CN209142387U - Vert rotor aircraft for a kind of dismountable tail portion of wing - Google Patents
Vert rotor aircraft for a kind of dismountable tail portion of wing Download PDFInfo
- Publication number
- CN209142387U CN209142387U CN201821162972.0U CN201821162972U CN209142387U CN 209142387 U CN209142387 U CN 209142387U CN 201821162972 U CN201821162972 U CN 201821162972U CN 209142387 U CN209142387 U CN 209142387U
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- wing
- fuselage
- driving assembly
- motor
- tail portion
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Abstract
The utility model provides a kind of dismountable tail portion of wing and verts rotor aircraft, and by being equipped with reclining device in the tail portion of fuselage, reclining device drive connection has the second driving assembly and the second driving assembly is driven to rotate in the horizontal direction between vertical downward direction；And the bottom surface of two connecting rods and fuselage head is equipped with the first driving assembly straight down；Therefore the first driving assembly and the second driving assembly, constitute cross-shape layout；The aircraft of the utility model only has the motor of tail portion to vert, unlike to realize the complexity verted, therefore reduce overall mechanism in traditional rotor aircraft by way of tilting wing；And in the utility model two wings can with disassembled on fuselage, both can be changed to a cross layout quadrotor, realize a tractor serves several purposes.
Description
Technical field
The utility model relates to aircraft field, vert rotor aircraft for espespecially a kind of dismountable tail portion of wing.
Background technique
Unmanned air vehicle technique develops rapidly in recent years, is all widely applied in military and civil field, VTOL
Unmanned plane because having and being more widely applied scene and the market demand, represent an important development side of the following aircraft
To.
Tiltrotor, it is a kind of course of new aircraft that fixed wing aircraft and helicopter advantage combine together, rotor
Inclining rotary mechanism design is one of its core technology, is to realize such aircraft in helicopter flight mode and fixed-wing offline mode
Between the device converted.In the unmanned plane that existing power verts mode, most of reclining device is placed on wing, process of verting
In need to consider various bring unstability problems of verting, and by reclining device be placed on wing also increase it is integrally-built multiple
Miscellaneous degree；And aircraft reclining device is placed on wing on the market now, is resulted in the wing that verts and is required wing participation, if lacked
The case where wing will lead to abnormal flight is lacked.
Summary of the invention
Vert rotor aircraft to solve the above problems, the utility model provides a kind of dismountable tail portion of wing, pass through by
The tail portion of fuselage is arranged in reclining device, reduces the complexity of overall mechanism；And two wings can be in the utility model
It is disassembled on fuselage, both can be changed to the quadrotor of cross layout, realize a tractor serves several purposes.
To achieve the above object, the technical solution adopted in the utility model is to provide a kind of dismountable tail portion of wing and verts
Rotor aircraft, including fuselage, empennage, battery, control circuit board, two wings, two cross bars, two of them wing are arranged in fuselage
Two sides, the battery, control circuit board are built in fuselage, and control circuit board is connect with battery；Two cross bars are fixed on
Two wing bottoms and symmetrically, wherein the both ends of empennage are fixed at the same end of two cross bars, the two sides of the fuselage
It is respectively equipped with connecting rod that is parallel with wing and being located at below wing, wherein the bottom surface of two connecting rods and fuselage head is all provided with
There is the first driving assembly straight down, the tail portion of fuselage is equipped with reclining device, and wherein reclining device drive connection has the second drive
Dynamic component simultaneously drives the second driving assembly to rotate in the horizontal direction between vertical direction, wherein reclining device, the first driving assembly,
Second driving assembly is electrically connected with control circuit board respectively.
Specifically, the reclining device includes reclining device frame, motor swivel mount, the rudder connecting with control circuit board
Machine, worm screw, rotary shaft, first gear, surface set the limit cam there are two convex block；The limit cam, first gear difference
It is arranged on the rotary shaft, and the both ends of rotary shaft are separately positioned on the two sidewalls in motor swivel mount, wherein the two of rotary shaft
End extends outward and is fixedly connected respectively with the both ends of motor swivel mount；The inner sidewall of the reclining device frame is equipped with and is used for
The first limit switch block, the second limit switch block that control flaps organ closes and is electrically connected with steering engine, and the first limit switch block
The two sides of limit cam are located at the second limit switch block；The output shaft of steering engine is connect with worm screw, first gear and worm screw
On screw thread intermeshing so that rotary shaft drive motor swivel mount, limit cam rotation, touch the convex block of limit cam
Touch the first limit switch block or the second limit switch block.
