CN206050099U - A kind of multi-rotor aerocraft system for testing stability - Google Patents
A kind of multi-rotor aerocraft system for testing stability Download PDFInfo
- Publication number
- CN206050099U CN206050099U CN201620746028.4U CN201620746028U CN206050099U CN 206050099 U CN206050099 U CN 206050099U CN 201620746028 U CN201620746028 U CN 201620746028U CN 206050099 U CN206050099 U CN 206050099U
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- China
- Prior art keywords
- force transducer
- outfan
- main control
- rotor aerocraft
- control chip
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- 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.)
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Abstract
The utility model discloses a kind of multi-rotor aerocraft system for testing stability, including structure-steel framing, the bottom of the structure-steel framing is provided with lithium battery, the middle setting of the structure-steel framing has main control chip, Bluetooth communication modules, wireless WiFi transport modules, several are provided with the top of the structure-steel framing and fix motor folder, the bottom of the fixed motor folder is respectively provided with force sensor A, force transducer B, force transducer C, force transducer D, the outfan of the force transducer A, the outfan of the force transducer B, the outfan of the force transducer C, the outfan of the force transducer D, the lithium battery is connected with the input of the main control chip respectively, switch is additionally provided between the lithium battery and the main control chip；Inlay respectively and be provided with high definition touch display screen, physical button, light emitting diode, buzzer warning module in the outside of the structure-steel framing.This utility model can be adjusted, be corrected and assess the attitude stability of aircraft.
Description
Technical field
This utility model is related to a kind of multi-rotor aerocraft system for testing stability, belongs to technology of instrument and meter field.
Background technology
With developing rapidly for civilian multi-rotor aerocraft, ordinary people can also buy various by all means
Business or the multi-rotor aerocraft of self assembly.At the same time, air crash, the property loss of reduction people how is prevented to be exactly one heavy
The research project wanted.And it is at present existing mostly simply the frame for movement of aircraft is optimized, and most of accidents be by
Power System of Flight Vehicle is incorrect with remote control systems setting to be caused, and changes structure and sending out for air crash accident can not be solved from source
It is raw.If a kind of device can be before multi-rotor aerocraft takes off, the dynamical system, remote control systems to aircraft carries out ground
Or the flight detection of interior, the flight attitude of calculating simulation aircraft, and show that being convenient for people to adjustment observes on screen,
The state of flight of aircraft, adjustment countermeasures so not only can be changed in real time, and can reduce the accident rate of aircraft,
Reduce loss.Such invention and product are not found through inquiry, based on this utility model presented above.
Utility model content
The purpose of this utility model is the defect for overcoming prior art to exist, and solves above-mentioned technical problem, there is provided a kind of
Multi-rotor aerocraft system for testing stability, adjusts, corrects and assess the attitude stability of aircraft, so as to fundamentally with this
The risk of the air crash in the flight of aircraft open air is reduced, the safety of aircraft, reliability is improved.
This utility model is adopted the following technical scheme that：A kind of multi-rotor aerocraft system for testing stability, it is characterised in that
Including structure-steel framing, the bottom of the structure-steel framing is provided with lithium battery, and the middle setting of the structure-steel framing has main control chip, bluetooth to pass
Defeated module, wireless WiFi transport modules, are provided with several and fix motor folder, the fixed motor folder at the top of the structure-steel framing
Bottom be respectively provided with force sensor A, force transducer B, force transducer C, force transducer D, the output of the force transducer A
End, the outfan of the force transducer B, the outfan of the force transducer C, the outfan of the force transducer D, lithium electricity
Pond is connected with the input of the main control chip respectively, and switch is additionally provided between the lithium battery and the main control chip；
The outside of the structure-steel framing is inlayed respectively and is provided with high definition touch display screen, physical button, light emitting diode, buzzer warning module,
The outfan of the physical button is connected with the main control chip input, the outfan of the main control chip respectively with it is described
Light emitting diode, the buzzer warning module are connected, the main control chip respectively with the Bluetooth communication modules, the nothing
Mould is transmitted in line WiFi transport modules, the two-way cascade of the high definition touch display screen, the Bluetooth communication modules, the wireless WiFi
The external computer host computer of block.
Preferably, lithium battery adopt voltage for 3S 11.1V lithium battery.
Preferably, switch is using the microswitch for touching self-locking.
Preferably, main control chip adopts stm32f4 single-chip microcomputers.
Preferably, high definition touch display screen adopts 3.5 cun of TFT liquid crystal touch display screens, for showing current force transducer
A, force transducer B, force transducer C and lift, the dump energy of lithium battery, flying by lift generation detected by force transducer D
Row state and its 3D view.
Preferably, light emitting diode is arranged at the lower section of high definition touch display screen, and test system is indicated for sending HONGGUANG
System whether normal work.
Preferably, buzzer warning module adopts buzzer, for flight hazard alarm.
Preferably, model HC-05 of Bluetooth communication modules.
