CN205333865U - Unmanned aerial vehicle with redundant navigation feature - Google Patents
Unmanned aerial vehicle with redundant navigation feature Download PDFInfo
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- CN205333865U CN205333865U CN201520495355.2U CN201520495355U CN205333865U CN 205333865 U CN205333865 U CN 205333865U CN 201520495355 U CN201520495355 U CN 201520495355U CN 205333865 U CN205333865 U CN 205333865U
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Abstract
The utility model relates to an unmanned aerial vehicle with redundant navigation feature, include: driving system, the integrated navigation system that two sets of structures are the same who links to each other with processor module, integrated navigation system includes: inertial navigation system, GPS positioning system, inertial navigation system includes: accelerometer, gyroscope, it links to each other with corresponding modulate circuit respectively, and the output of each modulate circuit is continuous with processor module through two way analog switch, AD module, and two way analog switch's control end links to each other with processor module's control output, GPS positioning system includes, GPS receiving module, this GPS receiving module pass through the serial ports and link to each other with processor module.
Description
The application is divisional application, the application number of original application: 2015202036718, title: a kind of unmanned aerial vehicle with redundancy navigation feature, the applying date: 2015-04-07。
Technical field
This utility model relates to unmanned aerial vehicle field。
Background technology
The self-navigation of unmanned aerial vehicle controls there are two kinds of realization means, and one is INS (inertial navigation system), and another kind is to adopt system GPS(global positioning satellite system)；But aircraft is in flight course, navigation is just in case going wrong, and aircraft is easily lost, and causes unnecessary loss, in order to avoid the problem causing aircraft to lose due to fault of navigating。
Utility model content
The purpose of this utility model is to provide a kind of unmanned aerial vehicle with redundancy navigation feature, to solve the technical problem owing to navigation fault causes aircraft to lose。
In order to solve above-mentioned technical problem, this utility model provides a kind of unmanned aerial vehicle with redundancy navigation feature, including: for driving the dynamical system of unmanned aerial vehicle, the integrated navigation system identical with two groups of structures that processor module is connected, described integrated navigation system includes: inertial navigation system, GPS alignment system, described inertial navigation system includes: accelerometer, gyroscope, described accelerometer, gyroscope is connected with corresponding modulate circuit respectively, and the outfan of each modulate circuit is by two path analoging switch, A/D module is connected with processor module, the end that controls of described two path analoging switch is connected with the control output end of processor module；Described GPS alignment system includes, GPS receiver module, and this GPS receiver module is connected with processor module by serial ports；Described processor module is also connected with the memory module of storage cruise map；Being additionally provided with touch screen on the fuselage of described unmanned aerial vehicle, this touch screen is connected with processor module, to input control instruction；And described processor module is also connected with on-air radio transceiver module, and it is connected with ground control station by on-air radio transceiver module。
The dynamical system of described unmanned aerial vehicle, described integrated navigation system adopt hydrogen fuel cell as power supply。
Further, described processor module is also connected with image collecting device, and is suitable to be stored view data by memory module, and/or is sent to ground control station by on-air radio transceiver module。
Further, described on-air radio transceiver module includes: WiFi module and CDMA module, and described WiFi module is connected with processor module respectively with CDMA module。
The beneficial effects of the utility model are, the unmanned aerial vehicle with redundancy navigation feature of the present utility model, it can be prevented effectively from owing to navigation fault causes aircraft to lose by two groups of integrated navigation systems, and respectively group integrated navigation system includes inertial navigation system, GPS alignment system respectively, and achieve by two kinds navigate advantage combine together, improve navigation accuracy, in conjunction with airborne map, it is achieved that autonomous cruise function；This utility model can set that cruise route also by touch screen and checks corresponding data, offers convenience to use。
Accompanying drawing explanation
Below in conjunction with drawings and Examples, this utility model is further illustrated。
Fig. 1 is the theory diagram of unmanned aerial vehicle of the present utility model。
Detailed description of the invention
