Abstract: A flying object control device includes: a determination unit that determines, based on a remaining capacity of a battery, whether or not to restrict supply of surplus electric power to the battery, the surplus electric power being a surplus of electric power generated by a generator; and a control unit that, when the determination unit determines to restrict the supply of the surplus electric power to the battery, causes the surplus electric power to be consumed by a motor by increasing a rotor rotational speed that is a rotational speed of a rotor, and adjusts a steering angle of an elevator to restrict ascent of a fuselage caused by an increase in the rotor rotational speed.

Abstract: A tripod jack cylinder removal tool including a lifting eyebolt attached through an up flange and further through and up flange aperture to a lock nut. The flange is secured to a pipe at a pipe top end, the pipe further having a bottom end wherein a down flange having a down flange aperture is attached to the pipe and a bolt having threads protrudes through a down flange aperture.

Abstract: The present invention includes a thrust control apparatus, method and kit for a tiltrotor craft comprising a thrust control handle; a first and a second bar connected to the thrust control handle and connected to a floor support; a first end of a transverse bar connected to the first bar; a linker connected to a second end of the transverse bar; and a crankbell connected to the floor support below the first and a second bars, wherein a first end of the crankbell is connected to the linker, wherein the thrust control handle has a substantially linear motion that controls engine thrust, and the crankbell transfers the substantially linear motion of the handle into a substantially perpendicular motion that engages an engine thrust control at a second end of the crankbell.

Abstract: An unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having an open position and a closed position, the closed position establishing an interior that is weather resistant to an environment external to the UAV pod and a vertical takeoff and landing (VTOL) UAV enclosed in the UAV pod so that the UAV pod in the closed position provides a weather resistant interior for the VTOL UAV.

Abstract: The present invention provides a steering device that includes: a pair of armrests which are mounted on left and right sides of a seat for a vehicle and are formed to be movable in a forward and backward direction of the seat, and on which arms of a driver are placed; and a pair of steering members which are provided on the pair of armrests, are formed to be grasped by the driver in a state in which the arms of the driver are placed on the pair of armrests, and are moved in the forward and backward direction to change a steering angle of the vehicle. The armrests are configured to move in the forward and backward direction in association with the movement of the steering members in the forward and backward direction.

Abstract: An actuator for at least one flight control surface of an aircraft. The actuator has at least two actuator members for actuating the flight control surface between two extreme positions and a motor connected to the actuator members by at least one rotary motion transmission line. Each actuator member includes a drive pinion and the actuator is arranged so that the transmission line has an angular amplitude of less than one revolution during movement of the flight control surface between its two positions. The motion transmission line is arranged to allow only one angular position between the drive pinions and the actuator member.

Abstract: Control surface operating systems for controlling aerodynamic control surfaces of aircraft are provided. The systems includes a drive system operably connected to a drive shaft, the drive system including a continuously variable transmission, at least one actuator operably connected to the drive shaft and arranged to convert rotational movement of the drive shaft to move at least a portion of the aerodynamic control surface, and at least one control surface operably connected to the at least one actuator, wherein the at least one control surface is adjusted by the at least one actuator.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

Abstract: Automatic flight control actuator systems are provided. In one example, the system includes a pilot input linkage that receives an input and a flight surface output linkage adapted to control a flight surface. The system also includes a strain wave gear including a flex spline coupled to one of the pilot input linkage and the flight surface output linkage. The strain wave gear further includes a circular spline coupled to the other of the flight surface output linkage and the pilot input linkage, and coupled to the flex spline such that the input from the pilot input linkage is transferred to the flight surface output linkage via the strain wave gear.

Abstract: An electromechanical portion of the control stick includes a two-axis gimbal, with each axis including a mechanical gimbal structure supported by rolling element bearings, cam based centering mechanisms, linkages to connect a geared power-drive including a resolver commutated brushless DC motor and compound-planetary gearhead to provide active force feedback, and several electrically independent RVDT position sensors. The gearing architecture uses a fixed-cage, rotating internal gear arrangement on a planetary gearhead, which may be single or multi-stage. The output torque of the gearhead is provided by a feature on the outer housing of the rotating internal ring gear, allowing an axial placement of the entire power-drive in a more central location, reducing the moment load on the gearhead output cage bearings, and facilitating a compact drive arrangement of the gimbal using linkages. Additionally, a common power-drive can be used for both the roll and pitch axes.

Abstract: The present invention pertains to a four-bar vehicle controller providing up to three independent or combined axes of control inputted via a yoke, steering wheel or other hand operated input means attached to an aft end of a control input shaft rotatably mounted to and extending rearwardly from an upper bar member of a four-bar assembly. The assembly is configurable to provide an operator a familiar steering experience and to improve cockpit ergonomics and control inputs. A forward end of the control input shaft is configurable to impart yaw control input or steering control input, or both, to one or more rotation transmission means coupled with yaw control linkage or steering control linkage, or both. The vehicle controller is configurable to control a vehicle equipped to operate in, or a simulator equipped to simulate operation in, one or more transportation modes, such as flight, ground-based, or water-based transportation modes.

Abstract: Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides a first flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades.

