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FUNDAMENTAL PROBLEMS OF MISSILE GUIDANCE
TERRESTRIAL AND CELESTIAL REFERENCES
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acceleration accuracy aerodynamic aircraft airframe altitude amplifier amplitude analog computer angle angle of attack angular antenna applied autopilot axis bandwidth beam beam-rider bolometer celestial celestial navigation circuit coefficient command components constant control surface curve detector determined device earth effect employed energy equation error factor flight path gain guidance equipment guided missile guided missile system gyroscope indicated infrared input interceptor interceptor aircraft Laplace transform launching line-of-sight loop loran magnetic maximum measured method missile guidance system modulation motion nautical miles navigation noise obtained operation oscillator output parameters percent phase phugoid pitch polar position problem pulse radar radiation radio waves radome range receiver reflected result rotation semiactive servo system servomechanism shown in Fig signal simulation slope specific tactical target temperature tests thermocouple tion tracking radar trajectory transfer characteristic transfer function transmission transmitted vector velocity vertical voltage wavelength zero