Self-righting frame and aeronautical vehicle

• US 9,067,667 B2
• Filed: 09/09/2013
• Issued: 06/30/2015
• Est. Priority Date: 07/23/2010
• Status: Active Grant

• Current Assignee: Advanced Aerodynamics, LLC
• Original Assignee: Advanced Aerodynamics, LLC
• Inventors: Yan, Gaofei, Dees, James
• Primary Examiner(s): Ellis, Christopher P
• Application Number:
  US14/022,213
• Publication Number:
  US 20140014767A1
• Time in Patent Office: 659 Days
• Field of Search: 244/17.23, 244/17.11, 244/119, 244/8, 244/17.19, 446/36, 446/37
• US Class Current: 1/1
• CPC Class Codes: A63H 15/06 Self-righting toys
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: A63H 30/04 using wireless transmission
• CPC Class Codes: A63H 33/005 Motorised rolling toys
• CPC Class Codes: B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• CPC Class Codes: B64C 1/061 Frames
• CPC Class Codes: B64C 1/08 Geodetic or other open-frame structures
• CPC Class Codes: B64C 17/00 Aircraft stabilisation not otherwise provided for
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/30 for safety, e.g. with frangible components rotor guards B64U30/299
• CPC Class Codes: B64U 20/83 Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 30/298 Helicopter flybars
• CPC Class Codes: B64U 50/15 using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
• CPC Class Codes: B64U 60/60 with rolling cages

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.

Claims

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.

2. A self-righting frame assembly according to claim 1, further comprising:

a lift and stabilization panel having at least one arched surface, said lift and stabilization panel being carried by a portion of an upper region of said frame structure, said lift and stabilization panel providing at least one of;

enhanced control during any motion;

enhanced stability during any motion;

lift when said frame assembly is moving in a generally horizontal motion;

drag when said frame assembly is moving in a generally vertical motion.

3. A self-righting frame assembly according to claim 2, wherein said lift and stabilization panel is provided in one of:

integral with said frame structure, wherein said lift and stabilization panel and said frame structure are fabricated as a unitary structure;

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface considered to permanently retain said lift and stabilization panel and said frame structure together; and

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface enabling removal and reinstallation of said lift and stabilization panel to said frame structure.

4. A self-righting frame assembly according to claim 1, further comprising:

at least one propulsion system carried by at least one generally vertically oriented frame member and extending into 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.

5. A self-righting frame assembly according to claim 4, said at least one propulsion system, said power supply, and said electronics assembly is integrated within an enclosure, said enclosure being carried by at least one of said at least one generally vertically oriented frame member and said at least one generally horizontally oriented frame member.

6. A self-righting frame assembly according to claim 4, said at least one propulsion system further comprising at least one of:

at least one aerodynamic rotor, wherein said at least one aerodynamic rotor is located within said central void of said self-righting frame assembly,

at least one pair of counter-rotating rotors located along a common axis, wherein said at least one pair of counter-rotating rotors located along a common axis are located within said central void of said self-righting frame assembly;

at least one pair of counter-rotating rotors located along different axis, wherein said at least one pair of counter-rotating rotors located along a different axis are located within said central void of said self-righting frame assembly;

a jet pack,

a rocket propulsion system, and

a ducted fan.

7. A self-righting frame assembly according to claim 1, said frame structure comprising at least two vertically oriented frame members, said lift and stabilization panel being assembled to said frame structure extending between said adjacent frame members of said at least two vertically oriented frame members.

8. A self-righting frame assembly according to claim 1, 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, at a first point on an outer periphery of one of said at least one generally vertically oriented frame member, and at a second point on an outer periphery of one of said at least one generally horizontally oriented frame member, said first point and said second point defining a line, said apex extending vertically above said one of said at least one generally vertically oriented frame member at a height such that said center of gravity of said frame assembly is opposite of said straight line from said apex to produce said righting moment to return said frame assembly to an upright equilibrium position.

