Abstract: The present invention relates to a method and system for automatically detecting faults in a rotating shaft. The invention comprises the steps of: acquiring a vibration signal from the rotating shaft by means of at least one sensor; processing the signal acquired by the sensor in the time domain and in the frequency domain by means of a processor, obtaining energy measurements of the acquired signal as a result of said processing; comparing in the processor the energy measurements with previously established energy patterns; and finally determining if there is any fault in the rotating shaft based on the comparison between the energy measurements and the previously established patterns.

Abstract: A rocket stage for a spacecraft includes an engine, a tank for storing a fuel and an oxidizer for combustion in the engine, a rocket stage primary structure, and an engine thrust frame that connects and transmits forces between the engine and the primary structure. The engine thrust frame includes at least an internal part thereof arranged internally within the tank. This internal part of the engine thrust frame forms an imperforate partition that divides an interior space of the tank into at least two chambers for storing the fuel and the oxidizer separately from one another. Propellant management devices including liquid guide vanes and refillable liquid reservoirs may be provided in connection with the partition in the tank interior space.

Abstract: A rocket stage for a spacecraft includes an engine, a tank for storing a fuel and an oxidizer for combustion in the engine, a rocket stage primary structure, and an engine thrust frame that connects and transmits forces between the engine and the primary structure. The engine thrust frame includes at least an internal part thereof arranged internally within the tank. This internal part of the engine thrust frame forms an imperforate partition that divides an interior space of the tank into at least two chambers for storing the fuel and the oxidizer separately from one another. Propellant management devices including liquid guide vanes and refillable liquid reservoirs may be provided in connection with the partition in the tank interior space.