Self-Righting Frame And Aeronautical Vehicle
First Claim
1. An aeronautical vehicle that rights itself from an inverted state to an upright state, said aeronautical vehicle comprising:
- a self-righting frame assembly comprising;
a frame structure comprising;
at least one generally vertically oriented frame member having an generally uninterrupted, continuous peripheral edge between a top portion and a base portion, and at least one generally horizontally oriented frame, said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame being mechanically coupled to one another at each intersecting location, and said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame defining a central void, said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame being arranged in a fixed spatial relationship;
a weighted mass carried by 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 defined at a top of said at least one generally vertically oriented frame member 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.
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Accused Products
Abstract
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.
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Citations
23 Claims
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1. An aeronautical vehicle that rights itself from an inverted state to an upright state, said aeronautical vehicle comprising:
a self-righting frame assembly comprising; a frame structure comprising; at least one generally vertically oriented frame member having an generally uninterrupted, continuous peripheral edge between a top portion and a base portion, and at least one generally horizontally oriented frame, said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame being mechanically coupled to one another at each intersecting location, and said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame defining a central void, said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame being arranged in a fixed spatial relationship; a weighted mass carried by 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 defined at a top of said at least one generally vertically oriented frame member 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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. 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 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 vertically oriented frame members having an generally uninterrupted, continuous peripheral edge between a top portion and a base portion, said at least two vertically oriented frame members defining a central void, said at least two 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. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17)
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18. An aeronautical vehicle that rights itself from an inverted state to an upright state, said aeronautical vehicle comprising:
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a self-righting frame assembly comprising; at least two 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 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. - View Dependent Claims (19, 20, 21, 22, 23)
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Specification