Self-righting frame and aeronautical vehicle

A self-righting frame assembly for an aeronautical vehicle, said frame assembly comprising:

• a self-righting frame assembly comprising:
• a frame structure comprising:
• at least two generally vertically oriented frame members in registration with a plane extending radially outward from a central vertical axis of said self-righting frame assembly, said at least two generally vertically oriented frame members having an generally uninterrupted, continuous peripheral edge between a top portion and a base portion, said at least two generally vertically oriented frame members defining a central void, said at least two generally vertically oriented frames being arranged in a fixed spatial relationship;
• a weighted mass carried by a lower section of said frame structure for a purpose of positioning a center of gravity of said frame assembly proximate to a bottom of said frame assembly;
• and
• an apex formed at a top of said vertical axis at an upper portion of said vertical frames for providing an initial instability to begin a self-righting process when said frame assembly is placed in at least one of an off-kilter and an inverted orientation.

An aeronautical vehicle that rights itself from an inverted state to an upright state, said aeronautical vehicle comprising:

• a self-righting frame assembly comprising:
• at least two generally vertically oriented frame members in registration with a plane extending radially outward from a central axis of said self-righting frame assembly, said frame members having an uninterrupted, continuous peripheral edge between a top portion and a base portion, said frames defining a central void, said at least two generally vertically oriented frames being arranged in a fixed spatial relationship;
• a weighted mass at a lower section of said frame assembly for a purpose of positioning a center of gravity of said frame assembly proximate to a bottom of said frame assembly;
• and
• an apex formed at a top of said vertical axis at an upper portion of said vertical frames for providing an initial instability to begin a self-righting process when said frame assembly is inverted;
• wherein:
• when said frame assembly is inverted and resting on a frame assembly supporting surface, said frame assembly contacts said frame assembly supporting surface at said apex and at a point on at least one of said vertical frames and further wherein said apex extends from said top of said vertical axis and above said vertical frames a distance such that said central axis is sufficiently angulated from vertical to horizontally displace said center of gravity beyond said point of contact of said at least one vertical frame thereby producing a righting moment to return said frame assembly to an upright equilibrium position,
• at least one propulsion system mounted within said central void of said self-righting frame assembly, said at least one propulsion system oriented to provide a lifting force;
• a power supply carried by said self-righting frame assembly and operationally connected to said at least one propulsion system for operatively powering said at least one propulsion system;
• and
• an electronics assembly carried by said self-righting frame for receiving remote control commands and communicatively interconnected to said power supply for remotely controlling said aeronautical vehicle to take off, to fly, and to land on said frame assembly supporting surface.