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able to control acceleration aerodynamic-control moment coupling altitude analog computer angle of attack angle-of-attack error indicator angular motions atmospheric entries attempt to damp body axis characteristics cockpit coefficient control effectiveness control moment coupling control motions control the vehicle cross-controlling damping ratio deceleration reached divergence earth's atmosphere entry angle equations establish and maintain Euler Angle feet per second finger-tip ft/sec g units inertia inertia coupling l/2 standard l/radian Langley Research Center maximum deceleration pilot was able piloted entries Piloting task pitch and roll pitch control positive yawing pounds per square pulse rate of descent reaction control damping reaction-control effectiveness reference roll and pitch roll and yaw roll control satellite vehicle sec2 seconds the pilot shown in figure simulated entries square foot stability derivatives stability in yaw standard damping static stability tests three axes value of deceleration vehicle dynamics velocity winged-satellite vehicle yaw angle zero angle-of-attack error zero damping