CN104192303A - Small nose landing gear for unmanned aerial vehicle - Google Patents
Small nose landing gear for unmanned aerial vehicle Download PDFInfo
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- CN104192303A CN104192303A CN201410466157.3A CN201410466157A CN104192303A CN 104192303 A CN104192303 A CN 104192303A CN 201410466157 A CN201410466157 A CN 201410466157A CN 104192303 A CN104192303 A CN 104192303A
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- urceolus
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Abstract
The invention relates to a small nose landing gear for an unmanned aerial vehicle. A guide rod is coaxially arranged inside an outer cylinder, and a lower inner cylinder, a primary spring and an upper inner cylinder are arranged inside a cavity between the outer cylinder and the guide rod in sequence from bottom to top; a tire is arranged below the outer cylinder, a group of connecting inserting lug joints are respectively arranged on the upper end and the side face of a rocker arm wheel fork of the tire, the connecting inserting lug joints at the upper end are connected with a torque arm, and the lower parts of the connecting inserting lug joints on the side face are connected with the stretching end of the inner cylinder; a secondary spring is arranged on a limiting table at the bottom of the lower inner cylinder and is in contact with the bottom end surface of a clamping joint connected with the outer cylinder in a sliding mode, a lug plate is arranged on the outer periphery of the clamping joint, and the upper end of the torque arm is connected with the lug plate; a top support is arranged at the end, stretching out of the outer cylinder, of the upper inner cylinder. The landing gear is a fixed frame type semi-rocker arm nose landing gear, so that the stability of aircraft take-off and landing running and using maintainability are improved, and the landing impact energy is fully absorbed.
Description
Technical field
The present invention relates to a kind of SUAV (small unmanned aerial vehicle) nose-gear, be particularly useful on the narrow and small aircraft of chain-drive section bit space.
Background technology
Along with the development of middle-size and small-size Unmanned Aircraft Systems (UAS), unmanned plane technology is extensively quoted.Taking off of middle-size and small-size unmanned plane is subject to condition restriction with way of recycling, often in the majority with catapult-assisted take-off and parachuting recovery, but the in the situation that of conditions permit, the mode of rolling start and running landing is optimum.But wherein rolling start and running landing buffering shock-absorbing and the sliding race stability requirement to alighting gear is higher.At present, the comparatively easy finished product nose-gear using in SUAV (small unmanned aerial vehicle) not being suitable for designs and the unmanned plane of head narrow space for particular task.Its poor reliability, buffering shock-absorbing effect is bad, and defect and fault are difficult for being found.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of SUAV (small unmanned aerial vehicle) nose-gear, and the fixed frame formula half rocking arm nose-gear of this alighting gear improves the sliding race of aircraft, landing stability and working service, fully absorbs and landings impact energy.
For overcoming the above problems, concrete technical scheme of the present invention is as follows: a kind of SUAV (small unmanned aerial vehicle) nose-gear, inside at urceolus coaxially arranges pilot bar, has lower supreme bottom inner core, one-level spring and the upper inner cylinder of being provided with successively in the cavity between urceolus and pilot bar; Below urceolus, be provided with tire, the upper end of the rocking arm wheel fork of tire respectively has one group to be connected slotting terminal lug with side, and the slotting terminal lug of upper end is connected with toggle, and the external part of the slotting terminal lug bottom inner core of side connects; On the limit dais of bottom inner core bottom, be provided with two-level spring, two-level spring contacts with the bottom face of clamping of urceolus sliding block joint, on the excircle of clamping, is provided with auricle, and the upper end of toggle is connected with auricle; The end of stretching out urceolus in upper inner cylinder is provided with top support.
Described top support is dull and stereotyped pedestal, and its front end has one group of auricle being arranged in parallel, after one group of auricle perpendicular to vertical guide, and be connected with fuselage; One group, front auricle is connected with adjustment bolt and the clamp nut at top through after upper inner cylinder.
The middle part of described urceolus is provided with pitman arm, and pitman arm is connected with Linkage steering 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 symmetry of urceolus bearing is obliquely installed, and the other end of support arm is connected with aircraft body.
