CN105000186A - Anti-falling and anti-drifting unmanned aerial vehicle - Google Patents
Anti-falling and anti-drifting unmanned aerial vehicle Download PDFInfo
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Abstract
The invention provides an anti-falling and anti-drifting unmanned aerial vehicle. The anti-falling and anti-drifting unmanned aerial vehicle comprises an unmanned aerial vehicle body. At least one rotor is arranged on the unmanned aerial vehicle body. Wings are arranged on the left side and the right side of the unmanned aerial vehicle body respectively. Gas bags are arranged on the wings respectively. Protrusions protruding downwards are arranged at the bottoms of the gas bags. The two gas bags are located at the positions at the same height. The two gas bags are symmetrically arranged on the basis of the unmanned aerial vehicle body. Gas lighter than air is injected into the gas bags. The gas bags are arranged on the two sides of the unmanned aerial vehicle body respectively, and therefore when the aerial vehicle lands, the gas bags can serve as an undercarriage. The beneficial effects that buffering is achieved and damage to the unmanned aerial vehicle body is reduced can be achieved when the aerial vehicle falls and is exploded and falls to the ground. If the aerial vehicle falls to fields or water surfaces by accident, the aerial vehicle can float on the water surfaces under the action of the gas bags, damage caused when the aerial vehicle sinks into water is avoided, and the safety performance of the anti-falling and anti-drifting unmanned aerial vehicle is improved. In addition, the protrusions protruding downwards are arranged at the bottoms of the gas bags, and therefore when the spraying work is conducted, the protrusions can block side wind to reduce drifting of fog drops, and the utilization efficiency of the fog drops is improved.
Description
Technical field
The present invention relates to a kind of aircraft, be specifically related to a kind of anti-fall anti-drift unmanned vehicle.
Background technology
Agricultural aircraft aviation operating efficiency is high, and such as, in the operation of wheatland weed eradication, aviation sprays higher than ground machine efficiency 5 ~ 7 times, is equivalent to 200 ~ 250 times of artificial spraying, and ability of assaulting is strong, good to burst, explosive disease and pest control effect; Unintelligible to the capable ridge of Feng Hanghou by the restriction, particularly plant growth of crop growing state, aviation operation can solve plant growth later stage ground machine and to be difficult to go to the field the problem of operation.Compared with farm work, Aircraft idle job reduces operating cost in addition, can not leave the feature of rut print and damage crops etc.
At present mainly include large-scale fixed-wing agricultural aircraft that people drives, autogyro, propeller-parachuting and unpiloted fixed wing aircraft, single rotor helicopter, the many helighros of non co axial etc. for the aircraft of agricultural aviation operation.
Manned aircraft operation efficiency is high, but there are problems such as needing special airport, maintenance cost is high, air traffic control is strict.Unpiloted autogyro is owing to having the features such as and air traffic control low without the need to special airport, technical flight person, maintenance cost is few, and have that flying height is low, the advantage such as operating efficiency and precision is high, operation landform wide adaptability, more and more in agricultural production, obtain extensive concern.
But the many helighros of unpiloted single rotor helicopter, non co axial are for the common personnel that are engaged in agriculture, price still seems expensive, and need operating personal to have certain science and culture basis, misoperation is easy to occur the air crash accident such as " falling machine ", " aircraft bombing ", not only cause the heavy losses of aircraft itself, and bring serious damage to equipment and surface crops on machine, bring security threat also can to Ground Operation personnel simultaneously, therefore, its safety issue used is one of key issue of its fast development of restriction.Alighting gear is the important device of plant protection unmanned vehicle landing, certain buffer action can be played when the air crash of aircraft et out of order, but current landing gear buffer action is very limited, current needing badly develops a kind of novel landing gear, reduces the air crash loss of plant protection unmanned vehicle to greatest extent.
In addition, plant protection unmanned vehicle capacity weight amount is little, therefore the spraying operation mode of high concentration low capacity is usually adopted during plant protection operation, mist droplet particle size is smaller, droplet is easily subject to the interference of natural wind before entering crop canopies, drift about, thus larger impact is caused on the drug effect of plant protection operation.
