CN204197279U - A kind of retractable landing gear - Google Patents
A kind of retractable landing gear Download PDFInfo
- Publication number
- CN204197279U CN204197279U CN201420647150.7U CN201420647150U CN204197279U CN 204197279 U CN204197279 U CN 204197279U CN 201420647150 U CN201420647150 U CN 201420647150U CN 204197279 U CN204197279 U CN 204197279U
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- strut bar
- thrust
- unmanned plane
- strut
- hole
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Abstract
The utility model discloses a kind of retractable landing gear, described alighting gear comprises: flexible connecting member; First strut bar, one end of described first strut bar is fixedly connected with described unmanned plane; Second strut bar, one end of described second strut bar is flexibly connected by the other end of described flexible connecting member and described first strut bar, makes to carry out relative sliding using the central axis of the central axis of described first strut bar or described second strut bar as direction of slip between described second strut bar and described first strut bar; The utility model overcomes in prior art and is often made impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and made to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body time serious and unmanned plane be caused to the defect of secondary injury.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, particularly a kind of retractable landing gear.
Background technology
Robot airplane is called for short " unmanned plane ", is the not manned aircraft utilizing radio robot to handle with the process controller provided for oneself.Without driving compartment on machine, but the equipment such as autopilot, process controller, information collecting device are installed.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital communication.Can take off as conventional airplane under radio telecommand or launch with booster rocket, also can be taken to by machine tool and throw in flight in the air.
In prior art, unmanned plane adopts a strut bar usually, and one end of this strut bar is fixedly connected with the fuselage of unmanned plane, the other end supports unmanned plane as the strong point when unmanned plane needs land, and unmanned plane in land process owing to there is great impulsive force in principle of inertia, now often make impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and make to collide between alighting gear and ground in prior art, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body and secondary injury be caused to unmanned plane time serious.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of retractable landing gear, this alighting gear makes unmanned plane drop down onto ground in the mode cushioning landing, overcome in prior art and often make impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and make to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body time serious and unmanned plane be caused to the defect of secondary injury.
For solving the problems of the technologies described above, the utility model provides a kind of retractable landing gear, is applied to unmanned plane, and described alighting gear comprises: flexible connecting member; First strut bar, one end of described first strut bar is fixedly connected with described unmanned plane; Second strut bar, one end of described second strut bar is flexibly connected by the other end of described flexible connecting member and described first strut bar, makes to carry out relative sliding using the central axis of the central axis of described first strut bar or described second strut bar as direction of slip between described second strut bar and described first strut bar; Wherein, when described unmanned plane needs to drop down onto ground, described unmanned plane presses described first strut bar, and described first strut bar and described second strut bar carry out relative sliding by described flexible connecting member, makes described unmanned plane drop down onto ground in the mode cushioning landing.
Further, described flexible connecting member comprises: spring, and described first strut bar is hollow cylindrical structure, and the other end that described spring is arranged on described first strut bar is inner; First thrust piece, described first thrust piece is fixed on described first strut bar, and the other end of described first strut bar is provided with chute, one end of described spring contacts with described first thrust piece, described spring is moved in the sliding area of described first strut bar, is that described first strut bar offers the position of described chute and this interval of fixed position of described first thrust piece between described sliding area; Second thrust piece, described second thrust piece is connected with described chute slide rail through described second strut bar, the other end of described spring contacts with one end of described second strut bar, and described second strut bar is slided in described sliding area by described chute.
Further, described first thrust piece comprises: the first screw; First thrust hole, described first thrust hole is arranged on described first strut bar, and described first screw is fixedly connected with described first strut bar through described first thrust hole.
Further, described second thrust piece comprises: the second screw; Second thrust hole, described second thrust hole is arranged on described second strut bar, and described second screw is connected with described chute slide rail through described second thrust hole successively, makes described first strut bar, described second strut bar carries out relative sliding by described second screw, described chute.
Further, described first thrust piece also comprises: block, described block is built in described first strut member, and described block offers through hole, described block, described both first strut members are fixed through described first thrust hole, described through hole by described first screw successively, and one end of described spring contacts with described block.
Further, one end of described first strut bar is that bolt is connected with being fixedly connected with between described unmanned plane.
