Abstract: A system for controlling an electromechanical actuator of an aircraft includes a locking device configured to mechanically lock said actuator in a first fixed position and to mechanically unlock said actuator from said first fixed position and a controller configured to be in bi-directional communication with both said locking device and said actuator. The controller is configured to monitor a position of said actuator during flight and to detect when said actuator has not moved for a set amount of time, said controller further being configured to instruct said locking device to lock said actuator in said first, locked position when said set time has been reached. In addition, there is provided a method for controlling the thermal properties of an electromechanical actuator of an aircraft.

Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing.

Abstract: An aircraft includes a variable-speed gearbox. The variable-speed gearbox includes a low-speed gear train and a high-speed gear train, each gear train of which is configured to selectively provide torque from an engine of the aircraft to a proprotor. The variable-speed gearbox also includes a hydraulic system configured to provide torque to the proprotor. The hydraulic system includes a hydraulic pump driven by the engine of the tiltrotor aircraft and a variable-displacement motor driven by a hydraulic fluid from the hydraulic pump.

Abstract: Systems and methods for controlling thrust of an engine for an aircraft are described herein. A position of a thrust lever for controlling the engine is obtained from one or more sensors. Air data is obtained from one or more air data inputs. An air temperature data input is detected as compromised from the air data. In response to detecting the air temperature data input is compromised, a target engine rotational speed is determined based on the position of the thrust lever and at least one of altitude data and Mach number data from the air data. A rotational speed of the engine is adjusted to the target engine rotational speed to control thrust of the engine.

Abstract: An autothrottle system for an aircraft includes a motor, actuator assembly, and position sensor operatively connected between the motor and a moving portion of the actuator assembly. An electronic controller is configured to control the motor to move the actuator assembly to actuator positions based at least on position information from the position sensor to move the throttle lever to lever positions.

Abstract: An autothrottle system for an aircraft includes a motor, actuator assembly, and position sensor operatively connected between the motor and a moving portion of the actuator assembly. An electronic controller is configured to control the motor to move the actuator assembly to actuator positions based at least on position information from the position sensor to move the throttle lever to lever positions. When a surge condition is detected the autothrottle increases the throttle lever in a regulated manner for optimal performance over the different regions of an engine power output.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: The invention relates to a fan assembly having a rotatingly driven hub (7) and fan blades (10) which can be pivoted relative to the hub body (29). The fan blades (10) are adjusted by means of a linear drive in the form of a spindle drive (13) or a piston drive (52).

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle ?PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle ?PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Abstract: The present invention relates to an automatic method of regulating a power plant (3?) of an aircraft (1), the power plant having at least one turbine engine (3), each engine (3) being capable of operating in an idling mode of operation. A calculation system (15) executes stored instructions in order to implement the idling mode of operation as a function of operational and ordered conditions either via a first regulation mode by regulating a first speed of rotation (Ng) of said gas generator (4), or via a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine (7).

Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.

Abstract: The present invention relates to a system and method for harvesting wind energy from air exhausted by other systems. Ventilation and heat exchange systems force air movement using fans. Exhaust airflow may also be the result of a combustion system. The exhaust air is generally wasted as it is diffused back to the atmosphere. Significant energy may be recovered from this exhaust air using relatively small turbines inserted into the airflow. Careful positioning of the turbine maximizes the recovery efficiency.

Abstract: A sunlight filter device for a helicopter blade tracker includes a filter housing, a filter assembly and a mounting system. The filter housing has a first opening, a second opening and a receiving cavity formed between the first opening and the second opening. The filter assembly is mounted in the receiving cavity of the filter housing, and is adapted to block sunlight. The mounting system extends from the filter housing to securely mount the filter housing on the helicopter blade tracker.

