Abstract: A radiation shielding structure or vault includes an outer wall and an inner wall. The outer wall includes at least one outer wall panel formed into a cylinder shape having an outer wall opening. The inner wall includes at least one inner wall panel formed into a cylinder shape having an inner wall opening aligned with the outer wall opening. Tie rods secure the inner wall to the outer wall to support and hold the spacing between the walls. A tunnel structure is inside the inner wall opening and the outer wall opening. A radiation shielding door is coupled to the tunnel structure. A radiation shielding filler material is disposed in between the outer wall and the inner wall.

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract: A radiation shielding structure or vault includes an outer wall and an inner wall. The outer wall includes at least one outer wall panel formed into a cylinder shape having an outer wall opening. The inner wall includes at least one inner wall panel formed into a cylinder shape having an inner wall opening aligned with the outer wall opening. Tie rods secure the inner wall to the outer wall to support and hold the spacing between the walls. A tunnel structure is inside the inner wall opening and the outer wall opening. A radiation shielding door is coupled to the tunnel structure. A radiation shielding filler material is disposed in between the outer wall and the inner wall.

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract: A fuel feed system for a rotary-winged aircraft includes a fuel feed line extending from a fuel source to an engine and an engine fuel suction pump disposed at the fuel feed line to urge a flow of fuel through the fuel feed line to the engine. A collector is located along the fuel feed line between the fuel source and the engine to collect air-vapor bubbles which form in the flow of fuel. An air-vapor line extends from the top of the collector and merges with the fuel line section between the collector and the engine fuel pump. The air-vapor line is sized and configured to limit the flow of air-vapor from the collector to the engine fuel suction pump to a rate which the engine fuel suction pump can tolerate.