CN105480410A - 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
- CN105480410A CN105480410A CN201510940508.4A CN201510940508A CN105480410A CN 105480410 A CN105480410 A CN 105480410A CN 201510940508 A CN201510940508 A CN 201510940508A CN 105480410 A CN105480410 A CN 105480410A
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- Prior art keywords
- wheel
- steering
- fork
- wheel shaft
- shaft
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface 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 elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C2025/345—Multi-wheel bogies having one or more steering axes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
- Forklifts And Lifting Vehicles (AREA)
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
The present invention relates to small-sized unmanned aircraft landing-gear structural design field, be specially a kind of lifting gear for small-sized unmanned aircraft.
Background technology
In the design process of unmanned plane, for alighting gear, require its lightweight construction on the one hand, be in particular in smart structural design, rationally distributed, Material selec-tion is suitable for, also want the enormous impact brought when can bear aircraft landing on the other hand, be in particular in that alighting gear integral structure and wheel fork and wheel shaft cooperation place can bear the impact load on when aircraft lands and ground.Accomplish to meet unmanned plane to the functional requirement of alighting gear and harsh weight configuration index, in the unit design process of the transposition that rises and falls, under the prerequisite guaranteeing alighting gear strength and stiffness, to make every effort to accomplish that the structure of alighting gear is simple, perfect performance, and reach the lightest structural weight.
In the design process of certain novel unmanned plane, because this type unmanned plane have employed below fuselage with double fins, alighting gear is connected to the version of fuselage by vertical tail, and therefore conventional landing gear structure form cannot meet design requirement, needs to design a kind of novel landing gear mechanism.In this landing gear mechanism, in order to meet weight indicator, the material that in alighting gear main element and wheel fork assembly, wheel fork adopts is the duralumin of lighter in weight, and wheel shaft is owing to needing to bear huge impact load, need adopt rigidity and good No. 45 steel of intensity.
For the connection of wheel fork and wheel shaft, traditional design due to additional attaching parts too much, considerably increase the weight of wheel fork assembly.In order to expendable weight, in some designs wheel fork and wheel shaft are connected as a single entity, thus control the rotation of alighting gear front-wheel.But because wheel fork and wheel shaft are different materials here, cannot by be welded into one, so additional attaching parts must be adopted to make it be fixedly connected with.
Summary of the invention
In order to meet alighting gear complete function, the designing requirement of lightweight high strength, overcome wheel fork to be connected with wheel shaft high strength and the contradiction of lightweight packages, the present invention proposes a kind of lifting gear for small-sized unmanned aircraft, lightweight packages and there is the good load capacity that withstands shocks.
Technical scheme of the present invention is:
Described a kind of lifting gear for small-sized unmanned aircraft, is characterized in that: comprise outer panel (1), interior plate (2), trailing wheel (6), front-wheel (5), front-wheel steering steering wheel (12) and wheel shaft wheel fork assembly;
Outer panel (1), interior plate (2) are arranged in parallel, be connected by side plate annex (15), front wheel members (7) and steering wheel annex between outer panel (1) with interior plate (2), form the main body supporting structure of lifting gear; Described main body supporting structure is fixed with vertical tail attaching parts, for being connected with vertical tail below small-sized unmanned aircraft fuselage;
Directly be connected with trailing wheel (6) by hind axle in the middle part of main body supporting structure;
The anterior steering wheel annex (10) upper fixed installation front-wheel steering steering wheel (12) of main body supporting structure, the steering wheel connecting rod (13) of front-wheel steering steering wheel (12) to be connected with wheel shaft (4) end in wheel shaft wheel fork assembly by cranking arm, and front-wheel steering steering wheel (12) is by steering wheel connecting rod (13) and crank arm and drive wheel shaft (4) to rotate;
Wheel shaft (4) coordinates with the wheel fork (3) of wheel shaft wheel fork assembly through front wheel members (7); The end that wheel shaft (4) coordinates with wheel fork (3) is designed with disk, disc face is designed with non-circular boss, and has tapped bore on raised head face; The joint face that wheel fork (3) and wheel shaft (4) coordinate has and non-circular boss size, through hole that shape is identical; When wheel shaft (4) coordinates with wheel fork (3), non-circular boss inserts in described through hole, and in described tapped bore, be provided with the screw (16) of band pad, by fastening to wheel shaft (4) and wheel fork (3); Wheel fork (3) is connected with front-wheel (5) by front wheel spindle;
Rear portion steering wheel annex (11) upper fixed installation yaw rudder steering wheel (14) of main body supporting structure; Yaw rudder steering wheel (14) controls the yaw rudder below small-sized unmanned aircraft fuselage on vertical tail.