Abstract: A method for operating a wind turbine having at least one blade includes determining an ambient air operating envelope and controlling a power output of the wind turbine at least partially based on the determined ambient air operating envelope. Determining an ambient air operating envelope includes measuring at least one of an ambient air temperature, an ambient air pressure, an ambient air humidity, and wind turbine power output. The method also includes comparing at least one of a measured ambient air temperature, a measured ambient air humidity and a measured ambient air pressure to predetermined ambient air temperature, pressure and humidity values. The method further includes referencing the predetermined ambient air temperature, pressure and humidity values to at least one operational parameter of the wind turbine. The method also includes determining if an existing wind turbine power output is within a range associated with the determined ambient air operating envelope.

Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

Abstract: A system for arranging and operating an array of wind machines to protect crops from damaging weather conditions, such as freezing frost, rain and heat. The method includes a wind machine positioned to force air across the crop. The wind machine is preferably a propeller/tower configuration. The operational method of the wind machine array includes the steps of sensing ambient meteorological and the hardiness of the crop to withstand a particular adverse weather condition and operating the wind machines in response to these factors. Multiples of wind machines are employed in the preferred embodiment of the method, the siting of the wind machines preferably based upon topographic and historical meteorological conditions. The operation of the wind machines can be automatically and remotely operated with the aid of satellite communications including internet links.

Abstract: A direct driven wind turbine includes an electrical generator with a rotor and a stator, a hub for receiving a rotor blade, and actuator device. The hub is connected to the rotor of the electrical generator, and the hub and the rotor of the electrical generator are rotatable mounted in respect to the stator of the generator. The actuator device is constructed and arranged to rotate the hub of the wind turbine in respect to the stator of the electrical generator. The actuator device is the electrical generator, wherein the electrical generator of the wind turbine is used as a motor to rotate the hub of the wind turbine.

Abstract: A wind turbine 30 comprising: a rotor 36 having a plurality of blades 38; and a controller 100. The controller 100 is arranged to independently control each of the plurality of blades 38 and/or one or more components of each blade 38 in order to increase a driving moment of each blade 38 independently of other of the blades 38 when speed of wind acting on the wind turbine 30 is below rated. The controller 100 is also additionally or alternatively arranged to independently control each of the plurality of blades 38 and/or one or more components of each blade 38 independently of other of the blades 38 when wind force acting on the blades 38 is above cut-out in order to reduce a mechanical load experienced by at least a part of the wind turbine 30.

Abstract: Apparatus for controlling the power output efficiency of a power generation system based on an operator input. A processor is coupled to the input means and (i) receives the generated operator command, (ii) receives a plurality of detected ambient air conditions, (iii) receives a plurality of detected engine. performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient environmental conditions, and the engine performance parameters, and (v) outputs control commands to optimize the efficiency of the power generation system.

Abstract: A system for aircraft propulsion is disclosed herein. The system includes a power plant. The system also includes an open rotor module operable to rotate. The open rotor module has a plurality of variable-pitch blades. The system also includes a first linkage extending between the power plant and the open rotor module. The first linkage is operable to transmit rotational power to the open rotor module for rotating the plurality of variable-pitch blades. The system also includes an actuator operable to change a pitch of the plurality of variable-pitch blades. The system also includes a generator operable to generate electric power. The system also includes a second linkage extending between the power plant and the generator. The second linkage is operable to transmit rotational power to the generator. The generator is operable to convert the rotational power to electrical power. The system also includes a controller operably coupled to the actuator to vary a pitch of the plurality of variable-pitch blades.

Abstract: A wind energy plant has a rotor with a rotor hub mounted on a pod and a plurality of rotor blades adjustable by corresponding electrical drives. An electrical generator is connected to the rotor for supplying energy to electrical loads arranged in the rotor hub. A primary part of a rotary transformer arranged concentric to a rotor bearing is connected to the pod and a secondary part of the rotary transformer is arranged in the rotor hub and co-rotates with the rotor hub. A first frequency converter is connected between the primary part and a supply voltage source for generating a high-frequency field voltage from a low-frequency supply voltage, and a second frequency converter is connected between the secondary part and the electrical loads for generating a low-frequency load voltage from a transformed high-frequency field voltage.

