Abstract: An ignition system (10) includes a fuel injection opening (30), a fuel reforming device (70), an ignition gas injection opening (50) and an ignition gas supply passage (52). The fuel injection opening (30) injects the hydrocarbon fuel into the combustion chamber (20). The fuel reforming device (70) reforms the hydrocarbon fuel to the ignition gas which ignites automatically through contact with the oxidizing agent. The ignition gas injection opening (50) injects the ignition gas into the combustion chamber (20). The ignition gas supply passage (52) supplies the ignition gas to the ignition gas injection opening (50) from the fuel reforming device (70).

Abstract: A rocket engine has fuel passage of pipes 31-39, a catalyst section 51, a turbine 12, a first pump 11, a combustion chamber 21 and a nozzle 22. The fuel passage of pipes 31-39 supply the hydrocarbon fuel. The catalyst section 51 is provided on the way of the fuel passage of pipes 31-39 to gasify the fuel. The turbine 12 is driven with the gasified fuel. The first pump 11 supplies the fuel to the fuel passage of pipes 31-39 through the drive by the turbine 12. The combustion chamber 21 combusts the gasified fuel supplied from the fuel passage of pipes 31-39 and the oxidizer. The nozzle 22 sends out the combustion gas from the combustion chamber 21, and it is heat-exchanged with a part of the fuel passage of pipes 31-39.

Abstract: A manufacturing method of a turbine nozzle is provided. The method includes: (A) forming a first part which includes a blade and one of an inner ring portion and an outer ring portion integrated therein; (B) forming the other of the inner ring portion and the outer ring portion as a second part; (C) combining the first part and the second part such that an outer side surface of the inner ring portion and an inner side surface of the outer ring portion are arranged to oppose each other and that a gap is formed between the blade of the first part and the second part; and (D) flowing a brazing material in a molten state into the gap to braze the blade of the first part and the second part.

Abstract: A flying object capable of being launched in air is detachably mounted on a wing body of a launching apparatus. The launching apparatus is towed by an aircraft through a cable so as to be run and taken off. After raising the launching apparatus to a launching height of the flying object by the aircraft, the flying object is released from the wing body in air and then the flying object is ignited and launched in air in a launching system. The system for launching in air can be developed without newly developing a platform as a mother ship so that a research cost can be remarkably reduced. In the case that a small artificial satellite is installed in a flying object, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation.

Abstract: A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

Abstract: A flying object capable of being launched in air is detachably mounted on a wing body of a launching apparatus. The launching apparatus is towed by an aircraft through a cable so as to be run and taken off. After raising the launching apparatus to a launching height of the flying object by the aircraft, the flying object is released from the wing body in air and then the flying object is ignited and launched in air in a launching system. The system for launching in air can be developed without newly developing a platform as a mother ship so that a research cost can be remarkably reduced. In the case that a small artificial satellite is installed in a flying object, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation.

Abstract: A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.