A space vehicle has a frame with a configuration of fiber optic gyroscopes (FOGs) and control moment gyroscopes (CMGs) at the outer perimeter of the frame. The FOGs and CMGs provide guidance and control for the space vehicle. This arrangement results in the largest possible FOG and CMG diameters, and therefore yielding the highest signal sensitivities and precision inertial control of vehicle orientation and pointing. Because the configuration places these guidance and control system components at the perimeter of the vehicle, it also provides a platform for multi-aperture signal channels in the interior of the vehicle by freeing up volume within the vehicle.