Indoor aerial vehicles with advanced safety features
An aerial vehicle configured for operation within indoor spaces has a meshed construction with a housing defined by upper and lower sections having meshes provided above and below propellers and motors of the aerial vehicle. The aerial vehicle also includes a suite of sensors such as LIDAR sensors, time-of-flight sensors, cameras, ultrasonic sensors, or others. Meshes of the upper and lower sections include central openings along with spokes and concentric rings provided about the central openings. Meshes of the lower section have substantially larger central openings than meshes of the upper section, but feature more dense spokes or concentric rings beneath tips of the rotating propellers, which may be hinged or foldable in nature. Data captured by sensors of the aerial vehicle may be utilized for any purpose, such as to generate environment maps of an indoor space, or to monitor the indoor space for adverse conditions or events.
1. An aerial vehicle comprising:
a housing formed from an upper section, a lower section and a shroud joined to the upper section and the lower section, wherein the housing has a cross-sectional shape of a rounded square having a length approximately equal to a width, wherein a height of the housing is approximately one-sixth of the length or the width of the housing, and wherein a cross-section of the shroud has an arcuate shape;
a plurality of propulsion motors provided within the housing, wherein each of the propulsion motors is a brushless direct current motor configured to rotate a propeller at one or more rotational speeds;
a light detection and ranging sensor module configured to transmit beams of light along a first axis and to capture reflections of the transmitted light, wherein a portion of the light detection and ranging sensor extends above the upper section of the housing, and wherein the light detection and ranging sensor is configured to rotate the first axis about a second axis normal to the first axis;
a first time-of-flight sensor disposed within the upper section, wherein the first time-of-flight sensor is configured to transmit beams of light along a third axis and to capture reflections of the transmitted light, wherein the third axis is parallel to the second axis;
a first chamber having a first face and a second face, wherein the first chamber is disposed at one edge of the housing, wherein the first face is aligned parallel to the second axis, and wherein the first chamber further comprises:
a second time-of-flight sensor disposed within the first chamber, wherein the second time-of-flight sensor is configured to transmit beams of light along a fourth axis and to capture reflections of the transmitted light, wherein the fourth axis is normal to the first face;
a first illuminator and a second illuminator, wherein each of the first illuminator and the second illuminator is provided on either side of the second time-of-flight sensor, and wherein each of the first illuminator and the second illuminator is configured to project visible light from the first face;
a first camera disposed within the first chamber, wherein the first camera has a field of view oriented along a fifth axis, and wherein the fifth axis is normal to the second face; and
a second camera disposed within the first chamber, wherein the second camera has a field of view oriented along a sixth axis, and wherein the sixth axis is parallel to the fifth axis and normal to the second face;
a second chamber disposed at least in part within the housing, wherein at least a portion of the second chamber having a third face extends through the lower section of the housing, wherein the third face is aligned perpendicular to the second axis, and wherein the second chamber further comprises:
a plurality of arms extending within the housing, wherein each of the plurality of propulsion motors is coupled to one of the plurality of arms;
a third time-of-flight sensor disposed within the second chamber, wherein the third time-of-flight sensor is configured to transmit beams of light along a seventh axis and to capture reflections of the transmitted light, wherein the seventh axis is normal to the third face;
a third camera disposed within the second chamber, wherein the third camera has a field of view oriented along an eighth axis, and wherein the eighth axis is normal to the second face;
a third illuminator configured to project light from the third face; and
at least one electrical contact provided on the third face;
a plurality of pegs, wherein each of the plurality of pegs is coupled to the lower section, and wherein each of the plurality of pegs extends below the housing.
2. The aerial vehicle of claim 1 , wherein each of the upper section, the lower section and the shroud is formed from one of:
an acrylonitrile butadiene styrene;
a carbon fiber;
a composite material;
a metal;
a polycarbonate;
a polystyrene;
a recycled plastic; or
a rubber.