Summary of the invention
The present invention, for overcoming above-mentioned deficiency of the prior art, provides good anti-of a kind of safety performance and falls anti-drift unmanned vehicle, significantly can reduce the air crash loss of plant protection unmanned vehicle, and reduce the drift of droplet.
In order to achieve the above object, the technical scheme that the present invention takes: a kind of anti-falls anti-drift unmanned vehicle, comprises unmanned vehicle main body, and relative two sides of described unmanned vehicle main body are respectively equipped with air bag, and air bag is connected with unmanned vehicle main body.
In such scheme, be respectively equipped with air bag by two sides in unmanned vehicle main body, when aircraft lands, air bag can serve as alighting gear; Aircraft fall machine, aircraft bombing born time can play buffering, reduce the damage to unmanned vehicle main body, if aircraft falls accidentally on the water surface, aircraft can be made under the effect of air bag to bubble through the water column, aircraft submerged is avoided to cause damage, improve safety performance of the present invention, in addition, air bag can stop crosswind to a certain extent and reduce droplet drift.
Further, above-mentioned unmanned plane main body is provided with at least one rotor, and the profile of above-mentioned air bag is dirigible shape.Adopt rotor to drive and can improve maneuverability, also can reduce the work accident odds such as the machine of falling, improve the safety of operation, the air bag of dirigible shape can reduce the resistance of wind awing effectively, promotes flying power.
Further, the bottom of above-mentioned air bag has the projection protruded downwards.During spraying operation, in the process of flight, if time experience crosswind blows, projection better can stop crosswind and reduce droplet drift, improves the utilization ratio of droplet.
Further, above-mentioned air bag injects the gas being lighter than air.The buoyancy that air bag produces partially or completely can offset the weight of load in the deadweight of aircraft and operation gondola, thus can increase the capacity weight amount of aircraft, improves operating efficiency.
Further, the relative both sides of above-mentioned unmanned vehicle main body are respectively equipped with wing, and air bag is fixed on wing.In-flight, wing also can provide certain lift, increases the capacity weight amount of aircraft.
Further, above-mentioned unmanned vehicle main body is connected by the first tie-beam and the second tie-beam with wing.Connected by twin beams, wing degree of freedom can be limited.
Further, in order to rocking of reducing that aircraft produces awing, above-mentioned first tie-beam is through the both sides of unmanned vehicle bottom part body, the wing of unmanned vehicle main body both sides be separately fixed at be positioned at unmanned vehicle main body both sides the first tie-beam on, unmanned vehicle main body can be rotated around the first tie-beam, the both sides that the bottom of unmanned vehicle main body is relative are respectively equipped with draw-in groove, one end that second tie-beam is connected with unmanned vehicle main body is stuck in draw-in groove, and the second tie-beam can move in draw-in groove.Can move in draw-in groove by controlling the second tie-beam, the change of angle between unmanned vehicle main body and wing can be realized, to adapt to the manipulation needs of aircraft flight process medium velocity and attitude change, reduce the fugitiveness that aircraft produces awing.
Further, above-mentioned wing inside is provided with multiple rib in the arrangement of same direction, coated by moccasin outside rib, each rib is respectively equipped with first through hole that can coordinate with the first tie-beam and second through hole that can coordinate with the second tie-beam, first tie-beam is through the first through hole of each rib, and the second tie-beam is through the second through hole of each rib.The rib arranged can share the pressure that wing is subject to jointly, keeps the shape of wing.
Further, in order to ensure the shape stability of air bag, ensure that air bag can not extrude, roll and translation aloft, ensure stability during aerial work, improve aviation homework precision, the inside of above-mentioned air bag is provided with support frame, coated by moccasin outside support frame, first tie-beam and the second tie-beam are through air bag, and the first tie-beam is all connected with support frame with the second tie-beam.
Further, in order to ensure the reliability that the first tie-beam is installed, above-mentioned unmanned vehicle bottom part body is provided with snap component, and the first tie-beam is fixed on unmanned vehicle bottom part body by snap component.Unmanned vehicle main body and wing, air bag can be made to connect into an entirety, prevent from coming off, quick-detachment can be realized easily again.
