CN205602106U - Embedded four shaft air vehicle experimental apparatus - Google Patents
Embedded four shaft air vehicle experimental apparatus Download PDFInfo
- Publication number
- CN205602106U CN205602106U CN201620095319.1U CN201620095319U CN205602106U CN 205602106 U CN205602106 U CN 205602106U CN 201620095319 U CN201620095319 U CN 201620095319U CN 205602106 U CN205602106 U CN 205602106U
- Authority
- CN
- China
- Prior art keywords
- module
- aircraft
- sensor module
- control circuit
- wireless
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to the technical field of the aircraft technique and specifically relates to an embedded four shaft air vehicle experimental apparatus, including the aircraft, accessories and remote control ware, the aircraft includes first control circuit board and four rotors that are used for the VTOL, the first control circuit board includes microcontroller, the power modul, the angle sensor module, the angular velocity sensor module, electromotor drive module and wireless receiving module, the wireless module that connects, the angle sensor module, angular velocity sensor module and electromotor drive module all are connected with microcontroller, through wireless transmitting module and wireless receiving intermodule wireless connection between aircraft and remote controller. The utility model discloses have a plurality of rotors, a plurality of rotors can promote the power of taking off of aircraft, through the regulation and control between each rotor, can ensure the stability of aircraft, and the hardware of aircraft is miniature in addition, can alleviate aircraft self weight, reduces the energy resource consumption, has very strong practicality simultaneously.
Description
Technical field
This utility model relates to vehicle technology field, especially a kind of built-in type 4 axis air vehicle experimental device.
Background technology
Intelligence built-in type 4 axis aircraft is typical embedded product, and its core technology mainly includes embedded technology, automatic control technology, computer technology, Aircraft flight dynamics, disc-shaped flying craft half independent flight control system.Owing to using disc-shaped flying craft, owing to employing multiple rotor, property difference is not only existed between rotor, and there is disturbance each other, it is a system extremely dissipated, is simultaneously introduced angular transducer and angular rate gyroscope attitude stabilization inner looping the most in the controls, on the one hand intelligence built-in type 4 axis aircraft has multiple rotor, on the other hand belong to minute vehicle, there is the biggest difference with conventional aircraft, and at present the minute vehicle under low reynolds number be there is no mathematical model.
Utility model content
This utility model purpose is to overcome deficiency of the prior art, it is provided that a kind of built-in type 4 axis air vehicle experimental device.
In order to solve above-mentioned technical problem, this utility model is to be achieved through the following technical solutions:
A kind of built-in type 4 axis air vehicle experimental device, including aircraft, auxiliary accessories and remote controller, described aircraft includes first control circuit plate and four rotors for VTOL, described first control circuit plate includes microcontroller, power module, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module, described wireless connection module, angle-sensor module, angular-rate sensor module and motor drive block are all connected with microcontroller, described power module is respectively microcontroller, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module provide electric energy；
Described remote controller includes second control circuit plate, described second control circuit plate includes that wireless transmitter module, display screen, function button, display lamp, on & off switch and port, described aircraft are connected by wireless telecommunications between wireless transmitter module and wireless receiving module with between remote controller.
Preferably, being additionally provided with set of cells in described remote controller, described set of cells provides power supply for second control circuit plate.
Preferably, described first control circuit plate is additionally provided with, motor main switch, the first debugging mouth and first download mouth.
Preferably, described port includes the second debugging mouth, the second download mouth and USB interface.
Preferably, described auxiliary accessories includes TTL serial ports, charger and downloader.
Owing to using technique scheme, there is multiple rotor in this utility model, multiple rotors can promote the power of taking off of aircraft, by the regulation and control between each rotor, can ensure that the stability of aircraft, additionally the hardware of aircraft is miniature, can alleviate aircraft own wt, reduces energy resource consumption, so needing to use volume little, the components and parts of light weight, and as much as possible improve level of integrated system, there is the strongest practicality simultaneously.
Accompanying drawing explanation
Fig. 1 is structure schematic diagram of the present utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail, but the multitude of different ways that this utility model can be defined by the claims and cover is implemented.
As shown in Figure 1, including aircraft 1, auxiliary accessories and remote controller, described aircraft 1 includes first control circuit plate 2 and four rotors 3 for VTOL, described first control circuit plate 2 includes that microcontroller, power module, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module, described wireless connection module, angle-sensor module, angular-rate sensor module and motor drive block are all connected with microcontroller.
The major function of microcontroller is by the telecommand received, angle information and angle rate signal, through PID and fuzzy control operation, draws motor drive block control rate, exports and drive motor in the way of PWM.Owing to aircraft space is limited, it is contemplated that easy for installation.
Power module is respectively microcontroller, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module and provides electric energy；The main voltage provided has 2.5V, 3.3V, 5.O V and 7.5V, wherein 2.5V voltage provides power supply for signal amplifier, 3.3V provides power supply for microcontroller, 5.0V provides power supply for angle-sensor module and angular-rate sensor module and wireless receiving module, and 7.5V provides power supply for motor drive block.
Described remote controller includes second control circuit plate, described second control circuit plate includes wireless transmitter module, display screen, function button, display lamp, on & off switch and port, described aircraft is connected by wireless telecommunications between wireless transmitter module and wireless receiving module 9 with between remote controller, wherein display screen can show simulated flight interface, can be shown that relevant parameter.
Wireless receiving module is mainly used to realize the remote operating of people, and having the signal of four passages, respectively aircraft 1 provides lifting, Qian Houfei, left and right fly and rotate instruction.In order to improve degree of intelligence and the operability of aircraft, therefore be aircraft setting angle sensor assembly as gesture feedback sensor, the angle signal collected by angle-sensor module, aircraft 1 current pose can be perceived, and compare with targeted attitude, form closed loop control.Owing to four oar disc-shaped flying crafts 1 are systems extremely dissipated, for improving its flight stability, therefore add angular rate gyroscope feedback loop.