Abstract: The invention relates to an aircraft opening window comprising at least one pane (2) equipped with a movable frame (3), the assembly comprising the said movable frame (3) and the said at least one pane (2) being movable relative to a fixed frame (1), an element (4) for maneuvering the said movable assembly, a device for locking/unlocking and opening/closing the said movable assembly actuated by the said maneuvering element (4) and means for guiding and supporting the said movable assembly.

Abstract: A complex-dynamic air and ground vehicle control inceptor assembly that provides active positional control with the capability of back drive (pilot over-ride) via a direct connection between the lever, a high gear-ratio gearbox, and the motor without the use of a clutch.

Abstract: This invention discloses a steering structure of toy plane and an infrared four-channel remote-control electric toy plane. The steering structure of toy plane includes small internal guide, large external guide, elliptical shaft, and sector gear; the small internal guide has a rectangle hole with rounded angles and two arc-back bosses, and driven by the sector gear, the small internal guide contacts the elliptical shaft along the second and fourth quadrants; the large external guide has the elliptical hole, and driven by the sector gear, the large external guide contacts the elliptical shaft along first and third quadrants.

Abstract: There is described a helicopter having a transmission for transmitting motion from a driving member to a driven member; the transmission has at least a first gear driven by the driving member, and a second gear meshing with the first gear and in turn driving the driven member; the first and second gear have teeth shaped so that the gears mesh with one another at at least two pairs of respective simultaneously meshing teeth; the teeth of at least one of the gears have a profile having an end portion relieved with respect to a starting theoretical involute; and the pattern of the distance between the points of the end portion and the starting involute along an axis of the tooth has at least a first and a second segment sloping with respect to each other.

Abstract: Methods and apparatuses for supporting aircraft components, including actuators are disclosed. An apparatus in accordance with one embodiment of the invention includes an actuator housing having an actuator receptacle that securely yet releasably receives an actuator. The actuator receptacle can include conformal walls that conform at least in part to the shape of the actuator and can accordingly squeeze the actuator and properly align the actuator. At least one of the actuator walls can further include a projection that is releasably received in a corresponding recess of the actuator. One of both of these features can releasably secure the actuator relative to the aircraft, reducing and/or eliminating the likelihood that the actuator will be misaligned and/or mispositioned relative to the aircraft during installation and/or replacement.

Abstract: An override device comprising a manual control part, an inlet gear part, and an outlet gear part which are mounted to rotate about the same axis, means being interposed between the inlet gear part and the outlet gear part so that in normal operation the inlet gear part rotates the outlet gear part, the manual control part also carrying a cam which, in co-operation with complementary means of an intermediate part suitable for following said cam, serves to disengage the means interposed between the inlet gear part and the outlet gear part under the effect of torque exerted on the manual control part, the device also having means then enabling the manual control part to drive the outlet gear part, wherein the drive means interposed between the inlet gear part and the outlet gear part comprise a set of friction disks and spring means suitable for exerting a force to compress said disks against one another, and wherein the intermediate part suitable for following the cam carries at least one pusher-forming element

Abstract: Referring to FIG. 2, disclosed is an aircraft compound no-back/offset gearbox (2) with an integral load proportional safety (no-back) brake (50). The four gears are all 16 diametral pitch, involute external spur gears with 20 degree standard pressure angles. The two gear stages are interconnected with a mechanical fuse or shearout (40) designed to fail under excess shear loads and protect components downstream of the input shaft (10) from excess torque in the event of a system jam. The shearout (40) is essentially a quill shaft with external splines at both ends and an hourglass-shaped shear neckdown in the middle. The purpose of the no-back brake (50) is to prevent air loads from causing slat movement in the event of a torque tube disconnect. Referring to Figure, the no-back consists of a set of ball ramp (22) and brake plate components connected to the gearbox's output shaft.

Abstract: A geared rotary actuator comprises at least two axially aligned compound epicyclic gear trains driven by an input shaft so that output ring gears in each train rotate relatively. Sun gears in adjacent gear trains are drivingly coupled to the input shaft through a differential device which permits limited rotational displacement between the sun gears. An element, for example an aircraft lift control surface, may be mounted on one set of the ring gears by means of spindles which extend normally of a plane which includes the axes of the ring gears, so that as a result of stresses therein the element may tilt locally about the spindles.

Abstract: A rotary geared actuator for pivotally connecting a flap to a wing of an aircraft, includes at least two adjacent actuator slices rotatably coupled together, each actuator slice including a sun gear rotatably coupled to a drive shaft and having gear teeth with a curved profile to enable movement of the actuator slices with respect to each other in conformance with bending of the wing, planetary gears in surrounding and meshing engagement with the gear teeth of the sun gear, a movable ring gear in surrounding and meshing engagement with the planetary gears, and a fixed ring gear in surrounding and meshing engagement with the planetary gears on opposite sides of the movable ring gear, each fixed ring gear being in meshing engagement only with planetary gears of one actuator slice; at least one fixed side tie bar connecting each fixed ring gear with the wing; at least one movable flap side tie bar connecting each movable ring gear with the flap; securing pins for securing each fixed side tie bar to one fixed rin