CN102602532A - Sledge and wheel integrated landing gear for unmanned aircraft - Google Patents
Sledge and wheel integrated landing gear for unmanned aircraft Download PDFInfo
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- CN102602532A CN102602532A CN2011104280169A CN201110428016A CN102602532A CN 102602532 A CN102602532 A CN 102602532A CN 2011104280169 A CN2011104280169 A CN 2011104280169A CN 201110428016 A CN201110428016 A CN 201110428016A CN 102602532 A CN102602532 A CN 102602532A
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Abstract
The invention relates to a sledge and wheel integrated landing gear for an unmanned aircraft. The sledge and wheel integrated landing gear comprises a supporting arm and an aircraft wheel, wherein the upper end of the supporting arm is arranged at the bottom of the unmanned aircraft body; the aircraft wheel is arranged at the lower end of the supporting arm; a sledge is arranged between the aircraft wheel and the supporting arm; the upper end of the sledge is hinged to the lower end of the supporting arm of the landing gear; and the aircraft wheel is arranged at the lower end of the sledge. The sledge and wheel integrated landing gear is scientific in design and relatively low in cost and has a simple structure and a wide application range; due to a simple mechanical structure, the landing safety of the unmanned aircraft during landing is improved effectively, the shock absorption effect is good, and the sledge and wheel integrated landing gear is suitable for various environments with complicated terrains; the unmanned aircraft can be landed steadily in a flat flying place, a rugged land and a soft grass land, and obstacles with relatively large volumes can be kept away from the aircraft during landing; and furthermore, the sledge and wheel integrated landing gear occupies a small area and has a small volume, light mass, high reliability and long service life.
Description
Technical field
The invention belongs to the unmanned plane field, relate to lift, especially a kind of unmanned plane sledge wheel one alighting gear.
Background technology
Maturation gradually along with the robot airplane technology; And the continuous development of UAV control equipment and unmanned plane carrying equipment is perfect, and the application of unmanned plane constantly enlarges, and can be widely used in multiple fields such as military surveillance, geographical information collection, power circuit polling, aerial high-risk operations at present; Adopt unmanned plane to patrol and examine and to increase safety factor greatly; Increase the inspection number of times that cruises, reduce the cost of operation management, improve efficiency of operation; And operation is simpler, dependable performance, has better economic benefit and social benefit.Conventional fixed-wing layout unmanned plane stability is high, can carry as two-way camera take photo by plane, multiple airborne equipments such as The Cloud Terrace shooting, position fixing system, realization to target setting follow the tracks of, location, remote control, remote measurement and digital communication.
As taking off, navigate by water and land as conventional airplane, present unmanned plane alighting gear is divided into column support type and rocker-arm to unmanned plane, wherein under radio telecommand; The principal feature of telescopic landing gear is that bumper and load pillar integrate, and wheel directly is fixed on the piston rod of bumper, and the piston rod of telescopic landing gear not only bears axial force; And bear moment of flexure; Thereby easy abrasion and catching phenomenon occurs, make the sealing property variation of bumper, can not adopt bigger pressure; Pass through rotating rocking arm and link to each other and the principal feature of articulated landing gear is a wheel with the piston rod of bumper; Bumper is double as load pillar also; The piston of this form only bears axial force, does not bear moment of flexure, but the rocker-arm structure is complicated, and joint is stressed bigger; Therefore its wearing and tearing in use is also bigger, damages easily.
During the unmanned plane landing, alighting gear at first lands and slides a segment distance and slows down, and in the process of alightinging run, two kinds of present alighting gears all are in the state of low incidence, can not make full use of air resistance and brake, and the deceleration coasting distance is longer.Particularly, the operating environment of unmanned plane is complicated, usually needs to land in the natural environment in the open air; When on ups and downs runway, sliding, buffering and dodging ability when crossing over like obstacles such as irrigation canals and ditches, mounds are poor, and; Front-wheel can produce shimmyly when running into bumpy road surface, causes jolting of unmanned plane, is protection carrying equipment and body; Need load the equipment of anti-pendulum shake at unmanned plane, this has increased the complexity and the complete machine weight of installing again.
Find following related patent U.S. Patent No. through retrieval:
Be used for a kind of alighting gear (1) that is used for aircraft (2) of alighting gear (CN102050223) of aircraft, have: the erecting device (5) that is assembled to the fuselage (3) of aircraft (2); At least one wheel (6); And at least one hold-down arm (7), its have with erecting device (5) bonded assembly first end (8) and with first end (8) relatively and wheel (6) be suspended from its second end (9).The first end (8) of hold-down arm (7) has with rotation mode and is assembled to erecting device (5) bonded assembly pin (10) and extends across with the base portion (16) of hold-down arm (7); And; Automatically controlled actuator (20) is assembled to base portion (16), and, optionally started; With between first and second operating positions of the structure of awing hiding that limits alighting gear (1) respectively and the landing structure that descends, around pin (10) pivotal support arm (7).
