CN104787312A - Cross beam structure of skid landing gear - Google Patents
Cross beam structure of skid landing gear Download PDFInfo
- Publication number
- CN104787312A CN104787312A CN201510161289.XA CN201510161289A CN104787312A CN 104787312 A CN104787312 A CN 104787312A CN 201510161289 A CN201510161289 A CN 201510161289A CN 104787312 A CN104787312 A CN 104787312A
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- China
- Prior art keywords
- bow
- beams
- sleeve pipe
- landing gear
- beam structure
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The invention provides a cross beam structure of a skid landing gear. The cross beam structure is simple, easy to form and convenient to mount and dismount and comprises bow beams and a casing tube, wherein the left and right bow beams are formed by bending round tubes, the section of the casing tube is circular, two ends of the casing tube are inserted into the left and right bow beams respectively, and the casing tube is fixedly connected with at least one of the bow beams; one hole is formed in the position, close to the bow position, of each of the left and right bow beams, and the bow beams are connected with an aircraft body connector through the holes and bolts. Two symmetrical half cross beams are adopted and are connected through the casing tube in the middle, and forming is easy; during mounting, the beams are connected with an aircraft body through bolts, the two half cross beams can be independently connected with the aircraft body without left-right positioning, and mounting is convenient; half of the cross beam on one side can be independently replaced when damaged, and the cost is low.
Description
Technical field
The present invention relates to helicopter skid landing gear, particularly relate to the beam structure of skid landing gear.
Background technology
The alighting gear of depopulated helicopter generally adopts skid landing gear, primarily of crossbeam and slip pipe composition.At present, the structure of crossbeam is generally overall pipe and bends to arc symmetrical structure.When crossbeam is installed on fuselage, adopt upper and lower clip that crossbeam is stuck; Simultaneously for carrying out location, left and right, during assembling, half clip need be riveted on crossbeam.This kind of beam structure is shaping and install relative complex, and when the damage of half of crossbeam, need change whole crossbeam, cost is large.
Summary of the invention
The technical problem to be solved in the present invention: the object of the present invention is to provide a kind of easy-formation, do not need to carry out location, left and right and the convenient skid landing gear beam structure installed.
Technical scheme of the present invention:
a kind of beam structure of skid landing gear, comprising: bow beam, sleeve pipe, wherein: described bow beam is pipe brake forming, comprise two, left and right, described casing profile is annular arrangement, and described sleeve pipe two is inserted in two the described bow beams in left and right respectively, and described sleeve pipe is fixedly connected with bow beam described at least one; The described bow beam in two, left and right is respectively having a hole near arc place, is connected between described bow beam and body joint by described hole bolt.
Alternatively, being provided with a cross section in described hole is the lining of annular arrangement, and the two ends of described lining are welded with described hole outer rim; Connected by described lining bolt between described bow beam and body joint.
Alternatively, between described bow beam and sleeve pipe be bolt connection.
Alternatively, between described bow beam and sleeve pipe be riveted joint.
Beneficial effect of the present invention: beam structure of the present invention adopts two symmetrical half beams, centre is connected to form by sleeve pipe, easy-formation; Be connected with bolts during installation with fuselage, two half beams can be connected alone with fuselage, do not need to carry out location, left and right, convenient installation; Can change separately when half of crossbeam damages, cost is low.
Accompanying drawing explanation
fig. 1it is the beam structure signal of skid landing gear of the present invention
figure.
fig. 2be
fig. 1analysing and observe of middle A-A cross section
figure.
fig. 3be
fig. 1signal is amplified at middle I place
figure;
fig. 4it is left side bow beam structural representation
figure.
Wherein: 1 be bow beam, 2 be sleeve pipe, 3 be bolt, 4 be nut, 5 be packing ring, 6 for lining, 7 is hole.