Further preferred version, described a kind of lifting gear for small-sized unmanned aircraft, is characterized in that: the Strength surplus position at outer panel (1) and interior plate (2) rear portion has multiple circular lightening hole.
Beneficial effect
Lifting gear of the present invention has the following advantages:
1, in motion, can take off with the taxiing procedures landed in improve the control of sliding trajectory to aircraft and lateral stability;
2, in damping, the impact of trailing wheel suffered by landing moment as BOGEY WHEEL successively conducts to fuselage main structure by alighting gear dual-sided board, vertical tail attaching parts, has good damping effect;
3, in configuration aspects, the attaching parts of each annex of alighting gear side sheet room also as steering wheel and front-wheel while providing the supporting power to dual-sided board, improve the effective utilization to structure member, decrease the use of extra attaching parts, also the effect of loss of weight is had, stamp lightening hole at side plate rear strength flap portion simultaneously, effectively reduce structural weight;
4, at manufacture view, its structure is simple, and material is common, and member profile is succinct, is easy to processing, assembles up convenient and swift, for ease of maintenaince with replacing simultaneously.
Additional aspect of the present invention and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present invention and advantage will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1: be alighting gear overall construction drawing of the present invention;
Fig. 2: the constructional drawing being invention components;
Fig. 3: be connecting shaft view of the present invention;
Fig. 4: be wheel fork view of the present invention;
Wherein: 1, outer panel; 2, interior plate; 3, wheel fork; 4, wheel shaft; 5, front-wheel; 6, trailing wheel; 7, front wheel members; 8, front vertical tail attaching parts; 9, rear vertical tail attaching parts; 10, anterior steering wheel annex; 11, rear portion steering wheel annex; 12, front-wheel steering steering wheel; 13, steering wheel connecting rod; 14, yaw rudder steering wheel; 15, side plate annex; 16, screw.
Detailed description of the invention
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward ", " cw ", orientation or the position relationship of the instruction such as " conter clockwise " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.
The present invention be directed to the take-off and landing device designed with the Novel small-sized unmanned vehicle of double fins below fuselage, as shown in Figure 1, the lifting gear in the present embodiment comprises outer panel (1), interior plate (2), trailing wheel (6), front-wheel (5), front-wheel steering steering wheel (12) and wheel shaft wheel fork assembly.
Outer panel (1), interior plate (2) are arranged in parallel, be connected by side plate annex (15), front wheel members (7), anterior steering wheel annex (10) and rear portion steering wheel annex (11) between outer panel (1) with interior plate (2) and support, form the main body supporting structure of lifting gear; Described main body supporting structure is fixed with front vertical tail attaching parts (8) and rear vertical tail attaching parts (9), for being connected with vertical tail below small-sized unmanned aircraft fuselage, to support fuselage.
Directly be connected with trailing wheel (6) by hind axle in the middle part of main body supporting structure, trailing wheel (6) is main BOGEY WHEEL.
The anterior steering wheel annex (10) upper fixed installation front-wheel steering steering wheel (12) of main body supporting structure, for controlling front-wheel steering.The steering wheel connecting rod (13) of front-wheel steering steering wheel (12) to be connected with wheel shaft (4) end in wheel shaft wheel fork assembly by cranking arm, and front-wheel steering steering wheel (12) is by steering wheel connecting rod (13) and crank arm and drive wheel shaft (4) to rotate.
Wheel shaft (4) coordinates with the wheel fork (3) of wheel shaft wheel fork assembly through front wheel members (7), and the matching relationship of wheel shaft wheel fork assembly as shown in Figure 2.The end that wheel shaft (4) coordinates with wheel fork (3) is designed with disk, disc face is designed with non-circular boss, and has tapped bore on raised head face; The joint face that wheel fork (3) and wheel shaft (4) coordinate has and non-circular boss size, through hole that shape is identical; When wheel shaft (4) coordinates with wheel fork (3), non-circular boss inserts in described through hole, can realize wheel shaft (4) and drive wheel fork (3) to rotate.To go up to the air to prevent aircraft or advance middle wheel fork and wheel shaft depart from, the screw (16) being with pad be installed in described tapped bore, by wheel shaft (4) and wheel fork (3) fastening; Wheel fork (3) is connected with front-wheel (5) by front wheel spindle.
The design of this wheel shaft wheel fork assembly, compared to traditional fix in wheel shaft lower end one with material and have the circular piece in a hole, a flange is processed again on wheel fork, and utilize the design that wheel fork is fixedly connected with the circular steel part of wheel shaft lower end by four bolts and nut, there is better intensity and better manufacturability, its structure of what is more important is simple simultaneously, wheel fork could be fixedly connected with wheel shaft by the minimum needs of conventional confguration four bolts and nut, this new structure only needs a bolt and pad can realize being connected, this will save the quantity of attaching parts greatly, the weight of landing wheel fork assembly will be reduced, this is concerning extremely important aircraft.