Beneficial effect of the present invention is as follows:
1, the present invention is respectively equipped with air bag by two sides in unmanned vehicle main body, and when aircraft lands, air bag can serve as alighting gear; Aircraft fall machine, aircraft bombing born time can play buffering, reduce the damage to unmanned vehicle main body, if aircraft falls accidentally on field or the water surface, aircraft can be made under the effect of air bag to bubble through the water column, avoid aircraft submerged to cause damage, improve safety performance of the present invention.
2, the mode adopting many air bags, rotor, fixed-wing to combine, combines the advantage of conventional dirigible, helicopter, fixed wing aircraft.The profile of air bag is dirigible shape, effectively can reduce the resistance of wind awing, promotes flying power; Be full of the gas being lighter than air in air bag, the buoyancy that air bag produces partially or completely can offset the weight of load in the deadweight of aircraft and operation gondola, thus can increase the capacity weight amount of aircraft, improves operating efficiency; Adopt heligyro to drive and can improve maneuverability; Air bag is fixed on wing, and in-flight, wing also can provide certain lift, increases the capacity weight amount of aircraft.
3, the bottom of air bag has the projection protruded downwards, and during spraying operation, in the process of flight, if time experience crosswind blows, projection can stop crosswind and reduce droplet drift, improves the utilization ratio of droplet.
4, the bottom of unmanned vehicle main body is provided with draw-in groove and snap component, the change of wing relative to angle between unmanned vehicle main body can be realized, to adapt to the manipulation needs of aircraft flight process medium velocity and attitude change, unmanned vehicle main body and wing, air bag can be made again to connect into an entirety, prevent from coming off, and quick-detachment can be realized easily.
Accompanying drawing explanation
Fig. 1 is the anti-structural representation falling anti-drift unmanned vehicle of the embodiment of the present invention.
Fig. 2 is the underside structures schematic diagram (base plate dismounting) of the unmanned vehicle main body of the embodiment of the present invention.
Fig. 3 is A portion enlarged drawing in Fig. 2.
Fig. 4 is the turning buckle structure schematic diagram of the embodiment of the present invention.
Fig. 5 is the cross-sectional schematic of the air bag of the embodiment of the present invention.
Fig. 6 is the partial schematic diagram of the wing of the embodiment of the present invention.
Fig. 7 is the unmanned vehicle main body of the embodiment of the present invention and the assembling schematic diagram of tie-beam.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention will be further described, but embodiments of the present invention are not limited to this.
Embodiment
The present embodiment anti-falls the structure of anti-drift unmanned vehicle as shown in Fig. 1 to 7, comprise unmanned vehicle main body 1, the left and right sides of the front portion of unmanned vehicle main body 1 and the left and right sides at rear portion are symmetrical is respectively provided with four rotors 10, the left and right sides in the middle part of unmanned vehicle main body 1 is respectively equipped with wing 3, each wing 3 is respectively equipped with an air bag 2, two air bags 2 are located at sustained height position, and two air bags 2 are symmetrical arranged based on unmanned vehicle main body 1.Inject the gas being lighter than air in described air bag 2, such as helium, the buoyancy that air bag 2 is produced partially or completely can offset the weight of load in the deadweight of aircraft and operation gondola, thus can increase the capacity weight amount of aircraft, raising operating efficiency; In-flight, wing 3 also can provide certain lift, equally also can increase the capacity weight amount of aircraft.In spraying operation flight course, the bottom loaded medicine-chest of aircraft, shower nozzle is generally placed in wing 3 or/and unmanned vehicle main body 1 bottom surface, and between two air bags 2, multiple rotors 10 by aircraft in flight course rotate, can by the pros and cons of pesticide spraying crop.
In the present embodiment, the profile of above-mentioned air bag 2 is dirigible shape, and the air bag 2 of dirigible shape can provide the raising force the same with common dirigible in flight course, reduces the energy consumption of aircraft, can be good at promoting the flying power in flight course.Air bag 2 adopts the streamlined contour of dirigible, and the tail end of air bag 2 is also provided with empennage 20, and such structural balloon also can reduce the resistance of wind by actv. awing, promotes flying power.
