Abstract: The unmanned aerial vehicle (UAV) includes detachable motor arms. In this way, the UAV may be conveniently stored and transported, rapidly assembled in the field, and repaired in the event of a crash. The motor arms are also configured to separate from the fuselage in the event of a crash. An example unmanned aerial vehicle comprises: a fuselage and two motor arms. Each motor arm is detachably secured to the fuselage by two mechanical connectors and comprises a tube having a rotary wing propulsion system on each end and an electrical connector, positioned between the two rotary wing propulsion systems, configured to conductively interface with an electrical connector in an underside of the fuselage. The two mechanical connectors detachably securing each motor arm to the fuselage are configured to facilitate the separation of that motor arm from the fuselage during a crash.

Abstract: Implementations of an unmanned aerial vehicle (UAV) fuselage are provided. In some implementations, the fuselage comprises a frame having a shell removably secured thereto. The frame of the fuselage is made of printed circuit board (PCB) material that includes conductive tracks configured to conductively connect electrical components of the UAV. Due to the inherent rigidity of PCB material, the transfer of vibration loads to electrical components secured to the frame of the fuselage is minimized. While the shell is secured to the frame, an enclosure for any electrical components on the topside of the frame is formed. In this way, the encased electrical components may be protected from the environment (e.g., rain) and direct impact during a crash. In some implementations, the frame of the UAV fuselage may include a plurality of stiffening inserts that are positioned and configured to increase the rigidity of the frame.

Abstract: Implementations of an unmanned aerial vehicle (UAV) provided with detachable motor arms are provided. In this way, the UAV may be conveniently stored and transported, rapidly assembled in the field, and repaired in the event of a crash. Also, the motor arms are configured to separate from the fuselage of the UAV upon crashing into the ground and/or another object. In this way, damage to the motors arms and/or the fuselage of the UAV may be minimized or prevented. An example UAV comprises a fuselage having two motor arms detachably secured thereto, each motor arm is detachably secured to the fuselage by two mechanical connectors (or fuses) and comprises a tube having a rotary wing propulsion system on each end thereof. The mechanical connectors securing each motor arm to the fuselage of the UAV are configured to facilitate the separation of the motor arm from the fuselage during a crash.

Abstract: A system is provided comprising a control station for remotely controlling unmanned aerial vehicles (“UAV”). The control station is configured to display vehicle status data received from each UAV, including displaying a location of each UAV in a single interface. Through the single interface, the control station may receive a control command input associated with one of the UAVs. The control station may transmit the received control command, or a command derived therefrom, to the respective UAV. The single interface may provide for a user to view and control flight operation of each of the UAVs independently through the single interface.

Abstract: A system is provided comprising a control station for remotely controlling unmanned aerial vehicles (“UAV”). The control station is configured to display vehicle status data received from each UAV, including displaying a location of each UAV in a single interface. Through the single interface, the control station may receive a control command input associated with one of the UAVs. The control station may transmit the received control command, or a command derived therefrom, to the respective UAV. The single interface may provide for a user to view and control flight operation of each of the UAVs independently through the single interface.