Abstract: An aircraft display system has a display unit comprising a matrix array of LED's mounted in the glareshield. Air traffic command signals received by a datalink processor produce a visual indication on the display unit which is visible to the pilot when looking through the window. A button on the display unit is pressed by the pilot to acknowledge receipt of instructions. Other important messages are displayed by the display unit at different times. Radar altimeter height is displayed in a color which changes when the aircraft descends below its flare height. When on the ground, the display unit displays alphanumerically the distance-to-go to the end of the runway, and simultaneously displays stripes that move horizontally to indicate deviation of the aircraft from the runway center line.

Abstract: Abnormal start conditions, such as hot starts or hung starts, in an aircraft gas-turbine engine are monitored by deriving signals indicative of spool speed, engine temperature and fuel flow. A processor receives these signals and derives an indication of the rate of change of engine temperature. Signals indicative of whether the aircraft is on the ground or in the air are derived from a air speed sensor or undercarriage pressure switch. The processor monitors the relationship between these signals to determine when the relationship between them is indicative of an abnormal start condition and indicates this on a display such as by flashing the display of engine temperature.

Abstract: An adjustable restraint assembly connectable between a dome portion of a solid propellant rocket motor casing and a rigid base or support, for use during the curing of a propellant in the casing. The assembly includes an upper attach bracket connectable to the dome portion, a lower attach bracket connectable to a rigid base, upper and lower flanges connected to the upper and lower brackets, respectively, and an adjustable threaded turnbuckle-like member connected between the flanges. The assembly is used to establish a maximum net downward deflection of the dome portion upon maximum pressurization of the uncured propellant in the motor casing and is thereafter adjusted at various times during the curing process to reduce and ultimately eliminate the deflection in increments to thereby improve the bond between the grains of the cured propellant and the casing in the region of the forward dome.

Abstract: An adjustable restraint assembly connectable between a dome portion of a solid propellant rocket motor casing and a rigid base or support, for use during the curing of a propellant in the casing. The assembly includes an upper attach bracket connectable to the dome portion, a lower attach bracket connectable to a rigid base, upper and lower flanges connected to the upper and lower brackets, respectively, and an adjustable threaded turnbuckle-like member connected between the flanges. The assembly is used to establish a maximum net downward deflection of the dome portion upon maximum pressurization of the uncured propellant in the motor casing and is thereafter adjusted at various times during the curing process to reduce and ultimately eliminate the deflection in increments to thereby improve the bond between the grains of the cured propellant and the casing in the region of the forward dome.

Abstract: A carbon-carbon rocket motor exit cone having a threaded cylindrical section for attachment to the motor section is reinforced with a plurality of windings of carbon fiber around the cylindrical section.