Because the drugloading rate of aircraft is limited, so the liquid loaded in medicine-chest normally high concentration, and when sprinkling, it is very small that the medicine sprayed drips, so in the process of flight, if time experience crosswind blows, medicine drips and easily produces skew, the service efficiency that medicine can be caused like this to drip reduces, therefore the work efficiency of aircraft also can reduce simultaneously, therefore, the bottom of above-mentioned air bag 2 has the projection 21 protruded downwards, when being subject to crosswind impact, projection 21 bottom air bag 2 can play the effect stopping crosswind impact, improve droplet and be subject to the phenomenon that crosswind impact produces drift, in addition, the cross-sectional plane of protruding 21 diminishes from top to down gradually, and the front end of protruding 21 is cambered surface, the resistance be subject to in-flight can be reduced in.Air bag 2, when aircraft does not have operation, is exist with the form of alighting gear, plays a supporting role; At aircraft operation et out of order or when having contingency to produce, air bag 2 can provide a buffering to land when aircraft falls aloft, though crash into field or waterborne time, also can keep the complete of aircraft significantly.
The bottom of above-mentioned unmanned vehicle main body 1 is provided with the first tie-beam 4 and the second tie-beam 5, second tie-beam 5 has two, first tie-beam 4 is positioned at the second tie-beam 5 rear, wherein the first tie-beam 4 is horizontally through the bottom of unmanned vehicle main body 1, and the two ends of the first tie-beam 4 are stretched out outside unmanned vehicle main body 1 left and right sides, the wing 3 of unmanned vehicle main body 1 both sides is separately fixed on the first tie-beam 4 of respective side, and unmanned vehicle main body 1 can be rotated by a small margin around the first tie-beam 4, the angle of rotating is within 20 °, the left and right sides of the bottom of unmanned vehicle main body 1 is respectively equipped with draw-in groove 11, one end that second tie-beam 5 is connected with unmanned vehicle main body 1 is stuck in the draw-in groove 11 of every side, and the second tie-beam 5 can move in draw-in groove 11, the other end of the second tie-beam 5 is connected with wing 3, the bottom of unmanned vehicle main body 1 arranges base plate, base plate can stop the aperture position of draw-in groove 11, with the stroke of limit second tie-beam 5 movement.The inside of above-mentioned air bag 2 is provided with support frame 22, coated by moccasin outside support frame 22, and the first tie-beam 4 and the second tie-beam 5 are also through air bag 2, and the first tie-beam 4 is all connected with support frame 22 with the second tie-beam 5.In second tie-beam 5 is mobile in draw-in groove 11, unmanned vehicle main body 1 is rotated around the first tie-beam 4, realize the change of angle between unmanned vehicle main body 1 and wing 2, to adapt to the manipulation needs of aircraft flight process medium velocity and attitude change, enable aircraft stabilized flight.In order to ensure the stability that the first tie-beam 4 is installed, bottom above-mentioned unmanned vehicle main body 1, the set position of corresponding first tie-beam 4 offers groove 13, bottom unmanned vehicle main body 1, the position of respective grooves 13 is provided with snap component, described snap component comprises the limit fastener 121 being located at groove 13 two ends and the turning buckle 122 being covered on groove 13, the both sides of turning buckle 122 are respectively equipped with and connect buckle 1221, connect position set by buckle 1221 in correspondence bottom unmanned vehicle main body 1 and offer catching groove 14 respectively, the connection buckle 1221 of turning buckle 122 can with unmanned vehicle main body 1 bottom catching groove 14 snapping, during assembling, first tie-beam 4 embeds in limit fastener 121, then turning buckle 122 is covered on groove 13, turning buckle 122 is avoided to come off by connection buckle 1221 and catching groove 14 snapping, act at limit fastener 121 and turning buckle 122 simultaneously, first tie-beam 4 is limited in bottom unmanned vehicle main body 1, make its except beam to rotation except do not have other to move, turning buckle 122 can protect the first tie-beam 4 can not come off from aircraft in flight course.First tie-beam 4 fastens by limit fastener 121, ladder or projection are set on the first tie-beam 4 simultaneously, ladder on first tie-beam 4 or projection play the effect of moving-limiting under the barrier effect of limit fastener 121, make the first tie-beam 4 can not produce double swerve in flight course.
