig. 8 is to be fixedly connected with frame and the structural schematic diagram of rotary shaft,
Fig. 9 is the stereogram of Fig. 7,
Reference numerals list：1-head case, 2-head connecting rods, 3-rotors, 4-connections and self-locking mechanism, 5-tail portions connect
Bar, 6-unmanned planes, 7-wings, 8-tail portion connecting poles, 9-from lock barrel, and 10-connection rings, 11-rotary shafts, 12-connect
Plate II, 13-rotatable connection frameworks, 14-postive stop baffles I, 15-circular holes I, 16-support plates I, 17-connecting plates I, Gu 18-
Surely framework, 19-lock pillars, 20-lock roads, 21-support plates II are connected.
Specific implementation mode
With reference to the accompanying drawings and detailed description, the present invention is furture elucidated.It should be understood that following specific implementation modes are only
For illustrating the present invention rather than limiting the scope of the invention.
" preceding " alleged by the present invention refers to direction of advance when unmanned plane normal flight, otherwise is " rear "；
When "upper" alleged by the present invention refers to unmanned plane normal flight, the top for being located at the vertical direction of unmanned plane is "upper", instead
Be "lower".
Fig. 1 is the structural schematic diagram of structure of the invention folded state, and Fig. 2 is structure of the invention mounted on vertical take-off and landing unmanned
Vertical view state figure on machine, Fig. 3 are that structure of the invention looks up state diagram in vertical take-off and landing drone, and Fig. 4 is Fig. 2 exhibitions
State diagram after opening, Fig. 5 are the state diagrams after Fig. 3 expansion, and Fig. 6 is usage state diagram of the present invention, and Fig. 7 is connection and self-locking mechanism
Structural schematic diagram, Fig. 8 is to be fixedly connected with frame and the structural schematic diagram of rotary shaft, and reference numeral component names are followed successively by：1—
Head case, 2-head connecting rods, 3-rotors, 4-connections and self-locking mechanism, 5-tail portion connecting rods, 6-unmanned planes, 7-wings,
8-tail portion connecting poles, 9-from lock barrel, 10-connection rings, 11-rotary shafts, 12-connecting plates II, 13-rotatable connection structures
Frame, 14-postive stop baffles I, 15-circular holes I, 16-support plates I, 17-connecting plates I, 18-are fixedly connected with framework, 19-lock pillars,
20-lock roads.
6 rotor of this vertical take-off and landing drone, 3 foldable structure, which, which can fold, is tightly attached to VTOL
Behind the symmetrical both sides of standard of fuselage of unmanned plane 6, and opening, formed along the symmetrical quadrangle of fuselage, in vertical take-off and landing drone 6
Two middle part wings 7 front and back there are two rotor 3.The increase of rotor 3 vertical take-off and landing drone 6, which is taken off and put down, to fly
Power in the process increases the stationarity in descent, makes 6 fuselage of vertical take-off and landing drone more steady, avoid turning on one's side, especially
When it is 6 loading of vertical take-off and landing drone transport, the stationarity of flight is extremely important.
3 foldable structure of rotor includes 1, two head connecting rod 2 of head case and two tail portion connecting rods 5, the head cover
Shell 1 is used to cover on the head of vertical take-off and landing drone 6, which is fixed with vertical take-off and landing drone 6, two
The head connecting rod 2 is symmetrically positioned in the horizontal both sides of head case 1, and the front end of head connecting rod 2 is connect with head case 1, head
The tail end of connecting rod 2 is riveted with the front end of tail portion connecting rod 5, and the head connection is connected with tail portion can surround arbitrary rotation at its riveting
Turn, the head connecting rod 2 and tail portion connecting rod 5 are respectively provided with there are two rotor 3, and close head connecting rod 2 and 5 junction of tail portion connecting rod
Rotor 3 be located at the lower section of corresponding head connecting rod 2 or tail portion connecting rod 5, other rotors 3 be located at corresponding head connecting rod 2 or
The top of tail portion connecting rod 5.Head connecting rod 2 and tail portion connecting rod 5 provide installation fulcrum to rotor 3, and give rotor 3 and VTOL
The internal control system connecting line of unmanned plane 6 has a rigid support, it is ensured that and during high-speed flight, connecting line will not loosen,
The installation point of rotor 3 is firm, will not be destroyed there is a phenomenon where rotor 3 or out of control.Meanwhile head connecting rod 2 and tail portion connecting rod 5 can
Rotary folding is fixed to being mutually parallel convenient for limit at its riveting, and occupied space is also minimum.
