This demonstration models a flight control for the longitudinal motion of a Grumman Aerospace F-14 Tomcat. First order linear
approximations of the aircraft and actuator behavior are connected to an analog flight control design that uses the pilot s
stick pitch command as the set point for the aircraft s pitch Attitude and uses aircraft pitch angle and pitch rate to determine commands. A simplified Dryden wind gust model is incorporated to perturb the system.
This paper deals with the issue of incorporating pseudolite measurements into an integrated Global Positioning System/
Inertial Navigation System ~GPS/INS! positioning and Attitude system with a view to improving signal availability, solution reliability, and
accuracy in a localized area
This paper provides a rigorous comprehensive approach to the design of the principal software
algorithmsutilized inmodern-day strapdown inertial navigationsystems: integration of angular rate into Attitude,
acceleration transformation/integration into velocity, and integration of velocity into position.
