CN206288229U - A kind of SUAV landing buffer system - Google Patents
A kind of SUAV landing buffer system Download PDFInfo
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- CN206288229U CN206288229U CN201621299568.9U CN201621299568U CN206288229U CN 206288229 U CN206288229 U CN 206288229U CN 201621299568 U CN201621299568 U CN 201621299568U CN 206288229 U CN206288229 U CN 206288229U
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Abstract
A kind of SUAV landing buffer system, including being symmetricly set on the left landing buffer mechanism of body structure on two sides identical and right landing buffer mechanism, in right landing buffer mechanism, hold-down support is separately fixed on body, is conducive to spreading the landing load for being transferred to fuselage；Oil-gas type buffer and strut are connected by universal joint with hold-down support, discharge the rotational restraint of junction, it is to avoid skid produces clamping stagnation in sliding process；During aircraft landing, skid is slided towards airplane wingtip direction, compresses oil-gas type buffer, absorbs landing shock energy, reduces aircraft landing overload；Landing load passes to fuselage by skid, strut and oil-gas type buffer, while can be convenient for changing sleeve easy to wear using being threadedly coupled between skid and sleeve；And installed by by oil-gas type buffer " inversion ", the size with fuselage connects bearing is effectively reduced, obtain obvious weight loss effect；By strut and freely slidable skid, it is ensured that stability during aircraft landing.
Description
Technical field
The utility model is related to unmanned plane land technical field, more particularly to a kind of SUAV landing buffer system.
Background technology
Unmanned plane can be divided into for strategy, tactics, the large-scale unmanned plane attacked and for practicing shooting, meteorological exploration, aviation
Photography etc. SUAV, for large-scale unmanned plane, landing buffer system is generally oil-gas type undercarriage, the technology more into
It is ripe；But for SUAV, widely used at present is securing bracket structure, and the structure is general by metal tube or spring leaf structure
Into, landing shock energy is absorbed by the elastic deformation of structure during aircraft landing, buffering is less efficient, easily causes aircraft bounce,
Even aircraft is caused to be toppled over.
In addition, most of SUAVs all need to reuse, traditional securing bracket or chip architecture of the spring, due to buffering
Less efficient, landing shock overload is larger, and the structure service life of body is reduced to a certain extent.
Utility model content
The technical problem that the utility model is solved is to provide a kind of SUAV landing buffer system, with solution
State the shortcoming in background technology.
The technical problem that the utility model is solved is realized using following technical scheme：
A kind of SUAV landing buffer system, including it is symmetricly set on the body left landing buffer of structure on two sides identical
Mechanism and right landing buffer mechanism, in right landing buffer mechanism, hold-down support, No. two hold-down supports, No. three hold-down supports,
No. four hold-down supports and No. five hold-down supports are separately fixed on body, and one end of skid is by a universal joint and support
One end connects, and the other end is set with sleeve, and the other end of support is fixed on No. two hold-down supports, and a universal joint is arranged on
On a number hold-down support；Connecting rod one end is connected with a universal joint, and the other end is arranged on No. three hold-down supports, and oil-gas type delays
Rush device one end to be connected with No. two universal joints, the other end is connected with connector, No. two universal joints are arranged on No. four hold-down supports
On, strut one end is connected with No. three universal joints, and the other end is connected with connector, and No. three universal joints are arranged on No. five fixed branch
On seat, connector is arranged on sleeve.
It is provided with the utility model, on skid for covering sleeved screw thread.
In the utility model, oil-gas type buffer is reverse mounted, is conducive to reducing the size with fuselage connects bearing,
Obtain obvious weight loss effect.
In the utility model, connector is connection sheet, and is provided with connection sheet for installing lock bolt hole.
