CN105480410B - Take-off and landing device for small-sized unmanned aerial vehicle - Google Patents
Take-off and landing device for small-sized unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105480410B CN105480410B CN201510940508.4A CN201510940508A CN105480410B CN 105480410 B CN105480410 B CN 105480410B CN 201510940508 A CN201510940508 A CN 201510940508A CN 105480410 B CN105480410 B CN 105480410B
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- China
- Prior art keywords
- wheel
- fork
- shaft
- landing
- small
- Prior art date
Links
- 230000000694 effects Effects 0.000 abstract description 5
- 230000035939 shock Effects 0.000 abstract description 2
- 230000001603 reducing Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 238000010276 construction Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000002146 bilateral Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reaction Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000000630 rising Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000017105 transposition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by the ground or like engaging elements
- B64C25/34—Alighting gear characterised by the ground or like engaging elements wheeled type, e.g. multi-wheeled bogies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by the ground or like engaging elements
- B64C25/34—Alighting gear characterised by the ground or like engaging elements wheeled type, e.g. multi-wheeled bogies
- B64C2025/345—Multi-wheel bogies having one or more steering axes
Abstract
The invention discloses a take-off and landing device for a small-sized unmanned aerial vehicle. The take-off and landing device for the small-sized unmanned aerial vehicle comprises an external side plate (1), an internal side plate (2), a rear wheel (6), a front wheel (5), a front wheel steering engine (12) and a wheel axle and wheel fork component. The impact on the rear wheel, which is used as a bearing wheel, at the moment of landing is transmitted to a vehicle main structure after passing through landing gear double side plates and a vertical tail connecting piece in sequence so that good shock absorbing effect is realized. Each accessory between the external side plate and the internal side plate is also used as a connecting piece between the steering engine and the front wheel while being used for providing supporting forces to the double side plates; therefore, the effective utilization rate of the structural parts is increased, the additional connecting pieces is reduced in use and a weight reducing effect is also realized. And meanwhile, as lightening holes are punched in strength-rich parts of the rear parts of the side plates, the weight of the structure is effectively reduced. Through adoption of the design method of the wheel axle and wheel fork component, the invention is advantaged in that good strength and good manufacturability are realized, the number of the connecting pieces is greatly reduced and the weight of the take-off and landing wheel fork component is reduced.
Description
Technical field
It is specially a kind of for miniature self-service flight the present invention relates to small-sized unmanned aircraft landing-gear structural design field
The lifting gear of device.
Background technology
In the design process of unmanned plane, for undercarriage, its lightweight construction is on the one hand required, be in particular in structure
Design is ingenious, rationally distributed, and material selection is suitable, on the other hand can also undertake the huge punching brought when aircraft lands
Hit, be in particular at undercarriage overall structure and wheel fork and wheel shaft cooperation the impact that can be born when aircraft lands with ground
Load.Accomplish to meet unmanned plane to the functional requirement of undercarriage and the weight configuration index of harshness, in the entirety of transposition of rising and falling
In design process, on the premise of undercarriage strength and stiffness are ensured, to make every effort to accomplish the simple structure of undercarriage, performance is complete
It is kind, and reach most light construction weight.
In the design process of certain new unmanned plane, because the type unmanned plane employs fuselage lower section with double fins, rise
The frame that falls is connected to the structure type of fuselage by vertical tail, therefore the landing gear structure form of routine cannot meet design requirement, needs
Design a kind of new landing gear mechanism.In this landing gear mechanism, in order to meet weight indicator, undercarriage main element
And the material that wheel fork is used in wheel fork component is the duralumin of lighter in weight, and wheel shaft bears huge impact load due to needing
Lotus, need to be using rigidity and No. 45 good steel of intensity.
For the connection of wheel fork and wheel shaft, traditional design is excessive due to the connector for adding, and considerably increases wheel fork group
The weight of part.In order to mitigate weight, wheel fork is connected as a single entity with wheel shaft in some designs, so as to control turning for undercarriage front-wheel
It is dynamic.But because wheel fork and wheel shaft are different materials here, it is impossible to by being welded into one, so must be using additional connection
Part is fixedly connected it.
The content of the invention
In order to meet, undercarriage is full-featured, the design requirement of lightweight high intensity, overcomes wheel fork to connect with wheel shaft high intensity
The contradiction with lightweight packages is connect, the present invention proposes a kind of lifting gear for small-sized unmanned aircraft, lightweight packages
And with the good load-carrying ability that withstands shocks.
