[특허]Modular and morphable air vehicle

Piasecki, John W.

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특허 상세정보

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Modular and morphable air vehicle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B60F-005/02 B64C-027/20 B64C-003/56 B64C-027/08 B64C-027/22 B64C-037/00 B64C-029/00 B64C-039/00
출원번호	US-0205162 (2016-07-08)
등록번호	US-9610817 (2017-04-04)
발명자 / 주소	Piasecki, John W. Piasecki, Frederick W. Geiger, Brian Johnson, Douglas Pitcairn, David
출원인 / 주소	Piasecki, John W.
대리인 / 주소	Yarbrough, Robert J.
인용정보	피인용 횟수 : 8 인용 특허 : 28

초록

An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear.

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1. A personal air vehicle apparatus, the apparatus comprising: a. an air module, said air module being unmanned;b. a first rotor and a second rotor operably attached to said air module, said first rotor having a first rotor axis of rotation, said second rotor having a second rotor axis of rotation, said first and second rotor axes of rotation being selectably tiltable about an axis of rotor tilt between a horizontal position and a vertical position;c. a ground module, said ground module and said air module being configured to be selectably attached one to the other, said first and second rotors in combination being configured to support said ground module and said air module in a flight when said ground module and said air module are attached, said first and second rotors in combination being configured to support said air module in said flight when said ground module and said air module are not attached;d. a first circular duct surrounding a periphery of said first rotor;e. a second circular duct surrounding said periphery of said second rotor, said first rotor in combination with said first circular duct defining a first ducted fan, said second rotor in combination with said second circular duct defining a second ducted fan, said first circular duct and said second circular duct defining a first and a second circular wing, said first and said second circular wings providing a lift to said air module when said air module is flying and said first and second rotor axes of rotation are in said horizontal position;f. a control system, said control system being configured to detect an aircraft condition of said air module during flight;g. a ballistic parachute configured to lower said air module or said ground module to a ground, said control system being configured to trigger said ballistic parachute if said control system detects said aircraft condition. 2. The personal air vehicle of claim 1, said ballistic parachute comprising: a parachute mortar attached to said air module or said ground module and configured to launch said ballistic parachute upon command by said control system, said parachute mortar being capable of pointing said ballistic parachute in a direction selected by said control system. 3. The personal air vehicle of claim 2 wherein said control system selects said direction for projection of said ballistic parachute to accommodate a motion of said air module or said ground module. 4. The personal air vehicle of claim 3 wherein said control system selects said direction to accommodate an attitude of said air module or said ground module. 5. The personal air vehicle of claim 3 wherein said control system is configured to continuously monitor said motion and said attitude and to continuously select said direction and to point said parachute mortar based on said motion and said attitude. 6. The personal air vehicle of claim 1, said ballistic parachute comprising: a steerable rocket attached to said air module or said ground module and configured to launch said ballistic parachute upon command by said control system. 7. The personal air vehicle of claim 6 wherein said control system is configured to select a direction for launch of said ballistic parachute to accommodate a motion and an attitude of said air module or said ground module. 8. The personal air vehicle of claim 7 wherein said control system is configured to steer said rocket in said selected direction. 9. The personal air vehicle of claim 1, the personal air vehicle further comprising: an air bag, said air bag being attached to a bottom side of said ground module, said air bag being configured to inflate and to slow an impact between said ground module and a ground. 10. The personal air vehicle of claim 9, further comprising: a landing gear, said landing gear being attached to said ground module, said landing gear being configured to absorb said impact remaining after inflation of said air bag to protect an occupant of said ground module. 11. A personal air vehicle apparatus, the apparatus comprising: a. an air module;b. at least one rotary wing operably attached to said air module, said at least one rotary wing comprises a first rotor and a second rotor, said first rotor having a first rotor axis of rotation, said second rotor having a second rotor axis of rotation, said first and second rotor axes of rotation being selectably tiltable about an axis of rotor tilt between a horizontal position and a vertical position;c. a ground module, said ground module and said air module being configured to be selectably attached one to the other, said at least one rotary wing being configured to support said ground module and said air module in a flight when said ground module and said air module are attached, said rotary wing being configured to support said air module in said flight when said ground module and said air module are not attached;d. a first circular duct surrounding a periphery of said first rotor;e. a second circular duct surrounding said periphery of said second rotor, said first rotor in combination with said first circular duct defining a first ducted fan, said second rotor in combination with said second circular duct defining a second ducted fan, said first circular duct and said second circular duct defining a first and a second circular wing, said first and said second circular wings providing a lift to said air module when said air module is flying and said first and second rotor axes of rotation are in said horizontal position;f. a first wing extension and a second wing extension, said first wing extension being attached to said first circular duct, said second wing extension being attached to said second circular duct, said first and second wing extensions providing said lift to said air module when said air module is flying with said first and second rotor axes of rotation are in said horizontal position;g. a control system, said control system being configured to detect an aircraft condition of said air module during flight;h. a ballistic parachute configured to lower said air module or said ground module to a ground, said control system being configured to trigger said ballistic parachute if said control system detects said aircraft condition. 12. The personal air vehicle of claim 11, said ballistic parachute comprising: a parachute mortar attached to said air module or said ground module and configured to launch said ballistic parachute upon command by said control system, said parachute mortar being capable of pointing said ballistic parachute in a direction selected by said control system. 13. The personal air vehicle of claim 12 wherein said control system selects a direction for projection of said ballistic parachute to accommodate a motion of said air module or said ground module. 14. The personal air vehicle of claim 13 wherein said control selects said direction based on an attitude of said air module or said ground module. 15. The personal air vehicle of claim 14 wherein said control system is configured to continuously monitor said motion and said attitude of said air module and to point said parachute mortar based on said motion and said attitude. 16. The personal air vehicle of claim 11, said ballistic parachute comprising: a steerable rocket attached to said air module or said ground module and configured to launch said ballistic parachute upon command by said control system. 17. The personal air vehicle of claim 16 wherein said control system is configured to steer said steerable rocket to accommodate a motion and an attitude of said air module or said ground module. 18. The personal air vehicle of claim 11, the personal air vehicle further comprising: an air bag, said air bag being attached to a bottom side of said ground module, said air bag being configured to inflate and to slow an impact between said ground module and a ground. 19. The personal air vehicle of claim 18, further comprising: a landing gear, said landing gear being attached to said ground module, said landing gear being configured to absorb said impact remaining after inflation of said air bag to protect an occupant of said ground module.

이 특허에 인용된 특허 (28)

이 특허를 인용한 특허 피인용횟수: 8

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Modular and morphable air vehicle

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Modular and morphable air vehicle

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