In the present embodiment; as shown in Figure 6; described wing 3 inside is provided with multiple rib 31 in the arrangement of same direction; the equidistant arrangement of rib 31; the framework that all ribs 31 are formed is coated by moccasin; each rib 31 on average shares the pressure that wing 3 is subject to, and makes wing 3 can awing keep original shape.Each rib 31 is respectively equipped with first through hole 311 that can coordinate with the first tie-beam 4 and second through hole 312 that can coordinate with the second tie-beam 5, the central line alignment of the first through hole 311 of all ribs 31, the center also aligned of the second through hole 312 of all ribs 31, first tie-beam 4 is through the first through hole 311 of each rib 31, second tie-beam 5 is through the second through hole 312 of each rib 31, the first tie-beam 4 and the second tie-beam 5 is made to be hidden in wing 3, tie-beam is avoided to expose impact on the one hand attractive in appearance, tie-beam is avoided to expose and increase the windage of wing 3 on the other hand.
The moccasin that above-mentioned wing 3 and air bag 2 use is airship envelope, and airship envelope has explosion-resistance characteristic, improves the safety factor of aircraft.The support frame 22 of air bag 2 and the rib 31 of wing 3 adopt the light material such as aluminum alloy or carbon fiber, reduce the weight of aircraft, thus reduce energy consumption, promote flying power.
The present invention is anti-falls anti-drift unmanned vehicle in working flight, and the first tie-beam 4 is exactly connect and fix whole aircraft in the course of the work, makes aircraft not have too much activity.In second tie-beam 5 is movable in draw-in groove 11, can regulates the angle of unmanned vehicle main body 1 and wing 2 and air bag 3 simultaneously, enable aircraft stabilized flight, the manipulation that simultaneous adaptation aircraft flight process medium velocity and attitude change needs.Under the effect of the first tie-beam 4 and the second tie-beam 5, wherein the second tie-beam 5 is connected in the draw-in groove 11 of unmanned vehicle main body 1, servos control second tie-beam 5 relative movement in draw-in groove 11 is set bottom unmanned vehicle main body 1, second tie-beam 5 can be moved in the allowed band in draw-in groove 11, keep level motionless at wing 2, unmanned vehicle main body 1 is made to tilt with the needs of satisfied different flight attitude, user can change the angle of inclination of unmanned vehicle main body 1 at ground control cabinet manual control steering wheel, aircraft is coordinated to adjust pose aloft, the smooth flight of aircraft can be ensured, when aircraft moves ahead generation inclination time, can, by reducing the angle between unmanned vehicle main body 1 and wing, making wing continue flight attitude of remaining valid, lift can either be provided for flight, can energy consumption be reduced again, lifting flying power.
Above-described embodiments of the present invention, do not form limiting the scope of the present invention.Any amendment done within spiritual principles of the present invention, equivalent replacement and improvement etc., all should be included within claims of the present invention.
Claims (10)
1. anti-fall an anti-drift unmanned vehicle, comprise unmanned vehicle main body (1), it is characterized in that, relative two sides of described unmanned vehicle main body (1) are respectively equipped with air bag (2), and air bag (2) is connected with unmanned vehicle main body (1).
2. according to claim 1 resisting falls anti-drift unmanned vehicle, and it is characterized in that, described unmanned plane main body (1) is provided with at least one rotor (10), and the profile of air bag (2) is dirigible shape.
3. according to claim 1 resisting falls anti-drift unmanned vehicle, it is characterized in that, the bottom of described air bag (2) has the projection (21) protruded downwards.
4. according to claim 1 resisting falls anti-drift unmanned vehicle, and it is characterized in that, described air bag (2) injects the gas being lighter than air.
5. anti-according to any one of Claims 1-4 falls anti-drift unmanned vehicle, it is characterized in that, the relative both sides of described unmanned vehicle main body (1) are respectively equipped with wing (3), and air bag (2) is fixed on wing (3).
6. according to claim 5 resisting falls anti-drift unmanned vehicle, and it is characterized in that, described unmanned vehicle main body (1) is connected by the first tie-beam (4) and the second tie-beam (5) with wing (3).
