Abstract: An aircraft including a support structure, an outer skin connected to the support structure, a first port extending through the outer skin and defining a first break in the support structure. The aircraft also includes a first receptacle attached to the support structure proximate the first port and defining a first opening, a ball-mounted sensor assembly received in the first receptacle and extending downward from the outer skin, a second port extending through the outer skin and defining a second break in the support structure, a second receptacle attached to the support structure proximate the second port and defining a second opening. A method of retrofitting an aircraft to accommodate a ball-mounted sensor assembly and a payload is also disclosed.

Abstract: An aircraft includes a fuselage, an engine exhaust port extending through the fuselage, an air intake extending through the fuselage forward from, and adjacent to, the engine exhaust port, and an air cleaning assembly positioned over the air intake. The aircraft also includes a pressure recovery device including an outer wall positioned above the air cleaning assembly. A distance from a forward edge of the outer wall to the air cleaning assembly is greater than a distance from an aft edge of the outer wall to the air cleaning assembly. An inlet flow axis is defined normal to a cross-sectional flow area of the pressure recovery device at the forward edge, and is oriented upward at an acute angle relative to a longitudinal axis of the aircraft.

Abstract: An aircraft includes a fuselage, an engine exhaust port extending through the fuselage, an air intake extending through the fuselage forward from, and adjacent to, the engine exhaust port, and an air cleaning assembly positioned over the air intake. The aircraft also includes a pressure recovery device including an outer wall positioned above the air cleaning assembly. A distance from a forward edge of the outer wall to the air cleaning assembly is greater than a distance from an aft edge of the outer wall to the air cleaning assembly. An inlet flow axis is defined normal to a cross-sectional flow area of the pressure recovery device at the forward edge, and is oriented upward at an acute angle relative to a longitudinal axis of the aircraft.

Abstract: An aircraft has an outer skin defining a contour and an air intake assembly including an air cleaning assembly. The air cleaning assembly includes an exterior surface that conforms to the contour of the aircraft, and a lip secured to the outer skin. The air intake assembly includes a pressure recovery device including a flange secured to the lip of the air cleaning assembly, and also includes an outer wall spaced from the exterior surface of the air cleaning assembly.

Abstract: An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port. The receptacle includes an opening defined therein. The aircraft further includes a removable payload assembly coupled within the receptacle opening, and a pressure ring configured to form a seal between an inner surface of the receptacle and an outer surface of the payload assembly.

Abstract: An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port. The receptacle includes an opening defined therein. The aircraft further includes a removable payload assembly coupled within the receptacle opening, and a pressure ring configured to form a seal between an inner surface of the receptacle and an outer surface of the payload assembly.

Abstract: An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port. The receptacle includes an opening defined therein. The aircraft further includes a removable payload assembly coupled within the receptacle opening, and a pressure ring configured to form a seal between an inner surface of the receptacle and an outer surface of the payload assembly.

Abstract: An aircraft includes a support structure, an outer skin coupled to the support structure, and a port that defines a break in the support structure and extends through the outer skin. The aircraft also includes a receptacle coupled to portions of the support structure proximate the port, such that the receptacle routes at least a portion of the load borne by the support structure around the break defined by the port. The receptacle includes an opening defined therein. The aircraft further includes a removable payload assembly coupled within the receptacle opening, and a pressure ring configured to form a seal between an inner surface of the receptacle and an outer surface of the payload assembly.

Abstract: A door assembly for mounting on an aircraft includes a rail mounted exteriorly to an outer skin of the aircraft, and a door movably coupled to the rail. The door assembly also includes a motor mountable in an interior of the aircraft, and a shaft extending through a sealed shaft port in the outer skin of the aircraft. The shaft couples the motor to the door, such that the door is movable between a first position and a second position along an outer moldline of the aircraft.

Abstract: A door assembly for mounting on an aircraft includes a rail mounted exteriorly to an outer skin of the aircraft, and a door movably coupled to the rail. The door assembly also includes a motor mountable in an interior of the aircraft, and a shaft extending through a sealed shaft port in the outer skin of the aircraft. The shaft couples the motor to the door, such that the door is movable between a first position and a second position along an outer moldline of the aircraft.

Abstract: An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater.

Abstract: A barrier filter for use in an helicopter to remove contaminants from intake air prior to delivery to an engine. The helicopter has an intake and a peripheral external surface adjacent to the intake. The filter includes a pleated filter element mounted flush across the intake such as to meet the contour of the peripheral external surface. The filter element comprises a porous filter media and having a surface area such that a calculated speed of air flowing through the filter, when the engine is operating at take off power (TOP) or military intermediate rated power (IRP), is less than about 30 ft/sec. The filter may be retrofit into helicopters having other contaminant removal systems. Preferably, the filter is positioned such that intake air is delivered to the engine at a pressure which is substantially independent of whether the helicopter is moving in a forward direction or hovering with no forward motion.

Abstract: A barrier filter for use in an helicopter to remove contaminants from intake air prior to delivery to an engine. The helicopter has an intake and a peripheral external surface adjacent to the intake. The filter includes a pleated filter element mounted flush across the intake such as to meet the contour of the peripheral external surface. The filter element comprises a porous filter media and having a surface area such that a calculated speed of air flowing through the filter, when the engine is operating at take off power (TOP) or military intermediate rated power (IRP), is less than about 30 ft/sec. The filter may be retrofit into helicopters having other contaminant removal systems. Preferably, the filter is positioned such that intake air is delivered to the engine at a pressure which is substantially independent of whether the helicopter is moving in a forward direction or hovering with no forward motion.