초록 ▼

A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a dri

A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a drive train apparatus, optional single or multiple power means; congruously connected thereto horizontal thrust devices. Integral to the vertical lift devices; pitch axis control devices situated at the exhaust orifices therein to vector said devices exhaust slip stream by a autonomous flight control system providing pitch stability. The autonomous flight control system providing continuously all flight control of the apparatus and said system being interfaced to a semiautonomous flight director device providing discrete flight direction function codes thereto. The combined effect of the apparatus is: When the power system rotates; coincident rotation of the drive train causes the vertical lift apparatus and horizontal thrust apparatus to counter rotate at right angles simultaneously providing both vertical lift and gyroscopic roll stability and simultaneously providing both horizontal thrust and gyroscopic yaw stability during flight; the continuous control thereof being accomplished by the autonomous flight control system and the directional steering, and function thereof in four axis effected by the semiautonomous flight director device which provides discrete flight function codes to the autonomous flight control system so as to disallow the initiation of negative flight maneuvers and/or functions providing for the safe unskilled pilot operation of the apparatus or any aircraft employing a autopilot having a autonomous digital flight control system.

대표청구항 ▼

[ It is claimed:] [1.] An aircraft comprising: a body having a front end, a rear end, two opposite facing sides, a top end, and a bottom end, a longitudinal axis extending between said front and rear ends, front and rear openings extending through said body transverse to said longitudinal axis and b

[ It is claimed:] [1.] An aircraft comprising: a body having a front end, a rear end, two opposite facing sides, a top end, and a bottom end, a longitudinal axis extending between said front and rear ends, front and rear openings extending through said body transverse to said longitudinal axis and between said top and bottom ends, front and rear ducts defining said front and rear openings respectively with each of said ducts having top bottom ends, front and rear propeller means located in said front and rear openings for rotation about the front and rear axes respectively transverse to said axis, drive means extending along said longitudinal axis and coupled to said front and rear propeller means for rotating said front and rear propeller means in opposite directions to provide lift, and movable vanes located in line with said front and rear openings below said front and rear propellers for controlling the direction of air flow from said front and rear openings, said vanes extending in directions transverse to said longitudinal axis and transverse to said front and rear axes respectively at least one of said vanes is located below said front propeller means near an extension of its axis and has a length nearly equal to the maximum diameter of said front annular duct, at lease one of said vane is located below said rear propeller means near an extension of its axis and has a length nearly equal to the maximum diameter of said rear annular duct.