An apparatus comprising a space vehicle, the apparatus comprising: a steering law module to: calculate a first set of vectors including a first nominal vector pointing from the space vehicle to a target in an inertial reference frame, and a second nominal vector from a center of gravity of the space vehicle to a power source, and wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body; calculate a vector normal to the projected first and second nominal vectors and an angle between the projected vectors to determine when a singularity occurs as the angle between the projected nominal vectors approaches 0 degrees or 180 degrees; and calculate, when the singularity occurs, a second set of vectors, based on projecting the first set of vectors onto an orbital fixed frame plane, including an alternate primary vector, an alternate secondary vector, and an alternate normal vector; and an attitude controller configured to generate an attitude command based on the first set of vectors when it is determined the singularity does not occur, and based on the second set of vectors when it is determined that the singularity occurs, the attitude controller configured to transmit the attitude command to actuators of the space vehicle to maneuver the space vehicle between space vehicle orbital paths and/or orbital heights, in which the attitude controller generates the attitude command based on the first and/or the second set of vectors to prevent an unplanned rotation by the space vehicle. a steering law module to: calculate a first set of vectors including a first nominal vector pointing from the space vehicle to a target in an inertial reference frame, and a second nominal vector from a center of gravity of the space vehicle to a power source, and wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body; calculate a vector normal to the projected first and second nominal vectors and an angle between the projected vectors to determine when a singularity occurs as the angle between the projected nominal vectors approaches 0 degrees or 180 degrees; and calculate, when the singularity occurs, a second set of vectors, based on projecting the first set of vectors onto an orbital fixed frame plane, including an alternate primary vector, an alternate secondary vector, and an alternate normal vector; and calculate a first set of vectors including a first nominal vector pointing from the space vehicle to a target in an inertial reference frame, and a second nominal vector from a center of gravity of the space vehicle to a power source, and wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body; calculate a vector normal to the projected first and second nominal vectors and an angle between the projected vectors to determine when a singularity occurs as the angle between the projected nominal vectors approaches 0 degrees or 180 degrees; and calculate, when the singularity occurs, a second set of vectors, based on projecting the first set of vectors onto an orbital fixed frame plane, including an alternate primary vector, an alternate secondary vector, and an alternate normal vector; and an attitude controller configured to generate an attitude command based on the first set of vectors when it is determined the singularity does not occur, and based on the second set of vectors when it is determined that the singularity occurs, the attitude controller configured to transmit the attitude command to actuators of the space vehicle to maneuver the space vehicle between space vehicle orbital paths and/or orbital heights, in which the attitude controller generates the attitude command based on the first and/or the second set of vectors to prevent an unplanned rotation by the space vehicle. <EOS>