A field of test methods, and more particularly to a method for testing a device, the method including one operating stage corresponding to a stable value of one operating setpoint for the device and/or for a test bench for testing the device. The operating stage is finalized before a maximum duration threshold if a criterion associated with a set of physical parameters picked up during the operating stage is satisfied and if a confidence level associated with the set of physical parameters reaches at least a predetermined threshold.

A rocket motor assembly (3) for use with an aircraft ejection seat comprises a rocket motor (4) having a rocket motor housing (5) and an exhaust outlet (6-9) to permit exhaust gas to be output from the rocket motor (4) along a thrust vector. The rocket motor assembly (3) comprises a first rotational coupling (12) which is configured to rotationally couple a first part (13) of the rocket motor housing (5) to a support structure (10) and a releasable coupling (14) which is configured to releasably couple a second part (15) of the rocket motor housing (5) to the support structure (10). The releasable coupling (14) is configured to release the second part (15) of the rocket motor housing (5) to permit the rocket motor housing (5) to rotate about the rotational coupling (12) to change the angle of the thrust vector of exhaust gas output from the exhaust outlet (6-9).

A rocket motor assembly (3) for use with an aircraft ejection seat comprises a rocket motor (4) having a rocket motor housing (5) and an exhaust outlet (6-9) to permit exhaust gas to be output from the rocket motor (4) along a thrust vector. The rocket motor assembly (3) comprises a first rotational coupling (12) which is configured to rotationally couple a first part (13) of the rocket motor housing (5) to a support structure (10) and a releasable coupling (14) which is configured to releasably couple a second part (15) of the rocket motor housing (5) to the support structure (10). The releasable coupling (14) is configured to release the second part (15) of the rocket motor housing (5) to permit the rocket motor housing (5) to rotate about the rotational coupling (12) to change the angle of the thrust vector of exhaust gas output from the exhaust outlet (6-9).

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

An obtaining step for obtaining a measurement of the monitored parameter as measured by a sensor and corresponding to an operating point of the engine, the operating point being defined by at least one regulation parameter of the engine; an estimation step for estimating a value of the monitored parameter for this operating point on the basis of a regulated value or a filtered setpoint value of the at least one regulation parameter of the engine defining the operating point; a comparison step for comparing an error between the measurement of the monitored parameter and its estimate relative to at least one threshold determined on the basis of an uncertainty on the error evaluated for the operating point; and a notification step for sending a notification in the event of the at least one threshold being crossed.

An obtaining step for obtaining a measurement of the monitored parameter as measured by a sensor and corresponding to an operating point of the engine, the operating point being defined by at least one regulation parameter of the engine; an estimation step for estimating a value of the monitored parameter for this operating point on the basis of a regulated value or a filtered setpoint value of the at least one regulation parameter of the engine defining the operating point; a comparison step for comparing an error between the measurement of the monitored parameter and its estimate relative to at least one threshold determined on the basis of an uncertainty on the error evaluated for the operating point; and a notification step for sending a notification in the event of the at least one threshold being crossed.

An engine comprises a rotor disposed within a housing having a side wall, a top portion, and a bottom portion. The housing includes at least one energy burst ignition chamber and electrical device that introduces an electric charge into at least one energy burst ignition chamber. The rotor is constructed and arranged to spin within the housing by action of a force. At least one energy burst ignition chamber is constructed and arranged to electrically react with the gas disposed in at least one chamber such that the gas expands and drives the rotor. A control system is used for introducing electric charges into at least one energy burst ignition chamber at a controlled time interval.

A preceramic resin formulation comprising a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer. A ceramic material comprising a reaction product of the polycarbosilane preceramic polymer and organically modified silicon dioxide preceramic polymer is also described. Articles comprising the ceramic material are also described, as are methods of forming the preceramic resin formulation and the ceramic material.

A turbine pump assembly has a turbine, a centrifugal pump, and a passive electrical speed control system. The turbine has a peak efficiency at a first speed that is lower than a second speed at which the centrifugal pump is operating at a peak power requirement. A rocket thrust vector control system is also disclosed.

A ceramic composite tubular structure includes a monolithic ceramic preform being tubular-shaped created using an additive manufacturing process. The monolithic ceramic preform includes a first end, a second end, an inner surface, and an outer surface. The monolithic ceramic preform includes one or more apertures formed between the inner surface and the outer surface where at least one of the one or more apertures is open to at least one of the first end or the second end. An inner face sheet is formed on the inner surface of the monolithic ceramic preform by a first quantity of ceramic matrix composite plies. An outer face sheet is formed on the outer surface of the monolithic ceramic preform by a second quantity of ceramic matrix composite plies.