AMENDED CLAIMS received by the International Bureau on 07 April 2021 (07.04.2021)

1. An aerial vehicle comprising: a fuselage having a first height and a first rounded square cross-section, wherein the fuselage comprises four sides having the first height and a first width that are joined at four rounded comers to define the first rounded square cross- section, and wherein the first height is greater than the first width; a frame having a second height and a second rounded square cross-section, wherein the frame comprises four sides having the second height and a second width that are joined at four rounded comers to define the second rounded square cross-section, wherein the second height is less than the first height, and wherein the second width is greater than the first width, and wherein a centroid of the first rounded square cross-section is aligned along a first axis with a centroid of the second rounded square cross-section; a plurality of stmts, wherein each of the stmts has a proximal end joined to an external surface of one of the four rounded comers of the fuselage and a distal end joined to an internal surface of one of the four rounded comers of the frame; a plurality of propulsion motors, wherein each of the propulsion motors is a direct current motor having a housing coupled to one of the plurality of stmts, and wherein each of the propulsion motors is configured to rotate a propeller at one or more rotational speeds; a first time-of-flight sensor mounted at an upper end of the fuselage, wherein the first time-of-flight sensor is configured to transmit first light along a second axis normal to and radially outward from the first axis and to receive one or more reflections of the first light, and wherein the first time-of-flight sensor is configured to rotate the second axis about the first axis; a second time-of-flight sensor mounted to an upper edge of the frame, wherein the second time-of-flight sensor is configured to transmit second light above the frame and to receive one or more reflections of the second light; 106 a third time-of-flight sensor mounted to a lower edge of the frame, wherein the third time-of-flight sensor is configured to transmit third light below the frame and to receive one or more reflections of the third light; a visual camera provided within a chamber defined by the fuselage, wherein the visual camera comprises a lens defining a field of view extending normal to one of the sides of the fuselage; at least one memory component provided within the chamber; at least one transceiver provided within the chamber; and at least one computer processor provided within the chamber, wherein the at least one computer processor is in communication with each of the plurality of propulsion motors, the first time-of-flight sensor, the second time-of-flight sensor, the third time-of-flight sensor, the visual camera, the at least one memory component and the at least one transceiver.

2. The aerial vehicle of claim 1, wherein each of the struts comprises an inlet hole on an upper surface, wherein the fuselage comprises a plurality of outlet holes provided on a bottom surface, wherein the fuselage, the chamber and the struts define a plurality of flow paths, and wherein each of the flow paths extends between one of the inlet holes and one of the outlet holes through the chamber. 107

3. The aerial vehicle of claim 1, wherein a charging dock is provided in a first space of a facility, and wherein the memory component is programmed with at least a physical map of the facility and with one or more sets of instructions that, when executed by the at least one computer processor, cause the aerial vehicle to execute a method comprising: receiving, by the transceiver, an indication of a predetermined condition in a second space of the facility at a first time, wherein the fuselage is within the cavity of the charging dock at the first time; causing, by at least one of the propulsion motors, the aerial vehicle to ascend from the charging dock; generating, by the at least one processor, a route from the first space to the second space, wherein the route comprises a plurality of paths; causing the aerial vehicle to travel on the route to the second space; capturing, by the visual camera, a visual image at a second time, wherein the second time follows the first time, and wherein the aerial vehicle is within the second space at the second time; and determining, based at least in part on the visual image, that the predetermined condition existed within the second space at the second time based at least in part on the visual image. 108

4. A method comprising: receiving, by an aerial vehicle at a first location within a first space of a facility, an indication that one of an event or a condition exists within a second space of the facility at a first time; determining, by the aerial vehicle, at least one of a course, a speed or an altitude for travel from the first location to a second location within the second space based at least in part on information regarding a map of at least the first space and the second space stored in at least one memory component of the aerial vehicle; operating at least one of a plurality of propulsion motors of the aerial vehicle to cause the aerial vehicle to travel from the first location to the second location at the at least one of the course, the speed or the altitude; capturing at least a first image by at least one visual camera of the aerial vehicle at a second time, wherein the aerial vehicle is within a vicinity of the second location at the second time; and determining, by the aerial vehicle based at least in part on the first image, whether the event or the condition exists within the second space at the second time. 109

5. The method of claim 4, wherein the aerial vehicle comprises: a fuselage having a first height and a first cross-section, wherein the fuselage comprises a first plurality of sides having the first height and a first width that define the first cross-section, and wherein the first height is greater than the first width; a frame having a second height and a second cross-section, wherein the frame comprises a second plurality of sides having the second height and a second width that define the second cross-section, wherein the second height is less than the first height, and wherein the second width is greater than the first width, and wherein a centroid of the first cross-section is aligned along a first axis with a centroid of the second cross-section; a plurality of struts, wherein each of the struts has a proximal end joined to an external surface of the fuselage and a distal end joined to an internal surface of the frame; the plurality of propulsion motors, wherein each of the propulsion motors comprises a housing coupled to one of the plurality of struts, and wherein each of the propulsion motors is configured to rotate a propeller at one or more rotational speeds; a first time-of-flight sensor mounted in association with the fuselage; a second time-of-flight sensor mounted in association with the frame; a visual camera disposed within a chamber defined by the fuselage, wherein the visual camera comprises a lens defining a field of view extending normal to one of the first plurality of sides of the fuselage, and wherein the at least one memory component is provided within the chamber; at least one transceiver provided within the chamber; and at least one computer processor provided within the chamber, wherein the at least one computer processor is in communication with each of the plurality of propulsion motors, the first time-of-flight sensor, the second time-of-flight sensor, the visual camera, the at least one memory component and the at least one transceiver. 110

6. The method of claim 5, wherein the first time-of-flight sensor is configured to transmit first light along a second axis normal to the first axis and to receive reflections of at least some of the first light, wherein the first time-of-flight sensor is configured to rotate the second axis about the first axis, wherein the second time-of-flight sensor is mounted to an upper edge of the frame and configured to transmit second light above the frame along a third axis parallel to the first axis and to receive reflections of at least some of the second light, and wherein the aerial vehicle further comprises a third time-of-flight sensor mounted to a lower edge of the frame and configured to transmit third light below the frame along a fourth axis parallel to the first axis and to receive reflections of at least some of the third light.

7. The method of claim 5, wherein the aerial vehicle further comprises: a first cover mounted to an upper edge of the frame, wherein the first cover comprises a first plurality of bars distributed within a first plane; and a second cover mounted to a lower edge of the frame, wherein the second cover comprises a second plurality of bars distributed within a second plane and an opening for accommodating the fuselage, wherein each of the propulsion motors is configured to rotate a propeller within a cavity defined by interior surfaces of the frame, the first cover and the second cover.

8. The method of claim 5, wherein each of the struts comprises an inlet hole on an upper surface, wherein the fuselage comprises a plurality of outlet holes provided on a bottom surface, wherein the fuselage and the struts define a plurality of flow paths, and wherein each of the flow paths extends from one of the inlet holes through the chamber defined by the fuselage to one of the outlet holes. 111

9. The method of claim 4, wherein the fuselage of the aerial vehicle is inserted into an opening of a charging dock at the first time, wherein the opening of the charging dock has a third height and a third cross-section, wherein the third cross-section is sized to accommodate the first cross-section of the fuselage, wherein operating the at least one of the plurality of propulsion motors of the aerial vehicle to cause the aerial vehicle to travel from the first location to the second location comprises: in response to receiving the indication, operating the at least one of the plurality of propulsion motors of the aerial vehicle to ascend from the charging dock.

10. The method of claim 4, further comprising: prior to the first time, capturing data by at least one of the first time-of-flight sensor, the second time-of-flight sensor or the visual camera while the aerial vehicle travels within at least the first space of the facility and the second space of the facility; determining positions corresponding to at least a first boundary of the first space based at least in part on the captured data, wherein the first boundary is one of a floor, a ceiling or a wall; determining positions corresponding to at least a second boundary of the second space based at least in part on the captured data, wherein the second boundary is one of a floor, a ceiling or a wall; generating the map based at least in part on the positions corresponding to at least the first boundary and the positions corresponding to at least the second boundary; and storing information regarding the map in the at least one memory component. 112

11. The method of claim 4, wherein receiving the indication that the one of the event or the condition exists within the second space of the facility at the first time comprises: determining that at least one sensor in one of the first space or the second space has indicated that the one of the event or the condition is occurring within the second space at the first time, wherein determining the at least one of the course, the speed or the altitude comprises: selecting the second location based at least in part on a third location of the at least one sensor; and generating at least one path for the aerial vehicle to travel from the first location to the second location based at least in part on the map, and wherein operating the at least one of the propulsion motors of the aerial vehicle comprises: causing the aerial vehicle to travel from the first location to the second location via the at least one path.

