Earth off|nadir pointing technology can be used on a small satellite to provide larger nadir earth surface imaging coverage. In this paper, the satellite attitude dynamics equations including the gravity|gradient torque and wheel motor torque are derived using Euler parameters. The necessary conditions for optimum solutions subject to the performance index are obtained via Pontryagin’s principle. The resulting two|point boundary value problem is solved numerically with an optimal slew illustrated by example.  Earth off | nadir pointing technology can be used on a small satellite to provide larger nadir earth surface imaging coverage. In this paper, the satellite attitude dynamics equations including the gravity | gradient torque and wheel motor torque are derived using Euler parameters The necessary conditions for optimum solutions subject to the performance index are derived via Pontryagin’s principle. The resulting two | point boundary value problem is solved numerically with an optimal slew illustrated by example. 