Equations of motion of the airplane subject to the influence of cross wind, rudder steering, and drag chute, during runout, are developed which would be valid even when the direction-of-travel angle and the yaw angle are large. A procedure of synthesizing the runout path step by step explicitly is presented. A flight vehicle capable of orbiting around the earth usually does not have ground steering capability because its weight has to be held to a minimum. This study will enable a designer to determine whether or not the vehicle will have inherent stability to land on a runway.

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