Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The proprotor hub assembly includes a hook receiver. The propulsion assembly includes a gimbal lock positioned about the mast. The gimbal lock includes a locking ring and a gimbal lock hook. The gimbal lock is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The gimbal lock hook is hooked to the hook receiver in the engaged position to secure the locking ring to the proprotor hub assembly.

Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The propulsion assembly includes a gimbal lock assembly positioned about the mast and including a plurality of radially outwardly extending and circumferentially distributed rollers. The gimbal lock assembly is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. In the disengaged position, the gimbal lock assembly enables the gimballing degree of freedom. In the engaged position, the rollers of the gimbal lock assembly contact the proprotor hub assembly to disable the gimballing degree.

Abstract: An orthogonal turbine having a first blade, a second blade, a first traverse connected to the first blade, a second traverse connected to the second blade, a first speed adjusting member having a first void, a first rear stop, and a first front stop, a second speed adjusting member, a disc having a first pin connected to the disc, and a shaft connected to the disc, where the shaft is configured to rotationally engage the first speed adjusting member and the shaft is configured to rotationally engage the second speed adjusting member, where the first speed adjusting member is connected to the first traverse, where the second speed adjusting member is connected to the second traverse, where the first speed adjusting member is rotationally engaged to the second speed adjusting member, and where the first void is configured to receive the first pin.

Abstract: The invention provides a vertical axis wind turbine to produce power relative to wind speed resulting in high torque output. During operation, all the blades of the turbine are in a continuous movement of changing their angles from fully open to fully overlap position during each rotation. At the heart of this concept is a frame circumventing the rotor, formed of a pair of top coaxial rings superimposed over bottom coaxial rings defining a central vertical axis distant from the shaft axis, each pair of top and bottom rings are freely movable by being mounted on bushings to the shaft by radially disposed beams and vertically disposed mounting members fixedly connecting the top and bottom rings. The Blade angle relative to incoming wind is controlled by these pair of rings which are controlled by the pair of weathervanes rotating on the central turbine shaft axis.

Abstract: A drive apparatus for an electrical generator (2) is disclosed. The apparatus includes arms (6) adapted to support blades (14) in a flow of fluid. A central shaft (4) pivotably supports each of the arms about a respective horizontal axis such that flowing fluid engages the blades to cause rotation of the shaft about its longitudinal axis to actuate an electrical generator (28). A flap (16) adjusts orientation of the arms about the respective horizontal axes in dependence on direction of fluid flow.

Abstract: A flyweight for use in a ram air turbine has a body with a circumferentially enlarged portion extending between flat sides spaced by an angle of between 45 degrees and 150 degrees. A pivot point is defined by a bore at a circumferentially intermediate point in the body, and in a relatively thin inner portion. The relatively thin inner portion extends beyond the pivot point to an end that will be radially inward when the flyweight is mounted in a ram air turbine. A governor, a ram air turbine and a method are also described.

Abstract: Variable-pitch propeller (1) of the type comprising at least one blade (6a, 6b, 6c) rotatably pivoted (20a, 20b, 20c) to a cylindrical casing of the propeller (3a, 3b, 4), a shaft coupled to an engine and coaxial to that propeller casing, a kinematic system (7, 8a, 8b, 8c, 10a, 10b, 10c, 11), coupled to the shaft, or to the propeller casing, and to above mentioned at least one blade, for regulating the rotary motion of said at least one blade around its own pivot axis to the propeller casing, as well as means (2, 14, 15) for transmitting the rotary motion of the shaft to the propeller casing, the propeller being shaped to provide at least one not null angular range for the free relative rotation of the above mentioned at least one blade (6a, 6b, 6c) around its pivot axis, relatively to the propeller casing (3a, 3b, 4). The propeller also comprises at least one elastic element (18, 18?) countering the relative rotation of said at least one blade relatively to the propeller casing (3a, 3b, 4), or vice versa.

Abstract: A blade pitch controlling apparatus and an application thereof are described. The blade pitch controlling apparatus includes a centrifugal device and a blade pitch variable device, and the blade pitch variable device is arranged under the centrifugal device. The blade pitch variable device has a downward stroke that is variable by the centrifugal device according to a centrifugal force induced thereon so as to drive the blade pitch variable device to change the setting angle of the blades of the wind power generator.

Abstract: A pop-off valve that, in one embodiment, provides overboost protection for an aircraft engine, is described. The pop-off valve includes a housing adapted for connection to a portion of a drive device containing a pressure medium. It also includes a pressure body movably disposed in the housing such that, in operation, a first side of the pressure body is exposed to the pressure medium while a second side is exposed to a reference force. In addition, the pop-off valve incorporates a control device adapted to receive at least one signal concerning at least one operating parameter of the drive device and, in response to the operating parameter signal, to control the reference force. As a result of movement of the pressure body within the housing, at least one first opening in the housing is exposed, permitting venting of the pressure medium.

Abstract: An aircraft control system includes a propeller governor in which a stepper motor is used to apply a compression force on a speeder spring, and a turbocharger in which a stepper motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the stepper motor in the propeller governor and the stepper motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.