12. The method of claim 4, wherein determining whether the event or the condition exists within the second space comprises: determining, based at least in part on the first image, that the one of the event or the condition exists within at least one of the first space or the second space; and transmitting, by the aerial vehicle, at least one message indicating that the one of the event or the condition exists within the at least one of the first space or the second space to at least one of: an intermediary device located within the facility; or a computer device external to the facility. 13. The method of claim 4, wherein the one of the event or the condition is one of: a high temperature condition; a low temperature condition; a fire; a flood; an unauthorized entry into the facility; a temperature above or below a predetermined setpoint; presence of smoke; presence of water; presence of unauthorized personnel; a level of carbon dioxide above a predetermined setpoint; a level of carbon monoxide above a predetermined setpoint; a level of a hydrocarbon above a predetermined setpoint; or a level of radon above a predetermined setpoint. 14. A system comprising: an aerial vehicle comprising: a fuselage having a first height and a first substantially square cross-section, wherein a bottom of the fuselage comprises a first electrical contact and a second electrical contact arranged in a pattern; a first frame having a second height and a second substantially square cross- section, wherein a centroid of the first substantially square cross-section is aligned along a first axis with a centroid of the second substantially square cross-section; a plurality of struts, wherein each of the struts has a proximal end joined to an external surface of the fuselage and a distal end joined to an internal surface of the frame; a plurality of propulsion motors, wherein each of the propulsion motors has a housing coupled to one of the plurality of struts, and wherein each of the propulsion motors is configured to rotate a propeller at one or more rotational speeds; a first time-of-flight sensor mounted at an upper end of the fuselage, wherein the first time-of-flight sensor is configured to transmit first light along a second axis normal to and radially outward from the first axis and to receive one or more reflections of the first light; a second time-of-flight sensor mounted to an upper edge of the frame, wherein the second time-of-flight sensor is configured to transmit second light above the frame and to receive one or more reflections of the second light; a third time-of-flight sensor mounted to a lower edge of the frame, wherein the third time-of-flight sensor is configured to transmit third light below the frame and to receive one or more reflections of the third light; a visual camera provided within a chamber defined by the fuselage, wherein the visual camera comprises a lens defining a field of view extending normal to one of the sides of the fuselage; at least one memory component provided within the chamber; at least one transceiver provided within the chamber; and at least one computer processor provided within the chamber, wherein the at least one computer processor is in communication with each of 115 the plurality of propulsion motors, the first time-of-flight sensor, the second time-of-flight sensor, the third time-of-flight sensor, the visual camera, the at least one memory component and the at least one transceiver; and a charging dock comprising: a second frame having a third height and a third substantially square cross- section, wherein the second frame comprises an upper surface, a lower surface, and an opening within the upper surface having a fourth height and a fourth substantially square cross-section, wherein a bottom of the opening comprises at least a third electrical contact and a fourth electrical contact arranged in the pattern, wherein the third substantially square cross-section is substantially similar to the second substantially square cross-section, wherein the opening is configured to accommodate at least a lower end of the fuselage therein, and wherein a centroid of the third substantially square cross-section and a centroid of the fourth substantially square cross-section are aligned along the first axis when at least the lower end of the fuselage is accommodated within the opening.

15. The system of claim 14, wherein each of the struts comprises an inlet hole on an upper surface, wherein the fuselage comprises a plurality of outlet holes provided on the bottom of the fuselage, wherein the fuselage and the struts define a plurality of flow paths, and wherein each of the flow paths extends from one of the inlet holes through the chamber defined by the fuselage to one of the outlet holes.