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1. Field of the Invention
The present invention relates in general to inertial navigation systems (INS), and more
particularly to a kinematics equations integrator device and method for obtaining the
attitude of a vehicle from the closed-form integration of kinematics equations utilizing a
four-dimensional operator such that the magnitude of said four-dimensional operator is
always equal to unity.
2. Background Art
Inertial navigation systems (INS) are widely used in several flight vehicle applications such
as aircraft, missiles, spacecraft and satellites. These self-contained navigation systems
determine the attitude or position of the flight vehicle relative to some reference coordinate
frame. The INS works by integrating the angular velocity or rates of acceleration,
measured by onboard sensors, to obtain position with respect to a body-centered
coordinate frame.