Abstract: Provided is a diagnosis device that can determine the status of an anomaly besides the presence of an anomaly of a driven member. The diagnosis device is configured to diagnose a driven member having a rotary shaft, the driven member is rotated by driving of an externally mounted motor, and the diagnosis device calculates an estimated torque resistance of a combination of the driven member and the motor based on actual operation data obtained by driving the driven member by using the motor and finds a driven member and motor three-dimensional table that is a three-dimensional table of angles, angular velocities, and estimated torque resistances, finds a reference-state three-dimensional table that is a three-dimensional table of angles, angular velocities, and estimated torque resistances in a reference state, and calculates a determination three-dimensional table from a difference between the driven member and motor three-dimensional table and the reference-state three-dimensional table.

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.