Detailed description of the invention
Embodiment 1:
as Fig. 1extremely
fig. 4shown in, the beam structure of a kind of skid landing gear that the present invention proposes, comprise assembly: bow beam 1, sleeve pipe 2, wherein: two bow beams 1 are pipe brake forming, sleeve pipe 2 cross section is annular arrangement, sleeve pipe 2 two is inserted in two bow beams 1 in left and right respectively, the inside face blind-mate of outside face and left and right two bow beams 1 of sleeve pipe 2.Sleeve pipe 2 is connected by bolt 3, nut 4 and packing ring 5 with the bow beam 1 of the left and right sides; Two bow beams 1 are respectively having a hole 7 near arc place, and between bow beam 1 and the body joint above it, passing hole 7 is connected with another bolt.
Further preferably, also have cross section be the lining 6 of annulus cylindricality through hole 7, be blind-mate between lining 6 and hole 7, the two ends that lining 6 stretches out hole 7 are welded with hole 7 outer rim; Bolt connection is carried out by lining 6 between bow beam 1 and body joint.This kind of scheme can increase the bolt Joint strenght between bow beam 1 and body joint.
The beam structure of the present embodiment adopts two symmetrical half beams, is middlely connected to form by sleeve pipe 2, easy-formation; Be connected with bolts during installation with fuselage, two half beams can be connected alone with fuselage, do not need to carry out location, left and right, convenient installation; Can change separately when half of crossbeam damages, cost is low.
Embodiment 2:
as Fig. 1extremely
fig. 4shown in, the present invention proposes
a kind of beam structure of skid landing gearcomprise assembly: bow beam 1, sleeve pipe 2, wherein: two bow beams 1 are pipe brake forming, sleeve pipe 2 cross section is annular arrangement, sleeve pipe 2 two is inserted in two bow beams 1 in left and right respectively, the inside face blind-mate of outside face and left and right two bow beams 1 of sleeve pipe 2.Sleeve pipe 2 and left and right sides bow beam 1 all pass through rivet interlacement; Two bow beams 1 are respectively having a hole 7 near arc place, and between bow beam 1 and the body joint above it, passing hole 7 bolt connects.
Further preferably, also have cross section be the lining 6 of annulus cylindricality through hole 7, be blind-mate between lining 6 and hole 7, the two ends that lining 6 stretches out hole 7 are welded with hole 7 outer rim; Bolt connection is carried out by lining 6 between bow beam 1 and body joint.This kind of scheme can increase the bolt Joint strenght between bow beam 1 and body joint.
Equally, the beam structure in the present embodiment adopts two symmetrical half beams, and centre is connected to form by sleeve pipe, easy-formation; Be connected with bolts during installation with fuselage, two half beams can be connected alone with fuselage, do not need to carry out location, left and right, convenient installation; Can change separately when half of crossbeam damages, cost is low.
Claims (4)
1. the beam structure of a skid landing gear, it is characterized in that, comprise: bow beam (1), sleeve pipe (2), wherein: described bow beam (1) is pipe brake forming, comprise two, left and right, described sleeve pipe (2) cross section is for being annular arrangement, described sleeve pipe (2) two is inserted in two the described bow beams (1) in left and right respectively, and described sleeve pipe (2) is fixedly connected with bow beam described at least one (1); Two, left and right described bow beam (1) is respectively having a hole (7) near arc place, is connected between described bow beam (1) and body joint by described hole (7) bolt.
2. the beam structure of skid landing gear according to claim 1, is characterized in that: be provided with the lining (6) that a cross section is annular arrangement in described hole, the two ends of described lining (6) are welded with hole (7) outer rim; Connected by described lining (6) bolt between described bow beam (1) and body joint.
3. the beam structure of skid landing gear according to claim 1 and 2, is characterized in that: for bolt connects between described bow beam (1) and sleeve pipe (2).