Shape, front end extend to the outside extension to the head connecting rod 2 from itself and 1 junction of head case in obtuse angle, extend
After head case 1, the linear parallel with VTOL aircraft fuselage is bent, the tail portion connecting rod 5 is linear.Head
The structure of connecting rod 2 avoids contact with abrasion, and in reality in order to ensure after folding, head connecting rod 2 does not touch head case 1
Now connection head is to wing 7, and material most saves, and path is most short, and the shape of tail portion connecting rod 5 is most saved also for material, and path is most short.
The support of head connecting rod 2 and tail portion connecting rod 5 is opened, and is formed quadrangle form, is allowed rotor 3 is fully dispersed to open, provide
More balanced motive force.
Structure of the invention is integrally located at the lower section of wing 7, be on the one hand it is easy for installation, on the other hand, from VTOL without
Analyzed in man-machine 6 flight theory, from the lower section of wing 7, with its be in the end of wing 7 from the straight line on tail portion and head,
And height is not higher than the position of 7 height of wing, is capable of providing the most effective motive force of highest.
The head connecting rod 2 and tail portion connecting rod 5 are connected by connection and self-locking mechanism 4, and the connection and self-locking mechanism 4 wrap
It includes：For connect tail portion connecting rod 5 be fixedly connected framework 18, the rotatable connection framework 13 for connecting head connecting rod 2 and rotation
Axis 11, rotary shaft 11 are fixedly connected with framework 18 is fixedly connected with, and rotatable connection framework 13 can surround rotary shaft 11 and rotate.Only
There is rotatable connection framework 13 that can surround rotary shaft 11 to rotate, and be fixedly connected with framework 18 and be fixedly connected with rotary shaft 11, works as rotation
Lock pillar 19 in shaft 11 need precession lock road 20, or from lock road 20 in screw out when, it is only necessary to firmly stir and be fixedly connected with structure
Frame 18 can be realized as, ingenious in design, easy to use.
It is fixedly connected in framework 18 and rotatable connection framework 13 and is both provided with postive stop baffle, postive stop baffle is for limiting fixation
Connection framework 18 and the framework 13 that is rotatably connected can rotate the angle of arrival.During foldable structure of the present invention is in expansion,
After head connecting rod 2 is fixed, when pulling tail portion connecting rod 5, tail portion connection is rotated to be contradicted with postive stop baffle, draws motionless position
It sets, is just just that tail portion pull rod can be with 8 fixed position of tail portion connecting pole.So that the position of positioning tail portion connecting rod 5 is more just
It is prompt, quick.
The framework 18 and the top for the framework 13 that is rotatably connected of being fixedly connected is in circular arc curved shape, described to be fixedly connected
The top overlapping of framework 18 and rotatable connection framework 13, the rotary shaft 11 run through the lap, will be fixedly connected with framework
18 connect with rotatable connection framework 13.Circular arc curved shape allows head connecting rod 2 and tail portion connecting rod 5 after the completion of folding, mutually
Between have a certain distance, give rotor 3 certain storage gap, after the completion of avoiding folding, the rotor 3 on head connecting rod 2 rubs
It touches the friction of the rotor 3 on tail portion connecting rod 5 and tail portion connecting rod 5 and touches head connecting rod 2.
The rotary shaft 11 is relatively set with two radially-protruding lock pillars 19 close to its top, described from 9 court of lock barrel
To the setting of one end of rotary shaft 11 there are two road 20 is locked, the lock road 20 is from the rim openings from lock barrel 9 and direction is from lock tube
9 circumference tilts of cylinder, the diameter of lock pillar 19 is no more than the width for locking road 20, during rotary shaft 11 is inserted from lock barrel 9, two
Lock pillar 19 can enter lock road 20 from the opening in lock road 20 simultaneously, and the roads Bing Yusuo 20 are locked.
The lower section of two middle part wings 7 of vertical take-off and landing drone 6 is provided with from lock barrel 9, and the rotary shaft 11 can
It is inserted into from lock barrel 9, and is locked with from lock barrel 9 after directional-rotation.In use, 7 lower surface of wing in unmanned plane 6 is opened
Hole will be inserted into from one end of lock barrel 9 in trepanning in one connection ring 10 of circumference fixing sleeve or connector from lock barrel 9,
And will be fixed in trepanning from lock barrel 9 by connection ring 10 or connector, the leakage of lock road 20 is outside wing 7.
