CN103318405A - Unmanned plane - Google Patents
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- CN103318405A CN103318405A CN2013103027228A CN201310302722A CN103318405A CN 103318405 A CN103318405 A CN 103318405A CN 2013103027228 A CN2013103027228 A CN 2013103027228A CN 201310302722 A CN201310302722 A CN 201310302722A CN 103318405 A CN103318405 A CN 103318405A
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- 230000001939 inductive effect Effects 0.000 claims description 4
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Abstract
The invention discloses an unmanned plane which belongs to the technical field of aircrafts. The unmanned plane comprises: a fuselage, two propellers disposed at the nose, two propellers arranged at the tail, a power unit for providing power to the propellers, a power supply which is electrically connected with the power unit, and a plurality of undercarriage arms arranged at two sides of the fuselage. Each undercarriage arm is respectively connected with the fuselage through an electric folding mechanism, and each undercarriage arm is provided with at least two wheels. The two propellers arranged at the tail are connected with the fuselage through a rotatable transverse shaft. The undercarriage of the unmanned plane also comprises a motor used for providing power to the rotatable transverse shaft and a control device used for controlling the electric folding mechanism to fold and controlling the motor to adjust the two propellers arranged at the tail to be in the horizontal or vertical direction. Through the above technical scheme, the undercarriage of the unmanned plane is retractable, and the unmanned plane can run on the ground.
Description
Technical field
The present invention relates to the unmanned plane technical field, particularly a kind of unmanned plane.
Background technology
Robot airplane, abbreviation unmanned plane (UAV) is a kind of new concept weapon equipment that is in developing rapidly, it has advantages of maneuverability, reaction is quick, nobody flies, operation requirements is low.Unmanned plane can be realized image real-time Transmission, high-risk regional detecting function by carrying multiclass sensor, is that the strong of satellite remote sensing and traditional air remote sensing replenishes.At present, the range of use of unmanned plane has been widened military affairs, scientific research, civilian three large fields, specifically in electric power, communication, meteorology, agricultural, ocean, exploration, photograph, prevent and reduce natural disasters, the fields such as Crop Estimation, drug law enforcement anti-smuggling, border patrol, public security anti-terrorism use very wide.
In realizing process of the present invention, the contriver finds that there is following problem at least in prior art:
Retractable landing gear complex structure in the alighting gear of present unmanned plane, applicability is relatively poor, and can not be used for ground run.
Summary of the invention
In order to solve unmanned plane landing gear structure complexity in the prior art, problem poor for applicability, the embodiment of the invention provide a kind of unmanned plane.
The embodiment of the invention provides a kind of unmanned plane, described unmanned plane comprises: fuselage, be located at two groups of screw propellers of head, be located at two groups of screw propellers of tail, the engine installation of power is provided for described screw propeller, the power supply that is electrically connected with described engine installation, and a plurality of booms that rise and fall that place respectively described fuselage both sides, each boom that rises and falls is connected with described fuselage by a power fold mechanism respectively, and described each boom that rises and falls is provided with at least two wheels, described two groups of screw propellers being located at tail are connected with described fuselage by a rotatable transverse axis, and described unmanned plane alighting gear also comprises:
Motor is used to described rotatable transverse axis to rotate power is provided;
Control setup is used for controlling described power fold mechanism folding, and by the described motor of control, is in horizontal or vertical direction to adjust described two groups of screw propellers being located at tail;
Described control setup places in the described fuselage, and described control setup is electrically connected with described power supply, described power fold mechanism and described motor respectively.
In a kind of implementation of the embodiment of the invention, described power fold mechanism is the metal steering base.
In the another kind of implementation of the embodiment of the invention, the steering angle scope of described metal steering base is 0～45 degree.
In the another kind of implementation of the embodiment of the invention, described each boom that rises and falls comprises first boom and second boom that rises and falls that rises and falls, described first end that rises and falls boom is connected with described power fold mechanism, the other end is connected with described second end that rises and falls boom, wherein, described first rise and fall the angle between the boom of boom and described second that rises and falls is 90～135 degree.
In the another kind of implementation of the embodiment of the invention, described first boom that rises and falls is telescopic arms, and described control setup also is used for controlling the described first length of rising and falling boom.
In the another kind of implementation of the embodiment of the invention, described first boom that rises and falls is hydraulic stem.
In the another kind of implementation of the embodiment of the invention, be positioned at the rise and fall other end of boom of second of described fuselage homonymy and interconnect by the 3rd boom that rises and falls, described wheel is located at the described the 3rd and is risen and fallen on the boom.