The technical scheme is that：
A kind of lifting gear for small-sized unmanned aircraft, it is characterised in that：Including outer panel (1), interior plate
(2), trailing wheel (6), front-wheel (5), front-wheel steer steering wheel (12) and wheel shaft wheel fork component；
Outer panel (1), interior plate (2) parallel arrangement, between outer panel (1) and interior plate (2) pass through side plate annex (15),
Front wheel members (7) and steering wheel annex are connected, and form the main body supporting structure of lifting gear；It is solid in the main body supporting structure
Surely there is vertical tail connector, for being connected with small-sized unmanned aircraft fuselage lower section vertical tail；
Main body supporting structure middle part is directly connected to by hind axle with trailing wheel (6)；
Front-wheel steer steering wheel (12), front-wheel steer steering wheel are fixedly mounted on the anterior steering wheel annex (10) of main body supporting structure
(12) steering wheel connecting rod (13) is connected by cranking arm with wheel shaft (4) end in wheel shaft wheel fork component, front-wheel steer steering wheel (12)
Rotated by steering wheel connecting rod (13) and drive wheel shaft (4) of cranking arm；
Wheel shaft (4) coordinates through the wheel fork (3) of front wheel members (7) and wheel shaft wheel fork component；Wheel shaft (4) and wheel fork (3)
The end of cooperation is designed with disk, and non-circular boss is designed with disc face, and screwed hole is provided with raised head face；Wheel fork
(3) it is provided with and non-circular boss size, shape identical through hole on the joint face coordinated with wheel shaft (4)；Wheel shaft (4) and wheel fork
(3) when coordinating, non-circular boss is inserted in the through hole, and the screw (16) of pad is provided with the screwed hole, will
Wheel shaft (4) is fastened with wheel fork (3)；Wheel fork (3) is connected by front axle with front-wheel (5)；
Rudder steering wheel (14) is fixedly mounted on rear portion steering wheel annex (11) of main body supporting structure；Rudder steering wheel (14)
Rudder on the vertical tail of control small-sized unmanned aircraft fuselage lower section.
Further preferred scheme, a kind of lifting gear for small-sized unmanned aircraft, it is characterised in that：Outside
The Strength surplus position at plate (1) and interior plate (2) rear portion is provided with multiple circle lightening cores.
Beneficial effect
Lifting gear of the invention has advantages below：
1st, in terms of motion, can take off and improve steady with horizontal to the sliding trajectory of aircraft in the taxiing procedures for landing
Qualitatively control；
2nd, in terms of damping, the trailing wheel as BOGEY WHEEL successively passes through undercarriage bilateral in the impact suffered by landing moment
Plate, vertical tail connector are conducted to fuselage main structure, there is preferable damping effect；
3rd, in configuration aspects, each annex of undercarriage side sheet room has also served as rudder while the supporting force to dual-sided board is provided
The connector of machine and front-wheel, improves the effective utilization to structure member, reduces the use of extra connector, also there is loss of weight
Effect, while having stamped lightening core in side plate rear strength flap portion, effectively reduce construction weight；
4th, in manufacture view, its simple structure, material is common, and member profile is succinct, it is easy to process, while the side of assembling up
Just it is quick, it is easy to maintenance and replacing.
Additional aspect of the invention and advantage will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by practice of the invention.
Brief description of the drawings
Of the invention above-mentioned and/or additional aspect and advantage will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Fig. 1：It is undercarriage overall construction drawing of the present invention；
Fig. 2：It is the structure chart of invention components；
Fig. 3：It is connecting shaft view of the present invention；
Fig. 4：It is wheel fork view of the present invention；
Wherein：1st, outer panel；2nd, interior plate；3rd, wheel fork；4th, wheel shaft；5th, front-wheel；6th, trailing wheel；7th, front wheel members；8th, it is preceding
Vertical tail connector；9th, rear vertical tail connector；10th, anterior steering wheel annex；11st, rear portion steering wheel annex；12nd, front-wheel steer steering wheel；13、
Steering wheel connecting rod；14th, rudder steering wheel；15th, side plate annex；16th, screw.