Vertical take-off and landing drone 6 is provided with tail portion connecting pole 8, the tail of described two tail portion connecting rods 5 in the middle part of its empennage
End is fixed with tail portion connecting pole 8.The end of the tail portion connecting rod 5 is provided with annulus, and the tail portion connecting pole 8 is inserted into
In annulus, connecting pole 8 end in tail portion is equipped with expanded spheres, prevents annulus from falling off.The structure is for ease of realization, and material most saves
Connection type.
One embodiment as the concrete structure for being fixedly connected with framework 18 and the framework 13 that is rotatably connected in the present invention：
The framework 18 that is fixedly connected includes two parallel connecting plates I 17, the tops of two connecting plates I 17 with rotation
Axis 11 connects, and tail portion is provided with support plate I 16, and described two connecting plates I 17 are fixed flat by rotary shaft 11 and support plate I 16
It goes, postive stop baffle I 14 is provided between described two connecting plates I 17.
The rotatable connection framework 13 includes two parallel connecting plates II 12, the tops of two connecting plates II 12 with
Rotary shaft 11 connects, and tail portion is provided with support plate II, and described two connecting plates II 12 are fixed flat by rotary shaft 11 and support plate II
It goes, postive stop baffle II is provided between described two connecting plates II 12.
One end of the postive stop baffle I 14 beyond connecting plate I 17 circular arc curved shape outside, the other end without departing from
The inside of the circular arc curved shape of connecting plate I 17.
The outside of circular arc curved shape of the one end of postive stop baffle II beyond connecting plate II 12, the other end is without departing from connection
The inside of the circular arc curved shape of plate II 12.
The center of the support plate I 16 and postive stop baffle I 14 offers circular hole I 15, and tail portion connecting rod 5 passes through circular hole I
15, and be secured to.
The center of the support plate II and postive stop baffle II offers circular hole II, and head connecting rod 2 passes through circular hole II, and with
It is fixed.
Be fixedly connected framework 18 and rotatable connection framework 13 in the embodiment are built by multiple plates, and consumptive material is few,
Tail portion connecting rod 5 and head connecting rod 2 can be fixed, stable structure, total quality is light.And for the ease of in actual fabrication, support plate
II, postive stop baffle II, support plate I 16 and postive stop baffle I 14 are docked by symmetrical two panels, they are to have two in this way
The completely the same two sheets docking fixation of a structure forms, and when making, it is few to make number of molds, and installation is shared everything, more anxious
Fast.
The structure of the method for folding of vertical take-off and landing drone rotor, the vertical take-off and landing drone rotor is for example above-mentioned, including with
Lower operating procedure：
Step 1：Position rotor：Stir rotor so that rotor is parallel with corresponding head connecting rod and tail portion connecting rod, and rotor is consolidated
It is fixed, no longer rotate；
Step 2：Remove the tail end of tail portion connecting rod：The tail end of tail portion connecting rod is removed from the connecting pole of tail portion, and towards outside fuselage
Side rotating tail connecting rod, until tail portion connecting rod is aligned with head connecting rod；
Step 3：Remove connection and self-locking mechanism：The rotary shaft of connection and self-locking mechanism is rotated from from lock barrel and is removed, and
Towards airplane tail group pull connection and self-locking mechanism, until head connecting rod and tail portion connecting rod be adjacent to fuselage it is parallel；
Step 4：Step 2 and step 3 are repeated, the head connecting rod of the aircraft other side and tail portion connecting rod are removed.
The structure of the method for deploying of vertical take-off and landing drone rotor, the vertical take-off and landing drone rotor is for example above-mentioned, and uses
The method stated, which folds, to be completed, including following operating procedure：
Step（1）：Securement head case：By head cover valve jacket on the head of vertical take-off and landing drone so that two groups of heads connect root
The both sides of fuselage are symmetrically positioned in tail portion connecting rod, and positioned at the lower section of wing；
Step（2）：The head connecting rod and tail portion connecting rod of fuselage side are installed：The connection and self-locking of the side are pulled towards fuselage outer side
Mechanism, head connecting rod and tail portion connecting rod synchronous rotary, until connection and self-locking mechanism be moved to the side below the lock barrel, will
Connection and the lock pillar precession of self-locking mechanism are from the lock road of lock barrel, then tail portion connecting rod end annulus is pulled to fly towards VTOL
The tail portion of machine is moved, until the realization maximum angle limit of the lock pillar of connection and self-locking mechanism, at this point, the tail end of tail portion connecting rod is rigid
It is located at the lower section of airplane tail group well, tail portion connecting rod is fixed on the connecting pole of tail portion；
Step（3）：The head connecting rod and tail portion connecting rod of the fuselage other side are installed：Repeat step（2）By the head of the fuselage other side
Connecting rod and the expansion of tail portion connecting rod, and it is fixed.