In the another kind of implementation of the embodiment of the invention, also comprise described second degree of packing up and the sensor that puts down degree of rising and falling boom of surveying, described sensor is positioned at described second and rises and falls on the boom, and described sensor is electrically connected with described control setup.
In the another kind of implementation of the embodiment of the invention, described sensor is inductive pickoff.
In the another kind of implementation of the embodiment of the invention, described control setup is microcomputer.
The beneficial effect that the technical scheme that the embodiment of the invention provides is brought is:
The boom that will rise and fall is connected with power fold mechanism, thereby the alighting gear of realizing unmanned plane is collapsible, in addition, two groups of screw propellers being located at tail are connected with fuselage by a rotatable transverse axis, and adopt motor to provide power for rotatable transverse axis rotates, control setup is by the control motor, and two groups of screw propellers being located at tail with adjustment are in horizontal or vertical direction; Thereby realize unmanned plane at ground run, this unmanned plane is simple in structure, and applicability is wide, and is easy to operate.
Description of drawings
In order to be illustrated more clearly in the technical scheme in the embodiment of the invention, the accompanying drawing of required use was done to introduce simply during the below will describe embodiment, apparently, accompanying drawing in the following describes only is some embodiments of the present invention, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the unmanned plane structural representation that the embodiment of the invention provides;
Fig. 2 is the partial schematic diagram that the alighting gear of the unmanned plane that provides of the embodiment of the invention is in collapsed state;
Fig. 3 is that first boom that falls is in the partial schematic diagram of elongation state in the alighting gear of the unmanned plane that provides of the embodiment of the invention;
Fig. 4 is the back view of the unmanned plane that provides of the embodiment of the invention;
Fig. 5 is the lateral plan of the unmanned plane that provides of the embodiment of the invention.
The specific embodiment
For making the purpose, technical solutions and advantages of the present invention clearer, embodiment of the present invention is described further in detail below in conjunction with accompanying drawing.
The embodiment of the invention provides a kind of unmanned plane, referring to Fig. 1～5, this unmanned plane comprises: fuselage 1, be located at two groups of screw propellers 21 of head, be located at two groups of screw propellers 22 of tail, the engine installation 3 of power is provided for screw propeller, the power supply (not shown) that is electrically connected with engine installation 3, and a plurality of booms 4 that rise and fall that place respectively fuselage 1 both sides, each boom 4 that rises and falls is connected with unmanned aerial vehicle body 1 by a power fold mechanism 5 respectively, and each boom 4 that rises and falls is provided with at least two wheels 6, two spiral 22 oars being located at tail are connected with fuselage 1 by a rotatable transverse axis 7, and the unmanned plane alighting gear also comprises:
The motor (not shown) is used to rotatable transverse axis to rotate power is provided;
The control setup (not shown) is used for the control power fold mechanism folding, and by the control motor, two groups of screw propellers being located at tail with adjustment are in horizontal or vertical direction;
Above-mentioned power supply, motor and control setup place in the fuselage, and control setup is electrically connected with power supply, power fold mechanism 5 and motor respectively.
Wherein, this power fold mechanism 5 is the metal steering base.Be subjected to the impact of external environment little when preferably, the metal steering base is used for this unmanned plane alighting gear.
Particularly, the steering angle scope of metal steering base is 0～45 degree.Steering angle refers to, the boom 4 rotating angle under the metal steering base drives of rising and falling.This steering angle is on the basis of boom folding and unfolding of realizing rising and falling, and the boom movement range scope of rising and falling is little, so that the present embodiment unmanned plane alighting gear windage in realizing the folding and unfolding process reduces, power-dissipation-reduced.Wherein, rise and fall the boom collapsed state referring to Fig. 2.
Particularly, each boom 4 that rises and falls comprises first boom 41 and second boom 42 that rises and falls that rises and falls, first end that rises and falls boom 41 is connected with power fold mechanism 5, a rise and fall end of boom 42 of first other end and second that rises and falls boom 41 is connected, wherein, first rise and fall the angle between the boom 42 of boom 41 and second that rises and falls is 90～135 degree.Because this boom that rises and falls is divided into two parts, and the angle between two parts can guarantee that second boom 42 that rises and falls reliablely and stablely parks on the ground when putting down, can guarantee that again second rises and falls boom 42 when packing up and the screw propeller at fuselage 1 two ends (comprising two groups of screw propellers 21 of being located at head and two groups of screw propellers 22 being located at tail) keeps certain distance d(d ﹥ 0), pack up bump in the process to avoid screw propeller to be subject to second boom 42 that rises and falls.
