Mitsubishi Heavy Industries Limited

Shozo Hidaka

Kensuke Futahashi

Mitsuru Inada

Atsushi Moriwaki

Masaaki Nagase

Toshiharu Fujita

Shuhei Hosaka

Kohei Kojima

A thrust control valve equipped with: a valve element, in which a gas injection passage, through which an operating gas is injected, is formed, with a valve-seating surface being formed in the gas injection passage; and a valve stem, which is provided in the interior of the gas injection passage and has a seated surface that makes contact with the valve-seating surface. A guide surface which makes contact with the inner circumferential surface of the gas injection passage of the valve element is formed on the outer circumferential surface of the valve stem. The guide surface is formed downstream from the seated surface in the direction of flow of the operating gas. A V-groove through which the operating gas flows is formed at the tip of the valve stem, downstream from the seated surface in which the guide surface is formed.

Thrust control valve and flying object

A thruster valve for controlling a flow of high temperature fluid, comprising a valve casing, a graphite liner, a drive rod, and at least one relief hole. The graphite liner is disposed in a through hole within the valve casing. The drive rod being slidably received in drive rod through holes within the graphite liner, such that a seal is formed and maintained between the drive rod and the graphite liner. The drive rod is arranged so as to be driven in an axial direction by an actuator attached to an end of the drive rod arranged outside the valve casing. At least one of the relief holes is formed to extend through the graphite liner and valve casing to communicate the cavity with the exterior of the valve casing provide a drain passage. Thus, leakage of the high temperature fluid is prevented.

High temperature resistant seal structure, valve comprising the same and aerospace craft side thruster

A three-axis attitude control propulsion device and a flying object like a rocket including the device are provided in which combustion gas for attitude control can be efficiently used. A three-axis attitude control propulsion device, having six nozzles has a motor caseand three-way discharge changeover valves' of a valve plug rotation type enabling a changeover of a flow passage by rotation of the valve plug. Combustion gasis generated by combustion of propellantin the motor case. The three-axis attitude control propulsion device is operated so that one or two of the nozzles are opened to thereby discharge the combustion gasand the remaining five or four nozzles are fully closed. Thereby, a three-axis attitude control of pitch control, roll control and yaw control, and control of a neutral state, can be selected.

Three-axis attitude control propulsion device and flying object comprising the same

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Komaki, Japan

Shozo Hidaka