CN104044731B - Aircraft landing device and aircraft - Google Patents
Aircraft landing device and aircraft Download PDFInfo
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- CN104044731B CN104044731B CN201410298829.4A CN201410298829A CN104044731B CN 104044731 B CN104044731 B CN 104044731B CN 201410298829 A CN201410298829 A CN 201410298829A CN 104044731 B CN104044731 B CN 104044731B
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- aircraft
- earth
- locating slot
- switch
- controller
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Abstract
The invention discloses an aircraft landing device which is installed on an aircraft body of the aircraft. The aircraft landing device comprises a foot stool, a controller, a ground touch switch and at least one motor, wherein the foot stool supports the aircraft body; the bottom of the foot stool is provided with a first positioning groove; the controller is arranged in the aircraft body; the ground touch switch is positioned in the first positioning groove and electrically connected with the controller; the at least one motor is electrically connected with the controller and drives the aircraft body to fly; when the foot stool of the aircraft lands off, the ground touch switch touches the ground and sends a ground touch signal to the controller, and the controller controls the motors to stop operating according to the ground touch signal. The invention also provides the aircraft. The aircraft landing device and the aircraft which are provided by the invention can effectively prevent the aircraft in landing from jumping continuously.
Description
Technical field
The present invention relates to aviation field, more particularly, to a kind of aircraft landing gear and aircraft.
Background technology
Unpiloted small aircraft, for large-scale manned aircraft, has miniaturization, flexible, price
Cheaply, rise and fall convenient feature, be therefore widely used in model plane, agricultural, fire-fighting and field of taking photo by plane.
In prior art, because aircraft cannot detect whether aircraft lands, when aircraft lands, aircraft exists
Can occur in the presence of inertia continuously to bounce, until motor quits work.The above-mentioned spring-like movement of aircraft most probably causes
Centre-of gravity shift during aircraft lands, thus lead to the damage of components of aircraft.
Content of the invention
It is an object of the invention to when solving above-mentioned aircraft lands, when the spring-like movement of aircraft causes aircraft lands
Centre-of gravity shift, thus lead to the problem of the damage of components of aircraft.
On the one hand, there is provided a kind of aircraft landing gear, it is installed on the fuselage of aircraft.Described aircraft landing gear
Including foot rest, controller, contact to earth switch and at least one motor.Described foot rest supports described fuselage, and the bottom of described foot rest sets
There is the first locating slot.Described controller in described fuselage, the described switch that contacts to earth be positioned described first locating slot and with institute
State controller to be electrically connected with.Described motor is electrically connected with described controller and drives described fuselage flight.When described aircraft
When described foot rest lands, signal is contacted to earth to described controller in the described switch contact ground sending of contacting to earth, described controller according to
The described signal that contacts to earth controls described motor to quit work.
Preferably, described aircraft landing gear also includes protection cap, and contact to earth described in described protection cap masking switch, works as institute
When stating protection cap contact ground, contact to earth described in described protection cap triggering switch.
Preferably, the described switch that contacts to earth includes circuit board, adapter and triggers button, and described circuit board is positioned described the
In one locating slot, on described circuit board, the described switch 23 that contacts to earth is by described adapter and described control for described adapter
Device is electrically connected with, and described triggering button is convexly equipped in described circuit board and exposes to described first locating slot, and described protection cap includes
Location division, the first occlusion part being convexly equipped in described location division and the second occlusion part, described location division cover described circuit board and with
Described circuit board is fixed, and described first occlusion part covers described adapter, and described second occlusion part covers described triggering button.
Preferably, the material of described protection cap is flexible glue material.
Preferably, described foot rest includes the support of a pair of opposing, and one end of support described in a pair is respectively positioned in institute
State the bottom of fuselage, the direction expansion that the other end of support described in a pair is directed away from described fuselage from described fuselage bottom is prolonged
Stretch, described first locating slot is located therein a described support.
Preferably, the bottom of each described support is additionally provided with least one second locating slot, described aircraft lands dress
Put and also include multiple elastic components corresponding with described second locating slot, described elastic component is respectively positioned in described second locating slot
And expose to described second locating slot.