This SUAV (small unmanned aerial vehicle) nose-gear adopts urceolus, pilot bar and upper and lower inner core joint, and connect by spring, thereby play the effect of damping, simultaneously by the oblique decomposition of force of rocking arm wheel fork, can be that vertical displacement is absorbed by the two-stage spring on shock strut by horizontal impact Conversion of Energy, increase front-wheel stability, improve the sliding stability of running.
Preferably, top support is connected with urceolus by two horizontal auricles, and limit the upper-lower position of alighting gear left button by adjusting the structure of bolt and clamp nut, and provide auxiliary rotating shaft, one group of vertical auricle structure of top support tailoring, can be fixed on the sidewall laminate of chain-drive section load box structure, to fuselage transmitted load.
Preferably, pitman arm is set on urceolus, and is connected with steering engine by Linkage steering, can transmit steering torque by connecting rod.
Preferably, connect urceolus bearing and body itself by support arm, to play the object of stablizing nose-gear.
Brief description of the drawings
Fig. 1 is the structural representation of SUAV (small unmanned aerial vehicle) nose-gear.
Fig. 2 is SUAV (small unmanned aerial vehicle) nose-gear urceolus inner component explosive view.
Detailed description of the invention
As depicted in figs. 1 and 2, a kind of SUAV (small unmanned aerial vehicle) nose-gear, inside at urceolus 1 coaxially arranges pilot bar 8, in cavity between urceolus 1 and pilot bar 8, have lower supreme bottom inner core 3, one-level spring 4 and the upper inner cylinder 2 of being provided with successively, one-level spring 4 can absorb suffered power on upper inner cylinder 2 and bottom inner core 3; Below urceolus 1, be provided with tire 18, the upper end of the rocking arm wheel fork 9 of tire respectively has one group to be connected slotting terminal lug with side, and the slotting terminal lug of upper end is connected with toggle 10, and the external part of the slotting terminal lug bottom inner core 3 of side connects; On the limit dais of bottom inner core 3 bottoms, be provided with two-level spring 5, two-level spring 5 contacts with 11 bottom faces of clamping of urceolus 1 sliding block joint, two-level spring 5 can the power of sorption on urceolus 1 and rocking arm wheel fork 9, on 11 the excircle of clamping, be provided with auricle, the upper end of toggle 10 is connected with auricle; The end of stretching out urceolus 1 in upper inner cylinder 2 is provided with top support 14.
Described top support 14 is dull and stereotyped pedestal, and its front end has one group of auricle being arranged in parallel, after one group of auricle perpendicular to vertical guide, and be connected with fuselage; One group, front auricle is connected with adjustment bolt 6 and the clamp nut 7 at top through upper inner cylinder 2 is rear.
The middle part of described urceolus 1 is provided with pitman arm 15, and pitman arm 15 is connected with Linkage steering 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 12,13, two V-shaped layouts of support arm of support arm that the end symmetry of urceolus bearing 12 is obliquely installed, and the other end of support arm 13 is connected with aircraft body.
In sum, when the design of this SUAV (small unmanned aerial vehicle) nose-gear two-stage recoil spring is slided race and landing to aircraft, obviously, shock-absorbing effect is fine for buffering, and wherein, in the time that aircraft is slided race, two-level spring is brought into play Main Function, obvious for the shock-absorbing effect that jolts of sliding race process; In the time of aircraft landing, two-stage spring plays a role simultaneously, and damping, buffering effect is very large, has well ensured the stability of takeoff and landing; The connection structure of thin-walled wheel fork can be that vertical displacement is absorbed by the two-stage spring on shock strut by horizontal impact Conversion of Energy, increases front-wheel and stablizes distance, improves landing stability.
Claims (4)
1. a SUAV (small unmanned aerial vehicle) nose-gear, it is characterized in that: in the inside of urceolus (1), pilot bar (8) is coaxially set, in the cavity between urceolus (1) and pilot bar (8), has lower supreme bottom inner core (3), one-level spring (4) and the upper inner cylinder (2) of being provided with successively; Be provided with tire (18) in the below of urceolus (1), the upper end of the rocking arm wheel fork (9) of tire respectively has one group to be connected slotting terminal lug with side, and the slotting terminal lug of upper end is connected with toggle (10), and the external part of the slotting terminal lug bottom inner core (3) of side connects; On the limit dais of bottom inner core (3) bottom, be provided with two-level spring (5), two-level spring (5) contacts with (11) bottom face of clamping of urceolus (1) sliding block joint, on the excircle of (11) of clamping, be provided with auricle, the upper end of toggle (10) is connected with auricle; The end of stretching out urceolus (1) in upper inner cylinder (2) is provided with top support (14).
