CN204965717U - Remote control system - Google Patents
Remote control system Download PDFInfo
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- CN204965717U CN204965717U CN201520592163.3U CN201520592163U CN204965717U CN 204965717 U CN204965717 U CN 204965717U CN 201520592163 U CN201520592163 U CN 201520592163U CN 204965717 U CN204965717 U CN 204965717U
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Abstract
The utility model discloses a remote control system, including aircraft and ground remote control unit, the aircraft includes a GPS module, a height sensor, first master controller, a RF module and a magnetometer, and ground remote control unit includes second master controller, the 2nd RF module and the 2nd GPS module, a GPS module, a height sensor, a RF module and magnetometer respectively with first master controller communication connection, the 2nd RF module and the 2nd GPS module respectively with second master controller communication connection, the second master controller to first master controller sends a control signal who is used for controlling the cloud platform camera lens orientation of aircraft. The utility model discloses can detect high, the position and the relative angle information of remote control unit and aircraft to adjust the cloud platform camera lens direction on the aircraft with this, thereby realize letting cloud platform camera lens all the time facing to the remote controller.
Description
Technical field
The utility model relates to a kind of telechirics.
Background technology
In prior art, although have telepilot to control aircraft, be difficult to realization and allow carry-on platform-lens all the time facing to telepilot, this technical matters becomes this area great difficult problem urgently to be resolved hurrily.
Utility model content
The technical problems to be solved in the utility model is difficult to realize allowing carry-on platform-lens all the time facing to the defect of telepilot to overcome in prior art, provides a kind of telechirics.
The utility model solves above-mentioned technical matters by following technical proposals:
The utility model provides a kind of telechirics, its feature is, comprise aircraft and ground remote controller, described aircraft comprises GPS (GPS) module, the first height sensor, the first primary controller, RF (radio frequency) module and a magnetometer, and described ground remote controller comprises the second primary controller, the 2nd RF module and the second GPS module; Described first GPS module, described first height sensor, a described RF module and described magnetometer communicate to connect with described first primary controller respectively, described 2nd RF module and described second GPS module communicate to connect with described second primary controller respectively, and a described RF module and described 2nd RF module communicate to connect;
Described first primary controller is for obtaining the primary importance signal of the positional information for characterizing described aircraft of described first GPS module generation, and obtain the first altitude signal of the elevation information for characterizing described aircraft that described first height sensor generates, and by a described RF module and described 2nd RF module, described primary importance signal and described first altitude signal are sent to described second primary controller; Described second primary controller is for receiving the second place signal of the positional information for characterizing described ground remote controller of described second GPS module generation;
Described magnetometer relative to described aircraft have one fixing towards, described second primary controller is also for obtaining relative distance between described aircraft and described ground remote controller and relative height, and obtain the direction of described aircraft projection sensing ground remote controller projection and the angle of direct north, and the dead ahead of described aircraft and the angle of direct north, described second primary controller is also for sending one for controlling the control signal in the platform-lens direction of described aircraft by a described RF module and described 2nd RF module to described first primary controller.
Preferably, described ground remote controller also comprises the second height sensor, and described second primary controller is also for receiving the second altitude signal of the elevation information for characterizing described ground remote controller that described second height sensor generates.
Preferably, described first height sensor and described second height sensor are baroceptor.
Preferably, described aircraft also comprises gyroscope, and described gyroscope and described first primary controller communicate to connect.
Positive progressive effect of the present utility model is: the utility model can detect the height of telechiric device and aircraft, position and relative angle information, and regulate carry-on platform-lens direction with this, thus realize allowing platform-lens all the time facing to telepilot, solve the technical barrier that prior art exists.
Accompanying drawing explanation
Fig. 1 is the module diagram of the telechirics of preferred embodiment of the present utility model.
Embodiment
The utility model preferred embodiment is provided, to describe the technical solution of the utility model in detail below in conjunction with accompanying drawing.