Preferably, the material of described elastic component is ethylene-vinyl acetate copolymer flexible glue material.
On the other hand, there is provided a kind of aircraft, including fuselage.Described aircraft also includes above-mentioned aircraft lands dress
Put.
As can be seen here, the present invention provides aircraft landing gear and aircraft, by arranging on the foot rest of aircraft
Contact to earth switch, and when aircraft lands, the switch that contacts to earth can first contact ground and concurrently send the signal that contacts to earth to controller.Controller according to
The described signal control motor that contacts to earth quits work.After motor quits work, aircraft is out of service, such that it is able to effectively prevent
There is the action of continuous bounce in aircraft when landing, make aircraft grease it in, be prevented effectively from the parts of aircraft
Impaired.
Brief description
In order to be illustrated more clearly that technical scheme, below by the accompanying drawing work to use required in embodiment
Simply introduce it should be apparent that, drawings in the following description are only some embodiments of the present invention, general for this area
For logical technical staff, on the premise of not paying creative work, other accompanying drawings can also be obtained as these accompanying drawings.
Fig. 1 is the schematic diagram of the aircraft that the specific embodiment of the invention provides.
Fig. 2 is the schematic diagram in another direction of aircraft described in Fig. 1.
Fig. 3 is the circuit control schematic diagram of aircraft landing gear in Fig. 1.
Fig. 4 is the decomposing schematic representation of the aircraft shown in Fig. 2.
Fig. 5 is the enlarged diagram of circle V part in Fig. 4.
Specific embodiment
Below in conjunction with the accompanying drawing in embodiment of the present invention, the technical scheme in embodiment of the present invention is carried out clearly
Chu, it is fully described by.
Please with reference to Fig. 1 to Fig. 5, the aircraft 100 that the specific embodiment of the invention provides includes fuselage 10 and installs
Aircraft landing gear (sign) in described fuselage 10.Described aircraft landing gear includes foot rest 21, controller 22, touches
Ground switch 23 and at least one motor 24.Described foot rest 21 supports described fuselage 10, and the bottom of described foot rest 21 is provided with first and determines
Position groove 2111.Described controller 22 is in described fuselage 10.The described switch 23 that contacts to earth is positioned described first locating slot 2111
And be electrically connected with described controller 22.Described motor 24 is electrically connected with described controller 22 and drives described fuselage 10 to fly.
When the described foot rest 21 of described aircraft 100 lands, the signal that contacts to earth concurrently is sent to described in described switch 23 contact ground of contacting to earth
Controller 22, described controller 22 controls described motor 24 to quit work according to the described signal that contacts to earth.
As can be seen here, the present invention provides aircraft 100 and aircraft landing gear, by the foot rest in aircraft 100
On 21, setting is contacted to earth switch 23, and when aircraft 100 lands, the switch 23 that contacts to earth can first contact ground and concurrently send the signal that contacts to earth to controlling
Device 22 processed.Controller 22 controls described motor 24 to quit work according to the described signal that contacts to earth.After motor 24 quits work, flight
Device 100 is out of service, such that it is able to effectively prevent aircraft 100 from the action of continuous bounce occurring when landing, makes flight
Device 100 grease it in, the parts being prevented effectively from aircraft 100 are impaired.
In present embodiment, described aircraft 100 is quadrotor, and includes four motors 24, described motor 24
For brushless electric machine.When described aircraft 100 lands, the switch 23 that contacts to earth can first contact ground and concurrently send the signal that contacts to earth to controller
22.Controller 22 controls described four motors 24 to quit work according to the described signal that contacts to earth simultaneously.
In present embodiment, described switch 23 parts of contacting to earth expose to described first locating slot 2111, when described aircraft
It can be ensured that the described switch 23 that contacts to earth first is contacted with ground during 100 landing, thus ensureing that aircraft 100 can be timely when landing
Controlled motor 24 quits work, to avoid the generation of continuous bounce action.