A kind of unmanned plane undercarriage control system (CN101767649A) comprises jack, drive part, control part, Sensor section, rise and fall boom and decoupling rod, and jack adopts worm gear, worm structure; One end and the worm gear of the rocking arm of jack are connected; The other end is connected with an end of decoupling rod, and the other end of decoupling rod is connected through bearing pin with the boom top of rising and falling, and the end of worm screw is connected with drive part; Sensor section is installed in the spacing hole up and down of jack; Jack is fixedly mounted on the airframe on the load-carrying construction, and the upper end of the boom that rises and falls is connected with airframe through load rotating shaft on the airframe, and the lower end of the boom that rises and falls is connected with aircraft nose wheel; Control part is installed on the avionics equipment frame of aircraft, docks with drive part and Sensor section respectively through cable.
Through analyzing, above patent and present patent application exist more different.
Summary of the invention
The objective of the invention is to overcome the weak point of prior art, a kind of design science, unmanned plane alighting gear simple in structure, widely applicable, lower-cost are provided.
The present invention solves its technical matters and takes following technical scheme to realize:
A kind of unmanned plane sledge wheel one alighting gear; Comprise hold-down arm, wheel; Said hold-down arm upper end is installed in the bottom of unmanned aerial vehicle body, and wheel is installed in the lower end of hold-down arm, it is characterized in that: a sled is installed between said wheel and the hold-down arm; The upper end hinge of this sled is contained in the lower end of alighting gear hold-down arm, and wheel is installed in the lower end of this sled.
And said sled is the form of cranking arm.
And, between sled and hold-down arm, also being hinged with a bumper, the end hinge of this bumper is contained on the hold-down arm, and its other end hinge is contained in the crank position at sled middle part.
Advantage of the present invention and good effect are:
1, this alighting gear is installed sled between alighting gear hold-down arm and wheel, when unmanned plane lands, as can wheel be turned up when running into large-scale obstacle; Utilize sled on comparatively bumpy road face, to slide, thereby evading obstacle simultaneously, the fuselage that guarantees unmanned plane remains that horizontal direction is stable to slide; Make the unmanned plane can stable landing, effectively promote the safety performance of unmanned plane, and; The mode that wheel-ski combines has also avoided single sled landing-gear load amount light; The shortcoming of poor stability, and can reduce the wearing and tearing of unmanned plane, prolong the service life of unmanned plane.
2, this alighting gear is hinged with a bumper between sled and hold-down arm; Effectively promoted the damping performance of alighting gear; And can be through the folding and unfolding of control system control alighting gear, and can avoid unmanned plane in landing alighting run process because bumpyly jolt in the road surface, vibration etc. causes damage, simultaneously; Because alighting gear can bear bigger impact; The adjustable angle adjusting range of the alighting gear during landing is big, can help increasing resistance of taxing and quicken braking, shortens unmanned plane landing and sliding distance.
3, design science of the present invention, simple in structure, widely applicable, cost is lower; Effectively promote the safety of landing in the unmanned plane landing process through the simple machine structure, good damping effect is applicable to multiple environment with a varied topography; No matter in smooth flying field or in rugged soil; Still on soft meadow, can guarantee that aircraft safety lands reposefully, and can evade the bigger obstacle of volume; Structure takes up room little, and overall volume is little, light weight, reliability high, long service life.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the I portion enlarged diagram among Fig. 1.
The specific embodiment
Below in conjunction with accompanying drawing and through specific embodiment the present invention is made further detailed description, following examples are descriptive, are not determinate, can not limit protection scope of the present invention with this.
A kind of unmanned plane sledge wheel one alighting gear comprises hold-down arm 2, wheel 5, and said hold-down arm upper end is installed in the bottom of unmanned aerial vehicle body 1, and wheel is installed in the lower end of hold-down arm.A plurality of alighting gears can be installed in the bottom of the fuselage of unmanned plane involved in the present invention, and three alighting gears are installed in the present embodiment altogether, and wherein rear end of front end is two side by side.
Innovative point of the present invention is:
One sled 4 is installed between said wheel and the hold-down arm, and the upper end hinge of this sled is contained in the lower end of alighting gear hold-down arm, and wheel is installed in the lower end of this sled.This sled is the form of cranking arm, with the stability of raising hold-down arm and the cushion characteristic of wheel.
Between sled and hold-down arm, also be hinged with a bumper 3, the end hinge of this bumper is contained on the hold-down arm, and its other end hinge is contained in the crank position at sled middle part.
Principle of work of the present invention is:
When unmanned plane drops to comparatively smooth runway, slide through the wheel landing deceleration, when in unmanned plane is sliding, running into obstacle; Sled partly receives resistance and rotates around hinge; Wheel is turned up, and slides through sled, and the fuselage that guarantees unmanned plane remains that horizontal direction is stable to slide.Bumper can effectively alleviate the vibration that unmanned plane produces because of pavement roughness in sliding, and control system is through the flexible may command undercarriage control of control bumper.
