CN104002961A - Miniature helicopter undercarriage - Google Patents
Miniature helicopter undercarriage Download PDFInfo
- Publication number
- CN104002961A CN104002961A CN201410262739.XA CN201410262739A CN104002961A CN 104002961 A CN104002961 A CN 104002961A CN 201410262739 A CN201410262739 A CN 201410262739A CN 104002961 A CN104002961 A CN 104002961A
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- Prior art keywords
- supporting
- helicopter
- alighting gear
- spike
- chassis
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Links
- 238000010276 construction Methods 0.000 claims description 12
- 238000000034 method Methods 0.000 abstract description 9
- 230000003116 impacting effect Effects 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract 2
- 230000007704 transition Effects 0.000 abstract 2
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 230000035939 shock Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention relates to the technical field of air vehicles, and discloses a miniature helicopter undercarriage. The miniature helicopter undercarriage comprises two supporting feet arranged in parallel. Each supporting foot is provided with a supporting rod inclined at a set angle relative to the supporting foot. The miniature helicopter undercarriage further comprises transverse rods connected with the supporting rods, and the transverse rods are connected with the supporting feet through transition rods. An installation base for installing a helicopter base is arranged between the supporting rods. A supporting frame is arranged below the installation base and provided with a supporting structure. According to the miniature helicopter undercarriage, the transverse rods and the transition rods are arranged on the supporting feet, the impact resistant capacity of the supporting feet during landing is greatly improved, damage, caused by impacting, to a helicopter during landing is avoided, and the service life is effectively prolonged; the supporting structure is arranged, the impact resistance of the undercarriage is further improved, and the stability of a helicopter body in the flying process is improved; the undercarriage and the helicopter base are installed together, time and labor are saved in the assembling process, and meanwhile the whole helicopter body structure is compact.
Description
Technical field
The present invention relates to vehicle technology field, relate in particular to a kind of micro helicopter alighting gear.
Background technology
Alighting gear is to be arranged at aircraft bottom, for in aircraft takeoff landing on the ground or support aerocraft when planking and for ground (or water surface) mobile accessories apparatus, it is the indispensable pith of aircraft, does not have alighting gear aircraft not move on the ground.Alighting gear be unique one for supporting the parts of whole airplane, and alighting gear will bear certain impulsive force in the time that body lands.Landing gear structure of the prior art is easily subject to the recoil of bottom surface in the process of landing, and after using a period of time, the contact site of straight tube and pipe link easily fractures, and then fuselage is damaged.
There is unreasonable structure in the alighting gear of micro helicopter of the prior art, the process of rising and falling is unstable, the problems such as, effort time-consuming with fuselage assembling process, therefore, market is needed a kind of simple in structure, strong shock resistance badly, is saved time with fuselage assembling process, labour-saving micro helicopter alighting gear.
Summary of the invention
The object of the invention is to propose micro helicopter alighting gear, poor to solve in prior art alighting gear impact resistance, the problem of, effort time-consuming with fuselage assembling process.
For reaching this object, the present invention by the following technical solutions:
A kind of micro helicopter alighting gear, comprise two spikes that be arranged in parallel, on each described spike, be provided with described spike and be the strut bar that set angle tilts, also comprise the cross bar being connected with described strut bar, between described cross bar and described spike, be connected by transiting rod; Between described strut bar, be provided with the mount pad for mounting base, on described mount pad, be provided with the mounting hole of rectangular distribution; The below of described mount pad is provided with bracing frame, the curved structure of support frame as described above, and the two ends of described arcuate structure are fixed on described spike; Support frame as described above is provided with supporting construction.
Further, described support comprises chassis and be located at the axle bed on described chassis, and the bottom surface on described chassis is provided with for being fixed on the support pin in described mounting hole; Also comprise the link span being connected with chassis with described axle bed respectively.
Preferably, on described chassis, offer open-work; Described link span is provided with chute.
Further, described supporting construction comprises stay bearing plate, and described stay bearing plate is provided with pipe link.
Preferably, between described cross bar and described transiting rod, circular arc is connected; Between described transiting rod and described spike, circular arc is connected.
Further, a side of described spike is fixedly installed and is useful on the dividing plate that control setup is installed, and described dividing plate is provided with the open-work for expendable weight.
Preferably, between described mount pad and described support pin, be threaded connection.
Beneficial effect of the present invention is: the spike in the present invention is provided with cross bar and transiting rod, only increase simple structure, but can effectively strengthen the intensity of spike, the shock resistance of spike in the time of landing strengthened greatly, avoid impacting damage when helicopter is landed, effectively extended service life.
The present invention is provided with supporting construction below mount pad, has further strengthened the shock resistance of alighting gear, and has increased the stability of fuselage in flight course.
