CN104192303B - SUAV nose-gear - Google Patents
SUAV nose-gear Download PDFInfo
- Publication number
- CN104192303B CN104192303B CN201410466157.3A CN201410466157A CN104192303B CN 104192303 B CN104192303 B CN 104192303B CN 201410466157 A CN201410466157 A CN 201410466157A CN 104192303 B CN104192303 B CN 104192303B
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- CN
- China
- Prior art keywords
- urceolus
- nose
- auricle
- gear
- suav
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- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
Landscapes
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
- Axle Suspensions And Sidecars For Cycles (AREA)
Abstract
The present invention relates to a kind of SUAV nose-gear, be coaxially disposed guide post in the inside of urceolus, supreme under having in the cavity between urceolus and guide post be sequentially provided with lower tub, one-level spring and upper inner cylinder；At the tire that is connected with of urceolus, the upper end of the rocking arm wheel fork of tire and side are respectively arranged with one group and connect slotting terminal lug, and the slotting terminal lug of upper end is connected with toggle, and the external part of the slotting terminal lug lower tub of side connects；Being provided with two-level spring on limiting stand bottom lower tub, what two-level spring was slidably connected with urceolus clamp, and bottom face contacts, and is provided with auricle on the excircle clamped, and the upper end of toggle is connected with auricle；The end stretching out urceolus in upper inner cylinder is provided with top support。The fixed frame formula half rocking arm nose-gear of this undercarriage, improves the sliding race of aircraft, landing stability and working service, fully absorbs and landing impact energy。
Description
Technical field
The present invention relates to a kind of SUAV nose-gear, be particularly suited on the narrow and small aircraft of chain-drive section bit space。
Background technology
Along with the development of middle-size and small-size UAS, unmanned air vehicle technique is extensively quoted。Taking off of middle-size and small-size unmanned plane is subject to conditions with way of recycling, often reclaims in the majority with catapult-assisted take-off and parachuting, but when conditions permit, the mode of rolling start and running landing is optimum。But wherein rolling start and running landing are higher to buffering shock-absorbing and the sliding race stability requirement of undercarriage。At present, the comparatively easy finished product nose-gear used on SUAV is not particularly suited for designing for particular task and the unmanned plane of head narrow space。Its poor reliability, buffering shock-absorbing effect is bad, and defect and fault are not easily found。
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of SUAV nose-gear, the fixed frame formula half rocking arm nose-gear of this undercarriage, improves the sliding race of aircraft, landing stability and working service, fully absorbs and landing impact energy。
For solving problem above, the concrete technical scheme of the present invention is as follows: a kind of SUAV nose-gear, it is coaxially disposed guide post in the inside of urceolus, supreme under having in the cavity between urceolus and guide post is sequentially provided with lower tub, one-level spring and upper inner cylinder；At the tire that is connected with of urceolus, the upper end of the rocking arm wheel fork of tire and side are respectively arranged with one group and connect slotting terminal lug, and the slotting terminal lug of upper end is connected with toggle, and the external part of the slotting terminal lug lower tub of side connects；Being provided with two-level spring on limiting stand bottom lower tub, what two-level spring was slidably connected with urceolus clamp, and bottom face contacts, and is provided with auricle on the excircle clamped, and the upper end of toggle is connected with auricle；The end stretching out urceolus in upper inner cylinder is provided with top support。
Described top support is flat board pedestal, and there is one group of auricle being arranged in parallel its front end, and rear set auricle is perpendicular to vertical guide, and is connected with fuselage；One group of front auricle is connected with adjustment bolt and the binding nut at top after upper inner cylinder。
The middle part of described urceolus is provided with pitman arm, and pitman arm is connected with steering link one end by pin-and-hole, and the other end connects steering-engine, and steering-engine is fixed on aircraft body。
The excircle of described urceolus is provided with urceolus bearing, the support arm that the end symmetric of urceolus bearing is obliquely installed, and the other end of support arm is connected with aircraft body。
This SUAV nose-gear adopts urceolus, guide post and upper and lower inner core joint, and be attached by spring, thus playing the effect of damping, simultaneously by the oblique force resolution of rocking arm wheel fork, horizontal impact energy can be converted into vertical displacement absorbed by the two-stage spring on shock strut, increase front-wheel stability, improve sliding race stability。
