Abstract: A blade heater (10) for an aircraft engine propulsor blade (14) has a foil pattern (18) which is comprised of a plurality of elements (25-56). The resistance of the elements (25-56) varies according to the distance between the elements (25-56) and the leading edge (12) of the blade (14).

Abstract: A multi-pulse pulse compression radar system transmits two or more radar pulses having different frequency components having a time delay therebetween. A signal conditioning stage time and phase aligns the received signals and provides a composite radar signal having time and phase continuity throughout.

Abstract: An aircraft engine propeller synchrophasing system (4) has a gain stage (8) which varies the gain of the system (4) according to the magnitude of the difference between the preferred propeller relative phase and the measured propeller relative phase.

Abstract: A deicing system for an aircraft engine (4) having blades (14, 16) fixedly attached to rotating propulsors (6, 8) has emitters (22, 28) which irradiate microwave beams (24, 26, 30 32) onto coatings (18, 20) which are fixedly attached to said blades (14, 16). Substantially more of the energy of the beams (24, 26, 30, 32) is absorbed by the coatings (18, 20) than by any water or ice on the blades (14, 16) causing any ice which is on the blades (14, 16) to be thrown off by the centrifugal force of the rotating propulsors (6, 8).

Abstract: Representational efficiency is realized by employing a set (6) of variable length bit patterns (7-14) having a first and last bit equal to a particular binary value and havin only singularly occurring bits equal to said value. The patterns (7-14) can be unambiguously concatenated to form a data stream (15). A communication system (16) can achieve improved throughout by employing said patterns (16).

Abstract: A divider unit (15), having a divider circuit (16) and a divider controller (17), generates signed quotient and signed remainder signals in response to input signed dividend and signed divisor signals. The divider circuit (16) has an adder/subtracter unit (22), a mux (24), a zero/sign detector unit (23), and a shiftable register (28) which are controlled by the divider controller (17) and which cooperate to iteratively generate signed partial remainder and signed partial dividend signals, necessary for the computation of signed quotient and signed remainder signals, using either a restoring or non-restoring binary division algorithm.

Abstract: Pitch of a blade (12) on an aircraft engine propulsor (14) is determined by employing a shaft (22) and a bevel gear (23) to alter relative circumferential distance between a first set of teeth (25) and a second set of teeth (26). Said teeth (25,26) creates fluctuations in a magnetic field generated by a magnetic poll piece (28a) wherein said fluctuations are converted to a signal (30) by a coil (28) located on a subsequent engine section (8). The time between pulses of the signal (30) is a function of said relative circumferential distance whereby the time between pulses is a function of the pitch of the blade (12).