CN204802064U - Aircraft and fuselage structure thereof - Google Patents
Aircraft and fuselage structure thereof Download PDFInfo
- Publication number
- CN204802064U CN204802064U CN201520208090.3U CN201520208090U CN204802064U CN 204802064 U CN204802064 U CN 204802064U CN 201520208090 U CN201520208090 U CN 201520208090U CN 204802064 U CN204802064 U CN 204802064U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- battery case
- main body
- airframe structure
- fuselage main
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model provides an aircraft and fuselage structure thereof. This fuselage structure includes a fuselage main part, this fuselage main part has the battery jar and inside holds the chamber, this battery jar is located the lower part of this fuselage main part and is used for holding battery pack, this inside holds the inside that the chamber was located this battery jar inboard and was lain in this fuselage main part, this inside holds the chamber and is used for the at least aircraft intraware of holding, the opening of this battery jar makes this at least aircraft intraware to hold the intracavity via this inside of battery jar entering, this aircraft intraware includes a main control board the utility model provides an aircraft and fuselage structure thereof can conveniently install subassemblies such as antenna, battery to battery jar and the inside design of holding the chamber make the intraware of aircraft for example main control board etc. Can rearmounted fixed mounting, are showing the ease for operation and the convenience that have promoted the aircraft installation.
Description
Technical field
The utility model is in particular to a kind of aircraft and airframe structure thereof.
Background technology
In prior art, fuselage due to aircraft needs to be fixedly connected with as battery pack, antenna etc. with multiple external device or structure example and to be electrically connected, and connection in external structure and be electrically connected the restriction and impact that all can produce under many circumstances each other, thus cause aircraft that the problem of inconvenience is installed.Further, in this case, in the installation process of aircraft, the connection of each assembly, fixing, install and must be undertaken by comparatively strict order, more exacerbate the problem that it installs inconvenience.
Utility model content
The technical problems to be solved in the utility model is to overcome the defect that aircraft sequence of erection in prior art is inflexible, install inconvenience, providing a kind of aircraft and airframe structure thereof.
The utility model solves above-mentioned technical matters by following technical proposals:
The utility model provides a kind of airframe structure of aircraft, comprise a fuselage main body, its feature is, this fuselage main body has a battery case and an inner container cavity, this battery case is used for set battery assembly, this inner container cavity to be located at inside this battery case and to be positioned at the inside of this fuselage main body, and this inner container cavity is used for accommodating at least one aircraft interior components, and the opening of this battery case makes this at least one aircraft interior components be able to enter in this inner container cavity via this battery case.
Airframe structure of the present utility model, makes the connection lead of some external modules such as LED, motor etc., penetrates the aircraft interior components that this inner container cavity accommodates to be connected to inside, the master control board of such as aircraft via this battery case.And more specifically, LED and motor are arranged on the machine wall of this airframe structure, its connection lead to this battery case place, is then connected to through this battery case and this inner container cavity the master control board being positioned at this inner container cavity through the machine wall cavity inside machine wall.This just means, any one connection lead is not exposed to this airframe structure outside, simultaneously again to complete the installation of various assembly and connection lead after complete airframe structure machine-shaping again.This makes installation process become very convenient, flexible.
Preferably, the bottom of this fuselage main body is located at by this battery case, and this at least one aircraft interior components comprises a master control board.
Preferably, the surface that this battery case contacts with battery component is provided with at least one guide groove, and the bearing of trend of this at least one guide groove is vertical with the opening direction of this battery case, and the front end of each root guide groove is equipped with a flaring targeting port.
Preferably, this fuselage main body also has connection jaws, and the connection lead of at least one aircraft assembly is connected to the interface of this master control board via this connection jaws, and this at least one aircraft assembly comprises motor and/or LED (light-emitting diode) lamp.
Preferably, the interface of this master control board comprises cradle head control interface, RF (radio frequency) interface and/or USB interface (USB).
Preferably, this fuselage main body also has an antenna opening, and this antenna opening is used for inserting removably to connect for the containment structure of an antenna and fixing this antenna.
Preferably, this fuselage main body also has a wiring lid, and this wiring lid is used for closing this connection jaws, and this connection jaws is located at the bottom of this fuselage main body, and this antenna opening is located at the top of this fuselage main body.
