The inverse snlution problem of vehicle motion in maneuvering flight is discussed in which the control inputs can be determined su as to enable a vehicle to perform a specified maneuver. For a nonlinear dynamic system such as a helicopter, imprnviug the mathematical model of helicopter maneuvering flight and the corresponding solution technique is one of the most complex and challenging problems in applied mechanics. In this paper a set of nonlinear equations governing the helicopter in maneuvering flight is developed and solved by using a new iuverse solution technique. The inverse solution technique is improved to emphasize nonlineaedy and good stability and convergence of the sample calculations of level turn, lateral jink, and pup-up maneuvers for twn kinds of helicopters. Beginning with a set of prescribed flight conditions, this inverse solution calculates the flight path, velocity, and other kinematic parameters first, and then the control inputs, flight altitude, and the load factor for the specified maneuver.