Further, described aircraft landing gear also includes protection cap 25, described protection cap 25 cover described in contact to earth out
Close 23.When described protection cap 25 contact ground, described protection cap 25 trigger described in contact to earth switch 23.The setting of described protection cap 25
Put switch 23 directly contact ground of contacting to earth described in can avoiding, the stability of the switch 23 that contacts to earth described in effective protection.
Refer to Fig. 5, specifically, the described switch 23 that contacts to earth includes circuit board 231, adapter 232 and triggering button 233.
Described circuit board 231 is positioned in described first locating slot 2111.Described adapter 232 is on described circuit board 231, described
The switch 23 that contacts to earth is electrically connected with described controller 22 by described adapter 232.Described triggering button 233 is convexly equipped in described electricity
Road plate 231 simultaneously exposes to described first locating slot 2111.
Described protection cap 25 includes location division 251, the first occlusion part 252 being convexly equipped in described location division 251 and the second screening
Stopper 253.During installation, described location division 251 covers described circuit board 231, described first screening fixing with described circuit board 231
Stopper 252 covers described adapter 232, and described second occlusion part 253 covers described triggering button 233.
In present embodiment, in described first locating slot 2111, it is provided with a pair of locating dowel 2112 and at least one support column
2114.The described circuit board 231 contacting to earth switch 23 is provided with a pair first location holes 2311.The location division 251 of described protection cap 25
It is provided with a pair second location holes 2511.Each locating dowel 2112 is provided with the 3rd location hole 2115.During installation, described locating dowel
2112 and described support column 2114 support described circuit board 231, described protection cap 25 cover described in contact to earth switch 23.Described second
Location hole 2511, described first location hole 2311 and described 3rd location hole 2115 align respectively, and pass through screw (not shown)
Sequentially pass through described second location hole 2511, described first location hole 2311 and described 3rd location hole 2115, thus will be described
Protection cap 25, the described switch 23 that contacts to earth is fixing with described foot rest 21.This kind of positioning mode it can be ensured that described contact to earth switch 23 with
Foot rest 21 is firmly combined together, it is to avoid the switch 23 that contacts to earth is departed from foot rest 21.
In present embodiment, the material of described protection cap 25 is flexible glue material, and described flexible glue is ethene-vinyl acetate copolymerization
Thing (ethylene-vinyl acetate copolymer, EVA).When described aircraft 100 lands, described flexible glue material can
To play cushioning effect to the described switch 23 that contacts to earth, contact to earth described in effective protection switch 23.
Further, described foot rest 21 includes the support 211 of a pair of opposing.Described in a pair, one end of support 211 is divided
It is not positioned the bottom of described fuselage 10, the other end of support 211 described in a pair is directed away from described from described fuselage 10 bottom
The direction expansion of fuselage 10 extends, and described first locating slot 2111 is located therein a described support 211.
In present embodiment, the bottom of each described support 211 is additionally provided with least one second locating slot 2113, such as schemes
Shown in 5.Described aircraft landing gear also includes the multiple elastic components 26 corresponding with described second locating slot 2113.Install
When, described elastic component 26 is respectively positioned in described second locating slot 2113 and exposes to described second locating slot 2113.Work as institute
When stating aircraft 100 landing, the setting of described elastic component 26, cushioning effect can be played to described aircraft 100, it is to avoid flight
Device 100 is impaired when landing.
In present embodiment, the material of described elastic component 26 is ethylene-vinyl acetate copolymer (ethylene-vinyl
Acetate copolymer, EVA) flexible glue material.
The above is the preferred embodiment of the present invention it is noted that for those skilled in the art
For, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications are also considered as
Protection scope of the present invention.