Specifically, first driving assembly includes first motor, and the second driving assembly includes the second motor, wherein first
Motor is fixed at straight down on the bottom surface and two connecting rods of fuselage head, and first motor drive connection has first
Propeller；Wherein the second motor is fixed on the surface of motor swivel mount, and the drive connection of the second motor has the second propeller.
Specifically, the distance between described two cross bars are greater than the diameter of the second propeller.
Specifically, connecting screw is equipped in one end of the wing, the two sides of fuselage, which are respectively arranged with, is correspondingly connected with screw rod
Connecting hole, two wings are detachably connected by equipped realize of connecting screw and connecting hole with fuselage.
It specifically, further include undercarriage, the undercarriage is fixed on the bottom of fuselage.
Specifically, the empennage is inverted V-shaped structure.
The utility model has the beneficial effects that: the utility model is innovated in the mode of verting, by fuselage
Tail portion be equipped with reclining device, reclining device drive connection have the second driving assembly and drive the second driving assembly in the horizontal direction
It is rotated between vertical downward direction；And the bottom surface of two connecting rods and fuselage head is equipped with the first driving straight down
Component；Therefore the first driving assembly and the second driving assembly, constitute cross-shape layout；The aircraft of the utility model only has tail portion
Motor vert, vert unlike to be realized by way of tilting wing in traditional rotor aircraft, therefore reduce integrated machine
The complexity of structure；And in the utility model two wings can with disassembled on fuselage, both can be changed to cross layout
Quadrotor realizes a tractor serves several purposes.Wherein at work, the second driving assembly of tail portion is realized horizontal by reclining device
Switch vertically downward, other three first driving assemblies of aircraft do not work when the second driving assembly of tail portion is horizontal positioned, entirely
Aircraft is exactly that a tail pushes away aircraft；Four motors all work when vertically downward, are exactly the quadrotor of cross layout.
Detailed description of the invention
Fig. 1 is the utility model structure diagram.
Fig. 2 is the utility model bottom view.
Fig. 3 is the explosive view of reclining device in the utility model.
Drawing reference numeral explanation: 1. reclining devices；11. inclining rotary mechanism frame；12. motor swivel mount；13. steering engine；14. snail
Bar；15. limit cam；16. first gear；17. rotary shaft；18. swivel bearing；101. the first limit switch block；102. second
Limit switch block；111. mounting hole；21. fuselage；22. undercarriage；23. wing；24. empennage；25. first motor；26. the first spiral shell
Revolve paddle；27. the second propeller；28. the second motor；29. cross bar；211. connecting rod.
Specific embodiment
The utility model is described in detail with Figure of description combined with specific embodiments below.
Below by specific embodiment, the utility model is described in further detail.It please refers to shown in Fig. 1-3, this is practical new
Type verts rotor aircraft, including fuselage 21, empennage 24, battery, control circuit board, two machines about a kind of dismountable tail portion of wing
The two sides of fuselage 21 are arranged in 23, two cross bars 29 of the wing, two of them wing 23, and the battery, control circuit board are built in machine
In body 21, and control circuit board is connect with battery；Two cross bars 29 are fixed on two wings, 23 bottom and symmetrically, wherein empennage
24 both ends are fixed at the same end of two cross bars 29, and the two sides of the fuselage 21 are respectively equipped with and position parallel with wing 23
Connecting rod 211 in 23 lower section of wing, wherein the bottom surface on 21 head of two connecting rods 211 and fuselage is equipped with straight down
The tail portion of first driving assembly, fuselage 21 is equipped with reclining device 1, and wherein the drive connection of reclining device 1 has the second driving assembly simultaneously
The second driving assembly is driven to rotate in the horizontal direction between vertical direction, wherein reclining device 1, the first driving assembly, second drive
Dynamic component is electrically connected with control circuit board respectively.
The utility model is also innovated in the mode of verting, and by being equipped with reclining device in the tail portion of fuselage 21, is inclined
Rotary device drive connection has the second driving assembly and the second driving assembly is driven to rotate in the horizontal direction between vertical downward direction；
And the bottom surface on 21 head of two connecting rods 211 and fuselage is equipped with the first driving assembly straight down；Therefore the first driving
Component and the second driving assembly constitute cross-shape layout；The aircraft of the utility model only has the motor of tail portion to vert, not
As the complexity verted, therefore reduce overall mechanism is realized in traditional rotor aircraft by way of tilting wing 23；
And in the utility model two wings 23 can with disassembled on fuselage 21, both can be changed to the quadrotor flight of cross layout
Device realizes a tractor serves several purposes.Wherein at work, the second driving assembly of tail portion is realized horizontal and vertical downward by reclining device
Switching, other three first driving assemblies of aircraft do not work when the second driving assembly of tail portion is horizontal positioned, and entire aircraft is exactly one
A tail pushes away aircraft；Four motors all work when vertically downward, are exactly the quadrotor of cross layout.
