Abstract: In a valve control unit for a ram jet propulsion system having a power unit space a valve for controlling a fuel quantity required to the propulsion system, and a valve adjusting unit which is constructed to be operable by means of an electronic control unit, the valve is combined with its valve adjusting unit and its electronic control unit to form a thermally insulated valve assembly. The valve assembly is configured for the arrangement in the power unit space.

Abstract: In a valve control unit for a ram jet propulsion system having a power unit space a valve for controlling a fuel quantity required to the propulsion system, and a valve adjusting unit which is constructed to be operable by means of an electronic control unit, the valve is combined with its valve adjusting unit and its electronic control unit to form a thermally insulated valve assembly. The valve assembly is configured for the arrangement in the power unit space.

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.