Specific embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from start to finish
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
It is exemplary to scheme the embodiment of description, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention is described with simplified, must have specific orientation, Yi Te rather than the device or element for indicating or imply meaning
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
The take-off and landing device designed the present invention be directed to novel small-sized unmanned vehicle of the fuselage lower section with double fins, such as
Shown in Fig. 1, the lifting gear in the present embodiment includes outer panel (1), interior plate (2), trailing wheel (6), front-wheel (5), front-wheel steer
Steering wheel (12) and wheel shaft wheel fork component.
Outer panel (1), interior plate (2) parallel arrangement, between outer panel (1) and interior plate (2) pass through side plate annex (15),
Front wheel members (7), anterior steering wheel annex (10) and rear portion steering wheel annex (11) connection support, form the main body of lifting gear
Supporting construction；Preceding vertical tail connector (8) and rear vertical tail connector (9) are fixed with the main body supporting structure, for it is small-sized
Unmanned vehicle fuselage lower section vertical tail connection, to support fuselage.
Main body supporting structure middle part is directly connected to by hind axle with trailing wheel (6), and trailing wheel (6) is main BOGEY WHEEL.
Front-wheel steer steering wheel (12) is fixedly mounted on the anterior steering wheel annex (10) of main body supporting structure, for controlling front-wheel
Turn to.The steering wheel connecting rod (13) of front-wheel steer steering wheel (12) is connected by cranking arm with wheel shaft (4) end in wheel shaft wheel fork component,
Front-wheel steer steering wheel (12) is rotated by steering wheel connecting rod (13) and drive wheel shaft (4) of cranking arm.
Wheel shaft (4) coordinates through the wheel fork (3) of front wheel members (7) and wheel shaft wheel fork component, and wheel shaft wheel fork component is matched somebody with somebody
Conjunction relation is as shown in Figure 2.The end that wheel shaft (4) coordinates with wheel fork (3) is designed with disk, and non-circular male is designed with disc face
Platform, and screwed hole is provided with raised head face；It is provided with the joint face that wheel fork (3) coordinates with wheel shaft (4) big with non-circular boss
Small, shape identical through hole；When wheel shaft (4) coordinates with wheel fork (3), non-circular boss is inserted in the through hole, is capable of achieving wheel shaft
(4) wheel fork (3) is driven to rotate.In order to wheel fork departs from wheel shaft in preventing aircraft from going up to the air or advancing, pacify in the screwed hole
Equipped with the screw (16) with pad, wheel shaft (4) and wheel fork (3) are fastened；Wheel fork (3) is connected by front axle with front-wheel (5).
The design of this wheel shaft wheel fork component, compared to it is traditional wheel shaft lower end fix one with material and open
There is the circular piece in individual hole, then a flange is processed on wheel fork, and utilize four bolts and nut by wheel fork and wheel shaft lower end
The design that circular steel part is fixedly connected, with more preferable intensity and more preferable manufacturability, while what is more important its knot
Structure is simple, and traditional structure at least needs four bolts and the nut wheel fork could to be fixedly connected with wheel shaft, and this new structure is only needed
One bolt and pad are to be capable of achieving connection, and this will greatly save the quantity of connector, will reduce the weight of landing wheel fork component
Amount, this is extremely important for aircraft.
Rudder steering wheel (14) is fixedly mounted on rear portion steering wheel annex (11) of main body supporting structure；Rudder steering wheel (14)
Rudder on the vertical tail of control small-sized unmanned aircraft fuselage lower section, to control to be turned in aircraft flight.