The above two method simplest method of structure folding and expanding to realize the present invention can quickly, efficiently by this be sent out
Bright structure, which is realized, to be folded and is unfolded, and will not damage structure of the invention.
The technical means disclosed in the embodiments of the present invention is not limited to the technical means disclosed in the above technical means, and further includes
By the above technical characteristic arbitrarily the formed technical solution of combination.
It is enlightenment with above-mentioned desirable embodiment according to the present invention, through the above description, relevant staff is complete
Various changes and amendments can be carried out without departing from the scope of the technological thought of the present invention' entirely.The technology of this invention
Property range is not limited to the contents of the specification, it is necessary to determine its technical scope according to right.
Claims (10)
1. vertical take-off and landing drone rotor foldable structure, which is characterized in that including：
For the head case mounted on vertical take-off and landing drone Handpiece Location；
Two head connecting rods, front end can rotationally be connected to the both sides of head case respectively；
Two tail portion connecting rods, front end can rotationally be connected to the tail end of head connecting rod respectively；One head connecting rod and a tail
Portion's connecting rod connection, and it is symmetrically positioned in the horizontal both sides of vertical take-off and landing drone；
Several rotors, at least provided with a rotor above and below each head connecting rod and tail portion connecting rod.
2. vertical take-off and landing drone rotor foldable structure according to claim 1, which is characterized in that every head connecting rod and
Tail portion connecting rod is respectively provided with there are two rotor, and close head connecting rod and the rotor of the junction of tail portion connecting rod are arranged at head company
The top in head connecting rod or tail portion connecting rod is arranged in the lower section of bar and tail portion connecting rod, other rotors.
3. vertical take-off and landing drone rotor foldable structure according to claim 1, which is characterized in that the head connecting rod and
Tail portion connecting rod is connected by connection and self-locking mechanism, and the connection and self-locking mechanism include：
It is fixedly connected with framework, for connecting tail portion connecting rod；
Be rotatably connected framework, for connecting head connecting rod；
Rotary shaft, rotary shaft are fixedly connected with framework is fixedly connected with, and rotatable connection framework can rotate around the axis of rotation,
Postive stop baffle, is fixedly connected in framework and rotatable connection framework and is both provided with postive stop baffle, and postive stop baffle is solid for limiting
Surely connection framework and the framework that is rotatably connected can rotate the angle of arrival；
It is provided with from lock barrel below two middle part wings of vertical take-off and landing drone, the rotary shaft is inserted into self-locking
In sleeve, and it is locked with self-locking sleeve after directional-rotation.
4. vertical take-off and landing drone rotor foldable structure according to claim 3, which is characterized in that the rotary shaft is close
Its top is relatively set with two radially-protruding lock pillars,
It is described from lock barrel towards rotary shaft one end setting there are two lock road, the lock road from the rim openings from lock barrel simultaneously
It is tilted towards self-locking circumference, the diameter of lock pillar is no more than the width for locking road, during rotary shaft is inserted from lock barrel, two
A lock pillar can enter lock road from the opening in lock road simultaneously, and the roads Bing Yusuo are locked.Vertical take-off and landing drone is in its empennage
Portion is provided with tail portion connecting pole, and the tail end of described two tail portion connecting rods is fixed with tail portion connecting pole.
5. vertical take-off and landing drone rotor foldable structure according to claim 1, which is characterized in that described to be fixedly connected with structure
The top of frame and rotatable connection framework is in circular arc curved shape, the top weight for being fixedly connected with framework and the framework that is rotatably connected
Folded, the rotary shaft runs through the lap, will be fixedly connected with framework and is connected with rotatable connection framework.