Abstract: A fan system includes a fan and a fan rotation speed control. The speed control is operable to command the fan to rotate at a speed selected from a certain range of rotation speeds. A fan oscillation detector may be coupled with the fan to detect oscillation of the fan as the speed control is operated to rotate the fan at various speeds among the range of fan rotation speeds. The fan oscillation detector may comprise an accelerometer or other device. Oscillation amounts detected by the oscillation detector are compared against each other or against an oscillation threshold value. A programmer device identifies fan rotation speeds at which the oscillation amount exceeds the threshold or is otherwise unacceptable, and programs the fan rotation speed control to prevent an operator from being able to select those speeds at which the oscillation amount exceeds the threshold or is otherwise unacceptable.

Abstract: A system for arranging and operating an array of wind machines to protect crops from damaging weather conditions, such as freezing frost, rain and heat. The method includes a wind machine positioned to force air across the crop. The wind machine is preferably a propeller/tower configuration. The operational method of the wind machine array includes the steps of sensing ambient meteorological and the hardiness of the crop to withstand a particular adverse weather condition and operating the wind machines in response to these factors. Multiples of wind machines are employed in the preferred embodiment of the method, the siting of the wind machines preferably based upon topographic and historical meteorological conditions. The operation of the wind machines can be automatically and remotely operated with the aid of satellite communications including internet links.

Abstract: The present invention relates to a system and method for harvesting wind energy from air exhausted by other systems. Ventilation and heat exchange systems force air movement using fans. Exhaust airflow may also be the result of a combustion system. The exhaust air is generally wasted as it is diffused back to the atmosphere. Significant energy may be recovered from this exhaust air using relatively small turbines inserted into the airflow. Careful positioning of the turbine maximizes the recovery efficiency.

Abstract: A wind turbine pitch control system is disclosed that provides a pulsed torque to the blade pitch actuator if continuous torque fails to adjust the blade pitch angle to a commanded pitch angle. This invention provides a cost-effective way to increase peak torque capability for existing wind turbines that have problems, under certain operating conditions, moving blades per the control command.

Abstract: A control method and system for a controllable pitch marine propeller including operating modes comprised of a maneuvering mode and a cruise mode and check modes comprised of an engine check mode and propeller check mode. The cruise mode provides for wide open throttle acceleration and power stop. Smooth transition sub-modes are provided for providing smooth transition between cruise mode and maneuvering mode and vice versa. The system operates by a lever (28) which controls a pitch control unit (10) which in turn controls engine speed and also the pitch of propeller blades (12) of propeller (14). Thus, dependent on the position of the control lever (28) in either maneuvering mode or cruise mode, an appropriate engine speed and propeller pitch is selected automatically for driving a watercraft.

Abstract: Provided are an apparatus and method for controlling a vertical axis wind power generation system that controls the rotation of guide vanes according to wind direction and speed, appropriately controls a direction of wind passing over an impeller, thereby maintaining a rotational speed generating the maximum power, maintains output power of a generator as rated power according to wind direction and speed, and stops the generator when a low or high wind speed outside a setting value range, an error in a structure, a fault in a braking unit, and/or a fault in guide vanes is detected.

Abstract: The invention relates to a hydraulic fluid actuator configuration with a working piston (2) that is guided in an actuating cylinder (4), with this piston being supplied pressure on both sides. In order to prevent an excursion of the working piston (2) from its neutral position (x=0) due to leakage, a hydraulic fluid displacement device (20) is suggested, which supplies a control volume over a period of a harmonic movement of the working piston (2) to the side of the working piston (2) to which it traveled.