Claims (3)
1. a unmanned plane sledge is taken turns the one alighting gear; Comprise hold-down arm, wheel; Said hold-down arm upper end is installed in the bottom of unmanned aerial vehicle body, and wheel is installed in the lower end of hold-down arm, it is characterized in that: a sled is installed between said wheel and the hold-down arm; The upper end hinge of this sled is contained in the lower end of alighting gear hold-down arm, and wheel is installed in the lower end of this sled.
2. unmanned plane sledge wheel one alighting gear according to claim 1, it is characterized in that: said sled is the form of cranking arm.
3. unmanned plane sledge wheel one alighting gear according to claim 1 is characterized in that: between sled and hold-down arm, also be hinged with a bumper, the end hinge of this bumper is contained on the hold-down arm, and its other end hinge is contained in the crank position at sled middle part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104280169A CN102602532A (en) | 2011-12-19 | 2011-12-19 | Sledge and wheel integrated landing gear for unmanned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104280169A CN102602532A (en) | 2011-12-19 | 2011-12-19 | Sledge and wheel integrated landing gear for unmanned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102602532A true CN102602532A (en) | 2012-07-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011104280169A Pending CN102602532A (en) | 2011-12-19 | 2011-12-19 | Sledge and wheel integrated landing gear for unmanned aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106218874A (en) * | 2016-07-23 | 2016-12-14 | 广东容祺智能科技有限公司 | A kind of many rotor wing unmanned aerial vehicles foot rest damping device |
| CN107444622A (en) * | 2016-05-31 | 2017-12-08 | 比亚迪股份有限公司 | For unmanned plane landing gear assembly and there is its unmanned plane |
| CN108357666A (en) * | 2017-01-26 | 2018-08-03 | 南京中云图空间信息技术有限公司 | A kind of multi-rotor unmanned aerial vehicle arc undercarriage |
| CN110386245A (en) * | 2019-08-16 | 2019-10-29 | 西安星火航电智能科技有限公司 | A kind of rotation direction has the unmanned plane undercarriage and unmanned plane of damping |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN114408199A (en) * | 2022-01-28 | 2022-04-29 | 广东皓耘科技有限公司 | Unmanned aerial vehicle positioning and correcting mechanism and undercarriage positioning auxiliary device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB274167A (en) * | 1926-04-07 | 1927-07-07 | Cierva Juan De La | Improvements in under-carriages or landing gear for aircraft |
| GB647642A (en) * | 1940-02-23 | 1950-12-20 | Albert Saporta | Landing gear enabling an aircraft to land on and take off from unprepared ground |
| GB756111A (en) * | 1953-08-11 | 1956-08-29 | Morane Saulnier | Improvements in retractable landing gears for aircraft |
| CN201086822Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Rear kneeing type damping device for undercarriage of pilotless plane |
| CN202429347U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Ski-wheel integrated undercarriage for unmanned aerial vehicle |
-
2011
- 2011-12-19 CN CN2011104280169A patent/CN102602532A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB274167A (en) * | 1926-04-07 | 1927-07-07 | Cierva Juan De La | Improvements in under-carriages or landing gear for aircraft |
| GB647642A (en) * | 1940-02-23 | 1950-12-20 | Albert Saporta | Landing gear enabling an aircraft to land on and take off from unprepared ground |
| GB756111A (en) * | 1953-08-11 | 1956-08-29 | Morane Saulnier | Improvements in retractable landing gears for aircraft |
| CN201086822Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Rear kneeing type damping device for undercarriage of pilotless plane |
| CN202429347U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Ski-wheel integrated undercarriage for unmanned aerial vehicle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107444622A (en) * | 2016-05-31 | 2017-12-08 | 比亚迪股份有限公司 | For unmanned plane landing gear assembly and there is its unmanned plane |
| CN107444622B (en) * | 2016-05-31 | 2020-01-03 | 比亚迪股份有限公司 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it |
| CN106218874A (en) * | 2016-07-23 | 2016-12-14 | 广东容祺智能科技有限公司 | A kind of many rotor wing unmanned aerial vehicles foot rest damping device |
| CN108357666A (en) * | 2017-01-26 | 2018-08-03 | 南京中云图空间信息技术有限公司 | A kind of multi-rotor unmanned aerial vehicle arc undercarriage |
| CN110386245A (en) * | 2019-08-16 | 2019-10-29 | 西安星火航电智能科技有限公司 | A kind of rotation direction has the unmanned plane undercarriage and unmanned plane of damping |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN114408199A (en) * | 2022-01-28 | 2022-04-29 | 广东皓耘科技有限公司 | Unmanned aerial vehicle positioning and correcting mechanism and undercarriage positioning auxiliary device |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120725 |