It please refers to shown in Fig. 3, specifically, the reclining device 1 includes inclining rotary mechanism frame 11, motor swivel mount 12, rudder
Machine 13, worm screw 14, surface set that there are two the limit cams 15 of convex block, bearing suit, first gear 16；Its centre bearer bush fills
17, two swivel bearings 18 of rotary shaft, two inner walls of the inclining rotary mechanism frame 11 are equipped with the installation of corresponding swivel bearing 18
Hole 111, two swivel bearings 18 are fixed in two mounting holes 111；The limit cam 15, first gear 16 are arranged respectively
In rotary shaft 17, and the both ends of rotary shaft 17 are separately positioned on two swivel bearings 18, and wherein the both ends of rotary shaft 17 are outward
Extend and is fixedly connected respectively with the both ends of motor swivel mount；Close to the interior of limit cam 15 in the inclining rotary mechanism frame 11
Side wall is equipped with the first limit switch block 101, the second limit switch block 102 being electrically connected with steering engine 13, and the first limit is opened
It closes block 101 and the second limit switch block 102 is located at the two sides of rotary shaft 17；The steering engine 13 is drivingly connected with worm screw 14,
Screw thread in first gear 16 and worm screw 14 is intermeshed, so that rotary shaft 17 drives motor swivel mount, limit cam 15
Rotation, and when the convex block of limit cam 15 is adjacent to the first limit switch block 101 or is adjacent to the second limit switch block 102, institute
Steering engine 13 is stated to stop working.
When the winged control of aircraft or remote controler provide the signal that verts, steering engine 13 starts that worm screw 14 is driven to rotate, and worm screw 14 stings
Close first gear 16, first gear 16 rotate and drive in rotary shaft 17 motor swivel mount and limit cam 15 together
Rotation.Wherein active force derives from steering engine 13, and scroll bar 2 and first gear 16 are used as movement transforming device, and first gear 16 passes through
Rotary shaft 17 drives motor swivel mount and limit cam 15 to move simultaneously, and movement end point is by the triggering of limit cam 15 first
Limit switch block 101 or the second limit switch block 102 determine.Relative to traditional technology, aircraft is may be implemented one in the application
Determine precisely verting in spatial dimension, operation precision and stability during aircraft flight can be improved, and work as limit convex
When the convex block of wheel 15 encounters the first limit switch block 101 or the second limit switch block 102, switch triggering signal simultaneously stops steering engine 13
Operating is verted, it can be achieved that being automatically stopped, and further improves operation precision and stability.
It please refers to shown in Fig. 1-2, specifically, first driving assembly includes first motor 25, the second driving assembly packet
Include the second motor 28, wherein first motor 25 be fixed at straight down 21 head of fuselage bottom surface and two connecting rods
On 211, and the drive connection of first motor 25 has the first propeller 26；Wherein the second motor 28 is fixed on the table of motor swivel mount
Face, and the drive connection of the second motor 28 has the second propeller 27.
It please refers to shown in Fig. 1-2, specifically, the distance between described two cross bars 29 are greater than the straight of the second propeller 27
Diameter.The diameter that the distance between two cross bars 29 are greater than the second propeller 27 can guarantee that reclining device drives the second propeller 27
When, the normal work of the second propeller 27, the case where avoiding the second propeller 27 from getting to cross bar 29 appearance.
Specifically, connecting screw is equipped in one end of the wing 23, the two sides of fuselage 21, which are respectively arranged with, to be correspondingly connected with
The connecting hole of screw rod, two wings 23 are detachably connected by connecting screw and equipped realize of connecting hole with fuselage 21.When by wing
23 dismantle from 21 two sides of fuselage, and aircraft both can be changed to the quadrotor of cross layout, realize a tractor serves several purposes.
It specifically, further include undercarriage 22, the undercarriage 22 is fixed on the bottom of fuselage 21.The undercarriage 22 added can
To facilitate aircraft taking off and descent, the case where encountering landing, undercarriage 22 also acts as certain buffer function,
Aircraft can be protected.
