Abstract
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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