70 results about "Translational motion" patented technology

Methods and systems are provided for nautical stationkeeping of free-floating objects. In one example, a method includes adjusting translational motion of a body freely floating in water by rotating the body. The translational motion may be adjusted, for instance, to maintain the body within a geographic area. In certain examples, the adjustment of the translational motion may be realized via a Magnus effect induced by rotating the body. The body may be configured as, for example, a free-floating object such as a wave engine.

The invention relates to an ultrasonic inspection system (600) designed for the automated non-destructive testing of large composite structures, particularly in the aerospace industry. Traditional ultrasonic inspection requires precise probe positioning, which can be affected by discrepancies between the CAD model used for programming and the actual part. The proposed system includes a probe holder moved by an end effector (650), ensuring constant alignment of the ultrasonic probe (150) despite these discrepancies. The probe holder incorporates a dual compliance mechanism: an upper system allowing limited translational movement with elastic return to maintain alignment, and a lower system providing angular adjustments via two intersecting axes of rotation. Rolling elements ensure a constant distance and orientation between the ultrasonic probe and the surface to be inspected.Adapted to complex geometries, this system allows reliable automated ultrasonic control, compensating for positioning variations, thus improving the accuracy and repeatability of defect detection Figure 6.

The invention provides an electric control method and device for a safety seat and the safety seat, and relates to the technical field of safety seats, in electric units of the safety seat, a first electric unit is used for driving a seat body to do one of rotary motion and translation motion relative to a base, and a second electric unit is used for driving the seat body to do other one of rotary motion and translation motion relative to the base; the second electric unit is used for driving the seat body to do the other one of the rotary motion and the translational motion relative to the base; the method comprises the steps of controlling the first electric unit to act; judging whether a first feedback signal corresponding to the first electric unit is received or not, wherein the first feedback signal corresponding to the first electric unit is an in-place feedback signal when the first electric unit reaches a preset position and / or a resistance-encountering feedback signal when the first electric unit encounters resistance; if yes, the state of the first electric unit is judged; if the first electric unit is in the in-place movement state, it is judged that the first target action is completed. The position of the seat can be flexibly adjusted in different dimensions, and diversified use requirements of users are met.

The present invention relates to a trolley-type landing gear with a retractable rotating frame, comprising a strut buffer, a frame, wheels, shock absorber cylinders, a double parallelogram mechanism, a retractable actuator cylinder, and a strut coordination rod; the frame is equipped with wheels at the front and rear. By utilizing the inherent characteristics of the motion adder of the double parallelogram mechanism, the present invention isolates the translational and rotational motions of the frame from each other, so that the translational motion of the frame only drives the strut buffers, and the rotational motion of the frame only drives the shock absorbers. The rigid body rotation of the frame is transmitted to the shock absorber via the double parallelogram mechanism and does not affect the strut buffer. In other words, the shock absorber not only performs the function of shock absorption but also performs the function of retracting and extending the landing gear, achieving both functions using a single mechanism.

The invention provides a bending actuation type four-degree-of-freedom micro-motion platform with double piezoelectric actuators and an excitation method of the bending actuation type four-degree-of-freedom micro-motion platform, and belongs to the technical field of image stabilization and vibration suppression platforms. The micro-motion platform comprises a tail end platform, eight first bolts, two flexible hinges, two amplitude-change poles, four strain gauges, two piezoelectric actuators, two second bolts and a base; all the components are fixedly connected through the first bolt and the second bolt; the flexible hinge is used for transmitting linear and bending motion, and the piezoelectric actuator can achieve displacement output in a bending mode in the up-down direction and the left-right direction under the control of two paths of voltage. By coordinating the bending directions of the two piezoelectric actuators, the tail end platform can achieve translational motion along the Y axis and the Z axis and rotational motion around the Y axis and the Z axis, and therefore four-degree-of-freedom precise micro-motion adjustment is completed. The invention has the advantages of compact structure, small number of drivers, fast response and high precision, and is suitable for aerospace, navigation and other application scenes with strict requirements on optical imaging stability.

The present disclosure relates to a processing circuit configured to determine information indicative of a position of a translational movement sensor (16) on a vessel (10), and to a method for determining the information, the vessel (10) extending along a vessel longitudinal axis (xmv) in a longitudinal direction, preferably corresponding to an expected direction of travel of the vessel (10). The vessel (10) extends in the vertical direction along a vessel vertical axis (zmv) and in the transverse direction along a vessel transverse axis (ymv). The transverse axis is perpendicular to each of the longitudinal axis and the vertical axis.

The present invention relates to a slat (108) for the leading edge of a swept aircraft wing, the slat comprising slat tracks (114) which determine the path of motion of the slat when it moves from a retracted position (FIG. 7) to a fully deployed position (FIG. 15). Each slat track (114) has a shape that follows a spiral path. Thus, the motion of the slat comprises a rotational component about a first axis that may be perpendicular to a flight path (120) and a translational component parallel to the first axis. When viewed from above, the slat may move primarily in a direction parallel to the flight path (120).

The invention relates to a seat (10) for a cabin crew mounted in an aircraft cabin, comprising: a seat structure (11) fastened to an aircraft floor; a cushion plate (12) and a backrest (13) mechanically connected to the seat structure (11), the cushion plate (12) being movable between a raised position and a lowered position; a space filling device (17) between a seat structure (11) and a bulkhead (16) of an aircraft cabin, the space filling device (17) comprising: a fixing part (20) fastened to the seat structure (11); and a movable part (21) which can be moved in translation relative to the fixed part (20) in order to be able to adjust the width of the space filling device (17) to a gap between the seat structure (11) and the partition plate (16).