As shown in Figure 1, a kind of unmanned aerial vehicle with redundancy navigation feature of the present utility model, including: for driving the dynamical system of unmanned aerial vehicle, the integrated navigation system identical with two groups of structures that processor module is connected, described integrated navigation system includes: inertial navigation system, GPS alignment system, described inertial navigation system includes: accelerometer, gyroscope, described accelerometer, gyroscope is connected with corresponding modulate circuit respectively, and the outfan of each modulate circuit is by two path analoging switch, A/D module is connected with processor module, the end that controls of described two path analoging switch is connected with the control output end of processor module；Described GPS alignment system includes, GPS receiver module, and this GPS receiver module is connected with processor module by serial ports；Described processor module is also connected with the memory module of storage cruise map；Being additionally provided with touch screen on the fuselage of described unmanned aerial vehicle, this touch screen is connected with processor module, to input control instruction；And described processor module is also connected with on-air radio transceiver module, and it is connected with ground control station by on-air radio transceiver module。
Concrete, this unmanned aerial vehicle not only overcomes INS and easily produces offset error, and error infinitely becomes big defect, also overcome GPS output speed slow, and due to weather, the defect that the intermittent signal that the reasons such as position cause is lost, has merged both advantages, it is ensured that unmanned aerial vehicle autonomous cruise；And by two groups of integrated navigation systems, it is to avoid owing to navigation fault causes the phenomenon that aircraft loses, it is also possible to by the cruise memory module of map of touch screen and storage, unmanned plane is directly set flight path。
Described processor module is also connected with image collecting device, and is suitable to be stored view data by memory module, and/or is sent to ground control station by on-air radio transceiver module, to realize the unmanned aerial vehicle acquisition function to ground data。Described on-air radio transceiver module includes: 2G module (or 3G or 4G module), WiFi module and the CDMA module being connected with processor module。Described processor module is such as but not limited to adopting S3C2440 embedded chip。
The dynamical system of described unmanned aerial vehicle, described integrated navigation system adopt hydrogen fuel cell as power supply。
Being provided with thin-film solar cells on the wing of unmanned aerial vehicle, thin-film solar cells is for powering to the dynamical system of described unmanned aerial vehicle, described integrated navigation system。
Claims (1)
1. a unmanned aerial vehicle with redundancy navigation feature, it is characterised in that including:
Dynamical system, the integrated navigation system identical with two groups of structures that processor module is connected, described integrated navigation system includes: inertial navigation system, GPS alignment system,
Described inertial navigation system includes: accelerometer, gyroscope, described accelerometer, gyroscope are connected with corresponding modulate circuit respectively, and the outfan of each modulate circuit is connected with processor module by two path analoging switch, A/D module, the control end of described two path analoging switch is connected with the control output end of processor module；
Described GPS alignment system includes, GPS receiver module, and this GPS receiver module is connected with processor module by serial ports；Described processor module is also connected with the memory module of storage cruise map；Being additionally provided with touch screen on the fuselage of described unmanned aerial vehicle, this touch screen is connected with processor module；
Described processor module is also connected with image collecting device, and is suitable to be stored view data by memory module, and/or is sent to ground control station by on-air radio transceiver module。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520495355.2U CN205333865U (en) | 2015-04-07 | 2015-04-07 | Unmanned aerial vehicle with redundant navigation feature |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520495355.2U CN205333865U (en) | 2015-04-07 | 2015-04-07 | Unmanned aerial vehicle with redundant navigation feature |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520203671.8U Division CN204556838U (en) | 2015-04-07 | 2015-04-07 | A kind of unmanned aerial vehicle with redundancy navigation feature |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205333865U true CN205333865U (en) | 2016-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520495355.2U Expired - Fee Related CN205333865U (en) | 2015-04-07 | 2015-04-07 | Unmanned aerial vehicle with redundant navigation feature |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017084045A1 (en) * | 2015-11-18 | 2017-05-26 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle aircraft, and navigation method and system |
-
2015
- 2015-04-07 CN CN201520495355.2U patent/CN205333865U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017084045A1 (en) * | 2015-11-18 | 2017-05-26 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle aircraft, and navigation method and system |
| CN107110977A (en) * | 2015-11-18 | 2017-08-29 | 深圳市大疆创新科技有限公司 | A kind of unmanned plane during flying device, air navigation aid and system |
| US10825347B2 (en) | 2015-11-18 | 2020-11-03 | SZ DJI Technology Co., Ltd. | Unmanned aircraft, and method and system for navigation |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder |
Address after: 102488 910, 9 / F, building 8, courtyard 1, Tianxing street, Fangshan District, Beijing Patentee after: ZHONGKE SHENGDONG (BEIJING) MEDIA TECHNOLOGY Co.,Ltd. Address before: 100041 Beijing city Shijingshan District high Jing Lu No. 6 convenient service center two floor room 206 Patentee before: ZHONGKE SHENGDONG (BEIJING) MEDIA TECHNOLOGY Co.,Ltd. |
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| CP02 | Change in the address of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160622 Termination date: 20210407 |
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| CF01 | Termination of patent right due to non-payment of annual fee |