A rocket engine system including a coolant source containing a coolant fuel. The coolant source for providing the coolant fuel to a first surface of a wall partially defining a combustion chamber of a rocket engine, and the coolant fuel provides film cooling of the first surface of the wall. An oxidizer source for providing an oxidizer to a second surface of the wall. A monitor configured to control flow of the coolant fuel and the oxidizer, and to ensure that a stoichiometry of a combination of the coolant fuel and the oxidizer, after the coolant fuel has completed the film cooling of the first surface of the wall, is appropriate for generating a combustion of the combination of the coolant fuel and the oxidizer.

The present invention provides a water-cooled flue gas collecting apparatus disposed in a flow path formed inside a wake treatment structure for cooling and discharging flue gas generated from a test propulsion system. The water-cooled flue gas collecting apparatus includes a gas guiding portion having a flue gas inlet at one end through which the flue gas enters, a gas pipe connected to the flue gas inlet at one end to pass through the other end of the gas guiding portion and form an extension at the other end, and a collecting portion connected to the other end of the gas pipe to collect the flue gas entering through the gas pipe from the flue gas inlet. According to the present invention, the apparatus may be used in rocket propulsion systems of various sizes and allows quantitative analyses.

The present invention provides a water-cooled flue gas collecting apparatus disposed in a flow path formed inside a wake treatment structure for cooling and discharging flue gas generated from a test propulsion system. The water-cooled flue gas collecting apparatus includes a gas guiding portion having a flue gas inlet at one end through which the flue gas enters, a gas pipe connected to the flue gas inlet at one end to pass through the other end of the gas guiding portion and form an extension at the other end, and a collecting portion connected to the other end of the gas pipe to collect the flue gas entering through the gas pipe from the flue gas inlet. According to the present invention, the apparatus may be used in rocket propulsion systems of various sizes and allows quantitative analyses.

A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

A multi-pulse propulsion system for a launch vehicle includes a multi-pulse rocket motor module, a launchable payload module, and a safety module that is electromechanically coupled to the multi-pulse rocket motor module and the payload module. The safety module includes at two sensors for detecting at least one environmental characteristic and/or event that is common to both the multi-pulse rocket motor module and the payload module, such that the safety module is configured to activate the multi-pulse rocket motor module and the payload module in response to the detected environmental characteristic and/or event.

A multi-pulse propulsion system for a launch vehicle includes a multi-pulse rocket motor module, a launchable payload module, and a safety module that is electromechanically coupled to the multi-pulse rocket motor module and the payload module. The safety module includes at two sensors for detecting at least one environmental characteristic and/or event that is common to both the multi-pulse rocket motor module and the payload module, such that the safety module is configured to activate the multi-pulse rocket motor module and the payload module in response to the detected environmental characteristic and/or event.

An effector health monitor system is configured for coupling with an energetic component. The effector health monitor system includes a characteristic sensor suite including at least first and second characteristic sensors. The first characteristic sensor is proximate to the energetic component and configured to measure a failure characteristic of the energetic component. The second characteristic sensor is configured to measure at least one environmental characteristic proximate to the energetic component. A communication hub is coupled with the first and second characteristic sensors, and is configured to communicate the measured failure and environmental characteristics outside of an effector body. A failure identification module compares the measured failure characteristic with a failure threshold and identifies a failure event. A failure model generation module logs the at least one measured environmental characteristic preceding the identified failure event with the identified failure event and generates a failure model including updating the failure model.

An effector health monitor system is configured for coupling with an energetic component. The effector health monitor system includes a characteristic sensor suite including at least first and second characteristic sensors. The first characteristic sensor is proximate to the energetic component and configured to measure a failure characteristic of the energetic component. The second characteristic sensor is configured to measure at least one environmental characteristic proximate to the energetic component. A communication hub is coupled with the first and second characteristic sensors, and is configured to communicate the measured failure and environmental characteristics outside of an effector body. A failure identification module compares the measured failure characteristic with a failure threshold and identifies a failure event. A failure model generation module logs the at least one measured environmental characteristic preceding the identified failure event with the identified failure event and generates a failure model including updating the failure model.

A multi-pulse propulsion system for a launch vehicle includes a multi-pulse rocket motor module, a launchable payload module, and a safety module that is electromechanically coupled to the multi-pulse rocket motor module and the payload module. The safety module includes at two sensors for detecting at least one environmental characteristic and/or event that is common to both the multi-pulse rocket motor module and the payload module, such that the safety module is configured to activate the multi-pulse rocket motor module and the payload module in response to the detected environmental characteristic and/or event.