Abstract: A variable pitch fan in which the pitch of the fan blades is varied under control of a controller according to the speed of the fan. The controller is programmed to respond to increased fan speed by decreasing pitch of the fan blades. The variable pitch fan has a piston extending axially from a main shaft, about which main shaft a fan blade hub rotates. A pitch shifter is mounted on a cylinder, which itself is mounted on the piston. The pitch shifter is actuated by hydraulic fluid supplied through the main shaft to the cylinder. The piston is preferably axially stationary in relation to the main shaft. The cylinder is secured against rotational movement by cooperating out of round surfaces. Grease for the pitch shifter is supplied through the guide pin. One guide pin may be used for grease supply, while another may be used for excess grease return.

Abstract: In an individual rotor blade control device for a helicopter main rotor with a rotor shaft that can be driven by a main drive, with an even number of rotor blades that are arranged on the periphery of a rotor hub, with primary control mechanisms for collective and sinusoidal, cyclic rotor blade adjustment, which include a transfer element for the control movements from a non-rotating system to a rotating system and with actuators that are individually allocated to the rotor blades, wherein the actuator control movement is superimposed onto the control movement of the primary control mechanisms and each actuator is equipped with a safety device in order to bring the actuator into its final position and keep it there, if necessary, it is suggested that the setting angle change of one half of the rotor blades have an opposed direction due to the securing of the actuators in their final positions, like the setting angle change of the other half of rotor blades, and that the rotor blades of each half be distribute

Abstract: Apparatus for controlling the power output efficiency of a power generation system based on an operator input. A processor is coupled to the input means and (i) receives the generated operator command, (ii) receives a plurality of detected ambient air conditions, (iii) receives a plurality of detected engine performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient environmental conditions, and the engine performance parameters, and (v) outputs control commands to optimize the efficiency of the power generation system.

Abstract: A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process the rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of a mistracking rotor blade into alignment with a reference path. The trim tab is deflected by an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element.

Abstract: A system and method of automatically setting a flat rate engine power setting of an aircraft determines the weight of loaded cargo containers to determine the total gross weight of the aircraft prior to take-off, determines, from the total gross weight, the required flat rate engine power for the aircraft, such as by inputting the stored value into a look-up table, and automatically sets the flat rate setting of the aircraft's engines to correspond to the determined required engine power, prior to take-off, by sending the obtained required flat rate engine power as a command signal to an engine control system.

Abstract: A method and apparatus for controlling a propulsion engine output in a vessel, based on the net axial force on a propeller shaft in the vessel. The apparatus includes a regulating loop with a computer which continuously controls the delivery of fuel to the vessel's engine, and optionally controls the attack angle of the vessel's propeller blades. Control of the fuel delivery is performed in accordance with predetermined control algorithms, and optionally, by operator-set parameter values and maneuvering operations. The apparatus further includes at least one force sensor mounted to a bearing which supports the vessel's propeller shaft. The force sensor, which is preferably mounted to a thrust bearing, detects a net axial force on the propeller shaft. The net axial force detected is then used as a parameter in the control algorithms and therefore as a factor in controlling the delivery of fuel.

Abstract: An engine control system for a helicopter having at least one engine is provided, including an electronic engine control unit for each engine and further including a manually operated system for backing up each electronic engine control unit in the event of a failure thereof or for permitting optional manual engine operation. The engine control system includes at least one collective pitch stick and at least one twist grip rotatably mounted on the collective pitch stick. Each twist grip includes a normal (NORM) position within the range of the operating arc which is coincident with a detent. The system includes means for electronically actuating the detent to retract when the twist grip is rotated out of the NORM position into a manual operating mode, so that the electronic disablement of the detent permits an operator to smoothly operate the twist grip through the operating arc when the engine control system is in a manual control mode.

Abstract: A propeller blade tip path plane-inclining device which is provided with a fuselage, a propeller including a center piece rotating unitary with a rotation shaft in association therewith and a plurality of blades extending substantially horizontally from the center piece and differing the variation in pitch during the rotation thereof from one another, a motor for driving the propeller for rotation, a position detector for detecting the position of the propeller in the propeller rotation plane, and a control device for controlling the motor in accordance with an output signal of the position detector.