6. vertical take-off and landing drone rotor foldable structure according to claim 5, which is characterized in that described to be fixedly connected with structure
Frame includes two parallel connecting plates I, and with rotation axis connection, tail portion is provided with support plate I, institute at the top of two connecting plates I
It states two connecting plates I and is fixed with support plate I by rotary shaft parallel, postive stop baffle I is provided between described two connecting plates I；
The rotatable connection framework includes two parallel connecting plates II, the tops of two connecting plates II with rotation axis connection,
Tail portion is provided with support plate II, and described two connecting plates II fix parallel, described two connecting plates with support plate II by rotary shaft
Postive stop baffle II is provided between II；
The outside of circular arc curved shape of the one end of the postive stop baffle I beyond connecting plate I, the other end is without departing from connecting plate I
The inside of circular arc curved shape；
The outside of circular arc curved shape of the one end of postive stop baffle II beyond connecting plate II, circle of the other end without departing from connecting plate II
The inside of arc curved shape；
The center of the support plate I and postive stop baffle I offers circular hole I, and tail portion connecting rod passes through circular hole I, and is secured to；
The center of the support plate II and postive stop baffle II offers circular hole II, and head connecting rod passes through circular hole II, and solid with it
It is fixed.
7. vertical take-off and landing drone rotor foldable structure according to claim 1, which is characterized in that the head connecting rod is in
Obtuse angle shape, front end extends to the outside extension from itself and head case junction, after extending beyond head case, bending with it is vertical
The parallel linear of landing airframe, the tail portion connecting rod are linear.
8. vertical take-off and landing drone rotor foldable structure according to claim 1, which is characterized in that vertical take-off and landing drone
It is provided with tail portion connecting pole in the middle part of its empennage, the tail end of described two tail portion connecting rods is fixed with tail portion connecting pole.
9. the method for folding of vertical take-off and landing drone rotor, which is characterized in that the structure of the vertical take-off and landing drone rotor is as above
It states described in any claim, including following operating procedure：
Step 1：Position rotor：Stir rotor so that rotor is parallel with corresponding head connecting rod and tail portion connecting rod, and rotor is consolidated
It is fixed, no longer rotate；
Step 2：Remove the tail end of tail portion connecting rod：The tail end of tail portion connecting rod is removed from the connecting pole of tail portion, and towards outside fuselage
Side rotating tail connecting rod, until tail portion connecting rod is aligned with head connecting rod；
Step 3：Remove connection and self-locking mechanism：The rotary shaft of connection and self-locking mechanism is rotated from from lock barrel and is removed, and
Towards airplane tail group pull connection and self-locking mechanism, until head connecting rod and tail portion connecting rod be adjacent to fuselage it is parallel；
Step 4：Step 2 and step 3 are repeated, by the head connecting rod of the aircraft other side and tail portion connecting rod from tail portion connecting pole and connection
And removed on self-locking mechanism, and it is close with unmanned aerial vehicle body.
10. the method for deploying of vertical take-off and landing drone rotor, which is characterized in that the structure of the vertical take-off and landing drone rotor is as above
It states in claim 1-8 described in any claim, and is folded and completed with the method described in claim 9, including following operation
Step：
Step (1)：Securement head case：By head cover valve jacket on the head of vertical take-off and landing drone so that two groups of heads connect root
The both sides of fuselage are symmetrically positioned in tail portion connecting rod, and positioned at the lower section of wing；
Step (2)：The head connecting rod and tail portion connecting rod of fuselage side are installed：The connection and self-locking of the side are pulled towards fuselage outer side
Mechanism, head connecting rod and tail portion connecting rod synchronous rotary, until connection and self-locking mechanism be moved to the side below the lock barrel, will
Connection and the lock pillar precession of self-locking mechanism are from the lock road of lock barrel, then tail portion connecting rod end annulus is pulled to fly towards VTOL
The tail portion of machine is moved, until the realization maximum angle limit of the lock pillar of connection and self-locking mechanism, at this point, the tail end of tail portion connecting rod is rigid
It is located at the lower section of airplane tail group well, tail portion connecting rod is fixed on the connecting pole of tail portion；
Step (3)：The head connecting rod and tail portion connecting rod of the fuselage other side are installed：Step (2) is repeated by the head of the fuselage other side
Connecting rod and the expansion of tail portion connecting rod, and it is fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810486484.3A CN108438204A (en) | 2018-05-21 | 2018-05-21 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810486484.3A CN108438204A (en) | 2018-05-21 | 2018-05-21 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
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| CN108438204A true CN108438204A (en) | 2018-08-24 |
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| CN201810486484.3A Pending CN108438204A (en) | 2018-05-21 | 2018-05-21 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
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