Further, being additionally provided with set of cells in described remote controller, described set of cells provides power supply for second control circuit plate.
Further, described first control circuit plate is additionally provided with motor main switch, the first debugging mouth and first downloads mouth；First debugging mouth and first is downloaded mouth and is used for transmitting data.
Further, described port includes the second debugging mouth, the second download mouth and USB interface, and wherein the second debugging mouth, the second download mouth and USB interface are also used for transmitting data.
Further, described auxiliary accessories includes TTL serial ports, charger and downloader, and downloader can be by the download program of setting on the first control circuit plate 2 of aircraft 1.
The foregoing is only preferred embodiment of the present utility model; not thereby the scope of the claims of the present utility model is limited; every equivalent structure utilizing this utility model description and accompanying drawing content to be made or equivalence flow process conversion; or directly or indirectly it is used in other relevant technical fields, the most in like manner it is included in scope of patent protection of the present utility model.
Claims (5)
1. a built-in type 4 axis air vehicle experimental device, including aircraft, auxiliary accessories and remote controller, it is characterized in that: described aircraft includes first control circuit plate and four rotors for VTOL, described first control circuit plate includes microcontroller, power module, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module, described wireless connection module, angle-sensor module, angular-rate sensor module and motor drive block are all connected with micro-control module, described power module is respectively microcontroller, angle-sensor module, angular-rate sensor module, motor drive block and wireless receiving module provide electric energy；
Remote controller includes second control circuit plate, described second control circuit plate includes that wireless transmitter module, display screen, function button, display lamp, on & off switch and port, described aircraft are connected by wireless telecommunications between wireless transmitter module and wireless receiving module with between remote controller.
A kind of built-in type 4 axis air vehicle experimental device the most according to claim 1, it is characterised in that: being additionally provided with set of cells in described remote controller, described set of cells provides power supply for second control circuit plate.
A kind of built-in type 4 axis air vehicle experimental device the most according to claim 1, it is characterised in that: be additionally provided with on described first control circuit plate, motor main switch, the first debugging mouth and first download mouth.
A kind of built-in type 4 axis air vehicle experimental device the most according to claim 1, it is characterised in that: described port includes the second debugging mouth, the second download mouth and USB interface.
A kind of built-in type 4 axis air vehicle experimental device the most according to claim 1, it is characterised in that: described auxiliary accessories includes TTL serial ports, charger and downloader.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620095319.1U CN205602106U (en) | 2016-01-29 | 2016-01-29 | Embedded four shaft air vehicle experimental apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620095319.1U CN205602106U (en) | 2016-01-29 | 2016-01-29 | Embedded four shaft air vehicle experimental apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205602106U true CN205602106U (en) | 2016-09-28 |
Family
ID=56961404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620095319.1U Expired - Fee Related CN205602106U (en) | 2016-01-29 | 2016-01-29 | Embedded four shaft air vehicle experimental apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205602106U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394892A (en) * | 2016-12-07 | 2017-02-15 | 四川天辰智创科技有限公司 | Unmanned aerial vehicle |
-
2016
- 2016-01-29 CN CN201620095319.1U patent/CN205602106U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394892A (en) * | 2016-12-07 | 2017-02-15 | 四川天辰智创科技有限公司 | Unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105573333B (en) | A kind of modular control method for quadrotor | |
| CN205787904U (en) | Many rotor wing unmanned aerial vehicles flight control system based on STM32 | |
| CN105204514A (en) | Novel tilt-rotor unmanned aerial vehicle attitude control system | |
| CN206515700U (en) | A kind of UAV Flight Control System based on smart mobile phone | |
| CN106994874B (en) | It is suspended and is promoted and the dual-purpose intelligent walking-replacing tool of ground roll-out based on wind-force | |
| CN102814047A (en) | Autonomous return system and control method of dual-rotor remote-controlled model helicopter | |
| CN105045282A (en) | Control system of aircraft | |
| CN204355273U (en) | A kind of SCM Based multifunction micro four-axle aircraft | |
| CN205602106U (en) | Embedded four shaft air vehicle experimental apparatus | |
| CN204973065U (en) | Four rotor crafts of miniature | |
| CN205353763U (en) | A modular control panel for four rotor crafts | |
| CN204078068U (en) | A kind of four-axle aircraft of overlength flying power | |
| CN204832744U (en) | Stabilizer suitable for motion is shot | |
| CN107458593B (en) | Duct propulsion system based on multi-rotor unmanned aerial vehicle | |
| CN105700535B (en) | A kind of modular control panel for quadrotor | |
| CN205212736U (en) | Many machine controller of integrated form and many motor system | |
| CN107526361A (en) | A kind of built-in type 4 axis air vehicle experimental device | |
| CN205229807U (en) | Four miniature wing aircraft based on control model is felt to body | |
| CN208307006U (en) | A kind of sudden strain of a muscle word unmanned plane | |
| CN205190293U (en) | Projecting apparatus radiator fan control system | |
| CN203714175U (en) | Intelligent controller for aerial photograph aircraft | |
| CN210521767U (en) | Four shaft air vehicle based on remote control gloves are controlled | |
| CN210500286U (en) | Single-ball balance mobile robot | |
| CN106927028A (en) | Lift oar separates the electronic multiple wing unmanned plane dynamic structure of layout with gesture stability oar | |
| CN201729270U (en) | Electric screw pitch changing device for screw propeller-driven unmanned aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160928 Termination date: 20190129 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |