Abstract: It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself.

Abstract: It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself.

Abstract: In the cooling wall of a regenerative cooling rocket combustion chamber, the throat portion thereof in which the heat load is highest is formed of a porous material having a perspiring cooling action. The other portion in which the heat load is relatively low is designed to be cooled by conventional forced convection. By such a composite cooling system, a high cooling effect is provided and yet the pressure loss in the cooling passages is small and light weight and long life of the engine are attained concurrently.

Abstract: A method of producing rocket combustors wherein in forming an outer cylin by a powder metallurgical method on the outer side of a cylinder provided on its outer periphery with a cooling wall of channel construction having a plurality of grooves, a low-melting alloy is used as a filler to be filled into the grooves. It is also possible to form the outer cylinder after forming a Cu plating shell on the periphery of the inner cylinder filled with the low-melting alloy.

Abstract: The present invention is directed particularly to an improved method using owder metallurgy for the manufacture of the grooved cooling wall of a liquid-propellant rocket combustion chamber. The surface of an inner cylinder constituting the cooling wall is formed with cooling grooves, and these grooves are densely filled up with a filler such as paraffin wax. Thereafter, metal powder which will provide an outer cylinder is compression-molded to a predetermined thickness around the inner cylinder. This metal powder is the same material as the material of the inner cylinder. After the paraffin wax which is the filler is evaporated and removed, the compression-molded metal powder body is sintered in a furnace. During this sintering heat treatment, the inner and outer cylinders are rigidly joined together by the sintering reaction between the atoms of the inner cylinder and the atoms of the metal powder.