A flight test system uses a flight termination destruct charge that is configured to overpressurize a pressure vessel in a rocket motor to terminate thrust. The flight termination destruct charge is an electroexplosive detonator arranged on a final burn surface of a propellant contained in the pressure chamber. In a multi-pulse rocket motor, one of the pulses is ignited by the activation of the detonator. The activated detonator is configured to ignite the propellant grain without venting of the gas resulting from the burning of the propellant. Due to the burning of the propellant, the surface area in the pressure vessel is increased which causes increased pressure in the pressure vessel until a critical pressure is reached. When the critical pressure is reached, the rocket motor casing structural capabilities are exceeded. The overpressurized rocket motor casing then ruptures and thrust of the rocket motor is terminated.

A flight test system uses a flight termination destruct charge that is configured to overpressurize a pressure vessel in a rocket motor to terminate thrust. The flight termination destruct charge is an electroexplosive detonator arranged on a final burn surface of a propellant contained in the pressure chamber. In a multi-pulse rocket motor, one of the pulses is ignited by the activation of the detonator. The activated detonator is configured to ignite the propellant grain without venting of the gas resulting from the burning of the propellant. Due to the burning of the propellant, the surface area in the pressure vessel is increased which causes increased pressure in the pressure vessel until a critical pressure is reached. When the critical pressure is reached, the rocket motor casing structural capabilities are exceeded. The overpressurized rocket motor casing then ruptures and thrust of the rocket motor is terminated.

Provided is a failure diagnostic system for a spacecraft liquid propulsion system that enables to accurately diagnose a failure in a spacecraft and a failure diagnostic method for the spacecraft liquid propulsion system. This spacecraft liquid propulsion system includes a plurality of thrusters, and a supply pipe connected to the thrusters. This system includes a pressure sensor that detects an inner pressure of the supply pipe as time-series data, a frequency spectrum conversion unit that converts the time-series data into data of a frequency spectrum, a storage unit that stores data of a frequency spectrum generated based on an analytical model by computer simulation or a test result of a testing device as a data set, a comparator that compares the data set with the data of the frequency spectrum generated by the frequency spectrum conversion unit, and a determining unit that determines a failure in any one of the plurality of thrusters according to a comparison result of the comparator.

Provided is a failure diagnostic system for a spacecraft liquid propulsion system that enables to accurately diagnose a failure in a spacecraft and a failure diagnostic method for the spacecraft liquid propulsion system. This spacecraft liquid propulsion system includes a plurality of thrusters, and a supply pipe connected to the thrusters. This system includes a pressure sensor that detects an inner pressure of the supply pipe as time-series data, a frequency spectrum conversion unit that converts the time-series data into data of a frequency spectrum, a storage unit that stores data of a frequency spectrum generated based on an analytical model by computer simulation or a test result of a testing device as a data set, a comparator that compares the data set with the data of the frequency spectrum generated by the frequency spectrum conversion unit, and a determining unit that determines a failure in any one of the plurality of thrusters according to a comparison result of the comparator.

A method of operation of a complex system includes obtaining a population of operating points in a multidimensional space having axes, each representative of a parameter of a subsystem of the system that is represented for characterization purposes; followed by constructing a plurality of limit domains in that space, each constructed around a reference point to encompass a proportion of the population defined in the subsystem plane under consideration, which plane corresponds to a projection of the operating points obtained at system level into the plane of the subsystem under consideration; followed, for each subsystem, by defining qualifying domains by counting points of the population lying outside a given limit; and as functions of the result of the counting and a target proportion for the population defined for the system, adapting the domain to define modified domains characterizing operation of the subsystems approaching a defined target for the system.

A method of operation of a complex system includes obtaining a population of operating points in a multidimensional space having axes, each representative of a parameter of a subsystem of the system that is represented for characterization purposes; followed by constructing a plurality of limit domains in that space, each constructed around a reference point to encompass a proportion of the population defined in the subsystem plane under consideration, which plane corresponds to a projection of the operating points obtained at system level into the plane of the subsystem under consideration; followed, for each subsystem, by defining qualifying domains by counting points of the population lying outside a given limit; and as functions of the result of the counting and a target proportion for the population defined for the system, adapting the domain to define modified domains characterizing operation of the subsystems approaching a defined target for the system.

A vertical take-off and landing spacecraft includes a body, a plurality of engines provided in the body to produce a jet flow and generate thrust, an abnormal signal acquiring unit that acquires an abnormal signal indicative of a presence of an abnormal engine among the plurality of engines, and an engine control unit that outputs a stop signal that stops a specific engine among a plurality of operating engines based on the abnormal signal.

A vertical take-off and landing spacecraft includes a body, a plurality of engines provided in the body to produce a jet flow and generate thrust, an abnormal signal acquiring unit that acquires an abnormal signal indicative of a presence of an abnormal engine among the plurality of engines, and an engine control unit that outputs a stop signal that stops a specific engine among a plurality of operating engines based on the abnormal signal.

A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying, via a gas, a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and measuring a pressure of the gas. This process may be performed over time to determine a lifespan of the propellant grain.

An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.