Abstract: A flight control system that provides energy management for an aircraft. The flight control system includes an energy control system which generates a first error signal that is a function of an actual energy characteristic and a threshold energy characteristic. The energy characteristic may be the bleed rate of the aircraft. The error signal is converted into a control surface command signal which moves the control surface(s) of the aircraft, accordingly. The control system limits the movement of the control surface(s) so that the actual energy characteristic does not exceed the threshold energy characteristic. The energy control system can be coupled to a nominal control system which generates a second error signal that is a function of a pilot input command and a feedback signal which is indicative of the present state of the aircraft. The second error signal can also be converted to a control surface command signal which moves the control surface(s) of the aircraft.

Abstract: A T-38 trainer aircraft that is modified to have the wings of an F-5 fighter aircraft. The F-5 wings have leading edge flaps which increase aircraft maneuverability and allow the plane to be landed at a lower speed. The F-5 wing is coupled to existing wing joints of the fuselage by fittings which increase the angle of incidence of the aircraft approximately 2.degree.. The increased angle of incidence provides the pilot with a greater over the cone field of view. The modified T-38 also has a pair of forward strakes located on the leading edge of the aircraft nacelles. The forward strakes further increase the performance of the plane. Attached to the tail of the aircraft are a pair of aft strakes which counteract the pitch created by the forward strakes.

Abstract: An engine inlet having strakes for landing speed reduction on a trapezoidal wing shaped aircraft, specifically the T-38. The strakes are mounted on the engine inlet just forward of the wing leading edge and well above the wing plane. The preferred strakes have an area greater than 3% of the wing area and are uncanted with respect to the wing. Use of the strakes forstalls wing buffet, yet exhibits well behaved longitudinal stability at high angles of attack thereby allowing operation of the aircraft at higher angles of attack and associated higher coefficients of lift, such as during landing, resulting in a reduction of the landing speed of the aircraft. Various strakes in the placement thereof are disclosed.