Preferably, this fuselage main body also has a baffle plate, and this baffle plate is positioned at this battery case side, for being separated in outside this battery case by the connection lead of this at least one aircraft assembly.
The setting of baffle plate, makes many connection leads of aircraft be blocked in outside baffle plate, thus is convenient to the plug of battery component.
Preferably, this fuselage lower body part is also provided with one and rises and falls bridge joint mouth, and this alighting gear interface is used for removably fixedly mounting an alighting gear.
Preferably, this alighting gear interface comprises the chute be opened on the left and right sides sidewall of this fuselage lower body part and the positioning groove be connected with this chute, and this chute is for connecting the fixation kit of frame component, and this positioning groove is used for card and establishes this landing gear assembly.
The utility model additionally provides a kind of aircraft comprising airframe structure as above.
Preferably, this aircraft is telecontrolled aircraft.
Positive progressive effect of the present utility model is: the assemblies such as the aircraft in the utility model and airframe structure thereof can fix up an aerial wire easily, battery, and the design of battery case and inner container cavity makes the intraware of aircraft such as master control board etc. rearmountedly to fixedly mount, significantly improve ease for operation and the convenience of aircraft installation.
Accompanying drawing explanation
Fig. 1 is the block diagram at airframe structure one visual angle of aircraft in the utility model one preferred embodiment.
Fig. 2 is the block diagram at another visual angle of airframe structure of aircraft in the utility model one preferred embodiment.
Detailed description of the invention
Lift preferred embodiment below, and come by reference to the accompanying drawings clearlyer intactly the utility model to be described.
Aircraft in the present embodiment is a telecontrolled aircraft, and with reference to (Fig. 1,2 all mainly illustrates the bottom of fuselage main body) figure 1 and Fig. 2 Suo Shi, its airframe structure comprises a fuselage main body.This fuselage main body has the inner container cavity of a battery case 2, an antenna opening, two place's connection jaws 5 and 6, wiring lids, a baffle plate 3, rise and fall bridge joint mouth 4.
Wherein, this battery case 2 be located at this fuselage main body bottom and for set battery assembly, this inner container cavity to be located at inside this battery case and to be positioned at the inside of this fuselage main body, (that is this inner container cavity is used for an accommodating master control board 1, this inner container cavity is located in this master control board 1 place in Fig. 1), the opening of this battery case makes this master control board be able to enter in this inner container cavity via this battery case.In other words, the opening of this battery case is enough large, is able to be positioned over this fuselage body interior by this opening to make master control board.Should be noted that, the offering of this battery case makes the connection lead of motor, LED and some other aircraft assembly directly can be connected to this master control board 1 in this inner container cavity via battery case, aircraft is installed more easily or connects these aircraft assemblies.
Specifically, in the present embodiment, LED and motor are arranged on the machine wall of this airframe structure, and namely LED, motor should lay respectively in fact machine wall place and this inner container cavity place to the two ends of the connection lead of master control board.The machine wall of this airframe structure forms a machine wall cavity in inside while formation fuselage, these connection leads arrive in this inner container cavity through machine wall cavity, battery case and this inner container cavity by the setting position of LED, motor on machine wall successively, finally be connected to the corresponding interface place on this master control board, thus realize the connection of LED, motor and master control board.This just means, any one connection lead is not exposed to this airframe structure outside, simultaneously again to complete the installation of various assembly and connection lead after complete airframe structure machine-shaping again.This makes installation process very convenient, flexible.
But the difference based on the interface of this master control board 1 is arranged, be arranged in this master control board 1 of this inner container cavity part of interface may and be not easy to the connection lead of corresponding aircraft assembly to be connected to this master control board 1 via this battery case.Therefore, the present embodiment is also provided with the connection jaws 5 below fuselage main body, the setting position of this connection jaws 5 makes it the connection lead be convenient to for some assemblies such as motor in gps antenna, fuselage front and passes and be connected to the corresponding interface on this master control board 1, and it also can provide external RF interface.But it should be noted that this connection jaws 5 and 6 is not indispensable only for the realization of the connection of assembly and master control board 1.
Connection jaws 6 near the alighting gear interface being positioned at the right side of this fuselage main body is relatively little, and here connection jaws 6 can be provided as cradle head control interface and the USB interface of this master control board.When the installation of master control board 1 and the connection of part aircraft assembly all complete, here connection jaws 6 is connected to this master control board for The Cloud Terrace under can having completed the prerequisite of the part of installing or connect not affecting these.Meanwhile, this connection jaws 6 be provided as USB interface can greatly facilitate the software system of this aircraft etc. upgrading upgrade and and external device between data transmission.