Preferably, top support is connected with urceolus by two horizontal auricles, and the upper-lower position of undercarriage left button is limited by adjusting the structure of bolt and binding nut, and auxiliary rotating shaft is provided, one group of vertical ear chip architecture of top support tailoring, can be fixed on the sidewall laminate of chain-drive section load box structure, transmit load to fuselage。
Preferably, urceolus arranges pitman arm, and is connected with steering-engine by steering link, steering moment can be transmitted by connecting rod。
Preferably, urceolus bearing and body itself are connected by support arm, to play the purpose of stable nose-gear。
Accompanying drawing explanation
Fig. 1 is the structural representation of SUAV nose-gear。
Fig. 2 is SUAV nose-gear outer barrel part explosive view。
Detailed description of the invention
As depicted in figs. 1 and 2, a kind of SUAV nose-gear, it is coaxially disposed guide post 8 in the inside of urceolus 1, supreme under having in cavity between urceolus 1 and guide post 8 being sequentially provided with lower tub 3, one-level spring 4 and upper inner cylinder 2, one-level spring 4 can absorb power suffered on upper inner cylinder 2 and lower tub 3；Being connected with tire 18 at urceolus 1, the upper end of the rocking arm wheel fork 9 of tire and side are respectively arranged with one group and connect and insert terminal lug, and the slotting terminal lug of upper end is connected with toggle 10, the external part connection of the slotting terminal lug lower tub 3 of side；Limiting stand bottom lower tub 3 is provided with two-level spring 5, what two-level spring 5 was slidably connected with urceolus 1 clamp, and 11 bottom faces contact, two-level spring 5 can Absorption power on urceolus 1 and rocking arm wheel fork 9, clamp 11 excircle on be provided with auricle, the upper end of toggle 10 is connected with auricle；The end stretching out urceolus 1 in upper inner cylinder 2 is provided with top support 14。
Described top support 14 is flat board pedestal, and there is one group of auricle being arranged in parallel its front end, and rear set auricle is perpendicular to vertical guide, and is connected with fuselage；One group of front auricle is connected with adjustment bolt 6 and the binding nut 7 at top after upper inner cylinder 2。
The middle part of described urceolus 1 is provided with pitman arm 15, and pitman arm 15 is connected with steering link 16 one end by pin-and-hole, and the other end connects steering-engine 17, and steering-engine 17 is fixed on aircraft body。
The excircle of described urceolus 1 is provided with urceolus bearing 12, the support arm 13 that the end symmetric of urceolus bearing 12 is obliquely installed, and two V-shaped layouts of support arm, the other end of support arm 13 is connected with aircraft body。
In sum, when the design of this SUAV nose-gear two-stage buffer spring is to the sliding race of aircraft and landing, buffering is substantially, and shock-absorbing effect is fine, and wherein when aircraft slides race, two-level spring plays Main Function, obvious for the shock-absorbing effect that jolts slided in race process；When aircraft landing, two-stage spring plays a role simultaneously, and damping, buffering effect is very big, well ensure that the stability of takeoff and landing；Horizontal impact energy can be converted into vertical displacement and be absorbed by the two-stage spring on shock strut by the attachment structure of thin-walled wheel fork, increase front-wheel stable from, improve landing stability。
Claims (4)
1. a SUAV nose-gear, it is characterized in that: be coaxially disposed guide post (8) in the inside of urceolus (1), in the cavity between urceolus (1) and guide post (8), be sequentially provided with lower tub (3), one-level spring (4) and upper inner cylinder (2) from the bottom to top；Being connected with tire (18) at urceolus (1), the upper end of the rocking arm wheel fork (9) of tire and side are respectively arranged with one group and connect and insert terminal lug, and the slotting terminal lug of upper end is connected with toggle (10), and the slotting terminal lug of side is connected with the external part of lower tub (3)；The limiting stand of lower tub (3) bottom is provided with two-level spring (5), what two-level spring (5) was slidably connected with urceolus (1) clamp, and (11) bottom face contacts, being provided with auricle on the excircle of (11) of clamping, the upper end of toggle (10) is connected with auricle；The end stretching out urceolus (1) in upper inner cylinder (2) is provided with top support (14)。
2. SUAV nose-gear as claimed in claim 1, it is characterised in that: described top support (14) is flat board pedestal, and there is one group of auricle being arranged in parallel its front end, and rear set auricle is perpendicular to vertical guide, and is connected with fuselage；One group, front end auricle is connected with the adjustment bolt (6) at top and binding nut (7) afterwards through upper inner cylinder (2)。
3. SUAV nose-gear as claimed in claim 1, it is characterized in that: the middle part of described urceolus (1) is provided with pitman arm (15), pitman arm (15) is connected with steering link (16) one end by pin-and-hole, steering link (16) other end connects steering-engine (17), and steering-engine (17) is fixed on aircraft body。
