Abstract: The present invention provides a method of maintaining fan airflow at 100% for throttle transients from 100% military power to 30% thereof by increasing exhaust nozzle area as the fuel flow the engine decreases until the exhaust nozzle reaches its fully open position. Subsequent reductions in fuel flow produce a commensurate reduction fan airflow.

Abstract: A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelope and does maintain higher compressor rpm, turbine inlet temperature, and engine air flow at the idle or part power thrust settings by concomitantly adjusting fuel flow and engine exhaust nozzle area thereby enhancing thrust response, low cycle fatigue life, and engine stability.

Abstract: The present invention pertains to an apparatus to improve the efficiency and performance of an aerodynamic lift structure for use on sailing devices. A two-sided, spaced apart sail structure is provided with resiliently deformable struts for each side, attached at one end to a beam, fixed to the mast of the sailing device, the mast being rotatable about its vertical axis in either direction relative to vertical planes along the longitudinal axes of the sailing device and the boom in a manner whereby a cam action is produced by the beam to deform or bend the struts in a manner so as to vary the camber of the wing sail, the amount of camber of one side of the wing sail being greater than the concave curvature of the opposed side thus producing an airfoil configuration.