This antenna opening is used for inserting removably to connect for the containment structure of an antenna and fixing this antenna.The surface that this battery case contacts with battery component is provided with at least one guide groove, and the bearing of trend of this at least one guide groove is vertical with the opening direction of this battery case, and the front end of each root guide groove is equipped with a flaring targeting port.This baffle plate 3 is positioned at this battery case side, for being separated in outside this battery case by the connection lead of this at least one aircraft assembly.
This wiring lid is used for closing connection jaws, and connection jaws is located at the bottom of this fuselage main body, and this antenna opening is located at the top of this fuselage main body.Should be understood that, be only in Fig. 1 and schematically show two place's connection jaws 5 and 6, but the quantity of connection jaws and setting position all can be arranged according to actual needs comparatively flexibly.
This alighting gear interface 4 is positioned at this fuselage lower body part, for removably fixedly mounting an alighting gear.This alighting gear interface specifically comprises the chute be opened on the left and right sides sidewall of this fuselage lower body part and the positioning groove be connected with this chute, and this chute is for connecting the fixation kit of frame component, and this positioning groove is used for card and establishes this landing gear assembly.
Although the foregoing describe detailed description of the invention of the present utility model, it will be understood by those of skill in the art that this is only casehistory, protection domain of the present utility model is defined by the appended claims.Those skilled in the art, under the prerequisite not deviating from principle of the present utility model and essence, can make various changes or modifications to these embodiments, but these change and amendment all falls into protection domain of the present utility model.
Claims (11)
1. the airframe structure of an aircraft, comprise a fuselage main body, it is characterized in that, this fuselage main body has a battery case and an inner container cavity, this battery case is used for set battery assembly, this inner container cavity to be located at inside this battery case and to be positioned at the inside of this fuselage main body, and this inner container cavity is used for accommodating at least one aircraft interior components, and the opening of this battery case makes this at least one aircraft interior components be able to enter in this inner container cavity via this battery case.
2. airframe structure as claimed in claim 1, it is characterized in that, the bottom of this fuselage main body is located at by this battery case, and this at least one aircraft interior components comprises a master control board.
3. airframe structure as claimed in claim 1, it is characterized in that, the surface that this battery case contacts with battery component is provided with at least one guide groove, and the bearing of trend of this at least one guide groove is vertical with the opening direction of this battery case, and the front end of each root guide groove is equipped with a flaring targeting port.
4. airframe structure as claimed in claim 2, it is characterized in that, this fuselage main body also has connection jaws, and the connection lead of at least one aircraft assembly is connected to the interface of this master control board via this connection jaws, and this at least one aircraft assembly comprises motor and/or LED.
5. airframe structure as claimed in claim 4, it is characterized in that, the interface of this master control board comprises cradle head control interface, RF interface and/or USB interface.
6. airframe structure as claimed in claim 1, it is characterized in that, this fuselage main body also has an antenna opening, and this antenna opening is used for inserting removably to connect for the containment structure of an antenna and fixing this antenna.
7. airframe structure as claimed in claim 4, it is characterized in that, this fuselage main body also has wiring lid, and this wiring lid is used for closing this connection jaws, and this connection jaws is located at the bottom of this fuselage main body.
8. airframe structure as claimed in claim 4, it is characterized in that, this fuselage main body also has a baffle plate, and this baffle plate is positioned at this battery case side, for being separated in outside this battery case by the connection lead of this at least one aircraft assembly.
9. airframe structure as claimed in claim 1, is characterized in that, this fuselage lower body part is also provided with one and rises and falls bridge joint mouth, and this alighting gear interface is used for removably fixedly mounting an alighting gear.
10. airframe structure as claimed in claim 9, it is characterized in that, this alighting gear interface comprises the chute be opened on the left and right sides sidewall of this fuselage lower body part and the positioning groove be connected with this chute, this chute is for connecting the fixation kit of frame component, and this positioning groove is used for card and establishes this landing gear assembly.
