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Unmanned aerial vehicle

A technology of unmanned aerial vehicles and machine arms, which is applied in the field of unmanned aerial vehicles, can solve the problems of poor accuracy of the flying direction of unmanned aerial vehicles, achieve the effect of correct heading and improve operation efficiency

Pending Publication Date: 2021-06-18
BEIJING SANKUAI ONLINE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of this disclosure is to provide a drone to solve the problem of poor accuracy of the drone's flight direction due to the short distance between the dual RTK antennas installed in the center of the fuselage

Method used

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Embodiment Construction

[0027] Specific embodiments of the present disclosure will be described in detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to illustrate and explain the present disclosure, and are not intended to limit the present disclosure.

[0028] In this disclosure, unless stated to the contrary, the use of orientation words such as "inner" and "outer" refers to the closed cavity formed by the end cap and the mounting seat, and "inner" refers to the hollow space. The inside of the cavity, and "out" is the outside of the cavity. In addition, the purpose of terms such as "first" and "second" used is to distinguish different components, and does not have sequence or importance. In the following description, when referring to the drawings, the same reference numerals in different drawings denote the same or similar elements unless otherwise explained.

[0029] Such as figure 1 and figure 2 As ...

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Abstract

The invention relates to an unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage; multiple vehicle arms which extend outwards from the fuselage, wherein power systems are arranged at the tail ends of the vehicle arms, and the multiple vehicle arms at least comprise the first vehicle arm and the second vehicle arm which are located in the same extending direction; and the two RTK antennas which are respectively arranged at the tail ends of the first vehicle arm and the second vehicle arm and are mounted on the corresponding power systems. Thus, the two RTK antennas are arranged at the ends of the two vehicle arms in the same extension direction respectively, the span distance of the two RTK antennas in the direction perpendicular to the fuselage is large, more accurate angle measurement and calculation precision can be provided, course angle deviation in the flight operation process can be corrected in real time, the correctness and stability of the course can be ensured, and the operation efficiency of the unmanned aerial vehicle is improved. Besides, according to the included angle relation between the direction defined by the two RTK antennas and the direction of the fuselage of the unmanned aerial vehicle, the direction of the nose can be quickly determined, and the flight operation of the unmanned aerial vehicle is accurately guided.

Description

technical field [0001] The present disclosure relates to the technical field of drones, and in particular, to a drone. Background technique [0002] RTK (Real - time kinematic) carrier phase difference technology can provide real-time three-dimensional positioning results of the station in the specified coordinate system, which not only has high precision, but also has strong anti-electromagnetic interference ability. Applying RTK technology to the field of drones can improve the positioning accuracy of drones and reduce flight errors. In related technologies, a single RTK antenna or dual RTK antennas are usually installed on the fuselage, and a separate support structure is set at the same time. The RTK antenna is installed at the fuselage, so it is impossible to determine the direction of the nose, and the interference to the signal is large, and the transmission of information is unstable; if the dual RTK antenna is installed in the center of the fuselage, due to the sho...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/36
CPCB64C1/36
Inventor 毛一年王刚高焓郜奥林初征杨芳姜欣宏苏文兵唐河森马聪刘金来刘璐陆宏伟邱一可刘宝俊姚博瀚周东岳赵龙智吴振凯纪秀东闫波
Owner BEIJING SANKUAI ONLINE TECH CO LTD
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