Specifically, the empennage 24 is inverted V-shaped structure.Wherein the empennage 24 of inverted V-shaped structure can enhance the lifting of aircraft
Rudder steerage is strong.
Embodiment of above is only that preferred embodiments of the present invention are described, not to the utility model
Range be defined, under the premise of not departing from the spirit of the design of the utility model, this field ordinary engineering and technical personnel to this
The various changes and improvements that the technical solution of utility model is made should all fall into the guarantor that claims of the utility model determine
It protects in range.
Claims (7)
1. vert rotor aircraft for a kind of dismountable tail portion of wing, including fuselage, empennage, battery, control circuit board, two wings,
Two cross bars, two of them wing are detachably connected on the two sides of fuselage, and the battery, control circuit board are built in fuselage,
And control circuit board is connect with battery；Two cross bars be fixed on two wing bottoms and symmetrically, wherein the both ends of empennage are fixed
The same end of two cross bars is set, it is characterised in that: the two sides of the fuselage are respectively equipped with parallel with wing and are located at wing
The connecting rod of lower section, wherein the bottom surface of two connecting rods and fuselage head is equipped with the first driving assembly straight down, machine
The tail portion of body is equipped with reclining device, and wherein reclining device drive connection has the second driving assembly and drives the second driving assembly in water
Square rotated to between vertical direction, wherein reclining device, the first driving assembly, the second driving assembly respectively with control circuit board
Connection.
2. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 1, it is characterised in that: described to vert
Device include reclining device frame, motor swivel mount, the steering engine being connect with control circuit board, worm screw, rotary shaft, first gear,
Surface sets the limit cam there are two convex block；The limit cam, first gear are respectively sleeved in rotary shaft, and rotary shaft
Both ends are separately positioned on the two sidewalls in motor swivel mount, and wherein the both ends of rotary shaft extend outward and rotate respectively with motor
The both ends of frame are fixedly connected；The inner sidewall of the reclining device frame, which is equipped with, to be closed and electrically connects with steering engine for control flaps organ
The first limit switch block, the second limit switch block connect, and the first limit switch block and the second limit switch block are located at limit
The two sides of position cam；The output shaft of steering engine is connect with worm screw, and the screw thread in first gear and worm screw is intermeshed, so that rotation
Shaft drives motor swivel mount, limit cam rotation, and the convex block of limit cam is made to touch the first limit switch block or the second limit
Switch block.
3. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 2, it is characterised in that: described first
Driving assembly includes first motor, and the second driving assembly includes the second motor, and wherein first motor is fixed at straight down
On the bottom surface of fuselage head and two connecting rods, and first motor drive connection has the first propeller；Wherein the second motor is solid
It is scheduled on the surface of motor swivel mount, and the drive connection of the second motor has the second propeller.
4. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 3, it is characterised in that: described two
The distance between cross bar is greater than the diameter of the second propeller.
5. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 1, it is characterised in that: the wing
One end in be equipped with connecting screw, the two sides of fuselage are respectively arranged with the connecting hole for being correspondingly connected with screw rod, and two wings pass through connection
Screw rod is detachably connected with equipped realize of connecting hole with fuselage.
6. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 1, it is characterised in that: further included
Frame is fallen, the undercarriage is fixed on the bottom of fuselage.
7. vert rotor aircraft for the dismountable tail portion of a kind of wing according to claim 1, it is characterised in that: the empennage
For inverted V-shaped structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821162972.0U CN209142387U (en) | 2018-07-23 | 2018-07-23 | Vert rotor aircraft for a kind of dismountable tail portion of wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821162972.0U CN209142387U (en) | 2018-07-23 | 2018-07-23 | Vert rotor aircraft for a kind of dismountable tail portion of wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209142387U true CN209142387U (en) | 2019-07-23 |
Family
ID=67265024
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821162972.0U Active CN209142387U (en) | 2018-07-23 | 2018-07-23 | Vert rotor aircraft for a kind of dismountable tail portion of wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209142387U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874214A (en) * | 2020-07-31 | 2020-11-03 | 九成通用飞机设计制造(大连)有限公司 | Airplane flap mechanism based on linear execution control |
-
2018
- 2018-07-23 CN CN201821162972.0U patent/CN209142387U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874214A (en) * | 2020-07-31 | 2020-11-03 | 九成通用飞机设计制造(大连)有限公司 | Airplane flap mechanism based on linear execution control |
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