7. according to claim 6 resisting falls anti-drift unmanned vehicle, it is characterized in that, described first tie-beam (4) is through the both sides of unmanned vehicle main body (1) bottom, the wing (3) of unmanned vehicle main body (1) both sides is separately fixed at and is positioned on first tie-beam (4) of unmanned vehicle main body (1) both sides, and unmanned vehicle main body (1) can be rotated around the first tie-beam (4); The both sides that the bottom of unmanned vehicle main body (1) is relative are respectively equipped with draw-in groove (11), and one end that the second tie-beam (5) is connected with unmanned vehicle main body (1) is stuck in draw-in groove (11), and the second tie-beam (5) can move in draw-in groove (11).
8. according to claim 7 resisting falls anti-drift unmanned vehicle, it is characterized in that, described wing (3) inside is provided with multiple rib (31) in the arrangement of same direction, rib (31) outside is coated by moccasin, each rib (31) is respectively equipped with first through hole (311) that can coordinate with the first tie-beam (4) and second through hole (312) that can coordinate with the second tie-beam (5), first tie-beam (4) is through first through hole (311) of each rib (31), and the second tie-beam (5) is through second through hole (312) of each rib (31).
9. according to claim 7 resisting falls anti-drift unmanned vehicle, it is characterized in that, the inside of described air bag (2) is provided with support frame (22), support frame (22) outside is coated by moccasin, first tie-beam (4) and the second tie-beam (5) are through air bag (2), and the first tie-beam (4) is all connected with support frame (22) with the second tie-beam (5).
10. according to claim 6 resisting falls anti-drift unmanned vehicle, it is characterized in that, described unmanned vehicle main body (1) bottom is provided with snap component, and the first tie-beam (4) is fixed on unmanned vehicle main body (1) bottom by snap component.
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| CN201510402303.0A CN105000186B (en) | 2015-07-09 | 2015-07-09 | A kind of anti-drift unmanned vehicle of drop resistant |
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| CN201510402303.0A CN105000186B (en) | 2015-07-09 | 2015-07-09 | A kind of anti-drift unmanned vehicle of drop resistant |
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| CN105292474A (en) * | 2015-11-06 | 2016-02-03 | 中国航空工业经济技术研究院 | Aerial queue type agricultural unmanned aerial vehicle system |
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| CN106564580A (en) * | 2016-10-19 | 2017-04-19 | 南京达索航空科技有限公司 | Airship |
| CN107352034A (en) * | 2017-06-14 | 2017-11-17 | 广州越城丰茂农林科技有限公司 | New golden-pomelo yellow twig Control Technology |
| CN107539471A (en) * | 2016-06-28 | 2018-01-05 | 郑州航空工业管理学院 | A kind of ship wing multi-rotor unmanned aerial vehicle |
| CN108177787A (en) * | 2018-02-09 | 2018-06-19 | 重庆三峡学院 | A kind of bridge machinery unmanned plane emergency safety landing-gear |
| CN111186586A (en) * | 2019-12-11 | 2020-05-22 | 贵州电网有限责任公司 | Smog emission device suitable for unmanned aerial vehicle |
| CN114348265A (en) * | 2022-03-07 | 2022-04-15 | 中国商用飞机有限责任公司 | Wing body fusion body and aircraft |
| CN115520317A (en) * | 2022-09-28 | 2022-12-27 | 江苏科技大学 | Sea ice image acquisition device and sea ice identification method |
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| CN114348265A (en) * | 2022-03-07 | 2022-04-15 | 中国商用飞机有限责任公司 | Wing body fusion body and aircraft |
| CN114348265B (en) * | 2022-03-07 | 2024-06-07 | 中国商用飞机有限责任公司 | Wing body fusion body and aircraft |
| CN115520317A (en) * | 2022-09-28 | 2022-12-27 | 江苏科技大学 | Sea ice image acquisition device and sea ice identification method |
| CN116215900A (en) * | 2023-03-07 | 2023-06-06 | 深圳技术大学 | Double-airbag unmanned aerial vehicle |
| CN116215900B (en) * | 2023-03-07 | 2023-11-14 | 深圳技术大学 | Double-airbag unmanned aerial vehicle |
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| CN105000186B (en) | 2017-09-26 |
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