Preferably, physical knob works as test system reset key and closing key.
The beneficial effect reached by this utility model：（1）The present invention solves existing multi-rotor aerocraft practical flight appearance
State is difficult to the problem of simulating, verifying；（2）Not only can indoor on-line debugging aircraft reality flight attitude, and pass through 3D
The outdoor flight attitude of the real-time calculating simulation current aircraft of mode of image, adjusts, corrects and assess the appearance of aircraft with this
State stability；（3）The present invention fundamentally reduces the risk of the air crash in the flight of aircraft open air, improves the safety of aircraft
Property, reliability.
Description of the drawings
Fig. 1 is circuit connection block diagram of the present utility model.
Fig. 2 is structural representation of the present utility model.
Fig. 3 is the analog information schematic diagram of computer host computer of the present utility model.
The implication of labelling in figure：1- structure-steel framings, 2- fix motor folder, 3- force transducer A, 4- force transducer B, 5- power sensing
Device C, 6- force transducer D, 7- main control chips, 8- physical buttons, 9- buzzer warning modules, 10- light emitting diodes, 11- high definitions
Touch display screen, 12- lithium batteries.
Specific embodiment
Below in conjunction with the accompanying drawings this utility model is further described.Following examples are only used for clearly illustrating this
The technical scheme of utility model, and protection domain of the present utility model can not be limited with this.
Fig. 1 is circuit connection block diagram of the present utility model.Fig. 2 is structural representation of the present utility model.The present invention is proposed
A kind of multi-rotor aerocraft system for testing stability, it is characterised in that including structure-steel framing 1, the bottom of structure-steel framing 1 is provided with lithium electricity
There are main control chip 7, Bluetooth communication modules, wireless WiFi transport modules, the top of structure-steel framing 1 in pond 12, the middle setting of structure-steel framing 1
It is provided with several and fixes motor folder 2, the motor that fixed motor folder 2 clamps aircraft to be measured is detected, fixed motor folder 2
Bottom be respectively provided with force sensor A3, force transducer B4, force transducer C5, force transducer D6, the output of force transducer A3
End, the outfan of force transducer B4, the outfan of force transducer C5, the outfan of force transducer D6, lithium battery 12 respectively with master
The input of control chip 7 is connected, and switch is additionally provided between lithium battery 12 and main control chip 7；Inlay respectively in the outside of structure-steel framing 1
It is provided with high definition touch display screen 11, physical button 8, light emitting diode 10, buzzer warning module 9, the outfan of physical button 8
Be connected with 7 input of main control chip, the outfan of main control chip 7 respectively with light emitting diode 10,9 phase of buzzer warning module
Connection, main control chip 7 respectively with Bluetooth communication modules, wireless WiFi transport modules, the 11 two-way cascade of high definition touch display screen, it is blue
The external computer host computer of tooth transport module, wireless WiFi transport modules.
Wherein, structure-steel framing 1 is all parts for fixing in whole test system and fixed needs assessment detection
Aircraft, it is possible to prevent the device of aircraft takeoff；Force transducer A3, force transducer B4, force transducer C5, force transducer D6
For perceiving the lift size of each rotor, and the data for collecting are passed to into main control chip 7；
Used as a kind of preferred embodiment, lithium battery 12 adopts voltage for the lithium battery of the 11.1V of 3S, for whole survey
Test system is powered.
Used as a kind of preferred embodiment, switch is powered for whole test system using the microswitch for touching self-locking
Cut-out or opening.
Used as a kind of preferred embodiment, main control chip 7 adopts stm32f4 single-chip microcomputers, for processing all of system letter
Breath, controls the normal operation of whole test system.
Used as a kind of preferred embodiment, high definition touch display screen 11 adopts 3.5 cun of TFT liquid crystal touch display screens, is used for
Show the residue electricity of current force transducer A, force transducer B, force transducer C and lift, lithium battery 12 detected by force transducer D
Amount, the state of flight produced by lift and its 3D view.
Used as a kind of preferred embodiment, light emitting diode 10 is arranged at the lower section of high definition touch display screen 11, for sending out
Go out HONGGUANG to indicate test system whether normal work.
Used as a kind of preferred embodiment, buzzer warning module 9 adopts buzzer, for flight hazard alarm, when four
Individual fixed motor is risen after force parameter exceedes certain threshold value, then buzzer warning.
As a kind of preferred embodiment, model HC-05 of Bluetooth communication modules, as serial communication equipment and computer
Host computer carries out serial communication；The flight attitude of simulation is sent to computer as graphic transmission equipment by wireless WiFi transport modules
Host computer is processed and is shown.
The reset key worked as test system as a kind of preferred embodiment, physical knob 8 and closing key.
Fig. 3 is the analog information schematic diagram of computer host computer of the present utility model.The content of display includes current power sensing
Motor lift detected by device A, force transducer B, force transducer C and force transducer D, battery electric quantity, flight attitude, setting
Wind speed is arranged, wind direction is arranged, bluetooth is arranged, WiFi is arranged, and final stability assessment report.
