CN104691746A - Single-wheel strut landing gear structure for large wingspan lightweight unmanned aerial vehicle - Google Patents
Single-wheel strut landing gear structure for large wingspan lightweight unmanned aerial vehicle Download PDFInfo
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- CN104691746A CN104691746A CN201410745482.3A CN201410745482A CN104691746A CN 104691746 A CN104691746 A CN 104691746A CN 201410745482 A CN201410745482 A CN 201410745482A CN 104691746 A CN104691746 A CN 104691746A
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Abstract
The invention discloses a single-wheel strut landing gear structure for a large wingspan lightweight unmanned aerial vehicle. The landing gear structure comprises a landing gear upper part, a landing gear lower part and an aircraft wheel component, wherein the landing gear upper part comprises a strut, a connecting sleeve, an automatic centering and pull wire sleeve, a connecting flange, a connecting inner liner and a top end inner liner; the strut is of a thin-wall round pipe structure completely made of composite material, the upper part of the strut penetrates through the hollow connecting flange connected with an aircraft body, the connecting inner liner is arranged on the inner wall of the connecting flange, the top end inner liner sleeves the top end of the strut, and the bending moment borne by the landing gear is transferred to the aircraft body by using the connecting inner liner and the top end inner liner. The landing gear structure disclosed by the invention is connected with the aircraft body by using the two-point connection of the thin-wall flange and the top end inner liner, and due to the design of connecting the strut and an aircraft wheel connector by using standard parts, convenience of mounting, dismounting, maintenance and transportation of the landing gear structure can be greatly improved.
Description
Technical field
The present invention relates to a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure, belong to unmanned air vehicle technique field.
Background technology
Landing gear structure many employings all-metal material of current unmanned plane, be connected with body and adopt auricle formula to connect, and be designed with special energy disperser and turning equipment to ensure the safety of other structures of aircraft and equipment, but because large span lightweight unmanned plane rate of sinking is little, it is low to transship, structural weight is required extremely harsh, therefore traditional material and design can not meet the actual requirement of such aircraft, and existing landing gear structure weight is large, manufacturing cost is high, install repairing comparatively complexity.
Summary of the invention
Technical matters to be solved by this invention is: for overcoming prior art deficiency, provides a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure, with meet with low cost, lightweight, reliability is high, working service requirement easily.
Technical solution of the present invention is: a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure, comprises alighting gear top, gear down and wheel assemblies;
Alighting gear top comprises pillar, coupling bush, automatic centering and bracing wire sleeve, butt flange, connection liner and top liner, described pillar is full composite material thin-wall circular tube structure, column upper section is through the butt flange be connected with fuselage of hollow, connecting liner is placed on butt flange inwall, top liner is placed on the top of pillar, utilizes connection liner and top liner two place to be delivered on fuselage by the moment of flexure suffered by alighting gear; Lower rod end inside is provided with the coupling bush be connected with gear down, lower rod end outside is provided with automatic centering and bracing wire sleeve, bracing wire upper cartridge tapping is connected with the bracing wire be connected with wing that can improve alighting gear lateral rigidity, and bottom tapping connects one end of little spring;
Gear down connects by being connected tumbler with alighting gear top; Wheel assemblies is connected for driving whole alighting gear to move with part bottom of rising and falling.
Gear down comprises connecting panel, pourable resin chock and wheel fork, and pourable resin chock is placed between wheel fork and connecting panel, completes the rotation of wheel and reduces friction coefficient, connects tumbler and is located on connecting panel.
Wheel assemblies comprises deep groove ball bearing, wheel hub and wheel shaft, the two ends of the wheel shaft be wherein connected with wheel fork two ends are provided with endoporus, wheel shaft liner embeds in endoporus, automatic centering attaching parts is by wheel shaft liner access endoporus, be fixed by fluted nut, automatic centering attaching parts connects the other end of little spring; Deep groove ball bearing is installed in wheel hub, and wheel shaft is placed on deep groove ball bearing.
Wheel fork side is for turning over all over structure.
Except tire, all landing gear structure parts all adopt thin-wall construction.
The present invention's advantage is compared with prior art:
(1) the present invention adopts thin-walled composite material pillar as the main force support structure of alighting gear, other metal pieces also adopt thin-wall construction, and the rotating function of alighting gear replaces traditional each class bearing by pourable resin chock, these designs all greatly reduce structural weight.
(2) the present invention adopts the two-point form of thin-wall flange formula and top liner to be connected with fuselage according to the loading characteristic of self, and the pillar of design is standard room with wheel attaching parts and is connected, the convenient degree that these designs substantially increase landing gear structure dismounting, keep in repair and transport.
(3) the present invention is designed with High-strength cable in alighting gear both sides, and this design greatly can improve the lateral rigidity of alighting gear, and automatic centering and bracing wire sleeve part have the effect of connecting stay wire and automatic centering little spring simultaneously.
(4) the present invention utilizes the spring that weight is extremely light, pulling force is less to complete automatic centering function, and during to prevent unmanned plane airflight, aerodynamic loading makes wheel sway, causes calamitous landing.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is alighting gear upper mechanism schematic diagram;
Fig. 3 is gear down and wheel assemblies connection diagram;
Fig. 4 is wheel fork structural representation;
Fig. 5 is pourable resin chock structural representation;
Fig. 6 is coupling bush structural representation;
Fig. 7 is automatic centering and bracing wire tube-in-tube structure schematic diagram;
Fig. 8 is connecting board structure schematic diagram;
Fig. 9 is for connecting tumbler structural representation;
Figure 10 is connecting flange structure schematic diagram;
Figure 11 is for connecting inner lining structure schematic diagram;
Figure 12 is top inner lining structure schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in detail.
A kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure, comprises alighting gear top, gear down and wheel assemblies;
Alighting gear top comprises pillar 1, coupling bush 2, automatic centering and bracing wire sleeve 15, butt flange 16, connects liner 17 and top liner 18, described pillar 1 is full composite material thin-wall circular tube structure, pillar 1 top is through the butt flange 16 be connected with fuselage of hollow, connecting liner 17 is placed on butt flange 16 inwall, top liner 18 is placed on the top of pillar 1, utilizes connection liner 17 and top liner 18 liang of places to be delivered on fuselage by the moment of flexure suffered by alighting gear; Inside, pillar 1 lower end is provided with the coupling bush 2 be connected with gear down, outside, pillar 1 lower end is provided with automatic centering and bracing wire sleeve 15, bracing wire sleeve 15 top tapping is connected with the bracing wire 21 be connected with wing that can improve alighting gear lateral rigidity, and bottom tapping connects one end of little spring 14;
Gear down connects by being connected tumbler 4 with alighting gear top; Wheel assemblies is connected for driving whole alighting gear to move with part bottom of rising and falling.
Gear down comprises connecting panel 3, pourable resin chock 5 and wheel fork 6, and pourable resin chock is placed between wheel fork 6 and connecting panel 3, completes the rotation of wheel and reduces friction coefficient, connects tumbler 4 and is located on connecting panel 3.
Wheel assemblies comprises deep groove ball bearing 12, wheel hub 13 and wheel shaft 7, the two ends of the wheel shaft 7 be wherein connected with wheel fork 6 two ends are provided with endoporus, wheel shaft liner 20 embeds in endoporus, automatic centering attaching parts 11 accesses in endoporus by wheel shaft liner 20, be fixed by fluted nut 10, automatic centering attaching parts 11 connects the other end of little spring 14; Deep groove ball bearing 12 is installed in wheel hub 13, and wheel shaft 7 is placed on deep groove ball bearing 12.
In order to the rigidity improving wheel fork 6 carries out turning over all over design at wheel fork 6 side.
Except tire, all landing gear structure parts all adopt thin-wall construction.
Specific works mode of the present invention is as follows:
During the tasks such as alighting gear to realize internal field transfer, ground roll-out, takes off on airport after installing, landing, tire lands, and is realized the smooth rolling of wheel by deep groove ball bearing 12; And the turning process of unmanned plane is completed by wheel fork 6, connection tumbler 4 and pourable resin chock 5, pourable resin chock 5 can play and reduce wheel fork and the effect being connected friction coefficient between tumbler; But the little spring 14 in unmanned plane during flying process with certain pretension can prevent aerodynamic loading from making wheel deflect makes alighting gear self complete automatic centering function, to ensure unmanned plane not drift off the runway safe falling; The load that the main force support structure of alighting gear bears for composite material pillar is delivered to wheel shaft 7 by wheel, then is delivered to wheel fork 6 by wheel shaft 7, then is delivered to coupling assembling by wheel fork 6, is finally delivered to fuselage by the butt flange 16 on pillar and top liner 18.
The unexposed technology of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (5)
1. a large span lightweight unmanned plane single-wheel telescopic landing gear structure, is characterized in that, comprise alighting gear top, gear down and wheel assemblies;
Alighting gear top comprises pillar (1), coupling bush (2), automatic centering and bracing wire sleeve (15), butt flange (16), connect liner (17) and top liner (18), described pillar (1) is full composite material thin-wall circular tube structure, pillar (1) top is through the butt flange (16) be connected with fuselage of hollow, connecting liner (17) is placed on butt flange (16) inwall, top liner (18) is placed on the top of pillar (1), connection liner (17) and top liner (18) two place is utilized to be delivered on fuselage by the moment of flexure suffered by alighting gear, inside, pillar (1) lower end is provided with the coupling bush (2) be connected with gear down, pillar (1) outside, lower end is provided with automatic centering and bracing wire sleeve (15), bracing wire sleeve (15) top tapping is connected with the bracing wire (21) be connected with wing that can improve alighting gear lateral rigidity, and bottom tapping connects one end of little spring (14),
Gear down connects by being connected tumbler (4) with alighting gear top; Wheel assemblies is connected for driving whole alighting gear to move with part bottom of rising and falling.