3. The aerial vehicle of claim 1 , wherein the upper section comprises an upper frame and a plurality of upper mesh sections coupled to the upper frame,
wherein each of the upper mesh sections comprises a central opening defined by an inner ring, a plurality of spokes extending from the central opening, and a plurality of rings concentric with the inner ring,
wherein the lower section comprises a lower frame and a plurality of lower mesh sections coupled to the lower frame,
wherein each of the lower mesh sections comprises a central opening defined by an inner ring, a plurality of spokes extending from the central opening, and a plurality of rings concentric with the inner ring,
wherein a diameter of the central openings of each of the lower mesh sections is approximately twice a diameter of the central openings of each of the upper mesh sections,
wherein each of the central openings of the upper mesh sections are provided over one of the plurality of propulsion motors, and
wherein each of the central openings of the lower mesh sections are provided below one of the plurality of propulsion motors.
4. The aerial vehicle of claim 1 , wherein the shroud comprises a plurality of slats aligned about a perimeter, and
wherein a cross-section of the shroud has an arcuate shape.
5. An aerial vehicle comprising:
a housing comprising an upper section, a lower section and one or more side sections extending between the upper section and the lower section, wherein the upper section, the lower section, and the one or more side sections each comprise one or more openings defined therethrough, wherein the housing defines a cross-section substantially having a shape of a rounded square, and wherein a length or a width of the housing is substantially greater than a height of the housing;
at least one propulsion motor disposed within the housing, wherein the at least one propulsion motor is configured to rotate at least one propeller at one or more rotational speeds;
a first sensor, wherein the first sensor is configured to capture data regarding ranges to objects;
a second sensor disposed at a first face of the housing, the first face of the housing being disposed at a first side of the housing;
a third sensor disposed at a second face of the housing, the second face of the housing being disposed at the first side of the housing, wherein the second face is oriented at a non-parallel angle with respect to the first face;
a base member extending from the lower section of the housing, the base member comprising a third face;
a fourth sensor disposed at the third face; and
a plurality of pegs extending from the housing, wherein each of the plurality of pegs extends beyond the third face.
6. The aerial vehicle of claim 5 , wherein the first sensor is at least one of:
a light detection and ranging sensor module configured to transmit beams of light along a first axis and to capture reflections of the transmitted light, wherein a portion of the light detection and ranging sensor extends above the upper section of the housing, and wherein the light detection and ranging sensor is configured to rotate the first axis about a second axis normal to the first axis; or
a time-of-flight sensor disposed within the upper section, wherein the time-of-flight sensor is configured to transmit beams of light along a third axis and to capture reflections of the transmitted light, wherein the third axis is parallel to the second axis.
7. The aerial vehicle of claim 5 , wherein the second sensor is at least one of:
a time-of-flight sensor configured to transmit beams of light along a first axis and to capture reflections of the transmitted light, wherein the first axis is normal to the first face;
a camera having a field of view oriented along a second axis, and wherein the second axis is normal to the first face; or
an ultrasonic sensor configured to transmit sound and to capture reflections of the transmitted sound.
8. The aerial vehicle of claim 5 , wherein the third sensor is a camera having a field of view oriented along a first axis, wherein the first axis is normal to the second face.
9. The aerial vehicle of claim 5 , wherein the fourth sensor is one of:
a time-of-flight sensor configured to transmit beams of light along a first axis and to capture reflections of the transmitted light, wherein the first axis is normal to the third face;
a camera having a field of view oriented along a second axis, wherein the second axis is normal to the third face; or
an ultrasonic sensor configured to transmit sound from the third face and to capture reflections of the transmitted sound.
10. The aerial vehicle of claim 9 , wherein the aerial vehicle further comprises at least one of:
an illuminator configured to project light downward from the third face; and
at least one electrical contact provided on the third face.
