Autonomous aerial vehicle hardware configuration
An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.
1. An unmanned aerial vehicle (UAV), the UAV comprising:
a central body extending along a longitudinal axis from a forward end to an aft end, the central body having a port side and a starboard side on opposite sides of the longitudinal axis;
multiple rotor arms each having a proximal end coupled to the central body;
multiple rotor assemblies each arranged at a distal end of a rotor arm of the multiple rotor arms, the multiple rotor assemblies configured to provide propulsion for the UAV;
multiple image capture devices arranged along a surface of the central body of the UAV;
a battery pack for powering the UAV, the battery pack detachably coupled to an underside of the UAV and configured as an external handle for direct autonomous launch from, or autonomous land in, a hand of a user when attached; and
multiple protective structural elements that protrude from the central body, wherein at least one structural element is arranged in proximity to each image capture device of the multiple image capture devices to offset the image capture device from surfaces.
2. The unmanned UAV of claim 1 , wherein the battery pack is detachably coupled, both structurally and electrically, to the central body of the UAV using one or more magnetic couplings.
3. The unmanned UAV of claim 1 , wherein the battery pack includes one or more user interface components.
4. The unmanned UAV of claim 3 , wherein the user interface components allow the user to provide a control input to the UAV.
5. The unmanned UAV of claim 4 , wherein the user interface components are communicatively coupled to an internal control system of the UAV.
6. The unmanned UAV of claim 5 , wherein the interface features are communicatively coupled to an internal control system of the UAV via one or more detachable magnetic couplings.
7. The unmanned UAV of claim 4 , wherein the user interface components comprise a button configured to initiate the control input when pressed by the user.
8. The unmanned UAV of claim 4 , wherein the control input comprises an instruction to launch the UAV.
9. The unmanned UAV of claim 8 , wherein the control input further comprises an instruction for the UAV to enter autonomous flight.
10. The unmanned UAV of claim 4 , wherein the control input comprises an instruction to set flight parameters or constraints.
11. The unmanned UAV of claim 10 , wherein the flight parameters or constraints comprise one or more of flight mode, follow distance, or altitude.
12. The unmanned UAV of claim 4 , wherein the user interface components comprise a touch screen display configured to display and receive input via a contextual user interface.
13. The unmanned UAV of claim 1 , the UAV is configured to self-eject the battery pack when a pre-determined condition is detected.
14. The unmanned UAV of claim 1 , wherein battery pack includes textured surface elements to help the user grip the UAV during launch or land.
15. A detachable battery pack apparatus for powering an autonomous unmanned aerial vehicle (UAV), the UAV comprising:
a housing including walls substantially surrounding an interior space, the housing configured to be detachable couplable, both structurally and electrically, to an underside of a central body of the UAV using one or more detachable magnetic couplings; and
one or more battery modules arranged substantially within the interior space;
wherein, when coupled to an underside of the UAV, at least a portion of the detachable battery pack is configured as an external handle for autonomous launch of the UAV from, or autonomous land of the UAV in, a hand of a user,
wherein the detachable battery pack is configured to self-eject when the UAV makes impact with an obstacle,
wherein the detachable battery pack includes one or more user interface components configured to allow the user to provide a control input to the UAV when the detachable battery pack apparatus is coupled to the UAV, and
wherein the control input comprises an instruction to set flight parameters or constraints for autonomous flight.
16. The detachable battery pack apparatus of claim 15 , wherein the control input comprises an instruction to enter autonomous flight.
17. The detachable battery pack apparatus of claim 16 , wherein the one or more user interface components are communicatively coupled to an internal control system of the UAV via the one or more detachable electromagnetic couplings, wherein upon indication, the detachable battery pack self-ejects.
18. The detachable battery pack apparatus of claim 16 , wherein the control input comprises an instruction to launch the UAV.
19. The detachable battery pack apparatus of claim 16 , wherein the user interface components comprise a touch screen display configured to display and receive input via a contextual user interface.
20. An aerial vehicle comprising:
multiple rotor assemblies arranged along a surface of the aerial vehicle;
multiple image capture devices arranged along a surface of the aerial vehicle; and
a battery pack for powering the aerial vehicle, the battery pack detachably structurally and electrically coupled to an underside of the aerial vehicle via one or more magnetic couplings,
wherein, when coupled to the underside of the aerial vehicle, at least a portion of the battery pack is configured as a handle for autonomous launch from, or autonomous land in, a hand of a user; and
multiple protective structural elements that protrude from the aerial vehicle, wherein at least one structural element is arranged in proximity to each image capture device of the multiple image capture devices to offset the image capture device from surfaces.