Rear portion steering wheel annex (11) upper fixed installation yaw rudder steering wheel (14) of main body supporting structure; Yaw rudder steering wheel (14) controls the yaw rudder below small-sized unmanned aircraft fuselage on vertical tail, to control to turn in aircraft flight.
Adopt structure of the present invention, in motion, can take off with the taxiing procedures landed in improve the control of sliding trajectory to aircraft and lateral stability; In damping, the impact of trailing wheel suffered by landing moment as BOGEY WHEEL successively conducts to fuselage main structure by alighting gear dual-sided board, vertical tail attaching parts, has good damping effect; In configuration aspects, the attaching parts of each annex of alighting gear side sheet room also as steering wheel and front-wheel while providing the supporting power to dual-sided board, improve the effective utilization to structure member, decrease the use of extra attaching parts, also the effect of loss of weight is had, stamp lightening hole at side plate rear strength flap portion simultaneously, effectively reduce structural weight; At manufacture view, its structure is simple, and material is common, and member profile is succinct, is easy to processing, assembles up convenient and swift, for ease of maintenaince with replacing simultaneously.
Although illustrate and describe embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, those of ordinary skill in the art can change above-described embodiment within the scope of the invention when not departing from principle of the present invention and aim, revising, replacing and modification.
Claims (2)
1. for a lifting gear for small-sized unmanned aircraft, it is characterized in that: comprise outer panel (1), interior plate (2), trailing wheel (6), front-wheel (5), front-wheel steering steering wheel (12) and wheel shaft wheel fork assembly;
Outer panel (1), interior plate (2) are arranged in parallel, be connected by side plate annex (15), front wheel members (7) and steering wheel annex between outer panel (1) with interior plate (2), form the main body supporting structure of lifting gear; Described main body supporting structure is fixed with vertical tail attaching parts, for being connected with vertical tail below small-sized unmanned aircraft fuselage;
Directly be connected with trailing wheel (6) by hind axle in the middle part of main body supporting structure;
The anterior steering wheel annex (10) upper fixed installation front-wheel steering steering wheel (12) of main body supporting structure, the steering wheel connecting rod (13) of front-wheel steering steering wheel (12) to be connected with wheel shaft (4) end in wheel shaft wheel fork assembly by cranking arm, and front-wheel steering steering wheel (12) is by steering wheel connecting rod (13) and crank arm and drive wheel shaft (4) to rotate;
Wheel shaft (4) coordinates with the wheel fork (3) of wheel shaft wheel fork assembly through front wheel members (7); The end that wheel shaft (4) coordinates with wheel fork (3) is designed with disk, disc face is designed with non-circular boss, and has tapped bore on raised head face; The joint face that wheel fork (3) and wheel shaft (4) coordinate has and non-circular boss size, through hole that shape is identical; When wheel shaft (4) coordinates with wheel fork (3), non-circular boss inserts in described through hole, and in described tapped bore, be provided with the screw (16) of band pad, by fastening to wheel shaft (4) and wheel fork (3); Wheel fork (3) is connected with front-wheel (5) by front wheel spindle;
Rear portion steering wheel annex (11) upper fixed installation yaw rudder steering wheel (14) of main body supporting structure; Yaw rudder steering wheel (14) controls the yaw rudder below small-sized unmanned aircraft fuselage on vertical tail.
2. a kind of lifting gear for small-sized unmanned aircraft according to claim 1, is characterized in that: the Strength surplus position at outer panel (1) and interior plate (2) rear portion has multiple circular lightening hole.
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 true CN105480410A (en) | 2016-04-13 |
| CN105480410B CN105480410B (en) | 2017-05-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510940508.4A Expired - Fee Related CN105480410B (en) | 2015-12-15 | 2015-12-15 | Take-off and landing device for small-sized unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105480410B (en) |
Cited By (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 |
| US10946952B2 (en) | 2017-03-17 | 2021-03-16 | Safran Landing Systems Uk Ltd | Aircraft landing gear assembly |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090045283A1 (en) * | 2007-01-11 | 2009-02-19 | Lockheed Martin Corporation | System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations |
| 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 |
-
2015
- 2015-12-15 CN CN201510940508.4A patent/CN105480410B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090045283A1 (en) * | 2007-01-11 | 2009-02-19 | Lockheed Martin Corporation | System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations |
| 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 |
Cited By (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 |
| US10946952B2 (en) | 2017-03-17 | 2021-03-16 | Safran Landing Systems Uk Ltd | Aircraft landing gear assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105480410B (en) | 2017-05-24 |
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Granted publication date: 20170524 Termination date: 20191215 |
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| CF01 | Termination of patent right due to non-payment of annual fee |