11. The aerial vehicle of claim 5 , wherein the aerial vehicle further comprises at least one electrical contact provided on the third face,
wherein each of the plurality of pegs is provided in a predetermined arrangement corresponding to an arrangement of openings on a docking station,
wherein each of the holes is sized and shaped to accommodate one of the pegs, and
wherein the at least one electrical contact provided on the third face is in a location on the third face corresponding to a location of at least one electrical contact on a surface of the docking station.
12. The aerial vehicle of claim 5 , wherein at least one of the length or the width of the housing is approximately four times the height of the housing.
13. The aerial vehicle of claim 5 , wherein the aerial vehicle comprises a plurality of arms within the housing, and
wherein the at least one propulsion motor is joined to a distal end of one of the arms.
14. The aerial vehicle of claim 5 , wherein each of the upper section, the lower section and the shroud is formed from one of:
an acrylonitrile butadiene styrene;
a carbon fiber;
a composite material;
a metal;
a polycarbonate;
a polystyrene;
a recycled plastic; or
a rubber.
15. The aerial vehicle of claim 5 , wherein the upper section comprises an upper frame and an upper mesh coupled to the upper frame,
wherein the upper mesh comprises a central opening defined by an inner ring, a plurality of spokes extending from the central opening, and a plurality of rings concentric with the inner ring,
wherein the lower section comprises a lower frame and a lower mesh coupled to the lower frame,
wherein the lower mesh comprises a central opening defined by an inner ring, a plurality of spokes extending from the central opening, and a plurality of rings concentric with the inner ring,
wherein a diameter of the central opening of the at least one lower mesh section is approximately twice a diameter of the central opening of the upper mesh,
wherein the central opening of the at least one upper mesh section is provided over the at least one propulsion motor, and
wherein the central opening of the at least one lower mesh section is provided below the at least one propulsion motor.
16. The aerial vehicle of claim 5 , wherein the housing comprises a shroud having a plurality of slats aligned about a perimeter, and
wherein a cross-section of the shroud has an arcuate shape.
17. An aerial vehicle comprising:
a housing comprising an upper section, a lower section and one or more side sections extending between the upper section and the lower section, wherein the upper section, the lower section, and the one or more side sections each comprise one or more openings defined therethrough, and the housing comprises a first face and a second face disposed at a first side of the housing;
a plurality of propellers disposed within the housing;
at least one propulsion motor disposed within the housing, wherein the at least one propulsion motor is coupled to the plurality of propellers;
a first time-of-flight sensor disposed at the first face and oriented in a first direction;
a second time-of-flight sensor disposed proximate the upper section and oriented in a second direction that is generally orthogonal to the first direction;
a third time-of-flight sensor disposed proximate the lower section and oriented in a third direction that is generally opposite the second direction;
a first camera disposed at the second face and oriented in a fourth direction;
a second camera disposed at the second face and oriented in a fifth direction; and
a third camera disposed proximate the lower section and oriented in the third direction,
wherein the first time-of-flight sensor, the third time-of-flight sensor, the first camera, and the second camera are arranged and oriented such that, when the aerial vehicle is positioned above ground and oriented so that the first direction is generally parallel to the ground and the third direction is vertically downward towards the ground, the fourth direction and fifth direction are downward at an angle between an angle of the first direction and an angle of the third direction.
18. The aerial vehicle of claim 17 , wherein the second face is angled relative to the first face.
19. The aerial vehicle of claim 17 , wherein the aerial vehicle comprises a base member extending from the lower section, and
wherein the third time-of-flight sensor and the second camera are disposed at the base member.
20. The aerial vehicle of claim 17 , wherein the aerial vehicle further comprises a light detection and ranging sensor.
21. The aerial vehicle of claim 17 , wherein the third time-of-flight sensor is a one-dimensional time-of-flight sensor.
22. The aerial vehicle of claim 17 , wherein the first time-of-flight sensor and second time-of-flight sensor are a first type of time-of-flight sensor, and the third time-of-flight sensor is a second type of time-of-flight sensor.