A kind of retractable landing gear that the utility model provides, by one end of the first strut bar is fixedly connected with unmanned plane, second strut bar is flexibly connected by the other end of flexible connecting member and the first strut bar, make to carry out relative sliding using the central axis of the central axis of the first strut bar or the second strut bar as direction of slip between the second strut bar and the first strut bar, final realization is when unmanned plane needs to drop down onto ground, first unmanned plane presses the first strut bar, first strut bar presses the second strut bar by flexible connecting member, flexible buffer power existing for flexible connecting member, unmanned plane is made to drop down onto ground in the mode cushioning landing, overcome in prior art and often make impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and make to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body time serious and unmanned plane be caused to the defect of secondary injury.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
The integral structure schematic diagram of the retractable landing gear that Fig. 1 provides for the utility model embodiment; And
The fractionation structural representation of the retractable landing gear that Fig. 2 provides for the utility model embodiment.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, the every other embodiment that those of ordinary skill in the art obtain, all belongs to the scope of the utility model protection; Wherein involved in this enforcement "and/or" keyword, represent and or two kinds of situations, in other words, A and/or B mentioned by the embodiment of the present invention, illustrates A and B, A or B two kinds of situations, describes three kinds of states existing for A and B, as A and/or B, represent: only include A and do not comprise B; Only include B and do not comprise A; Comprise A and B.
A kind of retractable landing gear that the utility model embodiment provides, be applied to unmanned plane, this alighting gear makes unmanned plane drop down onto ground in the mode cushioning landing, overcome in prior art and often make impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and make to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body time serious and unmanned plane be caused to the defect of secondary injury.
Specifically, refer to Fig. 1-2, this alighting gear at least comprises: flexible connecting member, the first strut bar 100, second strut bar 101, wherein, one end of the first strut bar 100 is fixedly connected with the fuselage bottom of unmanned plane, and dismantles for ease of the first strut bar 100, to substitute and easy to maintenance, and the first strut bar 100 and being fixedly connected with between unmanned aerial vehicle body can be that bolt is connected, second strut bar 101 is flexibly connected by the other end of flexible connecting member and the first strut bar, in actual job process, flexible connecting member is as the buffer unit of alighting gear, make to carry out relative sliding using the central axis of the central axis of the first strut bar 100 or the second strut bar 101 as direction of slip between the second strut bar 101 and the first strut bar 100, final realization is when unmanned plane needs to drop down onto ground, first unmanned plane presses the first strut bar 100, first strut bar 100 presses the second strut bar 101 by flexible connecting member, flexible buffer power existing for flexible connecting member, unmanned plane is made to drop down onto ground in the mode cushioning landing.Wherein, the central axis of the first strut bar 100 and the central axis of the second strut bar 101 are on same is direct, and when unmanned plane drops down onto in the process on ground to cushion landing modes, relative distance between first strut bar 100 and the second strut bar 101 reduces gradually, and now flexible connecting member is in compressive state.
In the utility model embodiment, preferably, flexible connecting member at least comprises: spring 102, the first thrust piece, the second thrust piece, wherein, the first strut bar 100 is in hollow cylindrical structure (middle part of the first strut bar 100 is conducting structure), and now spring 102 is arranged on the inside of the other end of the first strut bar 100, first thrust piece is fixed on the first strut bar 100, one end of spring 102 contacts with the first thrust piece, first thrust piece is used for the end of support spring 102 as the strong point of spring 102, make spring 102 under the promotion of the second strut bar 101, realize compression, simultaneously, the other end of the first strut bar 100 is provided with chute 108, second thrust piece is connected with this chute 108 slide rail through the second strut bar 101, the other end of spring 102 contacts with the end, one end of the second strut bar 101, in actual job process, fixed position this section of interval at position and the first thrust piece that the first strut bar 100 offers chute 108 can be used as slip (compression) interval of spring 102, and the end, two ends of spring 102 corresponding and the first thrust piece respectively, the end of the second strut bar 101 contacts, when making unmanned plane press the first strut bar 100, the end of the first strut bar 100 presses spring 102, now because the other end of spring 102 contacts with the end of the second strut bar 101, make at the first strut bar 100, the pressure effect lower spring 102 of the second strut bar 101 starts to gradually reduce, and the first strut bar 100, second strut bar 101 starts relative sliding under the effect of chute 108, therebetween relative distance also reduces gradually, finally realize unmanned plane and drop down onto ground in the mode cushioning landing, the impulsive force of unmanned plane landing in prior art is prevented to directly act on alighting gear and make to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, also can impact unmanned aerial vehicle body and secondary injury be caused to unmanned plane time serious, decrease the maintenance cost of alighting gear, have the advantages that safety performance is high.
