Patent ID: 8528854

Claim:
A self-righting frame assembly for an aeronautical vehicle, said frame assembly comprising: at least two vertically oriented frames, said frames having an uninterrupted, continuous peripheral edge between a top portion and a base portion, said frames defining a central void and said frames having a central vertical axis, the at least two vertically oriented frames being arranged in a fixed spatial relationship; a weighted mass within said frame assembly and positioned proximate to a bottom of said frame assembly and along said central vertical axis for the 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 the self-righting frame produces a self righting moment to return to an upright equilibrium position: when said frame assembly is inverted and resting on a horizontal surface, said frame assembly contacts the horizontal 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, and when said frame assembly is positioned having the central vertical axis in a non vertical orientation position and resting on a horizontal surface, only two points of said frame assembly said contact said surface and said center of gravity, in conjunction with said two points of contact produce a righting moment to return said frame assembly to an upright equilibrium position.