This paper deals with a thrust generation method which can be applied to nuclear as well as chemical propulsion systems. It takes into consideration both incompressible and compress-ible flow cases, however both of these cases are based on one dimensional flow within an ideal rocket framework.In the case of constant area duct steady state flow the obtained Induced Thrust (IT) formula is: where p1 and p2 are opposing pressure fields and u* is a function of u2, p2 and u1 (u1 and u2 being opposing gas efflux velocities). For the compressible and incompressible flow fields, IT formulas are obtained but they are not as reliable.One feasible application for this launch-propulsion method is the Joined-Ship model. In this model the combustion chamber pressure within one space vehicle acts as the back pressure of the joined space vehicle and vice-versa. When the adaptive shroud that connects the two vehicles separates, the impulse resulting from plume impingement generated by the individual vehicles moving in opposite directions gives rise to the extra force which makes (IT) exceed ordinary thrust; that is thrust obtained from the two vehicles if their combustion chambers were fired individually (unlike the Joined -Ship model where the space ships are initially connected).The mathematical algorithm used to analyze the concept presented in this paper is original to the best of the author's knowledge.