The present invention is installed together alighting gear and support, make that assembling process saves time more, labour-saving simultaneously, make whole housing construction compacter; Meanwhile, owing to being provided with open-work on the chassis of support He on dividing plate, alleviated the weight of whole body, the dismounting making and assembling are more convenient.
Brief description of the drawings
Fig. 1 is the integral structure schematic diagram of the micro helicopter alighting gear that provides of the embodiment of the present invention one;
Fig. 2 is the stand structure schematic diagram of the micro helicopter alighting gear that provides of the embodiment of the present invention one;
Fig. 3 is the supporting construction schematic diagram of the micro helicopter alighting gear that proposes of the embodiment of the present invention one.
In figure:
1, spike; 2, strut bar; 3, cross bar; 4, transiting rod; 5, mounting hole; 6, mount pad; 7, support; 71, chassis; 72, support pin; 73, open-work; 74, axle bed; 75, chute; 76, link span; 8, bracing frame; 9, supporting construction; 91, stay bearing plate; 92, pipe link.
Detailed description of the invention
Further illustrate technical scheme of the present invention below in conjunction with accompanying drawing and by detailed description of the invention.
Embodiment mono-
As shown in Figure 1 to Figure 3, be a kind of micro helicopter alighting gear that the present embodiment proposes, comprise two spikes 1 that be arranged in parallel, on each spike 1, be provided with spike 1 and be the strut bar 2 that set angle tilts, as one preferred embodiment, angle of inclination is 15o.Also comprise the cross bar 3 being connected with strut bar 2, between cross bar 3 and spike 1, be connected by transiting rod 4.In the present embodiment, between cross bar 3 and transiting rod 4, circular arc is connected; Between transiting rod 4 and spike 1, circular arc is connected.
Between strut bar 2, be provided with the mount pad 6 for mounting base 7, on mount pad 6, be provided with the mounting hole 5 of rectangular distribution.Wherein, support 7 comprises chassis 71 and is located at the axle bed 74 on chassis 71, and the bottom surface on chassis 71 is provided with for being fixed on the support pin 72 in mounting hole 5, for actv. alleviates the weight on chassis 71, offers open-work 73 on chassis 71.As one preferred embodiment, between mount pad 6 and support pin 72, be threaded connection.
Also comprise the link span 76 being connected with chassis 71 with axle bed 74 respectively, link span 76 is provided with chute 75.
Spike 1 in the present embodiment is provided with cross bar 3 and transiting rod 4, only increase simple structure, but can effectively strengthen the intensity of spike 1, the shock resistance of spike 1 in the time of landing strengthened greatly, avoid impacting damage when helicopter is landed, effectively extended service life.
As embodiment further, the below of mount pad 6 is provided with bracing frame 8, the curved structure of bracing frame 8, and the two ends of arcuate structure are fixed on spike 1.Bracing frame 8 is provided with supporting construction 9, and supporting construction 9 comprises stay bearing plate 91, and stay bearing plate 91 is provided with pipe link 92.
The present embodiment is provided with supporting construction 9 below mount pad 6, has further strengthened the shock resistance of alighting gear, and has increased the stability of fuselage in flight course.
Embodiment bis-
The difference of the present embodiment and embodiment mono-is, in the present embodiment between cross bar and transiting rod for right angle is connected, between cross bar and spike also for right angle is connected.
In the present embodiment, a side of spike is fixedly installed and is useful on the dividing plate that control setup is installed, and dividing plate is provided with the open-work for expendable weight.
The present embodiment is installed together alighting gear and support, make that assembling process saves time more, labour-saving simultaneously, make whole housing construction compacter.Meanwhile, owing to being provided with open-work on the chassis of support He on dividing plate, alleviated the weight of whole body, the dismounting making and assembling are more convenient.
Know-why of the present invention has below been described in conjunction with specific embodiments.These are described is in order to explain principle of the present invention, and can not be interpreted as by any way limiting the scope of the invention.Based on explanation herein, those skilled in the art does not need to pay performing creative labour can associate other detailed description of the invention of the present invention, within these modes all will fall into protection scope of the present invention.
Claims (7)
1. a micro helicopter alighting gear, comprise two spikes (1) that be arranged in parallel, on each described spike (1), be provided with described spike (1) and be the strut bar (2) that set angle tilts, it is characterized in that: also comprise the cross bar (3) being connected with described strut bar (2), between described cross bar (3) and described spike (1), be connected by transiting rod (4);
Between described strut bar (2), be provided with the mount pad (6) for mounting base (7), on described mount pad (6), be provided with the mounting hole (5) of rectangular distribution;
The below of described mount pad (6) is provided with bracing frame (8), the curved structure of support frame as described above (8), and the two ends of described arcuate structure are fixed on described spike (1);
Support frame as described above (8) is provided with supporting construction (9).
