Abstract: In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.

Abstract: In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.

Abstract: A rudder control pedal assembly including an idler link pivotably coupled to a support frame at a first joint, a coupler link pivotably coupled to the idler link at a second joint, a drive link pivotably coupled to the coupler link at a third joint and pivotably coupled to the support frame at a fourth joint, and a pedal coupled to the coupler link and constrained to movement along an approximately linear travel path, wherein the support frame forms an imaginary fixed link to complete a four-bar linkage.

Abstract: Controlling a movement of an aircraft. A computer system detects a position of a group of integrated control levers for the aircraft. The computer system controls a forward thrust, a drag, and a reverse thrust generated by the aircraft based on the position of the group of integrated control levers.

Abstract: Systems and methods for jam mitigation in aircraft fly-by-wire systems are described herein. An example method of controlling an aircraft with a fly-by-wire system includes determining a current position of a pilot cockpit controller of the fly-by-wire system, determining an amount of pilot input force applied to the pilot cockpit controller, determining an expected pilot input force value that corresponds to the current position of the pilot cockpit controller, and, if the amount of pilot input force applied exceeds the expected pilot input force value by a threshold, generating a pilot command based on the amount of pilot input force applied and not the current position of the pilot cockpit controller.

Abstract: Systems and methods for jam mitigation in aircraft fly-by-wire systems are described herein. An example method of controlling an aircraft with a fly-by-wire system includes determining a current position of a pilot cockpit controller of the fly-by-wire system, determining an amount of pilot input force applied to the pilot cockpit controller, determining an expected pilot input force value that corresponds to the current position of the pilot cockpit controller, and, if the amount of pilot input force applied exceeds the expected pilot input force value by a threshold, generating a pilot command based on the amount of pilot input force applied and not the current position of the pilot cockpit controller.

Abstract: A rudder control pedal assembly including an idler link pivotably coupled to a support frame at a first joint, a coupler link pivotably coupled to the idler link at a second joint, a drive link pivotably coupled to the coupler link at a third joint and pivotably coupled to the support frame at a fourth joint, and a pedal coupled to the coupler link and constrained to movement along an approximately linear travel path, wherein the support frame forms an imaginary fixed link to complete a four-bar linkage.

Abstract: A rudder control apparatus includes a pair of pedal assemblies, coupled to a support frame for control of a rudder control device. Each one of the pedal assemblies includes an idler link, a coupler link, and a drive link. The idler link is coupled to the support frame and is pivotable relative to the support frame. The coupler link is coupled to the idler link and is pivotable relative to the idler link. The drive link is coupled to the coupler link and to the support frame and is pivotable relative to the coupler link and relative to the support frame. A pedal is coupled to the coupler link. A four-bar linkage is formed by the support frame, the idler link, the coupler link, and the drive link and confines movement of the pedal to a linear travel path in a forward direction and a rearward direction.

Abstract: An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.

Abstract: An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.

Abstract: A rudder control apparatus may include a laterally spaced apart pair of pedal assemblies each coupled to a support frame and a rudder control device, the pedal assemblies each including a four-bar linkage constrained to movement in an approximately vertical plane, and a pedal coupled to the four-bar linkage and constrained to movement in an approximately horizontal plane.

Abstract: The present invention resides in a process and apparatus for the electrolytic production of strong solutions of halogen oxyacids, more specifically for the production of such acids having a normality of about 0.1 to about 3.6 from the corresponding alkali metal salts of such acids. The present invention comprises establishing a solution of the corresponding alkali metal salt having a molar concentration less than that at which precipitation of said salt occurs. An electrolytic cell is provided comprising an anode compartment containing an anode, a cathode compartment containing a cathode, and a middle feed compartment intermediate the anode compartment and cathode compartment. The feed compartment is separated from the anode compartment by a diaphragm and from the cathode compartment by a cation-selective membrane. Means are provided for introducing said alkali metal salt solution into said middle feed compartment and for applying a voltage between the anode and cathode.

Abstract: A parallel to serial converter is described for recording channel applications, wherein a coded symbol comprising a plural number of bits is to be rotated or converted to a serial stream. The converter includes a variable delay section which accepts the parallel code inputs on a plurality of lines and delays each input bit a predetermined number of counts, depending upon which line it is input on. The delay unit supplies a selector array of gates with bit signals, and the selector array reorders the bits into the desired serial stream. An output register is provided to reclock the serial stream prior to further channel processing.

Abstract: Biofouling and scale control in conductive aqueous systems is effected on metal, preferably valve metal such as titanium, surfaces on which such fouling normally occurs by applying thereto a stable electrocatalytic coating, anodically polarizing said valve metal coating such that essentially only oxygen is evolved at the surface thereof, preferably at a rate of at least about 4.66 millimoles per square meter per hour without evolution of any chlorine. Periodic current reversal is effected to forestall biofouling upon any cathode utilized in implementing the instant invention.

Abstract: Biofouling and scale control in conductive aqueous systems is effected on metal, preferably valve metal such as titanium, surfaces on which such fouling normally occurs by applying thereto a stable electrocatalytic coating, anodically polarizing said valve metal coating such that only oxygen is evolved at the surface thereof, preferably at a rate at least about 4.66 millimoles per square meter per hour without evolution of any chlorine.

Abstract: Novel oxygen selective electrode comprising a coating on said anode consisting of delta manganese dioxide. This outer coating on the anode may be placed on the anode electrochemically by electrolyzing an acid saline solution having dissolved therein sufficient manganous chloride. Sufficient manganese dioxide is plated on said anode when the chlorine evolution essentially ceases during electrolysis.

Abstract: Novel oxygen selective electrode comprising a coating on said anode consisting of delta manganese dioxide. This outer coating on the anode may be placed on the anode electrochemically by electrolyzing an acid saline solution having dissolved therein sufficient manganous chloride. Sufficient manganese dioxide is plated on said anode when the chlorine evolution essentially ceases during electrolysis.

Abstract: Electrolysis of impure saline solutions containing dissolved iron and manganese causes deposits to form on the anodes of such electrolysis cell which rapidly reduces the efficiency of the cell. Pretreating the impure saline solutions with sodium hypochlorite solution formed from the reaction products of the electrolysis cell precipitates the iron and manganese dissolved therein and effectively prevents the formation of the deleterious deposits on the anode of said electrolytic cell.

Abstract: The formation of hardness-caused deposits on the cathodic surfaces of cells used in the electrolytic production of hypochlorite from impure saline solutions is reduced and good current efficiencies are realized by employing flat, continuous cathodes having a surface roughness of less than 2.54 .times. 10.sup.-.sup.4 cm. and passing said solution by said cathodes during electrolysis at a velocity of from 0.3 meter/sec. to the number which is equal to the log expressed by the formula: Log velocity (in m/sec/3) = 1.0 - (available Cl.sub.2 concentration, in grams per liter, divided by 4).