Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.

Abstract: An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.

Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.

Abstract: A pilot for a scramjet provides a flame front whose arrival at the wall of the scramjet combustor is delayed thereby reducing combustor heat load. By combining in-stream injection of fuel with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor center. This concept, referred to as “core-burning,” further reduces combustor heat load. One such pilot is for a two dimensional scramjet effective to propel a vehicle. This pilot includes a plurality of spaced apart struts separated by ducts and a strut pilot contained within each strut. A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake, an open bore scramjet isolator and a scramjet combustor. This centerbody pilot pod includes a pilot isolator disposed between the air intake and a pilot diffuser, the pilot diffuser disposed between the pilot isolator and a pilot with the pilot disposed between the pilot diffuser and a pilot combustor.

Abstract: An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.

Abstract: Augmentation of the thrust achieved by a supersonic nozzle of continuous curvature is achieved by causing secondary combustion to occur in an annular region of the interior of the divergent section of the nozzle. The secondary combustion forms a secondary combustion gas that complements the primary combustion gas passing through the nozzle and maintains a wall pressure that is equal to or greater than ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.

Abstract: Augmentation of the thrust achieved by a supersonic nozzle of continuous curvature is achieved by causing secondary combustion to occur in an annular region of the interior of the divergent section of the nozzle. The secondary combustion forms a secondary combustion gas that complements the primary combustion gas passing through the nozzle and maintains a wall pressure that is equal to or greater than ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.

Abstract: A transpiration cooling system for avoiding overheating of an airfoil is provided. The airfoil is provided with a plurality of apertures and a source of pressurized fluid for providing a flow of fluid through the apertures to establish an aerodynamic radius. The aerodynamic radius of curvature of leading edge is sufficiently greater than the mechanical radius of curvature of the leading edge that peak heat flux is independent of the mechanical radius of curvature. The mechanical radius of curvature is preferably less than 50% of the aerodynamic radius of curvature during hypersonic operation. Preferably the mechanical radius of curvature is the smallest allowed by the fabrication method (i.e., a knife edge), such as being less than about 0.02 inches, preferably less than about 0.01 inches. The transpiration blowing rate can be adjusted so that the blowing rate and aerodynamic radius of curvature are relatively low except during periods of maximum heat flux, such as the shock-on-lip point.

Abstract: A transpiration cooling system for avoiding overheating of an airfoil is provided. The airfoil is provided with a plurality of apertures and a source of pressurized fluid for providing a flow of fluid through the apertures to establish an aerodynamic radius. The aerodynamic radius of curvature of leading edge is sufficiently greater than the mechanical radius of curvature of the leading edge that peak heat flux is independent of the mechanical radius of curvature. The mechanical radius of curvature is preferably less than 50% of the aerodynamic radius of curvature during hypersonic operation. Preferably the mechanical radius of curvature is the smallest allowed by the fabrication method (i.e., a knife edge), such as being less than about 0.02 inches, preferably less than about 0.01 inches. The transpiration blowing rate can be adjusted so that the blowing rate and aerodynamic radius of curvature are relatively low except during periods of maximum heat flux, such as the shock-on-lip point.

Abstract: An improved ejector ramjet includes a nozzle and propulsion duct. The nozzle has first and second sides, which are preferably two-dimensional, and produces a primary fluid jet which causes secondary fluid to be entrained in the propulsion duct. The primary jet is oscillated providing energy exchange between the primary and secondary fluids in the propulsion duct in a substantially non-viscous fashion.

Abstract: A scramjet fuel injector of the type mounted flush to the wall of a combustor through which air flows is provided. The injector includes a generally elongated body including a surface substantially flush with the wall, the surface having a proximate end and a distal end, the proximate end encountering air into which the fuel is to be injected before the distal end. The fuel injector further includes at least one fuel inlet port connected to the body, at least one fuel exit port in the surface substantially flush with the wall, and at least one throat internal to the body through which fuel serially passes after passing through the inlet ports and before passing through the exit ports. This arrangement of the fuel exit ports and throats combine to create and maintain a substantially streamlined supersonic fuel jet plume shape having exit pressure locally matched with the flowing air.

Abstract: An improved ejector ramjet includes a nozzle having first and second sides, preferably two-dimensional, the nozzle producing a primary fluid jet which causes secondary fluid to be entrained in the engine. The improvement includes means for linearly oscillating the primary jet in a propulsion duct downstream from the primary nozzle, allowing energy exchange between primary and secondary fluids in a substantially non-viscous fashion.

Abstract: An armament system provides a launch tube filled with a mixture of gaseous propellant and a projectile possessing an external surface configuration which is effective to initiate a ram jet effect between the external surface of said projectile and the inner wall of said launch tube when said projectile is inserted at a high velocity into and along said tube.

Abstract: This invention provides a liquid propellant round of ammunition having a traveling charge which is ignited after both such charge and the projectile have received an initial forward acceleration.

Abstract: A feature of this invention is the provision of an ignition mechanism for a main combustion chamber including an ignition antechamber having a first cross-sectional area, an electrode, and an inlet port for liquid propellant; a conduit having a length over diameter ratio greater than one, a second cross-sectional area which is less than said first area, and an inlet which opens into said ignition antechamber and an outlet which opens through an orifice into said main combustion chamber.

Abstract: This invention provides an annular piston, annular control valve, liquid propellant gun system, having a dual angle injection mechanism to provide both bore and chamber gas requirements with a single injection control valve. The dual angle feature assures a stable combustion zone. A flexible lip on the projectile is used in conjunction with the dual angle injection mechanism to positively eliminate backflow of propellant through the injection mechanism during the ignition phase of the gun cycle.

Abstract: A feature of this invention is the provision in an annular piston, annular control valve, liquid propellant gun, of a check valve to permit liquid propellant under relatively low pressure to flow from the supply system into the combustion chamber and to preclude the pulse of pressure generated in the combustion chamber from feeding back to the supply system. This valve allows propellant to be removed automatically from the pumping chamber in the event of a misfire.Another feature of this invention is the provision in an annular piston, annular control valve, liquid propellant gun of a frangible stem which secures the projectile to the cartridge case. The stem breaks to release the projectile for travel down the gun bore when a predetermined level of combustion gas pressure has been developed in the combustion chamber.

Abstract: A gun is provided having a housing, a main gun barrel, a combustion chamber, a liquid propellant pumping chamber, and valve means for providing a variable orifice injection port intercoupling said pumping and combustion chambers which includes means for controlling the rate of opening of the orifice during the period of injection.

Abstract: This invention provides an annular piston, annular control valve, liquid propellant gun system, having a dual angle injection mechanism to provide both bore and chamber gas requirements with a single injection control valve. The dual angle feature assures a stable combustion zone. A flexible lip on the projectile is used in conjunction with the dual angle injection mechanism to positively eliminate backflow of propellant through the injection mechanism during the ignition phase of the gun cycle.

Abstract: This invention provides a liquid propellant round of ammunition having a traveling charge which is ignited after both such charge and the projectile have received an initial forward acceleration.