## Fixed-base Visual-simulation Study of Manually Controlled Operation of a Lunar Flying Vehicle |

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0.2°/sec rate deadband 500-foot-altitude acceleration altitude Angular acceleration approximately 150 feet Arithmetic mean Standard attitude control system average characteristic velocity average cruise velocity basic instrumentation body axes Center-of-gravity displacements center-of-gravity offsets characteristic velocity requirements closed-circuit television control characteristics deceleration phase deg/sec degrees of freedom desired landing deviation 0.2°/sec rate direction cosines displacement from take-off equations of motion feet 45.7 meters field of view fixed-base visual-simulation study fixed-reference flat-top trajectory flights were performed ft/sec m/sec horizontal-velocity indicators indicators were included Langley Research Center lunar flying vehicle lunar surface lunar thrust-weight ratio mean Standard deviation miss distance moments of inertia moving-reference near-hover conditions nearly zero Parameter Arithmetic mean pilot's task quaternions rate-command attitude control simulation equipment Standard deviation 0.2°/sec system with origin take-off point target crater terrain model three-axis gyro-horizon throttle deflection touchdown conditions touchdown velocities typical flight performed velocity indicators vertical-velocity indicators VH,c Xi displacement