In the utility model, the specific number of assembling steps of SUAV landing buffer system is as follows：
The left landing buffer mechanism of assembling body side, skid and sleeve is connected through a screw thread, by bolt first
Connector is fixed on sleeve；Secondly, by a universal joint, three Universal connectors of No. two universal joints and No. three universal joints
Head be bolted with a hold-down support, No. four hold-down supports and No. five hold-down supports respectively, support one end with No. one ten thousand
Connected to joint, the other end is bolted with No. two hold-down supports；Again, oil-gas type buffer is bolt-connected to
No. two universal joints, strut is bolt-connected to No. three universal joints, and skid is bolt-connected to a universal joint, even
Bar is connected with a universal joint, No. three hold-down supports respectively；Finally, oil-gas type buffer, strut and connector are connected；Treat
After left landing buffer mechanism assembling is finished, right landing buffer mechanism is being assembled according to above-mentioned steps.
Beneficial effect：The utility model is buffered using slide-type, simple structure, lightweight, low cost；It is universal by three
Joint is connected, it is to avoid skid produces clamping stagnation in sliding process；By increasing oil-gas type buffer, buffering efficiency is effectively improved,
Overload of landing is reduced, so as to reduce the landing load for passing to fuselage, the structural life-time of body is improved；Simultaneously in skid and sleeve
Between using threaded connection, can be convenient for changing sleeve easy to wear；And installed by by oil-gas type buffer " inversion ", effectively
Reduce the size with fuselage connects bearing, obtain obvious weight loss effect；By strut and freely slidable skid, it is ensured that fly
Stability when machine lands.
Brief description of the drawings
Fig. 1 is the front view of preferred embodiment of the present utility model.
Fig. 2 is the side view of preferred embodiment of the present utility model.
Fig. 3 is the isometric views of preferred embodiment of the present utility model.
Specific embodiment
In order that technological means, creation characteristic, reached purpose and effect that the utility model is realized are easy to understand, under
Face combines and is specifically illustrating, and the utility model is expanded on further.
Referring to a kind of SUAV landing buffer system of Fig. 1 ~ Fig. 3, including it is symmetricly set on body structure on two sides phase
Same left landing buffer mechanism and right landing buffer mechanism, right landing buffer mechanism includes body 1, oil-gas type buffer 2, skid
3rd, sleeve 4, connecting rod 5, the hold-down support 9, two of universal joint 8, of universal joint 7, two of a support 6, hold-down support 10,
11, No. four hold-down supports 12 of No. three hold-down supports, the hold-down support 15 of universal joint 14, five of connection sheet 13, three and strut 16；
Wherein, 11, No. four hold-down supports 12 of the hold-down support of hold-down support 10, three of hold-down support 9, two and No. five hold-down supports
15 are fixed on body 1 by rivet respectively, and one end of skid 3 is connected by a universal joint 7 with one end of support 6, separately
One end is set with sleeve 4, and the other end of support 6 is fixed on No. two hold-down supports 10, and a universal joint 7 is arranged on No. one admittedly
Determine on bearing 9；The one end of connecting rod 5 is connected with a universal joint 7, and the other end is arranged on No. three hold-down supports 11, and oil-gas type delays
Rush the one end of device 2 to be connected with No. two universal joints 8, the other end is connected with connection sheet 13, No. two universal joints 8 are arranged on No. four fixations
On bearing 12, the one end of strut 16 is connected with No. three universal joints 14, and the other end is connected with connection sheet 13, and No. three universal joints 14 are pacified
On No. five hold-down supports 15, connection sheet 13 is arranged on sleeve 4.
In the present embodiment, the screw thread for covering sleeved 4 is provided with skid 3.
In the present embodiment, oil-gas type buffer 2 is reverse mounted, is conducive to reducing the size with fuselage connects bearing,
Obtain obvious weight loss effect.
In the present embodiment, specific number of assembling steps is as follows：
The left landing buffer mechanism of assembling body 1 side, skid 3 and sleeve 4 is connected through a screw thread, by spiral shell first
Be fixed on connection sheet 13 on sleeve 4 by bolt；Secondly, by 7, No. two universal joints 8 of a universal joint and No. three universal joints 14
Three universal joints are bolted with 9, No. four hold-down supports 12 of a hold-down support and No. five hold-down supports 15 respectively, branch
The one end of frame 6 is connected with a universal joint 7, and the other end is bolted with No. two hold-down supports 10；Again, oil-gas type is delayed
Rush device 2 and be bolt-connected to No. two universal joints 8, strut 16 is bolt-connected to No. three universal joints 14, and skid 3 passes through
A universal joint 7 is bolted to, connecting rod 5 is connected with 7, No. three hold-down supports 11 of a universal joint respectively；Finally, by oil
Gas formula buffer 2, strut 16 is connected with connection sheet 13；After the assembling of Dai Zuo landing buffers mechanism is finished, according to above-mentioned steps group
Zhuan You landing buffers mechanism.