Abstract: A system for controlling propeller blade pitch is disclosed. The system comprises a transfer tube, wherein the transfer tube defines an element of the rotatable portion and wherein the transfer tube is non-translating relative the rotatable and non-rotatable portions. A transfer bearing for providing hydraulic fluid to and interfacing with the transfer tube is also used, wherein the transfer bearing is located on the non-rotatable portion. The system further includes a pitch change actuator and a mechanism form for actuating the pitch change actuator, wherein the mechanism is fluidically connected to and translatable relative to the transfer tube. A device for measuring blade angle of the propeller blade is also provided, wherein the device is separate and distinct from the transfer tube.

Abstract: A system for controlling functions of a propeller having a plurality of blades is disclosed. The system comprises an electronic control for controlling the functions of the propeller. A plurality of backup devices are provided for backing up the electronic control upon the occurrence of conditions. These conditions include at least one of testing, manual override, and a malfunction in the electronic control causing at least one of the functions to endanger safety. The system further includes a bypass device for bypassing the electronic control and for invoking at least one of the plurality of backup devices to acquire control over at least one of the functions. The bypass devices include a mechanism for determining the occurrence of at least one of the conditions and for actuating electronic control override.

Abstract: An air driven turbine having variable pitched blades is provided that includes a pitch change mechanism and associated control circuits for automatically adjusting the pitch of the blades during either rotating or non-rotating operational modes of the air driven turbine. The pitch control mechanism includes a resettable overspeed protection device which is directly actuated by an overspeed condition of the turbine and operates independently from the pitch change mechanism to move the blades to a failsafe, feathered, or coarse pitch, low speed position. The pitch control mechanism utilizes a linear actuator in the form of an acme screw drive. The air driven turbine includes a ball ramp thrust bearing for attaching the blades to a hub of the turbine in such a manner that during rotation of the turbine actuation loads on the pitch change mechanism are reduced.

Abstract: A ram air turbine is provided for use in driving electric and/or hydraulic power systems in an aircraft, wherein the ram air turbine includes primary and secondary speed control governors. The primary governor includes centrifugal flyweights for cam-actuated adjustment of the pitch angle of a turbine blade or blades, within a selected adjustment range, to achieve substantially constant turbine speed in response to varying air speed and/or load. The secondary governor preloads the turbine blade or blades to a selected midrange pitch angle in the at-rest condition, wherein the midrange pitch angle is chosen for faster turbine acceleration on deployment to the desired full-speed rotation. The secondary governor controls blade pitch angle until the turbine reaches a selected rotational speed, after which the primary governor regulates and adjusts blade pitch angle within the selected adjustment range.

Abstract: An overspeed protection system for an aircraft fan engine wherein blades are rotatable from a coarse pitch to a fine pitch to a thrust-reverse condition. A wobbler-type hydraulic motor is provided for rotating the blade. An overspeed governor is operatively associated with the motor for effecting rotation of the blades in a direction toward the coarse pitch condition. A control, including a solenoid valve actuatable in thrust-reverse mode, changes the sense of the hydraulic motor to drive the motor further into thrust-reverse on actuation of the overspeed governor means.

Abstract: Apparatus for controlling the pitch of the blades of a variable pitch, governor controlled, aerial propeller of which the pitch of the blades is variable between a coarse pitch limit and a fine pitch limit to match the torque of its prime mover has holding means (A) to maintain a forward thrust-generating blade pitch angle greater than the fine pitch limit with the prime mover idling as when an aircraft propelled by the propeller is taxi-ing whereby the propeller rotates more slowly, and hence more quietly, than it would otherwise. Preferably the holding means is effective by actuating a lock pitch solenoid valve (21) and an autofeather valve (18).

Abstract: A propeller control system, including a propeller governor, overspeed governor, and a bleed valve, is provided to control the flow of fluid under pressure from a pump to an hydraulically controlled, variable pitch propeller driven by a gas turbine engine. Under normal operating condition, the propeller governor controls the pressure of the fluid supplied to the propeller, adjusting its pitch as needed to maintain constant speed operation. The overspeed governor prevents overspeeding of the propeller and engine in the event that the propeller governor becomes inoperative, and, in the event that both governors become inoperative, the bleed valve prevents sudden increases in fluid pressure, attendant with the failure, from adjusting the pitch of the propeller towards an overspeed position.

Abstract: A pitch control system (10) for a variable pitch propeller effects engine governor (330), control of blade pitch under normal operating conditions and automatically effects direct (beta) control of blade pitch by the power lever (305) throughout a predetermined range of power lever settings. The system is hydromechanical and comprises a pitch actuator (40) and a pair of control valves (120 and 210), a first of the valves (120) applying a metered fluid pressure from a governor controlled pilot valve to the actuator and blocking that signal and replacing it with a supply fluid pressure at the point of transition from governor to beta control. The second control valve (210) effects a controlled draining of the actuator and connection thereof with the power lever (305).