11. 1 kinds of aircraft, is characterized in that, have as the airframe structure in claim 1-10 as described in any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520208090.3U CN204802064U (en) | 2015-04-08 | 2015-04-08 | Aircraft and fuselage structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520208090.3U CN204802064U (en) | 2015-04-08 | 2015-04-08 | Aircraft and fuselage structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204802064U true CN204802064U (en) | 2015-11-25 |
Family
ID=54586924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520208090.3U Active CN204802064U (en) | 2015-04-08 | 2015-04-08 | Aircraft and fuselage structure thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204802064U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799909A (en) * | 2016-05-04 | 2016-07-27 | 深圳市翰童科技有限公司 | Spliced airplane |
| CN107031841A (en) * | 2016-04-07 | 2017-08-11 | 广州极飞科技有限公司 | Aircraft |
| CN108064209A (en) * | 2017-04-26 | 2018-05-22 | 深圳市大疆创新科技有限公司 | Unmanned vehicle |
| WO2019127394A1 (en) * | 2017-12-29 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Protective cover of unmanned aerial vehicle fuselage, fuselage assembly and unmanned aerial vehicle |
| WO2019140640A1 (en) * | 2018-01-19 | 2019-07-25 | 深圳市大疆创新科技有限公司 | Arm assembly and unmanned aerial vehicle |
| WO2020000644A1 (en) * | 2018-06-26 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and aerial vehicle frame thereof |
-
2015
- 2015-04-08 CN CN201520208090.3U patent/CN204802064U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031841A (en) * | 2016-04-07 | 2017-08-11 | 广州极飞科技有限公司 | Aircraft |
| CN107031841B (en) * | 2016-04-07 | 2024-02-13 | 广州极飞科技股份有限公司 | Aircraft with a plurality of aircraft body |
| CN105799909A (en) * | 2016-05-04 | 2016-07-27 | 深圳市翰童科技有限公司 | Spliced airplane |
| CN108064209A (en) * | 2017-04-26 | 2018-05-22 | 深圳市大疆创新科技有限公司 | Unmanned vehicle |
| WO2019127394A1 (en) * | 2017-12-29 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Protective cover of unmanned aerial vehicle fuselage, fuselage assembly and unmanned aerial vehicle |
| WO2019140640A1 (en) * | 2018-01-19 | 2019-07-25 | 深圳市大疆创新科技有限公司 | Arm assembly and unmanned aerial vehicle |
| WO2020000644A1 (en) * | 2018-06-26 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and aerial vehicle frame thereof |
| CN110896630A (en) * | 2018-06-26 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Unmanned vehicles and frame thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204802064U (en) | Aircraft and fuselage structure thereof | |
| CN204776051U (en) | Unmanned aerial vehicle cabin structure | |
| CN103928789B (en) | There is the instrument of wiring board modular structure | |
| CN106898905A (en) | A kind of electrical box of stabilization terminal position degree | |
| CN106023560A (en) | Folding type unmanned aerial vehicle remote controller | |
| WO2016161975A1 (en) | Aircraft fuselage and aircraft with same | |
| CN209471376U (en) | A kind of UAV Flight Control device and unmanned plane | |
| CN205280110U (en) | A quick -witted case and stage body integral structure for navigating appearance system | |
| CN204164984U (en) | Lighting device | |
| CN205609632U (en) | Exempt from viscose and exempt from battery receiving device of screw | |
| CN106379523B (en) | A kind of modular transport unmanned plane | |
| CN217778983U (en) | Unmanned aerial vehicle | |
| CN204877440U (en) | Skeleton and logging instrument of logging instrument | |
| KR200483105Y1 (en) | Coupling Device For Joint Connector And Earth Terminal | |
| CN202616534U (en) | Connector | |
| CN207543418U (en) | A kind of car body controller protecting box | |
| CN105539857A (en) | Battery clamping structure for unmanned aerial vehicle | |
| CN103733744B (en) | Can from the detachable communication cartridge of device separates and the equipment corresponding with it, assembly and system | |
| CN205122664U (en) | Unmanned aerial vehicle is with intelligent battery fast -assembling module | |
| CN106143867A (en) | Aircraft fuselage and include its aircraft | |
| CN205581737U (en) | Quick detachable computer machine case | |
| CN205525002U (en) | Battery joint structure for unmanned aerial vehicle | |
| CN205124180U (en) | Electric motor car battery management system installs shell | |
| CN205541820U (en) | Double -deck control system of mutual LED display screen | |
| CN208258251U (en) | A kind of airborne signal exchange device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |