Abstract: Provided is a method for assigning register tags to instructions at issue time. The method comprises receiving an instruction for execution by a microprocessor. The method further comprises dispatching the instruction to an issue queue without assigning a register tag to the instruction. The method further comprises determining that the instruction is ready to issue. In response to determining that the instruction is ready to issue, the method comprises assigning an available register tag to the instruction. The method further comprises issuing the instruction.

Abstract: A method for restoring a mapper of a processor core includes saving first information in a staging latch. The first information represents a newly dispatched first instruction of the processor core and is saved in an entry latch of a save-and-restore buffer. In response to reception of a flush command of the processor core, the restoration of the mapper is begun with the first information from the staging latch without waiting for a comparison of a flush tag of the flush command with the entry latch of the save-and-restore buffer. A processor core configured to perform the method described above is also provided. A processor core is also provided that includes a dispatch, a mapper, a save-and-restore buffer that includes entry latches and is connected to the mapper via at least one pipeline, and a register disposed in the at least one pipeline.

Abstract: A controller for generating a bank angle limit for an aircraft during takeoff with an nonoperational engine. The controller operates so that there are minimum and maximum bank angle limits. Between these minimum and maximums, there is a linear relationship between aircraft airspeed and bank angle limit. However, before there is a change in aircraft airspeed from an increasing mode to a decreasing mode or vice versa, the bank angle limit remains constant until the change in aircraft airspeed is greater than or equal to a predetermined airspeed differential.

Abstract: A method of and apparatus for determining the actual lateral deviation from the centerline of a runway of an aircraft located outside the normal region covered by a glideslope beam is disclosed. The method comprises the steps of scaling a geometrically developed estimated lateral deviation value (Y.sub.estimate) with a compensation factor (K) and passing the result through a complementary filter. The complementary filter produces an estimated lateral deviation rate value (Y.sub.estimate) that is divided into the actual lateral deviation rate value (Y.sub.actual) produced by the inertial navigation system of the aircraft. The result of the division is the compensation factor (K) that is used to scale the geometrically developed estimated lateral deviation value. Preferably, the compensation factor is filtered by a first order lag filter prior to being used to scale the geometrically developed estimated lateral deviation value.

Abstract: A burner having a burner body in which combustion air is injected in an air flow pattern which establishes a relatively stagnant air region positioned within the flow of combustion air. A pilot flame injector is positioned to generate a pilot flame extending into the stagnant air region. The pilot flame can, thus, be maintained during the operation of the burner because the stable air conditions within the stagnant air region minimize disruption of the pilot flame by the flow of combustion air.A method for maintaining a uniform pilot flame within a burner operating over a range of combustion air flow rates by introducing combustion air into the burner and providing the combustion air with a flow configuration that establishes a stagnant air zone within the burner that is relatively independent of the flow rate of the combustion air. The pilot flame is then positioned within the stagnant air zone.An injector for feeding finely divided fuel to a burner.

Abstract: A burner having a burner body in which combustion air is injected in an air flow pattern which establishes a relatively stagnant air region positioned within the flow of combustion air. A pilot flame injector is positioned to generate a pilot flame extending into the stagnant air region. The pilot flame can, thus, be maintained during the operation of the burner because the stable air conditions within the stagnant air region minimize disruption of the pilot flame by the flow of combustion air.A method for maintaining a uniform pilot flame within a burner operating over a range of combustion air flow rates by introducing combustion air into the burner and providing the combustion air with a flow configuration that establishes a stagnant air zone within the burner that is relatively independent of the flow rate of the combustion air. The pilot flame is then positioned within the stagnant air zone.An injector for feeding finely divided fuel to a burner.