Further, the first rise and fall boom 41 is telescopic arms, and control setup also is used for the rise and fall length of boom 41 of control first.Control setup can be realized the control to the direction of wheel 6 by controlling the first length of rising and falling boom 41, thus when unmanned plane at ground run or when sliding, can control the direction of unmanned plane, as shown in Figure 3.
Preferably, the first rise and fall boom 41 is hydraulic stem.
Further, be positioned at the rise and fall other end of boom 42 of second of fuselage homonymy and interconnect by the 3rd boom 43 that rises and falls, wheel 6 is located at the 3rd and is risen and fallen on the boom 43.This first boom 41, second boom 42 and the 3rd boom 43 that rises and falls that rises and falls that rises and falls complements each other to form stable supporting construction.
Further, this unmanned plane also comprises second degree of packing up and the sensor 8 that puts down degree of rising and falling boom 42 of surveying, and sensor 8 is positioned at second and rises and falls on the boom 42, and sensor 8 is electrically connected with control setup.Sensor 8 can real-time detection this second state that rises and falls boom 42, control setup is accurately controlled the steering angle of power fold mechanism 5 according to the detection data of this sensor 8, so that second the rise and fall folding and unfolding position of boom 42 is more accurate.
Preferably, sensor is inductive pickoff.This inductive pickoff adopts non-contacting detection mode to guarantee that sensor can not wear and tear or be shifted.
Preferably, control setup can be microcomputer.
As from the foregoing, when unmanned plane in when flight, control setup control power fold mechanism is upwards folding, and then drives the boom that rises and falls and pack up; When unmanned plane grounded, control setup control power fold mechanism was folding downwards, and then drove the boom that rises and falls and put down.Referring to Fig. 4 and Fig. 5, when unmanned plane need to be at ground run, control setup control fold mechanism is folding downwards, and then drive the boom that rises and falls and put down, and the control motor is in vertical state so that be located at the screw propeller of tail, and then the control screw propeller of being located at tail rotates, and the screw propeller of being located at head does not rotate, thereby so that unmanned plane can slide forward, control simultaneously the first length of rising and falling boom and realize turning to.
Easily know, in other implementation, the screw propeller of being located at head also can also be made the pattern that can turn to, thereby the unmanned plane during for ground run provides power, in addition, also second boom that rises and falls can be set as telescopic arms and control travel direction.
The present invention is connected with power fold mechanism by the boom that will rise and fall, thereby the alighting gear of realizing unmanned plane is collapsible, in addition, two groups of screw propellers being located at tail are connected with fuselage by a rotatable transverse axis, and adopt motor to provide power for rotatable transverse axis rotates, control setup is by the control motor, and two groups of screw propellers being located at tail with adjustment are in horizontal or vertical direction; Thereby realize unmanned plane at ground run, this unmanned plane is simple in structure, and applicability is wide, and is easy to operate.
Above this only is the preferred embodiment of this invention, and be in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of doing, is equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. unmanned plane, described unmanned plane comprises: fuselage, be located at two groups of screw propellers of head, be located at two groups of screw propellers of tail, the engine installation of power is provided for described screw propeller, the power supply that is electrically connected with described engine installation, and a plurality of booms that rise and fall that place respectively described fuselage both sides, it is characterized in that, each boom that rises and falls is connected with described fuselage by a power fold mechanism respectively, and described each boom that rises and falls is provided with at least two wheels, described two groups of screw propellers being located at tail are connected with described fuselage by a rotatable transverse axis, and described unmanned plane alighting gear also comprises:
Motor is used to described rotatable transverse axis to rotate power is provided;
Control setup is used for controlling described power fold mechanism folding, and by the described motor of control, is in horizontal or vertical direction to adjust described two groups of screw propellers being located at tail;
Described control setup places in the described fuselage, and described control setup is electrically connected with described power supply, described power fold mechanism and described motor respectively.
2. unmanned plane as claimed in claim 1 is characterized in that, described power fold mechanism is the metal steering base.
3. unmanned plane as claimed in claim 2 is characterized in that, the steering angle scope of described metal steering base is 0～45 degree.
4. such as each described unmanned plane of claim 1～3, it is characterized in that, described each boom that rises and falls comprises first boom and second boom that rises and falls that rises and falls, described first end that rises and falls boom is connected with described power fold mechanism, the other end is connected with described second end that rises and falls boom, wherein, described first rise and fall the angle between the boom of boom and described second that rises and falls is 90～135 degree.
