Abstract: The invention relates to statistical processing of multi-dimensional samples according to a step-wise sequence of iterative tolerance limit definitions using rank statistics. The processing is performed in the context of defining tolerance limits for a population that are compared to multiple process limits or acceptance criteria, with the requirement that a specified fraction of the population be confirmed to fall within the stated acceptance criteria. The symmetry (or asymmetry) may be allocated and controlled by selecting the frequency of occurrence of a specific figure of merit, and its order or position, in the sequential embedding processing sequence.

Abstract: The invention relates to statistical processing of multi-dimensional samples according to a step-wise sequence of iterative tolerance limit definitions using rank statistics. The processing is performed in the context of defining tolerance limits for a population that are compared to multiple process limits or acceptance criteria, with the requirement that a specified fraction of the population be confirmed to fall within the stated acceptance criteria. The symmetry (or asymmetry) may be allocated and controlled by selecting the frequency of occurrence of a specific figure of merit, and its order or position, in the sequential embedding processing sequence.

Abstract: A non-aircraft-propelling auxiliary gas turbine engine assembly includes an auxiliary gas turbine engine and a mixing damper. The auxiliary engine and the mixing damper are installable in an aircraft having at least one aircraft-propelling main gas turbine engine. The auxiliary engine includes a compressor having a compressor inlet. The mixing damper has first and second inlets and has an outlet. The outlet is fluidly connectable to the compressor inlet. The first and second inlets are adapted to receive first and second gas streams which have been compressed by at least one main engine. An aircraft component includes a mixing damper. A controller includes a program which instructs the controller to increase/decrease a first gas stream in response to increasing/decreasing electrical demands on an electric generator operatively connected to an auxiliary gas turbine engine of an aircraft.

Abstract: A non-aircraft-propelling auxiliary gas turbine engine assembly includes an auxiliary gas turbine engine and a mixing damper. The auxiliary engine and the mixing damper are installable in an aircraft having at least one aircraft-propelling main gas turbine engine. The auxiliary engine includes a compressor having a compressor inlet. The mixing damper has first and second inlets and has an outlet. The outlet is fluidly connectable to the compressor inlet. The first and second inlets are adapted to receive first and second gas streams which have been compressed by at least one main engine. An aircraft component includes a mixing damper. A controller includes a program which instructs the controller to increase/decrease a first gas stream in response to increasing/decreasing electrical demands on an electric generator operatively connected to an auxiliary gas turbine engine of an aircraft.