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 seat base for use in aircraft has a first cross member, a second cross member, a first leg, a second leg, and a base plate having a first bendable tab and a second bendable tab facing away from the first tab. The first cross member, the second cross member, and the base plate are each configured to be secured to the first and second legs in an extended position and a retracted position. The first and second legs are configured to be secured to seat feet and floor tracking rails. The first and second cross members are secured to the base plate so as to allow for selective rotation of the first and second cross members in response to relative vertical movement of the first leg with respect to the second leg.

Abstract: An internally heated and pressurized system for fabricating a composite laminate structure and method for use thereof is disclosed. One of a plurality of thin, thermally conductive bond tools, prepreg fiber reinforced composite layers, and a pressure applying membrane are nested within a heated base, and then covered by a pressure sealed cover. The system is pressurized through the pressure sealed cover. The pressure causes the pressure applying membrane to force the prepreg fiber reinforced composite layers onto the upper surface of the bond tool. The heated base transfers heat to the composite layers via the bond tool, which heats and cures the composite layers together and to a shape determined by the upper surface of the bond tool. Each bond tool is formed with a generic lower surface for nesting within the heated base and an upper surface for forming composite layers into the shape of a specific part.

Abstract: A relief valve assembly limits the maximum torque of a gear motor of a hydraulically driven tool. The relief valve assembly dumps flow to a return channel to return hydraulic fluid to the supply when the relief valve assembly is activated. The relief valve assembly is placed in the channel of a directional valve spool, and varies its pressure setting depending upon spool position. This is useful to vary the pressure settings of a hydraulic motor in different directions.

Abstract: The invention relates to an extrusion blow-molded component (1) made of thermoplastic resin. The component (1) preferably comprises a recess in the exterior wall, the recess being configured as a blind bore (2) provided with at least one convolution (4). The blind bore (2) serves to receive a complementary fastening element (6) equipped with a threaded stem (17). A contour is provided in the region of the orifice (3) of the blind bore (2), the contour positively interacting with a contour that is complementary on the fastening element upon insertion of the fastening element (6), wherein the angular position of the contour (2) is selected such that inserting the contours into each other is possible only by overcoming an axial tension that is built up due to the rotating movement of the parts to each other under elastic deformation of the plastic (FIG. 1).

Abstract: The external crash attenuation airbag includes an inflatable bladder which is inflatable to an exterior of an aircraft, so that the inflatable bladder is generally located between the aircraft and a crash surface when inflated. The airbag includes a vent configured to burst at a predefined burst pressure, the vent being located along a side portion of the inflatable bladder. The airbag also includes a vent support located approximate the vent, the vent support being configured to prevent deformation and therefore maintain the effectiveness of a venting area of the vent, and the vent support being rigid and annular and includes an upper portion and a lower portion that are hinged together around the vent.

Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Abstract: The present application includes a blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor. A feedback lever associated with each blade is pivotally mounted to the rotating portion of a swashplate assembly. A pitch link connects an output arm of a lever to a pitch horn of a corresponding blade, and a feedback link connects the input arm of the lever to a yoke. Flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever. Rotation of the lever causes motion of the pitch link, which changes the pitch angle of the attached blade. This provides for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.

Abstract: According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Abstract: A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation.

Abstract: A rotary chuck includes a clamp assembly, a first drive mechanism for operating the clamp assembly to clamp an associated workpiece, a frame rotationally fixed to the clamp assembly, and a second drive mechanism for rotating the frame and the clamp assembly. The second drive mechanism can rotate the frame and the clamp assembly around 360 degrees. A pair of alignment springs are engaged with a mounting plate upon which the second drive mechanism is mounted. The mounting plate can pivot relative to a stable surface to which it is mounted, and the springs limit the pivotal movement. Each first and second drive mechanism includes a motor, and are connected to a microprocessor for operation of the respective motor.

Abstract: According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal.

Abstract: A mount system for supporting a transmission in an aircraft can include a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis; a second link coupled between the structure of the aircraft and the transmission, the second link having second axis; a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis; and a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis. A forward focal point of the first axis and the second axis has a different waterline component compared to an aft focal point of the third axis and the fourth axis.

Abstract: A bearing assembly can include a top retainer; a middle retainer having a first concave spherical surface; a bottom retainer having a second concave spherical surface; a spherical ball member; and an elastomeric member coupled to the first concave spherical surface, the second concave spherical surface, and an outer surface of the spherical ball member.

Abstract: A power generation device for a utility vehicle having a battery source, a logic/driver module operably coupled to the battery source and capable of outputting power to a motive drive system, an internal combustion engine capable of outputting a mechanical driving force, and a generator system operably coupled to the internal combustion engine and electrically coupled to the logic/driver module. The generator system is capable of operating as a generator in response to the mechanical driving force of the internal combustion engine, thereby outputting electrical energy to the logic/driver module, and further is capable of operating as an electric motor in response to input of electrical energy from the logic/driver module. Between a first voltage and a second voltage, the output of the generator is reduced. Between the second voltage and a third voltage, the generator output is reduced to zero and the internal combustion engine is reduced to idle.

Abstract: A method for fabricating a repair laminate for a composite part having an exposed surface includes applying a bonding material to the exposed surface and forming an uncured ply stack assembly on the bonding material. The uncured ply stack assembly is formed by forming and compacting a series of uncured ply stacks. The ply stack assembly and bonding material are then cured.

Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

Abstract: The adaptive reference model algorithm uses a gain scheduling feature combined with a customized Least-Squares routine as an adaptive method for adjusting feedback control so as to account for variations in Transfer Function (G), thereby optimizing the effectiveness of the Active Vibration Control (AVC) System. The Least-Squares routine identifies the transfer function in a background process without interruption of closed loop vibration control. This identification approach is accomplished without intentional interrogation of the AVC actuators and without intentional vibration level changes. For this adaptive control logic, the dynamic relationship between AVC actuators and AVC sensors is represented by a mathematical model of Transfer Function (G). The mathematical model of Transfer Function (G) is continuously updated by the Least-Squares routine.

Abstract: According to one embodiment, a drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion has less torsional stiffness than the first and second bearing housings such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing.