Abstract: A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or (iii), under certain emergency operating conditions; and, wherein the air inlet for such center boost engine is located at the root leading edge of the aircraft's vertical stabilizer.

Abstract: An improved jet engine two dimensional, asymmetric afterburner nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its low profile configuration, simplicity of construction, and lack of interference with, or excessive intrusion into, the wing spar structural space within the airfoil; yet, which permits minimization of the included angle between the wing chord reference plane and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified two dimensional, asymmetric convergent or CD nozzle construction, and an actuating mechanism therefore, which avoids the necessity to devote critical wing spar structural space to pneumatic load or pressure balance chambers, and wherein the nozzle may be shifted to a dry nozzle position--i.e.

Abstract: An improved pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its simplicity of construction, ease and reliability of operation, and improved simplified sealing characteristics; yet, which permits substantial reduction of the included angle between the wing chord reference plane WCRP and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle construction which permits of simplified, highly effective sealing arrangements and wherein when the nozzle is shifted to a dry nozzle position--i.e., the cruise position--the trailing edge line-of-sight into the nozzle is maintained at a minimum angle, preferably on the order of from about 5.degree. to about 10.degree.

Abstract: A retractable/deployable nozzle fairing for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the center boost engine's exhaust nozzle and reducing the diameter of the empennage outlet when deployed so as to minimize the base drag characteristics of the empennage body structure when the center boost engine is shut down. More particularly, an exhaust nozzle retractable/deployable fairing for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations, and/or (iii), under certain emergency operating conditions; and, wherein the retractable/deployable fairing member is formed of flexible sheet material that is fabricated into a truncated generally conical nozzle configuration--i.e.

Abstract: Combination primary and fan air thrust reversal control systems for long duct fan jet engines are disclosed. In one form, the system spoils and expands primary air and, then, allows the spoiled, expanded air to exit from the fan air duct exhaust nozzle while directing fan air in a thrust reversal direction out cascade vanes circumferentially located in the aft portion of the engine nacelle. In other forms, the system directs unequal pressure fan air and primary air through separate thrust reversal ducting and out cascade vanes circumferentially located in the engine nacelle. In equal pressure fan air and primary air systems, the air may be mixed in ducting prior to being emitted from common cascade vanes, or may be maintained separate prior to emission. In still other forms, the primary air is pre-exhausted through separate nozzles located in the primary duct wall, and a portion is then exhausted through the nacelle cascade vanes.