Abstract: An optical component protector, comprising a transparent plate, configured to be mounted in front of an optical component to be protected and a plenum chamber, connected to a top edge of a transparent plate wherein the plenum chamber is configured to receive a supply of gas from a gas supply and provide a curtain of the gas across a surface of the transparent plate that is on an opposite side of the transparent plate from the optical component.

Abstract: A negative hinge offset rotor head for a coaxial helicopter, the rotor head having two or more flapping rotor blades having outer and inner tips, the inner tips rotatably attached to a hinge attachment rotated by a driveshaft where the driveshaft is positioned between the rotor blades and the rotor blades' respective hinge attachment.

Abstract: A differential thrust vectoring system including a first thruster rotation assembly configured to rotate a first thruster relative of an aircraft, a second thruster rotation assembly configured to rotate a second thruster of an aircraft, and an actuator. The system is configured such that actuation of the actuator causes disparate rotation about the tilt axis of the first and second thrusters.

Abstract: A mast spacer provided between a mast bearing and a mast nut in a main shaft of a helicopter, has a cylindrical spacer body. A first end of the mast spacer is a bearing contact end which is fittable to an inner race of the mast bearing. For example, the bearing contact end is provided with bearing projections which are fittable to recesses provided in the inner race of the mast bearing. The spacer body is provided with slits, for example, a spiral slits penetrating its side wall. The slits have a linear shape crossing an axial direction of the cylindrical spacer body.

Abstract: A water turbine device is disclosed. The water turbine device includes a water shaft, a plurality of blade frames, a plurality of turbine blades, a pivot shaft and a blade control mechanism. The water shaft has a first axis. The plurality of blade frames are radially distributed around the water shaft. The plurality of turbine blades are mounted on the plurality of blade frames respectively. The pivot shaft is disposed on a corresponding one of the plurality of blade frames, has a second axis, and allows one of the plurality of turbine blades corresponding to the corresponding blade frame to be pivotally mounted on the corresponding blade frame. The blade control mechanism is disposed on an end opposite to the pivot shaft on the corresponding blade frame, wherein the turbine blade mounted on the corresponding blade frame has a stopper adjacent to the blade control mechanism.

Abstract: A blade device for a mixing propeller has a rocking shaft and a plurality of blade units. The blade unit is made of a flexible material and is installed on the rocking shaft via a fixing groove. The blade unit includes a horizontal propelling flexible blade and a vertical uplifting flexible blade. The fixing groove has a horizontal section and a vertical section. One end of the horizontal propelling flexible blade is inserted in the vertical section of the fixing groove while the other end of which is kept free so that it can swing back and forth. One end of the vertical uplifting flexible blade is inserted in the horizontal section of the fixing groove while the other end of which is kept free so that it can swing back and forth.

Abstract: A closure device for connecting two parts includes a first connecting module and a second connecting module. The first connecting module can be arranged on the second connecting module in a closing direction, is mechanically latched with the second connecting module by a latching means in a closed position, and is held at the second connecting module against the closing direction. The first connecting module can be released from the second connecting module by movement of the first connecting module in an opening direction. A form-fit element is arranged on one of the connecting modules, which is formed to engage a recess on the other one of the connecting modules after establishing the latching of the first connecting module with the second connecting module by moving the first connecting module relative to the second connecting module against the opening direction.

Abstract: A partly cruciform flexbeam (1) of a bearingless main rotor system of a helicopter with a hub drive and an airfoil blade. The partly cruciform flexbeam (1) comprises a flexbeam head (2) with a flat bearing laminate at one end, a root end (3) opposed to said flexbeam head (2) and a flexbeam body (6) between said flexbeam head (2) and said root end (3), said flexbeam body (6) being torsion soft with a substantially cruciform cross section. The invention is as well related to a method of manufacturing such a partly cruciform flexbeam (1).

Abstract: According to one embodiment, a bearing is situated in a rotor system. The bearing features a housing having a first opening therethrough, a first member disposed within the first opening and having a second opening therethrough, and an elastomeric bearing disposed within the second opening and having a third opening therethrough configured to receive a shaft. The first member having at least one substantially curved surface. A sliding element bearing disposed between the housing and the first member.

Abstract: An autorotative enhancement system comprises a transmission having a driveshaft configured to couple to an engine. A mast is configured to couple to multiple rotor blades. An autorotative assist unit is configured to the transmission and is configured to store energy during normal operation and drive the rotor blades through the transmission to provide supplemental autorotative assistance upon loss of engine power.

Abstract: A rotor blade assembly includes a flex-beam member and a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length. A rotor blade surrounds the flex beam member and extends from the torque tube to a blade tip. A connecting pin assembly secures the rotor blade and the torque tube at the flex-beam member. The connecting pin assembly includes a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade from a first rotor blade side and a second pin member located at a second rotor blade side. A clamping load between the first pin member and the second pin member secures the rotor blade and torque tube to the flex-beam member.