In the utility model embodiment, preferably, the first thrust piece at least comprises: the first screw 103, first thrust hole 104, wherein, the first thrust hole 104 is arranged on the first strut bar 100, and the first screw 103 is fixedly connected with the first strut bar 100 through the first thrust hole 104.In actual job process, in order to avoid due to the first screw 103, because of small volume, the boring groove of the first strut bar 100 blocks by non-can completely, spring 102 is finally caused from the space of the first screw 103 and the first strut bar 100 connecting portion, to walk around the first screw 103 and lose compression buffer action, this first thrust piece can also comprise a block 107, the contour structures of this block 107 and the boring structure of the first strut bar 100 suitable, make block 107 can be arranged on the inside of the first strut bar 100, and block 107 offers through hole, first screw 103 is successively through the first thrust hole 104, through hole is by block 107, both first strut members 100 are fixed, spring 102 is being contacted with block 107 all the time by the process compressed.
In the utility model embodiment, preferably, second thrust piece at least comprises: the second screw 105, second thrust 106, wherein, second thrust hole 106 is arranged on the second strut bar 101, and the second screw 105 is connected with chute 108 slide rail through the second thrust hole 106 successively, makes the first strut bar 100, second strut bar 101 can carry out relative sliding by the second screw 105, chute 108.
A kind of retractable landing gear that the utility model provides, its beneficial effect is as described below:
1., in the utility model, the second strut bar 101 is flexibly connected by the other end of flexible connecting member and the first strut bar 100, and flexible connecting member is as the buffer unit of alighting gear, make to carry out relative sliding using the central axis of the central axis of the first strut bar 100 or the second strut bar 101 as direction of slip between the second strut bar 101 and the first strut bar 100, final realization is when unmanned plane needs to drop down onto ground, first unmanned plane presses the first strut bar 100, first strut bar 100 presses the second strut bar 101 by flexible connecting member, flexible buffer power existing for flexible connecting member, unmanned plane is made to drop down onto ground in the mode cushioning landing, overcome in prior art and often make impulsive force directly act on this alighting gear by the mode of employing strut bar as alighting gear and make to collide between alighting gear and ground, and then unmanned plane is caused to the defect of secondary injury,
2., the utility model is interval as the slip (compression) of spring 102 by the first strut bar 100 being offered the position of chute 108 and fixed position this section of interval of the first thrust piece, and the end, two ends of spring 102 corresponding and the first thrust piece respectively, the end of the second strut bar 101 contacts, when making unmanned plane press the first strut bar 100, the end of the first strut bar 100 presses spring 102, now because the other end of spring 102 contacts with the end of the second strut bar 101, make at the first strut bar 100, the pressure effect lower spring 102 of the second strut bar 101 starts to gradually reduce, and the first strut bar 100, second strut bar 101 starts relative sliding under the effect of chute 108, therebetween relative distance also reduces gradually, finally realize unmanned plane and drop down onto ground in the mode cushioning landing, the impulsive force of unmanned plane landing in prior art is prevented to directly act on alighting gear and make to collide between alighting gear and ground, finally cause the ground terminal of alighting gear very easily impaired, decrease the maintenance cost of alighting gear, have the advantages that safety performance is high,
3., the utility model by setting up block 107 in the first thrust piece, and the boring structure of the contour structures of block 107 and the first strut bar 100 is suitable, make block 107 can be arranged on the inside of the first strut bar 100, and block 107 offers through hole, first screw 103 is successively through the first thrust hole 104, through hole is by block 107, both first strut members 100 are fixed, spring 102 is being contacted with block 107 all the time by the process compressed, avoid due to the first screw 103 that the boring groove of the first strut bar 100 blocks by non-can completely because of small volume, spring 102 is finally caused from the space of the first screw 103 and the first strut bar 100 connecting portion, to walk around the first screw 103 and lose compression buffer action.
It should be noted last that, above detailed description of the invention is only in order to illustrate the technical solution of the utility model and unrestricted, although be described in detail the utility model with reference to example, those of ordinary skill in the art is to be understood that, can modify to the technical solution of the utility model or equivalent replacement, and not departing from the spirit and scope of technical solutions of the utility model, it all should be encompassed in the middle of right of the present utility model.
Claims (6)
1. a retractable landing gear, is applied to unmanned plane, it is characterized in that, described alighting gear comprises:
Flexible connecting member;
First strut bar, one end of described first strut bar is fixedly connected with described unmanned plane;
Second strut bar, one end of described second strut bar is flexibly connected by the other end of described flexible connecting member and described first strut bar, makes to carry out relative sliding using the central axis of the central axis of described first strut bar or described second strut bar as direction of slip between described second strut bar and described first strut bar.
2. retractable landing gear as claimed in claim 1, it is characterized in that, described flexible connecting member comprises:
Spring, described first strut bar is hollow cylindrical structure, and the other end that described spring is arranged on described first strut bar is inner;
First thrust piece, described first thrust piece is fixed on described first strut bar, and the other end of described first strut bar is provided with chute, one end of described spring contacts with described first thrust piece, described spring is moved in the sliding area of described first strut bar, is that described first strut bar offers the position of described chute and this interval of fixed position of described first thrust piece between described sliding area;
Second thrust piece, described second thrust piece is connected with described chute slide rail through described second strut bar, the other end of described spring contacts with one end of described second strut bar, and described second strut bar is slided in described sliding area by described chute.
