CN205256659U - Undercarriage structure of multiaxis aircraft - Google Patents
Undercarriage structure of multiaxis aircraft Download PDFInfo
- Publication number
- CN205256659U CN205256659U CN201520974264.7U CN201520974264U CN205256659U CN 205256659 U CN205256659 U CN 205256659U CN 201520974264 U CN201520974264 U CN 201520974264U CN 205256659 U CN205256659 U CN 205256659U
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- footing
- support bar
- utility
- stay pipe
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Abstract
The utility model discloses an undercarriage structure of multiaxis aircraft, it contains multiaxis aircraft (1) and installs the undercarriage in its armshaft bottom, the undercarriage contain a whole for stay tube (2) of hollow tube column structure, the inside of this stay tube (2) is provided with its inner wall clearance sliding fit that can laminate bracing piece (3), a footing rather than normal running fit (4) are installed to the other end of bracing piece (3), the one end fixed mounting that bracing piece (3) are located near footing (4) has one positioning seat (5). The utility model discloses simple structure can realize multiaxis aircraft taking off and land under outdoor full topography feature to can be based on real -time topography and make corresponding adjustment, make its accommodation more extensively.
Description
Technical field
The utility model relates to the processing and manufacturing field of aircraft, what be specifically related to is a kind of landing gear structure of Multi-axis aircraft.
Background technology
The landing gear structure of common Multi-axis aircraft is fixed structure mostly in the market, and this kind of structure is mainly the ideal landing environment comparatively smooth for landing place, but seldom there is so desirable landing environment in actual wild environment, how much can there is irregular problem, for this, common way is, at the footing place of undercarriage, mobilizable angle is installed, this kind of structure up-and-down ground of can effectively fitting, but but cannot under the larger place environment of drop, carry out landing operation, have stronger limitation.
Utility model content
The utility model object is to provide a kind of landing gear structure of Multi-axis aircraft, and it can solve existing problem in background technology effectively.
In order to solve existing problem in background technology, it comprises Multi-axis aircraft 1 and is arranged on the undercarriage of its armshaft bottom, described undercarriage comprises the stay pipe 2 that an entirety is hollow tubular structure, the inside of this stay pipe 2 is provided with the support bar 3 that its inwall gap of can fitting is slidably matched, the other end of described support bar 3 is provided with a footing being rotatably assorted with it 4, described support bar 3 is positioned near one end of footing 4 and is installed with a positioning seat 5, one side of this positioning seat 5 is provided with the first ear seat 51, on the first described ear seat 51, be provided with it and be rotationally connected the telescoping cylinder 6 coordinating, the other end of this telescoping cylinder 6 is rotationally connected and coordinates with the second ear seat 7, the second described ear seat 7 is fixed on the bottom of armshaft.
In described stay pipe 2, be provided with spring, one end of this spring withstands on the end of support bar 3, and its other end withstands on the one end that is positioned at close armshaft in stay pipe 2.
Owing to having adopted above technical scheme, the utlity model has following beneficial effect: simple in structure, can realize the landing of Multi-axis aircraft under outdoor full terrain environment, and can make corresponding adjustment according to real-time landform, make its accommodation more extensive.
Brief description of the drawings
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is only embodiment more of the present utility model, for those of ordinary skill in the art, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is structural representation of the present utility model.
Detailed description of the invention
For technological means, creation characteristic that the utility model is realized, reach object and effect is easy to understand, below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is clearly and completely described.
Referring to Fig. 1, this detailed description of the invention is to be achieved by the following technical solutions, and it comprises Multi-axis aircraft 1 and is arranged on the undercarriage of its armshaft bottom, described undercarriage comprises the stay pipe 2 that an entirety is hollow tubular structure, the inside of this stay pipe 2 is provided with the support bar 3 that its inwall gap of can fitting is slidably matched, the other end of described support bar 3 is provided with a footing being rotatably assorted with it 4, described support bar 3 is positioned near one end of footing 4 and is installed with a positioning seat 5, one side of this positioning seat 5 is provided with the first ear seat 51, on the first described ear seat 51, be provided with it and be rotationally connected the telescoping cylinder 6 coordinating, the other end of this telescoping cylinder 6 is rotationally connected and coordinates with the second ear seat 7, the second described ear seat 7 is fixed on the bottom of armshaft.
In described stay pipe 2, be provided with spring, one end of this spring withstands on the end of support bar 3, and its other end withstands on the one end that is positioned at close armshaft in stay pipe 2.
Owing to having adopted above technical scheme, this detailed description of the invention has following beneficial effect: simple in structure, can realize the landing of Multi-axis aircraft under outdoor full terrain environment, and can make corresponding adjustment according to real-time landform, make its accommodation more extensive.
Finally it should be noted that: above embodiment only, in order to the technical solution of the utility model to be described, is not intended to limit; Although the utility model is had been described in detail with reference to previous embodiment, those of ordinary skill in the art is to be understood that, its technical scheme that still can record aforementioned each embodiment is modified, or part technical characterictic is wherein equal to replacement; And these amendments or replacement do not make the essence of appropriate technical solution depart from the spirit and scope of the each embodiment technical scheme of the utility model.
Claims (2)
1. a landing gear structure for Multi-axis aircraft, it comprises Multi-axis aircraft (1) and is arranged on the undercarriage of its armshaft bottom, it is characterized in that described undercarriage comprises the stay pipe that an entirety is hollow tubular structure (2), the inside of this stay pipe (2) is provided with the support bar (3) that its inwall gap of can fitting is slidably matched, the other end of described support bar (3) is provided with a footing being rotatably assorted with it (4), described support bar (3) is positioned near one end of footing (4) and is installed with a positioning seat (5), one side of this positioning seat (5) is provided with the first ear seat (51), on the first described ear seat (51), be provided with it and be rotationally connected the telescoping cylinder (6) coordinating, the other end of this telescoping cylinder (6) is rotationally connected and coordinates with the second ear seat (7), the second described ear seat (7) is fixed on the bottom of armshaft.
2. the landing gear structure of a kind of Multi-axis aircraft according to claim 1, it is characterized in that being provided with spring in described stay pipe (2), one end of this spring withstands on the end of support bar (3), and its other end withstands on the one end that is positioned at close armshaft in stay pipe (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520974264.7U CN205256659U (en) | 2015-12-01 | 2015-12-01 | Undercarriage structure of multiaxis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520974264.7U CN205256659U (en) | 2015-12-01 | 2015-12-01 | Undercarriage structure of multiaxis aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205256659U true CN205256659U (en) | 2016-05-25 |
Family
ID=55998204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520974264.7U Expired - Fee Related CN205256659U (en) | 2015-12-01 | 2015-12-01 | Undercarriage structure of multiaxis aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205256659U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347640A (en) * | 2016-09-30 | 2017-01-25 | 安徽翼讯飞行安全技术有限公司 | Unmanned aerial vehicle lander |
-
2015
- 2015-12-01 CN CN201520974264.7U patent/CN205256659U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347640A (en) * | 2016-09-30 | 2017-01-25 | 安徽翼讯飞行安全技术有限公司 | Unmanned aerial vehicle lander |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160525 Termination date: 20161201 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |