Abstract: Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.

Abstract: Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of ?F/?X as the first flight control surface is displaced, where ?F is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and ?X is a difference in position X2?X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

Abstract: An autonomous vehicle for passengers includes four steerable wheels where each steerable wheel is steered by a steering system having a set of two actuators. One actuator of each set of actuators is powered by a first power source while the other actuator of the set of powered by a second power source. Four controllers each control one actuator of each set of actuators and one actuator from another set of actuators.

Abstract: Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of ?F/?X as the first flight control surface is displaced, where ?F is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and ?X is a difference in position X2?X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

Abstract: Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.

Abstract: A servo-controlled system is disclosed for providing simulated feel equivalent to that of traditional mechanical hand controllers. Processed position and force sensor signals are used in a feedback loop that controls the motor mechanically connected to the stick. The feedback loop comprises a low-level motor feedback loop, and high-level force feel loop. The latter comprises static and dynamic performance components. The system allows variable and additional force cues to be specified externally to the system and felt by the operator, and/or external signal to backdrive die stick to follow a specified motion. The control framework permits the electronic coupling of motion and applied forces by pilots in a dual arrangement while retaining the above-mentioned features. It simulates cross-coupling mechanical compliance due to force fight between pilots detents and asymmetric force feel gradients. Parameters associated with loops and performance components can be specified independently.

Abstract: Systems, methods, and machine-executable programming products adapted for the control of aircraft or other vehicles by receiving from at least one Inertial Reference System (IRS), including a plurality of Inertial Reference Units (IRUs), signals representing vehicle state data; receiving from at least one Augmented Direct Mode Sensor (ADMS) signals representing independently-acquired vehicle state data corresponding to at least a subset of the signals received from the IRS; performing signal selection and fault detection processes on the signals received from the at least one IRS and on the corresponding signals received from the ADMS; based at least partly on the signal and fault detection processes, determining whether at least one component of at least one of the IRS and ADMS is in a fault condition; and based on the fault condition, providing to at least one vehicle control system device one or more vehicle control command signals.

Abstract: A servo-controlled system is disclosed for providing simulated feel equivalent to that of traditional mechanical hand controllers. Processed position and force sensor signals are used in a feedback loop that controls the motor mechanically connected to the stick. The feedback loop comprises a low-level motor feedback loop, and high-level force feel loop. The latter comprises static and dynamic performance components. The system allows variable and additional force cues to be specified externally to the system and felt by the operator, and/or external signal to backdrive die stick to follow a specified motion. The control framework permits the electronic coupling of motion and applied forces by pilots in a dual arrangement while retaining the above-mentioned features. It simulates cross-coupling mechanical compliance due to force fight between pilots detents and asymmetric force feel gradients. Parameters associated with loops and performance components can be specified independently.

Abstract: A servo-controlled system is disclosed for providing simulated feel equivalent to that of traditional mechanical hand controllers. Processed position and force sensor signals are used in a feedback loop that controls the motor mechanically connected to the stick. The feedback loop comprises a low-level motor feedback loop, and high-level force feel loop. The latter comprises static and dynamic performance components. The system allows variable and additional force cues to be specified externally to the system and felt by the operator, and/or external signal to backdrive the stick to follow a specified motion. The control framework permits the electronic coupling of the motion and applied forces by pilots in a dual arrangement while retaining the above-mentioned features. It simulates cross-coupling mechanical compliance due to force fight between pilots, detents and asymmetric force feel gradients. Parameters associated with loops and performance components can be specified independently.

Abstract: Systems, methods, and machine-executable programming products adapted for the control of aircraft or other vehicles by receiving from at least one Inertial Reference System (IRS), including a plurality of Inertial Reference Units (IRUs), signals representing vehicle state data; receiving from at least one Augmented Direct Mode Sensor (ADMS) signals representing independently-acquired vehicle state data corresponding to at least a subset of the signals received from the IRS; performing signal selection and fault detection processes on the signals received from the at least one IRS and on the corresponding signals received from the ADMS; based at least partly on the signal and fault detection processes, determining whether at least one component of at least one of the IRS and ADMS is in a fault condition; and based on the fault condition, providing to at least one vehicle control system device one or more vehicle control command signals.

Abstract: A servo controlled system is disclosed for providing simulated feel equivalent to that of traditional mechanical hand controllers using servomotors. Position and force sensor signals are processed and used in a feedback loop that controls the motor mechanically connected to the stick. The overall feedback loop is comprised of a low-level motor feedback loop, and high-level force feel loop. The two loops have associated performance parameters that can be specified independently. The high-level feel force loop is comprised of a static and dynamic performance components. Static and dynamic performance components can be specified independently. The system allows variable and/or additional force cues to be specified externally to the system and felt by the operator. The system also allows external signal to backdrive die stick to follow a specified motion.

Abstract: A method for controlling the addition of bleaching/delignifying reagents to obtain a substantially constant percentage of pulp delignification across the first bleaching stage. The present method allows substantial improvements in bleached pulp quality through proper addition of the bleaching/delignifying reagent flow rate. The efficiency of the bleaching/delignifying reagent is therefore greatly improved. Further, reduction of pulp off-grades, equipment corrosion and effluent loading are additional beneficial effects resulting from the present method.