5. unmanned plane as claimed in claim 4 is characterized in that, described first boom that rises and falls is telescopic arms, and described control setup also is used for controlling the described first length of rising and falling boom.
6. unmanned plane as claimed in claim 5 is characterized in that, described first boom that rises and falls is hydraulic stem.
7. unmanned plane as claimed in claim 4 is characterized in that, is positioned at the rise and fall other end of boom of second of described fuselage homonymy and interconnects by the 3rd boom that rises and falls, and described wheel is located at the described the 3rd and is risen and fallen on the boom.
8. unmanned plane as claimed in claim 4 is characterized in that, also comprises described second degree of packing up and the sensor that puts down degree of rising and falling boom of surveying, and described sensor is positioned at described second and rises and falls on the boom, and described sensor is electrically connected with described control setup.
9. unmanned plane as claimed in claim 8 is characterized in that, described sensor is inductive pickoff.
10. such as each described unmanned plane of claim 1～3, it is characterized in that, described control setup is microcomputer.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310302722.8A CN103318405B (en) | 2013-07-17 | 2013-07-17 | A kind of unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310302722.8A CN103318405B (en) | 2013-07-17 | 2013-07-17 | A kind of unmanned plane |
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| CN103318405A true CN103318405A (en) | 2013-09-25 |
| CN103318405B CN103318405B (en) | 2015-11-18 |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104044731A (en) * | 2014-06-26 | 2014-09-17 | 深圳市哈博森科技有限公司 | Aircraft landing device and aircraft |
| CN104787307A (en) * | 2015-03-31 | 2015-07-22 | 深圳一电科技有限公司 | Unmanned aerial plane system, unmanned aerial plane and control method of unmanned aerial plane system |
| CN104787319A (en) * | 2015-04-23 | 2015-07-22 | 张�杰 | Four-rotor aircraft provided with telescopic and foldable undercarriages |
| CN104908928A (en) * | 2015-06-23 | 2015-09-16 | 白立安 | Ground effect aircraft |
| CN105035303A (en) * | 2015-08-19 | 2015-11-11 | 无锡觅睿恪科技有限公司 | Folding type aerial photography aircraft |
| CN105270613A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Foldable telescopic six-shaft aircraft |
| CN105947206A (en) * | 2016-04-28 | 2016-09-21 | 华南农业大学 | Unmanned aerial vehicle capable of taking off and landing at will in fields and operation method of unmanned aerial vehicle |
| CN106042803A (en) * | 2016-05-22 | 2016-10-26 | 王静 | Amphibious unmanned aerial vehicle |
| CN106043664A (en) * | 2016-06-22 | 2016-10-26 | 宁波蓝飞鹂航空科技有限公司 | Novel folding deformable aircraft |
| WO2017008707A1 (en) * | 2015-07-15 | 2017-01-19 | 广州天翔航空科技有限公司 | Multi-rotor plant protection unmanned aerial vehicle of trolley design |
| CN106828867A (en) * | 2016-12-30 | 2017-06-13 | 易瓦特科技股份公司 | Noise-proofing formula unmanned plane |
| CN107000831A (en) * | 2016-12-30 | 2017-08-01 | 深圳市大疆创新科技有限公司 | Unmanned vehicle and its Landing Gear System |
| CN107108030A (en) * | 2016-09-21 | 2017-08-29 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| WO2017143643A1 (en) * | 2016-02-22 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Frame of unmanned aerial vehicle, unmanned aerial vehicle, and use method therefor |
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| CN109906796A (en) * | 2019-03-13 | 2019-06-21 | 河南科技学院 | A kind of crop topping machine based on plant protection drone |
| US10710711B2 (en) | 2016-09-21 | 2020-07-14 | SZ DJI Technology Co., Ltd. | Systems and methods for UAV sensor placement |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2759940Y (en) * | 2003-08-18 | 2006-02-22 | 欧阳厚成 | Rotor blade and double rotor on the blade |
| CN101575004A (en) * | 2009-06-09 | 2009-11-11 | 徐锦法 | Flight-mode-variable unmanned aircraft with multiple sets of coaxial rotors |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| CN103057702A (en) * | 2012-12-25 | 2013-04-24 | 天津全华时代航天科技发展有限公司 | Jet-propelled rotor helicopter |