9. A self-righting frame assembly according to claim 1, wherein said frame structure provides protection to said elements located within said frame structure.

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 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.

11. A self-righting frame assembly according to claim 10, further comprising a lift and stabilization panel having at least one arched surface, said lift and stabilization panel being carried by a segment of an upper region of said frame structure, said lift and stabilization panel, said lift and stabilization panel providing at least one of:

enhanced control during any motion;

enhanced stability during any motion;

lift when said frame assembly is moving in a generally horizontal motion; and

drag when said frame assembly is moving in a generally vertical motion.

12. A self-righting frame assembly according to claim 11, wherein said lift and stabilization panel is provided in one of:

integral with said frame structure, wherein said lift and stabilization panel and said frame structure are fabricated as a unitary structure;

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface considered to permanently retain said lift and stabilization panel and said frame structure together; and

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface enabling removal and reinstallation of said lift and stabilization panel to said frame structure.

13. A self-righting frame assembly according to claim 10, further comprising:

at least one propulsion system carried by at least one generally vertically oriented frame member of the at least two generally vertically oriented frame members and extending into 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.

14. A self-righting frame assembly according to claim 13, said at least one propulsion system, said power supply, and said electronics assembly is integrated within an enclosure, said enclosure being carried by at least one of said at least one generally vertically oriented frame member and said at least two generally horizontally oriented frame members.

15. A self-righting frame assembly according to claim 13, said at least one propulsion system further comprising at least one of:

at least one aerodynamic rotor, wherein said at least one aerodynamic rotor is located within said central void of said self-righting frame assembly,

at least one pair of counter-rotating rotors located along a common axis, wherein said at least one pair of counter-rotating rotors located along a common axis are located within said central void of said self-righting frame assembly;

at least one pair of counter-rotating rotors located along different axis, wherein said at least one pair of counter-rotating rotors located along a different axis are located within said central void of said self-righting frame assembly;

a jet pack,

a rocket propulsion system, and

a ducted fan.

16. A self-righting frame assembly according to claim 10, 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, at a first point on an outer periphery of a first of said vertical frames, and at a second point on an outer periphery of a second of said vertical frames, said first point and said second point defining a line, said apex extending vertically above said vertical frames at a height such that said center of gravity of said frame assembly is opposite of said straight line from said apex to produce said righting moment to return said frame assembly to an upright equilibrium position.

17. A self-righting frame assembly according to claim 10, wherein said frame structure provides protection to said elements located within said frame structure.

18. 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.

19. A self-righting frame assembly according to claim 18, further comprising a further comprising a lift and stabilization panel having at least one arched surface, said lift and stabilization panel being carried by a segment of an upper region of said frame structure, said lift and stabilization panel, said lift and stabilization panel providing at least one of:

enhanced control during any motion;

enhanced stability during any motion;

lift when said frame assembly is moving in a generally horizontal motion;

drag when said frame assembly is moving in a generally vertical motion.

20. A self-righting frame assembly according to claim 19, wherein said lift and stabilization panel is provided in one of:

integral with said frame structure, wherein said lift and stabilization panel and said frame structure are fabricated as a unitary structure;

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface considered to permanently retain said lift and stabilization panel and said frame structure together; and

said lift and stabilization panel and said frame structure are fabricated as separate elements and subsequently assembled into a single unit utilizing an attachment assembly interface enabling removal and reinstallation of said lift and stabilization panel to said frame structure.

21. A self-righting frame assembly according to claim 18, wherein said at least two generally vertically oriented frames are oriented substantially at equal angles one to the other such that their intersection defines said central vertical axis.

22. A self-righting frame assembly according to claim 18, wherein said at least two generally vertical frames define a substantially continuous outer curve about a periphery thereof.

23. A self-righting frame assembly according to claim 18, wherein said frame structure provides protection to said elements located within said frame structure.