Self-righting frame and aeronautical vehicle
View Patent ↗An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein.
1. A self-righting aeronautical vehicle, comprising:
a self-righting frame assembly having a plurality of frame members, the frame members being arranged in a fixed spatial relationship providing a passageway for airflow into and from an interior void,
at least a portion of the plurality of frame members form at least one dome shaped section;
at least one of an apex and a protrusion located generally centered within the at least one dome shaped section,
a propulsion system located within the interior void,
wherein, the at least one of the apex and the protrusion providing an initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the apex and the protrusion contacting the generally horizontal surface.
2. The self-righting aeronautical vehicle as recited in claim 1 , wherein the self-righting aeronautical vehicle is adapted to be instable when the self-righting aeronautical vehicle contacts the generally horizontal surface from flight.
3. The self-righting aeronautical vehicle as recited in claim 1 , wherein at least a portion of the plurality of frame members have an elongated shape.
4. The self-righting aeronautical vehicle as recited in claim 1 , wherein at least a portion of the plurality of frame members form a substantially continuous looped shape.
5. The self-righting aeronautical vehicle as recited in claim 1 , wherein the propulsion system is adapted to contribute to the self-righting process.
6. The self-righting aeronautical vehicle as recited in claim 1 , comprising
the apex, wherein the apex is located generally centered within the at least one dome shaped section,
wherein, the apex provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the apex and the protrusion contacting the generally horizontal surface.
7. The self-righting aeronautical vehicle as recited in claim 1 , comprising
the protrusion, wherein the protrusion is located generally centered within the at least one dome shaped section,
wherein, the protrusion provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the protrusion and the protrusion contacting the generally horizontal surface.
8. A self-righting aeronautical vehicle, comprising:
a self-righting frame assembly having a plurality of frame members, the frame members being arranged in a fixed spatial relationship providing a passageway for airflow into and from an interior void,
at least a portion of the plurality of frame members form at least one dome shaped section;
at least one of an apex and a protrusion located generally centered within the at least one dome shaped section,
a propulsion system located within the interior void,
wherein, the at least one of the apex and the protrusion providing an initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the apex and the protrusion contacting the generally horizontal surface,
wherein upon completion of a self righting process of the self-righting frame assembly, the propulsion system is oriented within the self-righting frame assembly to provide a lift force to the self-righting aeronautical vehicle.
9. The self-righting aeronautical vehicle as recited in claim 8 , wherein the self-righting aeronautical vehicle is adapted to be instable when the self-righting aeronautical vehicle contacts the generally horizontal surface from flight.
10. The self-righting aeronautical vehicle as recited in claim 8 , wherein at least a portion of the plurality of frame members have an elongated shape.
11. The self-righting aeronautical vehicle as recited in claim 8 , wherein at least a portion of the plurality of frame members form a substantially continuous looped shape.
12. The self-righting aeronautical vehicle as recited in claim 8 , wherein the propulsion system is adapted to contribute to the self-righting process.
13. The self-righting aeronautical vehicle as recited in claim 8 , comprising
the apex, wherein the apex is located generally centered within the at least one dome shaped section,
wherein, the apex provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the apex and the protrusion contacting the generally horizontal surface.
14. The self-righting aeronautical vehicle as recited in claim 8 , comprising
the protrusion, wherein the protrusion is located generally centered within the at least one dome shaped section,
wherein, the protrusion provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the protrusion and the protrusion contacting the generally horizontal surface.
15. A self-righting aeronautical vehicle, comprising:
a self-righting frame assembly having a plurality of frame members, the frame members being arranged in a fixed spatial relationship providing a passageway for airflow into and from an interior void,
the frame members having at least one arched section;
at least one of an apex and a protrusion located generally centered within the at least one arched section,
a propulsion system located within the interior void,
wherein, the at least one of an apex and a protrusion providing an initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of an apex and a protrusion contacting the generally horizontal surface,
wherein upon completion of a self righting process of the self-righting frame assembly, the propulsion system is oriented in a substantially vertical orientation.
16. The self-righting aeronautical vehicle as recited in claim 15 , wherein the self-righting aeronautical vehicle is adapted to be instable when the self-righting aeronautical vehicle contacts the generally horizontal surface from flight.
17. The self-righting aeronautical vehicle as recited in claim 15 , wherein at least a portion of the plurality of frame members have an elongated shape.
18. The self-righting aeronautical vehicle as recited in claim 15 , wherein at least a portion of the plurality of frame members form a substantially continuous looped shape.
19. The self-righting aeronautical vehicle as recited in claim 15 , wherein the propulsion system is adapted to contribute to the self-righting process.
20. The self-righting aeronautical vehicle as recited in claim 15 , comprising
the apex, wherein the apex is located generally centered within the at least one dome shaped section,
wherein, the apex provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the apex and the protrusion contacting the generally horizontal surface.
21. The self-righting aeronautical vehicle as recited in claim 15 , comprising
the protrusion, wherein the protrusion is located generally centered within the at least one dome shaped section,
wherein, the protrusion provides the initial instability to begin a self-righting process when said frame assembly is placed on a generally horizontal surface oriented having the at least one of the protrusion and the protrusion contacting the generally horizontal surface.