| CN203047530U (en) * | 2012-08-21 | 2013-07-10 | 深圳市大疆创新科技有限公司 | Aircraft foot stand and aircraft with same |
-
2013
- 2013-07-17 CN CN201310302722.8A patent/CN103318405B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2759940Y (en) * | 2003-08-18 | 2006-02-22 | 欧阳厚成 | Rotor blade and double rotor on the blade |
| CN101575004A (en) * | 2009-06-09 | 2009-11-11 | 徐锦法 | Flight-mode-variable unmanned aircraft with multiple sets of coaxial rotors |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| CN203047530U (en) * | 2012-08-21 | 2013-07-10 | 深圳市大疆创新科技有限公司 | Aircraft foot stand and aircraft with same |
| CN103057702A (en) * | 2012-12-25 | 2013-04-24 | 天津全华时代航天科技发展有限公司 | Jet-propelled rotor helicopter |
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| CN104044731A (en) * | 2014-06-26 | 2014-09-17 | 深圳市哈博森科技有限公司 | Aircraft landing device and aircraft |
| CN104787307A (en) * | 2015-03-31 | 2015-07-22 | 深圳一电科技有限公司 | Unmanned aerial plane system, unmanned aerial plane and control method of unmanned aerial plane system |
| CN104787319A (en) * | 2015-04-23 | 2015-07-22 | 张�杰 | Four-rotor aircraft provided with telescopic and foldable undercarriages |
| CN104908928A (en) * | 2015-06-23 | 2015-09-16 | 白立安 | Ground effect aircraft |
| WO2017008707A1 (en) * | 2015-07-15 | 2017-01-19 | 广州天翔航空科技有限公司 | Multi-rotor plant protection unmanned aerial vehicle of trolley design |
| CN105035303A (en) * | 2015-08-19 | 2015-11-11 | 无锡觅睿恪科技有限公司 | Folding type aerial photography aircraft |
| CN105270613A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Foldable telescopic six-shaft aircraft |
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| CN105947206A (en) * | 2016-04-28 | 2016-09-21 | 华南农业大学 | Unmanned aerial vehicle capable of taking off and landing at will in fields and operation method of unmanned aerial vehicle |
| CN105947206B (en) * | 2016-04-28 | 2018-05-18 | 华南农业大学 | It is a kind of can be in the unmanned plane and its operational method of the arbitrary landing operation in field |
| CN106042803A (en) * | 2016-05-22 | 2016-10-26 | 王静 | Amphibious unmanned aerial vehicle |
| CN107521677A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | Unmanned aerial vehicle foot stool control system and method |
| CN106043664A (en) * | 2016-06-22 | 2016-10-26 | 宁波蓝飞鹂航空科技有限公司 | Novel folding deformable aircraft |
| CN106043664B (en) * | 2016-06-22 | 2019-10-18 | 宁波创彩颜料有限公司 | A kind of novel folding morphing aircraft |
| CN107521677B (en) * | 2016-06-22 | 2022-05-13 | 北京臻迪机器人有限公司 | Unmanned aerial vehicle foot stool control system and method |
| US10710711B2 (en) | 2016-09-21 | 2020-07-14 | SZ DJI Technology Co., Ltd. | Systems and methods for UAV sensor placement |
| CN107108030A (en) * | 2016-09-21 | 2017-08-29 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| US11368002B2 (en) | 2016-11-22 | 2022-06-21 | Hydro-Quebec | Unmanned aerial vehicle for monitoring an electrical line |
| CN107000831A (en) * | 2016-12-30 | 2017-08-01 | 深圳市大疆创新科技有限公司 | Unmanned vehicle and its Landing Gear System |
| CN106828867A (en) * | 2016-12-30 | 2017-06-13 | 易瓦特科技股份公司 | Noise-proofing formula unmanned plane |
| WO2018120044A1 (en) * | 2016-12-30 | 2018-07-05 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and landing gear system thereof |
| CN109906796A (en) * | 2019-03-13 | 2019-06-21 | 河南科技学院 | A kind of crop topping machine based on plant protection drone |
| US12097956B2 (en) | 2021-04-30 | 2024-09-24 | Hydro-Quebec | Drone with tool positioning system |
| CN114132488A (en) * | 2021-11-24 | 2022-03-04 | 国网福建省电力有限公司南平供电公司 | Transmission of electricity inspection device based on internet big data |
| CN114132488B (en) * | 2021-11-24 | 2023-06-30 | 国网福建省电力有限公司南平供电公司 | Transmission of electricity inspection device based on internet big data |
| CN114537065A (en) * | 2022-02-28 | 2022-05-27 | 重庆交通大学 | Air-ground dual-purpose multifunctional unmanned aerial vehicle |
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