2. SUAV (small unmanned aerial vehicle) nose-gear as claimed in claim 1, is characterized in that: described top support (14) is dull and stereotyped pedestal, and its front end has one group of auricle being arranged in parallel, after one group of auricle perpendicular to vertical guide, and be connected with fuselage; One group, front auricle is connected with adjustment bolt (6) and the clamp nut (7) at top through after upper inner cylinder (2).
3. SUAV (small unmanned aerial vehicle) 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 Linkage steering (16) one end by pin-and-hole, the other end connects steering engine (17), and steering engine (17) is fixed on aircraft body.
4. SUAV (small unmanned aerial vehicle) 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 support arm (13) that the end symmetry of urceolus bearing (12) is obliquely installed, the other 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 |
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| CN104192303A true CN104192303A (en) | 2014-12-10 |
| CN104192303B CN104192303B (en) | 2016-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410466157.3A Active CN104192303B (en) | 2014-09-15 | 2014-09-15 | SUAV nose-gear |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908929A (en) * | 2015-05-25 | 2015-09-16 | 东莞市超音速模型科技有限公司 | Air vehicle shock absorption foot stand |
| CN105173066A (en) * | 2015-09-21 | 2015-12-23 | 中国运载火箭技术研究院 | Electrically-driven nose wheel steering device for unmanned aerial vehicle |
| 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 |
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| 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 |
| 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 |
| CN106275393A (en) * | 2016-08-31 | 2017-01-04 | 河南翱翔航空科技有限公司 | Unmanned plane nose-gear |
| WO2017008530A1 (en) * | 2015-07-16 | 2017-01-19 | 张萍 | Landing gear for unmanned aerial vehicle |
| 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 |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| CN106672221A (en) * | 2015-11-06 | 2017-05-17 | 珠海航太科技有限公司 | Light aircraft nose landing gear |
| CN108688796A (en) * | 2017-04-11 | 2018-10-23 | 波音公司 | Articulated landing gear with internal damping pillar |
| CN108820191A (en) * | 2018-07-20 | 2018-11-16 | 中国科学院工程热物理研究所 | Undercarriage cushioning structure and undercarriage near space solar energy unmanned plane |
| CN108910020A (en) * | 2018-07-14 | 2018-11-30 | 刘占波 | A kind of wheel system braked and raised speed for fixed-wing unmanned plane |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
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Cited By (18)
| 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 |
| CN105980250B (en) * | 2015-05-14 | 2018-09-04 | 深圳市大疆创新科技有限公司 | Undercarriage and the unmanned vehicle for using the undercarriage |
| CN104908929A (en) * | 2015-05-25 | 2015-09-16 | 东莞市超音速模型科技有限公司 | Air vehicle shock absorption foot stand |
| WO2017008530A1 (en) * | 2015-07-16 | 2017-01-19 | 张萍 | Landing gear for unmanned aerial vehicle |
| CN105173066A (en) * | 2015-09-21 | 2015-12-23 | 中国运载火箭技术研究院 | Electrically-driven nose wheel steering device for unmanned aerial vehicle |
| CN105173066B (en) * | 2015-09-21 | 2017-05-10 | 中国运载火箭技术研究院 | Electrically-driven nose wheel steering device for unmanned aerial vehicle |
| 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 |
| CN106672221A (en) * | 2015-11-06 | 2017-05-17 | 珠海航太科技有限公司 | Light aircraft nose landing gear |
| 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 |
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| 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 |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
| 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 |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| CN108688796A (en) * | 2017-04-11 | 2018-10-23 | 波音公司 | Articulated landing gear with internal damping pillar |
| CN108910020A (en) * | 2018-07-14 | 2018-11-30 | 刘占波 | A kind of wheel system braked and raised speed for fixed-wing unmanned plane |
| CN108820191A (en) * | 2018-07-20 | 2018-11-16 | 中国科学院工程热物理研究所 | Undercarriage cushioning structure and undercarriage near space solar energy unmanned plane |
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