Claims (6)
1. a kind of aircraft landing gear, is installed on the fuselage of aircraft it is characterised in that described aircraft landing gear includes
Foot rest, controller, contact to earth switch and at least one motor, and described foot rest supports described fuselage, and the bottom of described foot rest is provided with the
One locating slot, described controller in described fuselage, the described switch that contacts to earth be positioned described first locating slot and with described control
Device processed is electrically connected with, and described motor is electrically connected with described controller and drives described fuselage flight, when described in described aircraft
When foot rest lands, the described switch contact ground send the signal that contacts to earth to described controller of contacting to earth, described controller is according to described
The signal that contacts to earth controls described motor to quit work, and described aircraft landing gear also includes protection cap, described protection cap shelter
State the switch that contacts to earth, when described protection cap contact ground, contact to earth described in described protection cap triggering switch, and the described switch that contacts to earth includes
Circuit board, adapter and triggering button, described circuit board is positioned in described first locating slot, and described adapter is located at described electricity
On the plate of road, the described switch that contacts to earth is electrically connected with described controller by described adapter, and described triggering button is convexly equipped in described
Circuit board simultaneously exposes to described first locating slot, and described protection cap includes location division, is convexly equipped in the first of described location division and blocks
Portion and the second occlusion part, described location division is covered described circuit board and is fixed with described circuit board, and described first occlusion part covers
Described adapter, described second occlusion part covers described triggering button.
2. aircraft landing gear as claimed in claim 1 is it is characterised in that the material of described protection cap is flexible glue material.
3. aircraft landing gear as claimed in claim 1 is it is characterised in that described foot rest includes propping up of a pair of opposing
Frame, one end of support described in a pair is respectively positioned in the bottom of described fuselage, and described in a pair, the other end of support is from described fuselage
The direction expansion that bottom is directed away from described fuselage extends, and described first locating slot is located therein a described support.
4. aircraft landing gear as claimed in claim 3 it is characterised in that the bottom of each described support be additionally provided with to
Few second locating slot, described aircraft landing gear also includes multiple elastic components corresponding with described second locating slot, institute
State elastic component to be respectively positioned in described second locating slot and expose to described second locating slot.
5. aircraft landing gear as claimed in claim 4 is it is characterised in that the material of described elastic component is ethyl vinyl acetate
Ethylene copolymer flexible glue material.
6. a kind of aircraft, including fuselage it is characterised in that described aircraft is also included as claim 1 to 5 any one institute
The aircraft landing gear stated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410298829.4A CN104044731B (en) | 2014-06-26 | 2014-06-26 | Aircraft landing device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410298829.4A CN104044731B (en) | 2014-06-26 | 2014-06-26 | Aircraft landing device and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104044731A CN104044731A (en) | 2014-09-17 |
| CN104044731B true CN104044731B (en) | 2017-02-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410298829.4A Active CN104044731B (en) | 2014-06-26 | 2014-06-26 | Aircraft landing device and aircraft |
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| Country | Link |
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| CN (1) | CN104044731B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081077A (en) * | 2016-08-23 | 2016-11-09 | 成都翼高九天科技有限公司 | A kind of can the shockproof flight instruments of multiple-effect of flying for long time |
| CN106275397A (en) * | 2016-08-23 | 2017-01-04 | 成都翼高九天科技有限公司 | A kind of can the minute vehicle of automatic power |
| CN109987559A (en) * | 2019-04-30 | 2019-07-09 | 安徽柳工起重机有限公司 | A kind of protection buffer unit for preventing aerial working platform operation bucket from contacting to earth |
| CN112896512B (en) * | 2021-04-02 | 2022-06-21 | 福建汇仟航空科技有限公司 | Unmanned aerial vehicle and working method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973393A (en) * | 2010-09-30 | 2011-02-16 | 清华大学 | High-strength cage-type undercarriage of unmanned helicopter |
| CN102092475A (en) * | 2010-12-30 | 2011-06-15 | 清华大学 | Landing automatic flameout system for unmanned helicopter |
| CN202201169U (en) * | 2011-06-30 | 2012-04-25 | 中国商用飞机有限责任公司 | Aircraft tail sled device |
| CN202642094U (en) * | 2012-05-15 | 2013-01-02 | 南京信息工程大学 | Landing gear for unmanned aerial vehicle |
| CN103318405B (en) * | 2013-07-17 | 2015-11-18 | 国家电网公司 | A kind of unmanned plane |
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| CN104044731A (en) | 2014-09-17 |
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