Abstract: An anti-phase rotor system for an aircraft may include at least one rotor with at least two rotor blades. The aerodynamic profile of these two blades may be selected to create counteracting blade vortices to break up harmonic reinforcement due to the rotor blade passage. The aerodynamic profile may create a non-planar motion of one or more rotor blade passages, whereby the individual rotor blades are not co-planar during the rotation of said rotor. The rotor system may include a duct, which may include stationary vanes or struts configured in a manner so as to break up harmonic excitation to the rotor. The interior area of the duct at the area of the blade rotation may be designed in a manner so as to create a destructive rotor blade tip vortex interference.

Abstract: Processes for real-time drag optimization control for aeroelastic wing structures are disclosed. Adaptive reconfiguration of aircraft control surfaces by an online real-time drag optimization control approach to reduce or minimize drag may reduce the amount of fuel that is consumed by the aircraft during flight. The input data may be obtained from sensor information pertaining to the wing deflection and aircraft state information. The optimization approach may compute an optimal solution of the distributed flight control surface deflections that are integrated in a flight path angle flight control system.

Abstract: A flight control system for an aircraft having a multi-functional flight control surface. The aircraft has at least one multi-functional flight control surface formed by a sequence of flaps. The shape of each multi-functional flight control surface may be configured by a flight control to simultaneously adjust a trajectory of the aircraft in two or more of a pitch direction, a roll direction, and a yaw direction. The flight control for operating said the multi-functional flight control surface responds to both pilot commands and machine-generated commands. The machine-generated commands configure the shape of the surface of each multi-functional flight control surface in real-time based, at least in part, upon a set of flight objectives comprising: (a) minimizing drag of the aircraft, (b) aeroelastic modal suppression for the aircraft, and (c) maneuver load alleviation in the aircraft.

Abstract: An apparatus for a signer to apply a signature to a signature field of an electronic document. A personal electronic device includes a browser application, a screen, and an input unit. A logic activates a web link on the personal electronic device with the browser application to connect the personal electronic device and a remote server via a communications network. A logic presents a signor-side image copy of the electronic document with the signature field on the screen of the personal electronic device. A logic accepts the signature of the signer into the signature field from the input unit of the personal electronic device. And a logic communicates the electronic document containing the signature of the signer to the remote server.

Abstract: A method of driving an AC type PDP according to the present invention includes a full screen write step of applying a write voltage higher than a discharge starting voltage to respective cells constituting a screen of the PDP to cause a discharge in the respective cells for accumulation of wall charges therein, the method comprising a write preparation step of applying to the respective cells an auxiliary write voltage lower than the discharge starting voltage and having the same polarity as that of the write voltage to cause a discharge in a charged cell having wall charges accumulated before the application of the auxiliary write voltage for inversion of the polarity of a wall voltage in the charged cell, the write preparation step being performed prior to the full screen write step, wherein the application of the write voltage in the full screen write step is performed within a period during which space charges resulting from the discharge caused in response to the application of the auxiliary write voltag