Abstract: An automatic control system includes a multiplier for multiplying the error signal fed to an integrator in accordance with the state of the integrator. The multiplier multiplies the error signal by a unity gain factor over the normal range of integral control; whereas, the multiplier multiplies the error signal by a factor greater than one, typically ten, when the integrator output is saturated at either the minimum or maximum values. The high multiplication value of the error signal ensures a sufficiently quick recovery from an integrator saturation condition.

Abstract: An apparatus for controlling the phase of a slave propeller relative to that of a master propeller is shown and described. A logic means having a trajectory function, F(.phi..sub.E), which defines the region for phase holding, i.e. where the error correction signal, .phi..sub.EC, equals phase error .phi..sub.E. In the region of phase holding, normal control is achieved and there is no slipping of control from a first propeller blade to a second propeller blade.

Abstract: An improved slave propeller SYNCHROPHASER.RTM. device and mode logic for a multi-propeller aircraft is disclosed. A designated master propeller has at least one associated slave propeller which has its speed and phase controlled with respect to the master by initially controlling the speed of the slave propeller to within a selected constant number of RPM of the master so that the master and slave propellers are periodically in phase and then switching to phase control for controlling the speed of the slave propeller in the presence of a phase difference signal having an absolute magnitude less than a selected absolute magnitude. A selected phase difference relationship between the master and the slave may thus be effected with minimum transient effect on the speed of the slave propeller.

Abstract: A blade pitch angle control system for a wind turbine includes an improved control means (95) for providing a minimum pitch angle reference signal indicative of desired blade pitch at wind velocities less than rated. The control means includes means (35 and 30) for providing signals indicative of generated (output) power or torque and the rotational frequency of the wind turbine rotor. The output and rotor speed signals are input to a function generator which, in response to such signals, provides a signal indicative of the minimum pitch angle.

Abstract: This invention is an improvement in aircraft control systems that utilize feedback motion sensors to generate a control signal to control the aircraft. The improvement consists essentially of a complementary filter comprising a simplified model of the aircraft, a high-pass filter, a low-pass filter and a summing amplifier. The control signal is applied to the simplified model of the aircraft which ateempts to compute the vehicle response to the signal. This computed response is then fed into the high-pass filter to eliminate long-term errors in the calculated response, with the result that a good estimate of the high frequency content of the aircraft motion is obtained. In order to obtain a good estimate of the low frequency content of the motion a rate gyro signal is fed through the low-pass filter that eliminates all of the offending noise. The outputs from the high-pass and low-pass filters are summed by the summing amplifier to produce an estimated rate which is then used as a motion feedback signal.