Abstract: An outboard marine engine capable of preventing the generation of cavitation around a propulsion screw due to an abrupt increase in the rotational speed thereof for improved acceleration performance. To this end, a rotational speed sensor senses the number of revolutions per minute of the engine, and a bubble sensor senses the amount of bubbles generated around the propulsion screw and generates a corresponding bubble signal. A controller generates, based on the output signals of the sensors, a drive signal for controlling engine operating parameters. The controller includes a speed limiter for determining, based on the bubble signal from the bubble sensor, whether the amount of bubbles generated around the screw is equal to or greater than a predetermined value.

Abstract: The blade angle controlling pitch beam servo (26) of a helicopter tail rotor (22) is responsive to a main rotor torque signal (92) indicative of torque coupled to a helicopter main rotor (10) for providing torque compensation so that the helicopter airframe will not counter-rotate under the main rotor. The torque coupled to the main rotor is that amount of engine torque (76, 114) in excess of torque coupled to the tail rotor (81, 115) and helicopter auxiliaries (84, 116). The amount of torque compensation provided by the tail rotor is reduced by an amount indicative of aerodynamic forces (130) on the helicopter airframe.

Abstract: A variable-speed propeller in a ship drive has the hydraulic valves feeding the working chambers of the hydraulic drive for the variable-speed propeller formed as electromagnetic valves controlled by timing relays which can be switched by a rocker switch or push-button switches to adjust the propeller pitch by an angular increment controlled by the "on" time of the relays. The engine speed is detected and, when the engine speed exceeds the maximum speed of the engine, the relay associated with increased pitch is triggered to obtain an increment of engine-speed reduction, thereby preventing the system from inadvertently having the blade pitch reduced when the engine is at maximum speed.

Abstract: A ground mode pitch position logic and control is shown and described in this invention. A method for scheduling and limiting the pitch actuator reference signal in accordance with the actuator commanded schedule, propeller overspeed and propeller underspeed.

Abstract: A cam mechanism enabling the pilot to automatically advance the propeller low pitch stop with the engine power lever on airplanes with multibladed propeller systems having a beta control mechanism for adjusting the blade angle. The cam provides an inexpensive and reliable alternative to costly and complex automatic feathering systems.

Abstract: An oil distribution box for a marine controllable pitch propeller of the type having a main hydraulic servo within a hub for controlling the pitch of propeller blades rotatably carried by the hub and including a directional valve actuated by a tubular valve rod extending through the propeller shaft from the oil distribution box comprises an outer stationary housing, a shaft received within the housing and coupled to the propeller shaft and an auxiliary servo chamber cylinder coupled to the shaft. A piston received in the servo chamber is coupled to the valve rod. Oil is supplied to the valve rod through an elongated annular supply chamber defined between the shaft and the valve rod by spaced-apart seals, a port in the valve rod opening to the supply chamber, a port in the shaft opening to the supply chamber and a journal clearance seal between the housing and shaft in register with the port in the shaft.

Abstract: An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.

Abstract: An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.

Abstract: An adjusting device is provided for an airplane propulsion system using the reciprocating piston combustion engine and a propeller, which adjusting device simultaneously adjusts the throttle valve and the propeller pitch of the propellers. The adjusting device is formed with a connecting rod and a carrier rod connected thereto. The connecting rod is provided as an adjusting cable whereby the cable core is under spring pretensioning in lower rotational speeds of the motor.

Abstract: The present invention relates to a compound remote control device for controlling the pitch of a variable-pitch propeller on a ship's drive mechanism while at the same time controlling the speed of the ship's engine, and provides a control mechanism for compound control under various control conditions, whereby the conventional equipment being of a complex structure using 2 cams, is simplified by using one cam and a pressure-control valve cooperating therewith. With said control device, control of the speed of the aforesaid engine and the control of the pitch of the variable-pitch propeller are carried out by using air-pressure signals under various control conditions, that is, where the relationship of the various control air pressures in relation to the position of the control lever varies as for example shown in FIG. 1.