4. the beam structure of skid landing gear according to claim 1 and 2, is characterized in that: be riveted joint between described bow beam (1) and sleeve pipe (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161289.XA CN104787312A (en) | 2015-04-07 | 2015-04-07 | Cross beam structure of skid landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161289.XA CN104787312A (en) | 2015-04-07 | 2015-04-07 | Cross beam structure of skid landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104787312A true CN104787312A (en) | 2015-07-22 |
Family
ID=53552596
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510161289.XA Pending CN104787312A (en) | 2015-04-07 | 2015-04-07 | Cross beam structure of skid landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104787312A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108127934A (en) * | 2017-12-05 | 2018-06-08 | 深圳市科卫泰实业发展有限公司 | A kind of composite material multi-rotor aerocraft undercarriage and preparation method thereof |
| CN109278990A (en) * | 2017-07-19 | 2019-01-29 | 中国空空导弹研究院 | Support rod and the undercarriage and aircraft for using the support rod |
| CN110929444A (en) * | 2019-12-04 | 2020-03-27 | 中国直升机设计研究所 | Skid type undercarriage simulation design method |
| CN112173090A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Skid undercarriage and crossbeam height adjusting mechanism thereof |
| EP3782907A4 (en) * | 2018-04-17 | 2022-01-26 | Kawasaki Jukogyo Kabushiki Kaisha | Landing device and stiffened member |
| CN114248913A (en) * | 2022-03-01 | 2022-03-29 | 北京中航智科技有限公司 | Skid type undercarriage of unmanned helicopter |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1169936A (en) * | 1996-06-10 | 1998-01-14 | 法兰西欧洲科普特公司 | Helicopter landing gear with skids |
| US20100308156A1 (en) * | 2008-01-28 | 2010-12-09 | Martin Landry | Split Pivot Fitting for Helicopter Landing Gear |
| CN103693191A (en) * | 2012-09-27 | 2014-04-02 | 尤洛考普特公司 | Landing gear provided with a stiffening element to increase its roll stiffness, and aircraft |
| CN203939831U (en) * | 2014-05-05 | 2014-11-12 | 上海美申环境设施设备有限公司 | There is the portable casing post docking assembling connecting piece of the locking liner that expands |
-
2015
- 2015-04-07 CN CN201510161289.XA patent/CN104787312A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1169936A (en) * | 1996-06-10 | 1998-01-14 | 法兰西欧洲科普特公司 | Helicopter landing gear with skids |
| US20100308156A1 (en) * | 2008-01-28 | 2010-12-09 | Martin Landry | Split Pivot Fitting for Helicopter Landing Gear |
| CN103693191A (en) * | 2012-09-27 | 2014-04-02 | 尤洛考普特公司 | Landing gear provided with a stiffening element to increase its roll stiffness, and aircraft |
| CN203939831U (en) * | 2014-05-05 | 2014-11-12 | 上海美申环境设施设备有限公司 | There is the portable casing post docking assembling connecting piece of the locking liner that expands |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278990A (en) * | 2017-07-19 | 2019-01-29 | 中国空空导弹研究院 | Support rod and the undercarriage and aircraft for using the support rod |
| CN108127934A (en) * | 2017-12-05 | 2018-06-08 | 深圳市科卫泰实业发展有限公司 | A kind of composite material multi-rotor aerocraft undercarriage and preparation method thereof |
| CN108127934B (en) * | 2017-12-05 | 2020-11-17 | 深圳市科卫泰实业发展有限公司 | Composite material multi-rotor aircraft landing gear and manufacturing method thereof |
| EP3782907A4 (en) * | 2018-04-17 | 2022-01-26 | Kawasaki Jukogyo Kabushiki Kaisha | Landing device and stiffened member |
| CN110929444A (en) * | 2019-12-04 | 2020-03-27 | 中国直升机设计研究所 | Skid type undercarriage simulation design method |
| CN112173090A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Skid undercarriage and crossbeam height adjusting mechanism thereof |
| CN114248913A (en) * | 2022-03-01 | 2022-03-29 | 北京中航智科技有限公司 | Skid type undercarriage of unmanned helicopter |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150722 |