2. a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure as claimed in claim 1, it is characterized in that, gear down comprises connecting panel (3), pourable resin chock (5) and wheel fork (6), pourable resin chock is placed between wheel fork (6) and connecting panel (3), complete the rotation of wheel and reduce friction coefficient, connecting tumbler (4) and be located on connecting panel (3).
3. a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure as claimed in claim 2, it is characterized in that, wheel assemblies comprises deep groove ball bearing (12), wheel hub (13) and wheel shaft (7), the two ends of the wheel shaft (7) be wherein connected with wheel fork (6) two ends are provided with endoporus, wheel shaft liner (20) embeds in endoporus, automatic centering attaching parts (11) is by wheel shaft liner (20) access endoporus, be fixed by fluted nut (10), automatic centering attaching parts (11) connects the other end of little spring (14); Deep groove ball bearing (12) is installed in wheel hub (13), and wheel shaft (7) is placed on deep groove ball bearing (12).
4. a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure as claimed in claim 3, it is characterized in that, wheel fork (6) side is for turning over all over structure.
5. a kind of large span lightweight unmanned plane single-wheel telescopic landing gear structure as claimed in claim 4, it is characterized in that, except tire, all landing gear structure parts all adopt thin-wall construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410745482.3A CN104691746B (en) | 2014-12-08 | 2014-12-08 | A kind of big span lightweight unmanned plane single-wheel telescopic landing gear structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410745482.3A CN104691746B (en) | 2014-12-08 | 2014-12-08 | A kind of big span lightweight unmanned plane single-wheel telescopic landing gear structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104691746A true CN104691746A (en) | 2015-06-10 |
| CN104691746B CN104691746B (en) | 2016-08-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410745482.3A Active CN104691746B (en) | 2014-12-08 | 2014-12-08 | A kind of big span lightweight unmanned plane single-wheel telescopic landing gear structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017008530A1 (en) * | 2015-07-16 | 2017-01-19 | 张萍 | Landing gear for unmanned aerial vehicle |
| WO2017107753A1 (en) * | 2015-12-24 | 2017-06-29 | 广州亿航智能技术有限公司 | Drone |
| CN112776979A (en) * | 2021-04-02 | 2021-05-11 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN113733596A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | Composite material light undercarriage wheel structure and forming method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB398411A (en) * | 1932-04-26 | 1933-09-14 | Dornier Metallbauten Gmbh | Retractable landing gear for aircraft |
| GB673252A (en) * | 1950-04-18 | 1952-06-04 | John Harlin Geisse | Improvements relating to aircraft undercarriages |
| EP0039639A1 (en) * | 1980-05-07 | 1981-11-11 | AEROSPATIALE Société Nationale Industrielle | Landing gear strut for an aircraft main undercarriage |
| CN101142113A (en) * | 2005-03-16 | 2008-03-12 | Hr德克斯特隆公司 | Techniques for employing electric brakes to control movement of rotatable components |
-
2014
- 2014-12-08 CN CN201410745482.3A patent/CN104691746B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB398411A (en) * | 1932-04-26 | 1933-09-14 | Dornier Metallbauten Gmbh | Retractable landing gear for aircraft |
| GB673252A (en) * | 1950-04-18 | 1952-06-04 | John Harlin Geisse | Improvements relating to aircraft undercarriages |
| EP0039639A1 (en) * | 1980-05-07 | 1981-11-11 | AEROSPATIALE Société Nationale Industrielle | Landing gear strut for an aircraft main undercarriage |
| CN101142113A (en) * | 2005-03-16 | 2008-03-12 | Hr德克斯特隆公司 | Techniques for employing electric brakes to control movement of rotatable components |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017008530A1 (en) * | 2015-07-16 | 2017-01-19 | 张萍 | Landing gear for unmanned aerial vehicle |
| WO2017107753A1 (en) * | 2015-12-24 | 2017-06-29 | 广州亿航智能技术有限公司 | Drone |
| CN112776979A (en) * | 2021-04-02 | 2021-05-11 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN112776979B (en) * | 2021-04-02 | 2021-08-10 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN113733596A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | Composite material light undercarriage wheel structure and forming method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104691746B (en) | 2016-08-17 |
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