Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Abstract: A method and apparatus for determining the period Tp of a signal representing a digitally modulated waveform using NRZ coding with a discrete/integer number of a clock periods between signal transitions, where a periodic sequence of logic “1s” and logic “0s” is transmitted. The method samples an input periodic signal, constructs an estimate of the autocorrelation sequence rk of the sequence of samples, constructs a sequence of peaks pk, and computes the period Tp to be the time between the first pk sample (k=0), and the time location of the maximum value of pk based on the known Ts spacing of the pk sequence samples.

Abstract: A method and apparatus for determining the period Tp of a signal representing a digitally modulated waveform using NRZ coding with a discrete/integer number of a clock periods between signal transitions, where a periodic sequence of logic “1s” and logic “0s” is transmitted, is disclosed. The method comprises the steps of sampling an input periodic signal, constructing an estimate of the autocorrelation sequence rk of the sequence of samples, constructing a sequence of peaks pk, and computing the period Tp to be the time between the first pk sample (k=0), and the time location of the maximum value of pk based on the known Ts spacing of the pk sequence samples.

Abstract: An apparatus and method for determining the period of a data signal encoded using PN sequences may be implemented using software, and takes advantage of the fact that the signal is generated based upon a pseudo-random binary sequence, and of the fact that the order of the characteristic polynomial is known. The apparatus and method uses knowledge about the structure of the signal generator (i.e. the order of the characterizing polynomial of the encoding PN sequence), and recognizes the fact that short data tokens from the original signal can be used with the same success in determining the period as longer sequences having at least the length of the period.

Abstract: A method of estimating phase noise spectral density from a jitter versus time vector array obtained from a periodic signal having an average frequency includes the an initial step of converting the jitter verus time vector array to a phase error versus time vector array using an estimate of the average frequency of the periodic signal. A time to frequency transform is applied to the phase error versus time vector array to generate a phase error magnitude versus frequency vector array, and a phase noise spectral density vector array obtained by normalizing the phase error magnitude versus time vector array to a one hertz bandwidth.

Abstract: A method for determining the period of a periodic signal, possibly including noise, includes the step of calculating a signal representing the difference between the periodic signal, and the periodic signal delayed by a time T. The variance of the difference representative signal is then computed. The steps of computing a difference signal, and determining the variance of the difference signal is repeated for different times T. The period of the periodic signal is determined to be the time T producing the minimum variance. Apparatus implementing this method includes a source of the periodic signal. A difference circuit computes a signal representing the difference between the periodic signal, and the periodic signal delayed by a time T, and a variance circuit computes a signal representing the variance of the difference representative signal. A control circuit varies the time T. A minimum selector selects the time T producing the minimum variance as the period of the periodic signal.