4. SUAV nose-gear as claimed in claim 1, it is characterized in that: the excircle of described urceolus (1) is provided with urceolus bearing (12), the end symmetric of urceolus bearing (12) is tiltedly installed with support arm (13), and the upper end of support arm (13) is connected with aircraft body。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410466157.3A CN104192303B (en) | 2014-09-15 | 2014-09-15 | SUAV nose-gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410466157.3A CN104192303B (en) | 2014-09-15 | 2014-09-15 | SUAV nose-gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104192303A CN104192303A (en) | 2014-12-10 |
| CN104192303B true CN104192303B (en) | 2016-06-22 |
Family
ID=52077735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410466157.3A Expired - Fee Related CN104192303B (en) | 2014-09-15 | 2014-09-15 | SUAV nose-gear |
Country Status (1)
| Country | Link |
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| CN (1) | CN104192303B (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104908929B (en) * | 2015-05-25 | 2017-01-25 | 东莞市超音速模型科技有限公司 | Shock-absorbing foot rest of aircraft |
| CN105059532B (en) * | 2015-07-16 | 2017-11-28 | 湖南省金峰机械科技有限公司 | A kind of unmanned plane undercarriage |
| CN105173066B (en) * | 2015-09-21 | 2017-05-10 | 中国运载火箭技术研究院 | A UAV electric drive front wheel turning device |
| CN105197229A (en) * | 2015-10-16 | 2015-12-30 | 河南翱翔航空科技有限公司 | Front landing gear of unmanned aerial vehicle |
| CN106672221B (en) * | 2015-11-06 | 2019-10-15 | 珠海航太科技有限公司 | A kind of light aerocraft nose-gear |
| CN105292446B (en) * | 2015-11-16 | 2017-05-31 | 吉林大学 | A kind of damping undercarriage of four-axle aircraft |
| CN105923148A (en) * | 2016-05-19 | 2016-09-07 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage damping device |
| CN109592023B (en) * | 2016-07-05 | 2022-01-07 | 王晓飞 | Intelligent unmanned aerial vehicle capable of realizing remote control communication and working method thereof |
| CN106275393A (en) * | 2016-08-31 | 2017-01-04 | 河南翱翔航空科技有限公司 | Unmanned plane nose-gear |
| CN106428535A (en) * | 2016-12-02 | 2017-02-22 | 北京尖翼科技有限公司 | Nose landing gear of unmanned aerial vehicle |
| CN106628130B (en) * | 2016-12-26 | 2019-03-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane nose-gear damping steering mechanism |
| US10625849B2 (en) * | 2017-04-11 | 2020-04-21 | The Boeing Company | Levered landing gear with inner shock strut |
| CN108910020B (en) * | 2018-07-14 | 2019-11-22 | 神木特种飞行器工程研究院有限公司 | A kind of wheel system braked and raised speed for fixed-wing unmanned plane |
| CN108820191B (en) * | 2018-07-20 | 2024-05-07 | 中国科学院工程热物理研究所 | Landing gear shock absorption structure for solar unmanned aerial vehicle in near space and landing gear |
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| CN85205502U (en) * | 1985-12-19 | 1987-01-07 | 曾亿中 | Ejection automobile toy which is able to be repelled when meets an obstacle |
| DE3714363A1 (en) * | 1986-04-29 | 1987-11-05 | Technova Ipari Fejlesztesi Ban | Spring element for road and rail vehicles |
| US6202960B1 (en) * | 1998-11-06 | 2001-03-20 | The Boeing Company | Aircraft landing gear absorber |
| CN102874403A (en) * | 2012-10-25 | 2013-01-16 | 北京化工大学 | Airplane wheel system with combination of rigid solid tires and buffer support |
| CN103122961A (en) * | 2013-03-15 | 2013-05-29 | 洪子鑫 | Multilevel shock absorber |
| EP2607232A1 (en) * | 2011-12-21 | 2013-06-26 | Eurocopter Deutschland GmbH | Landing gear vibration absorber for a helicopter and method of operating said landing gear vibration absorber |
| DE202013105380U1 (en) * | 2013-11-26 | 2014-01-10 | Industrieanlagen-Betriebsgesellschaft Mbh | Chassis for a light aircraft or an unmanned aerial vehicle and aircraft with such a chassis |
| CN103523218A (en) * | 2013-10-12 | 2014-01-22 | 中国航天空气动力技术研究院 | Unmanned plane damping-adjustable front-wheel shimmy-damper |
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2014
- 2014-09-15 CN CN201410466157.3A patent/CN104192303B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85205502U (en) * | 1985-12-19 | 1987-01-07 | 曾亿中 | Ejection automobile toy which is able to be repelled when meets an obstacle |
| DE3714363A1 (en) * | 1986-04-29 | 1987-11-05 | Technova Ipari Fejlesztesi Ban | Spring element for road and rail vehicles |
| US6202960B1 (en) * | 1998-11-06 | 2001-03-20 | The Boeing Company | Aircraft landing gear absorber |
| EP2607232A1 (en) * | 2011-12-21 | 2013-06-26 | Eurocopter Deutschland GmbH | Landing gear vibration absorber for a helicopter and method of operating said landing gear vibration absorber |
| CN102874403A (en) * | 2012-10-25 | 2013-01-16 | 北京化工大学 | Airplane wheel system with combination of rigid solid tires and buffer support |
| CN103122961A (en) * | 2013-03-15 | 2013-05-29 | 洪子鑫 | Multilevel shock absorber |
| CN103523218A (en) * | 2013-10-12 | 2014-01-22 | 中国航天空气动力技术研究院 | Unmanned plane damping-adjustable front-wheel shimmy-damper |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN104192303A (en) | 2014-12-10 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
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Granted publication date: 20160622 |