Using structure of the invention, in terms of motion, improved to aircraft with the taxiing procedures for landing that can be taken off
The control of sliding trajectory and lateral stability；In terms of damping, as the trailing wheel of BOGEY WHEEL in the impact suffered by landing moment
Successively conducted to fuselage main structure by undercarriage dual-sided board, vertical tail connector, there is preferable damping effect；In configuration aspects,
Each annex of undercarriage side sheet room has also served as the connector of steering wheel and front-wheel while the supporting force to dual-sided board is provided, and improves
Effective utilization to structure member, reduces the use of extra connector, also plays the role of loss of weight, while at side plate rear portion
Lightening core has been stamped in Strength surplus part, effectively reduces construction weight；In manufacture view, its simple structure, material is common,
Member profile is succinct, it is easy to process, while assembling up convenient and swift, it is easy to maintenance and replacing.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from principle of the invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (2)
1. a kind of lifting gear for small-sized unmanned aircraft, it is characterised in that：Including outer panel (1), interior plate (2), after
Wheel (6), front-wheel (5), front-wheel steer steering wheel (12) and wheel shaft wheel fork component；
Outer panel (1), interior plate (2) parallel arrangement, pass through side plate annex (15), front-wheel between outer panel (1) and interior plate (2)
Connector (7) and steering wheel annex are connected, and form the main body supporting structure of lifting gear；It is fixed with the main body supporting structure
Vertical tail connector, for being connected with small-sized unmanned aircraft fuselage lower section vertical tail；
Main body supporting structure middle part is directly connected to by hind axle with trailing wheel (6)；
Front-wheel steer steering wheel (12), front-wheel steer steering wheel (12) are fixedly mounted on the anterior steering wheel annex (10) of main body supporting structure
Steering wheel connecting rod (13) be connected with wheel shaft (4) end in wheel shaft wheel fork component by cranking arm, front-wheel steer steering wheel (12) passes through
Steering wheel connecting rod (13) and drive wheel shaft (4) of cranking arm are rotated；
Wheel shaft (4) coordinates through the wheel fork (3) of front wheel members (7) and wheel shaft wheel fork component；Wheel shaft (4) coordinates with wheel fork (3)
End be designed with disk, non-circular boss is designed with disc face, and screwed hole is provided with raised head face；Wheel fork (3) with
It is provided with and non-circular boss size, shape identical through hole on the joint face that wheel shaft (4) coordinates；Wheel shaft (4) coordinates with wheel fork (3)
When, non-circular boss is inserted in the through hole, and the screw (16) of pad is provided with the screwed hole, by wheel shaft (4)
Fastened with wheel fork (3)；Wheel fork (3) is connected by front axle with front-wheel (5)；
Rudder steering wheel (14) is fixedly mounted on rear portion steering wheel annex (11) of main body supporting structure；Rudder steering wheel (14) is controlled
Rudder on the vertical tail of small-sized unmanned aircraft fuselage lower section.
2. a kind of lifting gear for small-sized unmanned aircraft according to claim 1, it is characterised in that：Outer panel (1)
And the Strength surplus position at interior plate (2) rear portion is provided with multiple circle lightening cores.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510940508.4A CN105480410B (en) | 2015-12-15 | 2015-12-15 | Take-off and landing device for small-sized unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510940508.4A CN105480410B (en) | 2015-12-15 | 2015-12-15 | Take-off and landing device for small-sized unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105480410A CN105480410A (en) | 2016-04-13 |
| CN105480410B true CN105480410B (en) | 2017-05-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510940508.4A CN105480410B (en) | 2015-12-15 | 2015-12-15 | Take-off and landing device for small-sized unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN105480410B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275393A (en) * | 2016-08-31 | 2017-01-04 | 河南翱翔航空科技有限公司 | Unmanned plane nose-gear |
| EP3375708A1 (en) | 2017-03-17 | 2018-09-19 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963524A (en) * | 2012-09-14 | 2013-03-13 | 马永政 | Slide-wheel composite type small and medium sized UAV landing gear system |
| CN104787309A (en) * | 2015-05-12 | 2015-07-22 | 厦门大学 | Landing gear of rotor unmanned aerial vehicle (UAV) |
| CN204822065U (en) * | 2015-07-28 | 2015-12-02 | 河南大诚通用航空科技有限公司 | Unmanned aerial vehicle's undercarriage |
| CN205293070U (en) * | 2015-12-15 | 2016-06-08 | 西北工业大学 | A device that takes off and land for small -size unmanned vehicles |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8079545B2 (en) * | 2007-01-11 | 2011-12-20 | Lockheed Martin Corporation | System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations |
-
2015
- 2015-12-15 CN CN201510940508.4A patent/CN105480410B/en not_active IP Right Cessation
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963524A (en) * | 2012-09-14 | 2013-03-13 | 马永政 | Slide-wheel composite type small and medium sized UAV landing gear system |
| CN104787309A (en) * | 2015-05-12 | 2015-07-22 | 厦门大学 | Landing gear of rotor unmanned aerial vehicle (UAV) |
| CN204822065U (en) * | 2015-07-28 | 2015-12-02 | 河南大诚通用航空科技有限公司 | Unmanned aerial vehicle's undercarriage |
| CN205293070U (en) * | 2015-12-15 | 2016-06-08 | 西北工业大学 | A device that takes off and land for small -size unmanned vehicles |
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| Publication number | Publication date |
|---|---|
| CN105480410A (en) | 2016-04-13 |
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Granted publication date: 20170524 Termination date: 20191215 |