In the present embodiment, oil-gas type buffer 2 and strut 16 are connected by universal joint with body 1 respectively, to discharge
The rotational restraint of junction, it is to avoid skid 3 produces clamping stagnation in sliding process；During aircraft landing, skid 3 is towards airplane wingtip direction
Slide, compression oil-gas type buffer 2 absorbs landing shock energy, reduce aircraft landing overload, landing load is by skid 3, support
Bar 16 and oil-gas type buffer 2 pass to fuselage, and five hold-down supports are installed on fuselage reinforcing frame, are conducive to diffusion to transmit
To the landing load of fuselage.
General principle of the present utility model and principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the utility model spirit and scope are not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appending claims and its equivalent thereof.
Claims (4)
1. a kind of SUAV landing buffer system, it is characterised in that including being symmetricly set on body structure on two sides identical
Left landing buffer mechanism and right landing buffer mechanism, in right landing buffer mechanism, hold-down support, No. two hold-down supports, three
Number hold-down support, No. four hold-down supports and No. five hold-down supports are separately fixed on body, and one end of skid is universal by No. one
Joint is connected with one end of support, and the other end is set with sleeve, and the other end of support is fixed on No. two hold-down supports, No. one ten thousand
It is arranged on a hold-down support to joint；Connecting rod one end is connected with a universal joint, and the other end is arranged on No. three fixed branch
On seat, oil-gas type buffer one end is connected with No. two universal joints, and the other end is connected with connector, and No. two universal joints are arranged on
On No. four hold-down supports, strut one end is connected with No. three universal joints, and the other end is connected with connector, and No. three universal joints are installed
On No. five hold-down supports, connector is arranged on sleeve.
2. a kind of SUAV landing buffer system according to claim 1, it is characterised in that use is provided with skid
In the sleeved screw thread of set.
3. a kind of SUAV landing buffer system according to claim 1, it is characterised in that oil-gas type buffer is
It is reverse mounted.
4. a kind of SUAV landing buffer system according to claim 1, it is characterised in that connector is connection
Piece, and be provided with connection sheet for installing lock bolt hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621299568.9U CN206288229U (en) | 2016-11-30 | 2016-11-30 | A kind of SUAV landing buffer system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621299568.9U CN206288229U (en) | 2016-11-30 | 2016-11-30 | A kind of SUAV landing buffer system |
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| Publication Number | Publication Date |
|---|---|
| CN206288229U true CN206288229U (en) | 2017-06-30 |
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ID=59097860
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621299568.9U Active CN206288229U (en) | 2016-11-30 | 2016-11-30 | A kind of SUAV landing buffer system |
Country Status (1)
| Country | Link |
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| CN (1) | CN206288229U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477031A (en) * | 2016-11-30 | 2017-03-08 | 江西洪都航空工业集团有限责任公司 | A kind of SUAV landing buffer system |
| CN109229372A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of seaplane pole structure |
| CN109941449A (en) * | 2019-03-18 | 2019-06-28 | 西安爱生技术集团公司 | A kind of landing energy absorption device of unmanned plane |
-
2016
- 2016-11-30 CN CN201621299568.9U patent/CN206288229U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477031A (en) * | 2016-11-30 | 2017-03-08 | 江西洪都航空工业集团有限责任公司 | A kind of SUAV landing buffer system |
| CN109229372A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of seaplane pole structure |
| CN109941449A (en) * | 2019-03-18 | 2019-06-28 | 西安爱生技术集团公司 | A kind of landing energy absorption device of unmanned plane |
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