Abstract: A coaxial, dual rotor system includes a first rotor assembly positioned at a rotor axis. A first rotor quill shaft is operably connected to the first rotor assembly at the rotor axis to drive rotation of the first rotor assembly about the rotor axis. A nonrotating static mast extends along the rotor axis through the first rotor quill shaft. A second rotor assembly is positioned at the rotor axis. A second rotor quill shaft is operably connected to the second rotor assembly to drive rotation of the second rotor assembly about the rotor axis. The second rotor quill shaft is coaxial with the first rotor quill shaft and disposed inside of the static mast. A second rotor bearing is positioned between the second rotor assembly and the static mast to transfer loads from the second rotor assembly to the static mast.

Abstract: A fluid turbine comprising a rotor, having an axis of rotation, comprising at least two rotor blades disposed at a radius from the axis of rotation, each rotor blade having a pitch axis and a variable pitch angle. The fluid turbine comprises a mechanism operable to control the pitch angle of at least one rotor blade about its pitch axis and to vary the pitch angle of the rotor blade between various pitch angles as the blade moves radially about the axis of rotation of the rotor.

Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.

Abstract: According to one embodiment, a rotor system includes an anti-rotation sleeve featuring an outer recess portion and a tilt sleeve positioned about the anti-rotation sleeve and having an opening therethrough. A first swashplate ring is positioned about the tilt sleeve and features an inner recess portion. An anti-rotation mechanism is disposed through the opening and at least partially in the outer recess portion and the inner recess portion. The anti-rotation mechanism is operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve. A second swashplate ring is positioned about the first swashplate ring and rotatable about the anti-rotation sleeve.

Abstract: A vertical axis wind turbine having a plurality of upright airfoils pivotally engaged. A continuous adjustment of the angle of attack of the airfoils to oncoming wind is provided by rotation of a control plate connected to the vanes which are mounted upon a rotating drive plate. A vane can be employed to rotate the control plate to affect the continuous adjustment of the airfoils.

Abstract: According to one embodiment, a control assembly includes a first gimbal and a second gimbal. The first gimbal is rotatable about a first axis of rotation. The first gimbal comprises a first linkage attachment point offset from the first axis of rotation. The second gimbal is rotatably coupled to the first gimbal and rotatable relative to the first gimbal about a second axis of rotation. The second gimbal comprises a second linkage attachment point offset from the second axis of rotation and a control shaft attachment point.

Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.

Abstract: A heater with 360° rotation of a heated air stream is provided. The device includes a housing, a motor, an impeller, a heating element, an air stream deflector and a rotational engine. More specifically, the device is directed toward a portable space heater having an outward radial projection of a heated air stream in combination with 360° rotational movement for reducing air temperature stratification and uneven heating problems in a room.

Abstract: The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).

Abstract: A coaxial dual-rotor model helicopter system includes a power control mechanism, a transmission mechanism, a control mechanism and a rotor mechanism. The rotor mechanism includes an upper rotor and a lower rotor coaxially installed on an upper side and a lower side of a main shaft and controlled by an inner shaft and an outer shaft for rotating. The control mechanism includes a Bell self-balance mechanism to control the upper rotor and a Bell-Hiller control structure to control the lower rotor. The power control mechanism controls the rotor mechanism through the transmission mechanism and the control mechanism. The present invention achieves balance effect through the upper rotor by employing the Bell self-balance mechanism that has a great stability to provide automatic control. The lower rotor aims to control direction and employs the Bell-Hiller control structure that has a high maneuverability to perform active control.

Abstract: A wind turbine for generating electricity has been developed. The turbine includes a housing for securement to a support. A wheel is mounted within the housing and is rotatable about a horizontal axis. The wheel has an axle assembly and a number of blade assemblies affixed thereto. Each of the blade assemblies has a frame with a spaced-apart pair of uprights and a crosspiece connecting the uprights. Each of the blade assemblies also having a pair of movable blades positioned within the frame with each of the blades being hingedly fastened to a respective one of the uprights. A brake actuator assembly is associated with each of the blades for relieving pressure imparted by strong winds on the blades. A brake operator assembly, disposed principally within said axle assembly, synchronizes the movement of the blades. An electrical current generator is connected to the wheel so as to be powered thereby.

Abstract: A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.

Abstract: A blowing mechanism for a column type electric fan comprises an impeller, a driving motor, a tube-like air ducting assembly, and a swing mechanism. The driving motor is mounted onto a supporting plate attached to the fan's housing. A micromotor of the swing mechanism is fixed onto a connecting disc-like part of the housing. The air ducting assembly comprises an inlet, an outlet, and a flow guiding plate and a flow deflecting plate connected between the top part and the bottom parts of the housing. An upper supporting shaft for the impeller is rotatably attached to the housing through a bearing, and a lower supporting shaft for the impeller is connected to an output shaft of the driving motor. The air ducting assembly is movably carried on the bearing rollers, the disposed on the supporting plate. A link rod of the swing mechanism is movably connected to a rocker extending from the air ducting assembly.

Abstract: A cooling fan is provided that does not place limitations on the installation conditions for the fan, is capable of cooling a backlight unit of a display panel with high efficiency, and produces less noise during operation. Also provided is an image display apparatus equipped with the cooling fan. The cooling fan includes a fan rotator composed of a rotational shaft that is rotationally driven by a driving motor and two vanes that have parallel revolution shafts that rotate together with the rotational shaft, are freely rotatable on the shafts, face one another, and revolve around the rotational shafts and a vane angle control unit that implements control so that each vane has a maximum rotation angle when a revolution angle of the vanes is in a vicinity of a first revolution angle and each vane has a rotation angle of 0° when a revolution angle of the vane is in a vicinity of a second revolution angle that is perpendicular to the first revolution angle.

Abstract: A control system for a rotorcraft is disclosed. The control system includes a stepped mixing linkage, such that a selected amount of right-left lateral cyclic output is generated for certain amounts of forward-aft cyclic input. The stepped mixing linkage includes two supporting links and a floating link pivotally coupled between the two supporting links. The ratio of the lengths of the two supporting links to the length of the floating link is small, thereby generating a selected lateral sinusoidal output, a selected rotation of the sinusoidal output, and a selected ramped output in response to each forward-aft pilot input command.

Abstract: Adjusting mechanism for desired angle of an oscillating electric fan is disclosed. The adjusting knob is conveniently located about the top rear portion of the fan motor, adjacent the clutch knob. Adjusting the oscillating angle may be made when the fan is at rest, when it is running and oscillating at the same time, or when it is running at a fixed direction. Adjusting is fast and simple, only one hand is needed and no tools and mechanical know-how is necessary.

Abstract: A feathering fluid-driven turbine comprises impellers, arranged around the turbine axis and affixed to axles disposed parallel to the axis of rotation of the turbine, and further comprises a vane, such as a wind vane, which points in the current direction of fluid flow, mounted on an axis. The impellers are operatively engaged by a feathering mechanism, which, responsive to the direction indicated by the vane, rotates the impellers along their axles so that impellers on the windward side of fluid flow are aligned to present maximum aerodynamic resistance to fluid flow and impellers on the leeward side of fluid flow are aligned to present minimum aerodynamic resistance, thereby maximizing torque output of the turbine regardless of direction of fluid flow. The feathering mechanism comprises an offset cam affixed to the axis of the vane, moving in conjunction therewith as the direction of fluid flow changes. Fitted to the cam is a collar that is rotatable with the rotation of the turbine.

Abstract: A cycloidal propeller to achieve strictly a rudder operation includes accessory apparatuses containing accessory drives. Clutches are used to couple the accessory drives to the propeller shafts, and additional clutches are provided to disengage the fixed connection of the normal propeller mechanism to the wing shafts in cruising operation.

Abstract: A helicopter blade pitch control system allows blade pitch to be controlled with regard to the degree of rotational position of the blade with respect to the direction of travel and also the degree of pitch. The invention provides an improved arrangement wherein speed paddles attach to rotor blades can change in pitch around the circle of rotation of the blade and also the amount of pitch change can be adjustably changed by the pilot. The apparatus includes a cylindrical member surrounding the rotor of the helicopter and being static with respect thereto so that variable pitch speed paddles connected to and forming a part of the blade assembly and which carry rotating foot members track the upper surface of the cylindrical member changing the pitch of the blade as it moves through a 360 degree rotation.

Abstract: Disclosed is a two cylinder water well pumping system which uses the wind as a primary driving force with an alternate electric motor drive for use when the wind force is not adequate. The wind drives a square wheel turbine which in turn drives a swash plate which provides a cam surface which then drives a semaphore assembly directly or indirectly connected to sucker cables in turn connected to two pistons carried, respectively, in two cylinder sleeves. The inclined angle of the swash plate alternately drives the pistons to pump water from a well into a storage tank also serving as a mainmast supporting said turbine. In an alterenative embodiment, an electric motor is connected to drive an osillatable bar on a mechancial relay. The oscillatable bar is connected by cables to the semaphore assembly, and may be disconnected from the semaphore assembly by a solenoid. In this embodiment, the sucker cables are connected to the rockable bar in the mechanical relay rather than to the semaphore assembly.