2. micro helicopter alighting gear according to claim 1, it is characterized in that: described support (7) comprises chassis (71) and be located at the axle bed (74) on described chassis (71), the bottom surface of described chassis (71) is provided with for being fixed on the support pin (72) in described mounting hole (5);
Also comprise the link span (76) being connected with chassis (71) with described axle bed (74) respectively.
3. micro helicopter alighting gear according to claim 2, is characterized in that: on described chassis (71), offer open-work (73);
Described link span (76) is provided with chute (75).
4. micro helicopter alighting gear according to claim 2, is characterized in that: described supporting construction (9) comprises stay bearing plate (91), and described stay bearing plate (91) is provided with pipe link (92).
5. micro helicopter alighting gear according to claim 1, is characterized in that: between described cross bar (3) and described transiting rod (4), circular arc is connected;
Between described transiting rod (4) and described spike (1), circular arc is connected.
6. micro helicopter alighting gear according to claim 5, is characterized in that: a side of described spike (1) is fixedly installed and is useful on the dividing plate that control setup is installed, and described dividing plate is provided with the open-work for expendable weight.
7. micro helicopter alighting gear according to claim 3, is characterized in that: between described mount pad (6) and described support pin (72), be threaded connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410262739.XA CN104002961A (en) | 2014-06-13 | 2014-06-13 | Miniature helicopter undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410262739.XA CN104002961A (en) | 2014-06-13 | 2014-06-13 | Miniature helicopter undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104002961A true CN104002961A (en) | 2014-08-27 |
Family
ID=51363926
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410262739.XA Pending CN104002961A (en) | 2014-06-13 | 2014-06-13 | Miniature helicopter undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104002961A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554714A (en) * | 2014-12-05 | 2015-04-29 | 张立 | Splitting type undercarriage for helicopter model |
| CN116101482A (en) * | 2023-04-17 | 2023-05-12 | 成都沃飞天驭科技有限公司 | Aircraft test platform and its landing gear, design method of landing gear |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201525501U (en) * | 2009-11-20 | 2010-07-14 | 无锡汉和航空技术有限公司 | Bracing frame of pilotless airplane |
| CN101830281A (en) * | 2010-05-18 | 2010-09-15 | 无锡汉和航空技术有限公司 | Unmanned helicopter for project |
| CN202754144U (en) * | 2012-07-30 | 2013-02-27 | 江阴市公安局 | Undercarriage |
| CN202896875U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | Fast assembling and disassembling structure of aircraft undercarriage |
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN203996875U (en) * | 2014-06-13 | 2014-12-10 | 杨雅茹 | A kind of micro helicopter alighting gear |
-
2014
- 2014-06-13 CN CN201410262739.XA patent/CN104002961A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201525501U (en) * | 2009-11-20 | 2010-07-14 | 无锡汉和航空技术有限公司 | Bracing frame of pilotless airplane |
| CN101830281A (en) * | 2010-05-18 | 2010-09-15 | 无锡汉和航空技术有限公司 | Unmanned helicopter for project |
| CN202754144U (en) * | 2012-07-30 | 2013-02-27 | 江阴市公安局 | Undercarriage |
| CN202896875U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | Fast assembling and disassembling structure of aircraft undercarriage |
| CN103803070A (en) * | 2014-01-24 | 2014-05-21 | 兰州神龙航空科技有限公司 | Engineering rotor-type unmanned aircraft |
| CN203996875U (en) * | 2014-06-13 | 2014-12-10 | 杨雅茹 | A kind of micro helicopter alighting gear |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554714A (en) * | 2014-12-05 | 2015-04-29 | 张立 | Splitting type undercarriage for helicopter model |
| CN116101482A (en) * | 2023-04-17 | 2023-05-12 | 成都沃飞天驭科技有限公司 | Aircraft test platform and its landing gear, design method of landing gear |
| CN116101482B (en) * | 2023-04-17 | 2023-07-18 | 成都沃飞天驭科技有限公司 | Aircraft test platform and its landing gear, design method of landing gear |
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| PB01 | Publication | ||
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| ASS | Succession or assignment of patent right |
Owner name: YANG YARU Free format text: FORMER OWNER: HAN SHIYU Effective date: 20141029 |
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| C41 | Transfer of patent application or patent right or utility model | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yang Yaru Inventor before: Han Shiyu |
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| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: HAN SHIYU TO: YANG YARU |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20141029 Address after: 075000 Zhangjiakou City, Hebei province Qiaodong District Lao Ya Zhuang Zhen Qian Tun Village No. 1 Applicant after: Yang Yaru Address before: 075000, No. 3, unit 14, building 203, Jianguo East Street, Xuanhua District, Hebei, Zhangjiakou Applicant before: Han Shiyu |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140827 |