As shown in Figure 1, telechirics of the present utility model comprises aircraft 1 and ground remote controller 2, wherein aircraft comprises the first GPS module 11, first height sensor 12, magnetometer 13, RF module 15 and first primary controller 16, and described ground remote controller comprises the second GPS module 21, second height sensor 22, second primary controller 23 and the 2nd RF module 24;
Described first GPS module 11, described first height sensor 12, described magnetometer 13 and a described RF module 15 communicate to connect with described first primary controller 16 respectively, described second GPS module 21, described second height sensor 22, described 2nd RF module 24 communicate to connect with described second primary controller 23 respectively, and a described RF module 15 communicates to connect with described 2nd RF module 24;
Described first GPS module 11 is for generating the primary importance signal of the positional information characterizing described aircraft 1 in real time, and described primary importance signal is sent to described first primary controller 16, described first height sensor 12 characterizes the first altitude signal of the elevation information of described aircraft 1 for life in real time, and described first altitude signal is sent to described first primary controller 16, described primary importance signal and described first altitude signal are sent to described second primary controller 23 by a described RF module 15 and described 2nd RF module 24 by described first primary controller 16;
Described second GPS module 21 is for generating the second place signal of the positional information characterizing described ground remote controller 2 in real time, and described second height sensor 22 is for generating the second altitude signal of the elevation information characterizing described ground remote controller 2 in real time; Described second primary controller 23 is for receiving described second place signal and described second altitude signal;
Described second primary controller 23 can obtain relative distance between described aircraft 1 and described ground remote controller 2 and relative height according to described primary importance signal, the second altitude signal, second place signal, the second altitude signal; Described magnetometer 13 relative to described aircraft 1 have one fixing towards, preferably, the dead ahead of magnetometer 13 fixed directional aircraft 1, thus the second primary controller 23 can obtain the dead ahead of aircraft 1 and the angle β (0-360 °) of direct north, in addition, described second primary controller 23 also points to the direction of ground remote controller 2 projection and the angle α (0-360 °) of direct north for obtaining the projection of described aircraft 1;
According to α and β, described second primary controller 23 is also for sending one for controlling the control signal in the platform-lens direction of described aircraft 1 to described first primary controller 16, now α=β, thus achieve and allow the platform-lens direction of aircraft 1 point to described ground remote controller 2. all the time
In the utility model, described first height sensor 12 and described second height sensor 22 are baroceptor, and in addition, described aircraft 1 also comprises gyroscope 14, and described gyroscope 14 communicates to connect with described first primary controller 16.
Although the foregoing describe embodiment of the present utility model, it will be understood by those of skill in the art that these only illustrate, 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 (4)
1. a telechirics, it is characterized in that, comprise aircraft and ground remote controller, described aircraft comprises the first GPS module, the first height sensor, the first primary controller, RF module and a magnetometer, and described ground remote controller comprises the second primary controller, the 2nd RF module and the second GPS module; Described first GPS module, described first height sensor, a described RF module and described magnetometer communicate to connect with described first primary controller respectively, described 2nd RF module and described second GPS module communicate to connect with described second primary controller respectively, and a described RF module and described 2nd RF module communicate to connect;
Described first primary controller is for obtaining the primary importance signal of the positional information for characterizing described aircraft of described first GPS module generation, and obtain the first altitude signal of the elevation information for characterizing described aircraft that described first height sensor generates, and by a described RF module and described 2nd RF module, described primary importance signal and described first altitude signal are sent to described second primary controller; Described second primary controller is for receiving the second place signal of the positional information for characterizing described ground remote controller of described second GPS module generation;
Described magnetometer relative to described aircraft have one fixing towards, described second primary controller is also for obtaining relative distance between described aircraft and described ground remote controller and relative height, and obtain the direction of described aircraft projection sensing ground remote controller projection and the angle of direct north, and the dead ahead of described aircraft and the angle of direct north, described second primary controller is also for sending one for controlling the control signal in the platform-lens direction of described aircraft by a described RF module and described 2nd RF module to described first primary controller.
2. telechirics as claimed in claim 1, it is characterized in that, described ground remote controller also comprises the second height sensor, and described second primary controller is also for receiving the second altitude signal of the elevation information for characterizing described ground remote controller that described second height sensor generates.
3. telechirics as claimed in claim 2, it is characterized in that, described first height sensor and described second height sensor are baroceptor.
4. telechirics as claimed in claim 1, it is characterized in that, described aircraft also comprises gyroscope, and described gyroscope and described first primary controller communicate to connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520592163.3U CN204965717U (en) | 2015-08-03 | 2015-08-03 | Remote control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520592163.3U CN204965717U (en) | 2015-08-03 | 2015-08-03 | Remote control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204965717U true CN204965717U (en) | 2016-01-13 |
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| CN201520592163.3U Active CN204965717U (en) | 2015-08-03 | 2015-08-03 | Remote control system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3538970A4 (en) * | 2016-12-15 | 2020-04-01 | Powervision Robot Inc. | Control system and method for drone with remote controller |
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2015
- 2015-08-03 CN CN201520592163.3U patent/CN204965717U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3538970A4 (en) * | 2016-12-15 | 2020-04-01 | Powervision Robot Inc. | Control system and method for drone with remote controller |
| US11275390B2 (en) | 2016-12-15 | 2022-03-15 | Powervision Robot Inc. | Control system and method for drone with remote controller |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160721 Address after: Jinxi town foxlink Kunshan road 215324 Suzhou City, Jiangsu province No. 388 Patentee after: KUNSHAN YOUNI ELECTRIC ENERGY SPORTS TECHNOLOGY CO., LTD. Address before: Hongkong Hongguang Road, Kowloon Bay China billion centre 10 floor Patentee before: You Li Science and Technology Ltd. |