The present invention is based on existing electronic technology, solves existing multi-rotor aerocraft practical flight attitude and is difficult to emulation and tests
The problem of card.Its remarkable advantage, not only can indoor on-line debugging aircraft reality flight attitude, and pass through 3D rendering
The real-time calculating simulation current aircraft of mode outdoor flight attitude, the attitude for being adjusted with this, being corrected and assess aircraft is steady
It is qualitative.So as to fundamentally reduce the risk of the air crash in the flight of aircraft open air, the safety of aircraft, reliability are improved.
The above is only preferred implementation of the present utility model, it is noted that for the common skill of the art
For art personnel, on the premise of without departing from this utility model know-why, some improvement and deformation can also be made, these change
Enter and deform also to should be regarded as protection domain of the present utility model.
Claims (9)
1. a kind of multi-rotor aerocraft system for testing stability, it is characterised in that including structure-steel framing (1), the structure-steel framing (1)
Bottom is provided with lithium battery (12), and the middle setting of the structure-steel framing (1) has main control chip (7), Bluetooth communication modules, wireless
WiFi transport modules, are provided with several and fix motor folder (2) at the top of the structure-steel framing (1), fixed motor folder (2)
Bottom is respectively provided with force sensor A (3), force transducer B (4), force transducer C (5), force transducer D (6), the power sensing
The outfan of device A (3), the outfan of the force transducer B (4), the outfan of the force transducer C (5), the force transducer
The outfan of D (6), the lithium battery (12) are connected with the input of the main control chip (7) respectively, the lithium battery (12)
Switch is additionally provided between the main control chip (7)；Inlay respectively and be provided with high definition touch display screen in the outside of the structure-steel framing (1)
(11), physical button (8), light emitting diode (10), buzzer warning module (9), the outfan of the physical button (8) and institute
State main control chip (7) input to be connected, the outfan of the main control chip (7) respectively with the light emitting diode (10), institute
State buzzer warning module (9) to be connected, the main control chip (7) respectively with the Bluetooth communication modules, the wireless WiFi
Transport module, the two-way cascade of the high definition touch display screen (11), the Bluetooth communication modules, the wireless WiFi transport modules
External computer host computer.
2. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the lithium battery
(12) voltage is adopted for the lithium battery of the 11.1V of 3S.
3. according to a kind of arbitrary described multi-rotor aerocraft system for testing stability of claim 1 or 2, it is characterised in that institute
Switch is stated using the microswitch for touching self-locking.
4. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the master control core
Piece (7) is using stm32f4 single-chip microcomputers.
5. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the high definition is touched
Display screen (11) is touched using 3.5 cun of TFT liquid crystal touch display screens, for showing current force transducer A, force transducer B, power sensing
Device C and lift detected by force transducer D, the dump energy of lithium battery (12), the state of flight produced by the lift and
Its 3D view.
6. a kind of multi-rotor aerocraft system for testing stability according to claim 5, it is characterised in that described luminous two
Pole pipe (10) is arranged at the lower section of the high definition touch display screen (11), the test system is indicated for sending HONGGUANG whether
Normal work.
7. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the buzzer
Alarm module (9) adopts buzzer, for flight hazard alarm.
8. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the bluetooth is passed
Model HC-05 of defeated module.
9. a kind of multi-rotor aerocraft system for testing stability according to claim 1, it is characterised in that the physics is pressed
Reset key and closing key that button (8) works as the test system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620746028.4U CN206050099U (en) | 2016-07-14 | 2016-07-14 | A kind of multi-rotor aerocraft system for testing stability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620746028.4U CN206050099U (en) | 2016-07-14 | 2016-07-14 | A kind of multi-rotor aerocraft system for testing stability |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206050099U true CN206050099U (en) | 2017-03-29 |
Family
ID=58377333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620746028.4U Expired - Fee Related CN206050099U (en) | 2016-07-14 | 2016-07-14 | A kind of multi-rotor aerocraft system for testing stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206050099U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107117330A (en) * | 2017-04-14 | 2017-09-01 | 安徽大学 | flight controller parameter adjusting and detecting device |
| CN109466796A (en) * | 2018-12-30 | 2019-03-15 | 东北农业大学 | The unmanned plane tensile test platform of low current alarm |
-
2016
- 2016-07-14 CN CN201620746028.4U patent/CN206050099U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107117330A (en) * | 2017-04-14 | 2017-09-01 | 安徽大学 | flight controller parameter adjusting and detecting device |
| CN107117330B (en) * | 2017-04-14 | 2020-04-28 | 安徽大学 | Flight controller parameter adjusting and detecting device |
| CN109466796A (en) * | 2018-12-30 | 2019-03-15 | 东北农业大学 | The unmanned plane tensile test platform of low current alarm |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170329 Termination date: 20190714 |