United States Patent US007249732B2 (12) (10) Patent N0.: US 7,249,732 B2 Sanders, Jr. et al. (45) Date of Patent: Jul. 31, 2007 (54) AERODYNAMICALLY STABLE, VTOL 3,110,456 A 11/1963 Creasey et a1. .......... .. 244/123 AIRCRAFT (Continued) (75) Inventors: John K. Sanders, Jr., Costa Mesa, CA OTHER PUBLICATIONS irltilelzniillillialfge33112222102111 http://WWW.aeromobile.c0rn/aer0m0bileivers2/GimbaliFan/ ’ ’ " ' b l f .htm. Beach, CA (US) gun a i an _ (Contrnued) (73) Assrgnee: UFOZ, LLC, Karlua, Oahu, HI (US) Primary ExamineriTimOthy D‘ Collins ( * ) Notice: Subject to any disclaimer, the term of this (74) Attorney’ Agent’ or FlrmiLelghton K‘ Chong patent is extended or adjusted under 35 U.S.C. 154(b) by 0 days. (57) ABSTRACT Ahover aircraft em lo 5 an air im eller en ine havin an air P y P g g (21) APP1~ NOJ 11/379,963 channel duct and a rotor With outer ends of its blades ?xed _ to an annular impeller disk that is driven by magnetic (22) Flled? APY- 24’ 2006 induction elements arrayed in the air channel duct. The _ _ _ air-impeller engine is arranged vertically in the aircraft (65) Pnor Pubhcatlon Data frame to provide vertical thrust for vertical takeoif and Us 2007/0034738 A1 Feb 15, 2007 landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyro Related US. Application Data scopic stability. An air vane assembly directs a portion of the (60) Division of application No. 10/763,973,‘ ?led on Jan. i?utiltrucsgggtoplgn? élofezllirgli agigal?eilovgrriigdgra 3211;521:222; 52’ 2:.)04inOZnPa; N011 719323851’ {65nd movement. The aircraft can employ a single engine in an 1m? 101211330030 app 10a Ion 0' ’ ’ e annular fuselage, tWo engines on a longitudinal fuselage on an‘ ’ ' chassis, three engines in a triangular arrangement for for Ward ?i t stabili , or other multi le en ine arran ements (51) Int. or. ‘y P g g B64C 15/00 (2006 01) in a symmetric, balanced con?guration. Other ?ight control (52) us. Cl. .................. .. 244/23 A- 244/121' 416/170 mechanisms. may be employed’ including Side wlnglets’ an 58 F M f Cl _? t_ s h ’ 244/1’2 1 12 3 overhead Wmg, and/or arr rudders or ?aps. An mtegrated ( ) 1e 0 assl ca Ion earc "" " ' T ' f ?ight control system can be used to operate the various ?ight 244/1712 60’ 23 R’ 23 A’ 23 B’ 1711f control mechanisms. Electric poWer is supplied to the mag 310/46’ 61T63’ 417/350’ 420’ 423'1’ 423'7’ netic induction drives by high-capacity lightweight batteries _ _ _ 416/170 or fuel cells. The hover aircraft is especially Well suited for See apphcanon ?le for Complete Search hlstory' applications requiring VTOL deployment, hover operation (56) References Cited for quiet surveillance, maneuvering in close air spaces, and Us. PATENT DOCUMENTS 2,077,471 A * 4/1937 Fink ........................ .. 244/123 2,943,816 A 7/1960 Hiller, Jr. .. 244/23 R 3,082,977 A * 3/1963 Arlin ..................... .. 244/1723 long duration ?ights for continuous surveillance of ground targets and important facilities requiring constant monitor ing. 17 Claims, 29 Drawing Sheets