4results about How to "Flight safety" patented technology

The invention discloses a method and a system for generating and executing an anti-interference flight strategy of a C2 link of an unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicle communication. The method comprises the following steps: acquiring urban building material parameters and unmanned aerial vehicle flight parameters; based on the parameters, combining a free space path loss model, a Rice fading model and a blade peak diffraction model to construct an urban environment channel model; injecting same-frequency Wi-Fi interference and building reflection interference signals to calculate a signal to interference plus noise ratio; based on the signal to interference plus noise ratio, calculating the bit error rate and evaluating the anti-interference performance, and generating an anti-interference optimization scheme including frequency band switching and flight height adjustment; and controlling the unmanned aerial vehicle to execute the strategy. Aiming at the problems of Wi-Fi co-frequency interference, building shielding, glass curtain wall multipath reflection and the like in a complex urban environment, frequency band self-adaptive switching and flight height optimization are realized through multi-model joint simulation and dynamic strategy generation, the bit error rate is reduced, the anti-interference capability is improved, and the method has the advantages of being simple in structure and convenient to operate. And the communication reliability and the flight safety of the unmanned aerial vehicle in a complex urban environment are effectively guaranteed.

The application relates to the technical field of unmanned planes, in particular to a linkage device for folding and locking a machine arm for plane performance, which comprises a plane main body, a rotating machine arm module, a folding and locking module and a central control module. The central control module is fixedly arranged at the top outer side of the plane main body and comprises a central control box, a driving control assembly, a transmission control assembly and a cooperative control assembly; the driving control assembly is connected with the folding and locking module through the transmission control assembly, and the driving control assembly is also connected with the installed rotating machine arm module through the cooperative control assembly. The folding and locking module and the rotating machine arm module are synchronously controlled through the central control module, the machine arm can be automatically turned over and unfolded and locked in multiple sections, the automatic unfolding and locking of the folded arm can be realized, the problem that the existing unmanned plane folding machine arm operation is complicated and is prone to accidental folding is solved, the linkage device has high portability, high reliability and rapid deployment capacity, and is especially suitable for unmanned plane formation performance scenes.

This invention discloses a self-stabilizing, wind-resistant VTOL fixed-wing UAV, belonging to the field of UAVs. The self-stabilizing, wind-resistant VTOL fixed-wing UAV includes a connector. A motor is fixedly connected to the top of the connector, and a rotating ring is fixedly connected to the top of the motor. A rotor blade is fixedly connected to the outer side of the rotating ring. A through groove is formed on the outer side of the rotating ring, and a cover plate is provided on the top of the rotating ring. An extension block is fixedly connected to the side of the cover plate near the through groove. A retaining plate is fixedly connected to the inner wall of the through groove, and a slot is formed on the inner side of the extension block. The retaining plate is located inside the slot. The rotating ring and the cover plate are snapped together by the retaining plate and the through groove. The rotating ring and the cover plate form a snap-fit ​​quick-release structure through the through groove, the retaining plate, the cylinder, and the round hole and slot of the extension block, achieving convenient assembly and disassembly with a stable connection. This effectively improves the efficiency of rotor blade assembly and disassembly and the ease of maintenance. Simultaneously, the tight snap-fit ​​ensures the dynamic balance of rotor rotation, enhancing the operational stability and wind resistance reliability of the UAV.

This invention relates to a flight control method and system for unmanned aerial vehicles (UAVs) based on fused altitude, comprising the following steps: after controlling the UAV to leave the ground, obtaining a first fused altitude H(k) based on a barometer mounted on the UAV; controlling the UAV to fly based on the first fused altitude H(k) until the first fused altitude H(k) ≥ the ground clearance H. G At that time, the second fused altitude H(p) is obtained based on the laser altimeter and barometer mounted on the UAV; and when the first fused altitude H(k) ≥ the ground altitude H G The drone is continuously controlled based on the second fused altitude H(p). This invention allows for the selection of corresponding altitude fusion strategies when the drone is at different altitudes, maximizing the accuracy of the altitude fusion results and thereby controlling the drone's safe and stable flight based on high-precision altitude information.