3. retractable landing gear as claimed in claim 2, it is characterized in that, described first thrust piece comprises:
First screw;
First thrust hole, described first thrust hole is arranged on described first strut bar, and described first screw is fixedly connected with described first strut bar through described first thrust hole.
4. retractable landing gear as claimed in claim 2, it is characterized in that, described second thrust piece comprises:
Second screw;
Second thrust hole, described second thrust hole is arranged on described second strut bar, and described second screw is connected with described chute slide rail through described second thrust hole successively, makes described first strut bar, described second strut bar carries out relative sliding by described second screw, described chute.
5. retractable landing gear as claimed in claim 3, it is characterized in that, described first thrust piece also comprises:
Block, described block is built in described first strut member, and described block offers through hole, described block, described both first strut members are fixed through described first thrust hole, described through hole by described first screw successively, and one end of described spring contacts with described block.
6. retractable landing gear as claimed in claim 1, is characterized in that,
One end of described first strut bar is that bolt is connected with being fixedly connected with between described unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420647150.7U CN204197279U (en) | 2014-10-31 | 2014-10-31 | A kind of retractable landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420647150.7U CN204197279U (en) | 2014-10-31 | 2014-10-31 | A kind of retractable landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204197279U true CN204197279U (en) | 2015-03-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420647150.7U Expired - Fee Related CN204197279U (en) | 2014-10-31 | 2014-10-31 | A kind of retractable landing gear |
Country Status (1)
| Country | Link |
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| CN (1) | CN204197279U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104986327B (en) * | 2015-06-17 | 2016-09-14 | 珠海市海卫科技有限公司 | Damping device |
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and an unmanned aerial vehicle using the landing gear |
| CN106347657A (en) * | 2016-09-30 | 2017-01-25 | 扬州锐德飞科技有限公司 | Unmanned aerial vehicle for surveying geographic information and working method thereof |
| 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 |
| CN108082459A (en) * | 2016-11-21 | 2018-05-29 | 成都天府新区光启未来技术研究院 | Undercarriage and aircraft |
| WO2018133192A1 (en) * | 2017-01-18 | 2018-07-26 | 深圳市大疆创新科技有限公司 | Stand assembly and unmanned aerial vehicle |
| CN110723279A (en) * | 2019-10-28 | 2020-01-24 | 中国人民解放军军事科学院国防工程研究院 | Unmanned aerial vehicle with protect function |
-
2014
- 2014-10-31 CN CN201420647150.7U patent/CN204197279U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and an unmanned aerial vehicle using the landing gear |
| WO2016179827A1 (en) * | 2015-05-14 | 2016-11-17 | 深圳市大疆创新科技有限公司 | Undercarriage and unmanned aerial vehicle using same |
| CN104986327B (en) * | 2015-06-17 | 2016-09-14 | 珠海市海卫科技有限公司 | Damping device |
| CN106347657A (en) * | 2016-09-30 | 2017-01-25 | 扬州锐德飞科技有限公司 | Unmanned aerial vehicle for surveying geographic information and working method thereof |
| 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 |
| CN106347657B (en) * | 2016-09-30 | 2019-02-19 | 扬州锐德飞科技有限公司 | A kind of unmanned plane and its working method for geography information exploration |
| CN108082459A (en) * | 2016-11-21 | 2018-05-29 | 成都天府新区光启未来技术研究院 | Undercarriage and aircraft |
| CN108082459B (en) * | 2016-11-21 | 2023-12-15 | 成都天府新区光启未来技术研究院 | Landing gear and aircraft |
| WO2018133192A1 (en) * | 2017-01-18 | 2018-07-26 | 深圳市大疆创新科技有限公司 | Stand assembly and unmanned aerial vehicle |
| CN110723279A (en) * | 2019-10-28 | 2020-01-24 | 中国人民解放军军事科学院国防工程研究院 | Unmanned aerial vehicle with protect function |
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| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 430000 Hubei province Wuhan Shiqiao Road No. 6 high-tech building Patentee after: EWATT CO., LTD. Address before: 430000 Hubei province Wuhan Shiqiao Road No. 6 high-tech building Patentee before: China Ewatt Technology Co., Ltd. |
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| C56 | Change in the name or address of the patentee | ||
| CP03 | Change of name, title or address |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan Shiqiao Road No. 6 high-tech building Patentee before: EWATT CO., LTD. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150311 Termination date: 20181031 |