The invention relates to an assembly of platforms (21), particularly for an aircraft seat, comprising: - a main platform (23), - a translation mechanism (31) enabling the main platform (23) to move in translation relative to a support (27), between a close and a distant position, - at least one arm (26) having a first end fixed to a structural element of a seat and a second end mounted for rotation relative to one end of the support (27), and - an extension platform (24) having at least one position in which, when the main platform (23) is in the distant position, the extension platform (24) extends in a plane parallel to the extension plane of the main platform (23) and having at least one portion offset longitudinally relative to the main platform (23) along the direction of translational movement (D1) so as to cover the translation mechanism (31). Figure 2a

Provided is a method of controlling horizontal translational motion of a rocket without changing the attitude of the body and without increasing manufacturing costs and operation costs. This allows for accurate execution of rocket landing operation. A rocket control system includes a gimbal actuator that controls a steering angle of a gimbal mechanism located on a lower side of the body of the rocket with respect to the center of gravity; a fin actuator that controls a steering angle of an attitude control fin located on an upper side of the body of the rocket with respect to the center of gravity; a measurement unit that measures a physical quantity related to motion of the body of the rocket; and a control unit that controls the gimbal mechanism and the attitude control fin according to a result of measurement by the measurement unit to control horizontal translational motion of the rocket.

The invention belongs to an aircraft ground test technology, and relates to a strength test restraining device for releasing rotational degree of freedom. Comprising a rubber cushion plate, a cover plate, an adapter plate, a force bearing shaft, a rocker arm support, a bearing support, a base, a first bearing a, a second bearing b and a locking nut. The device restrains the degree of freedom and releases the degree of freedom. Translation in the X direction and the Y direction is restrained by the rocker arm support. Translational motion in the Z direction is restrained by a force bearing assembling assembly composed of a force bearing shaft, a bearing support, a first bearing, a second bearing and a locking nut; the rotation in the X direction and the rotation in the Y direction are restrained by the bearing assembling assembly and the base. When the device is used for a sleigh undercarriage static test, the real installation state of the sleigh undercarriage can be completely simulated, and the rubber cushion plate can protect the sleigh undercarriage from being knocked and can also realize the real tire contact condition; the oval areas of the cover plate and the adapter plate simulate the actual contact area of the tire and the sleigh undercarriage, and the stress area is real.

A method for controlling an aerial vehicle, UAV, includes causing the UAV to adjust its orientation; monitoring a change in radio signal received at the UAV with the change in orientation; determining a translational movement of the UAV based on the monitored change; and causing translational movement of the UAV based on the determination.

The application provides a hinge and a vehicle. The hinge comprises a base, a connecting rod mechanism, a mounting seat and a rotating mechanism. The base is used for being connected to a vehicle body. In the application, the connecting rod mechanism plays a role of bearing the vehicle door and realizes a combined translational motion of the vehicle door in Y direction and Z direction, so that the mounting seat can move between a retracted position and an extended position. The transmission angle is changed by the rotating mechanism, and the rotating motion of the vehicle door in X direction is realized. The input end of the rotating mechanism is linked with the free end of the connecting rod mechanism, so that when the connecting rod mechanism acts, the rotating mechanism can act simultaneously to realize the translation and rotation of the vehicle door. The two groups of mechanisms are linked in the application, which improves the motion stability and structural compactness, and reduces the manufacturing cost.

The present invention provides a longitudinal attitude dynamics modeling method for a flapping-wing aircraft based on wind tunnel tests, including: simulating flight through wind tunnel tests to measure the experimental data of the longitudinal moment of the flapping-wing aircraft, calculating the average longitudinal moment and flapping frequency of the flapping-wing aircraft based on the experimental data; dividing the longitudinal moment into a first moment, a second moment and a third moment based on the flapping motion and translational motion of the flapping-wing aircraft, and the synergistic effect of the flapping motion and translational motion; establishing a no-inflow model for the longitudinal moment of the flapping-wing aircraft according to the first moment, and determining the first model parameter according to the average longitudinal moment and flapping frequency; based on the no-inflow model, establishing an inflow model for the longitudinal moment of the flapping-wing aircraft by combining the second moment and the third moment, and determining the second model parameter according to the average longitudinal moment and flapping frequency. The present invention avoids flight tests with higher equipment requirements, reduces the difficulty of data acquisition, and improves the modeling accuracy based on wind tunnel test data.

Control unit for a steer-by-wire steering system of a vehicle, comprising two control elements (1, 3) which are both coupled to each other and designed to be pluggable for exchange and which are configured to perform a rotational and / or translational movement for adjusting the steering angle, which can be positioned within the driver's reach on a cockpit (7) and on both sides of a driver's seat (5) at attachment points next to the driver's seat (5), wherein the control elements can be inserted into receptacles (9, 13, 15) formed at these positions, characterized in that the control elements (1, 3) are flexibly interchangeable on the vehicle interior and the receptacle (9) on the cockpit is designed as a rail in which the control elements (1, 3) can be guided on both sides to a spacer (11).

A control mechanism for an aircraft, comprising: a switching mechanism having a translatable portion and a rotatable portion, the translatable portion being reversibly translatable and connectable to a manipulator; a manipulator connector connected to the translatable portion of the switching mechanism; a differential device connected to the rotatable portion of the conversion mechanism, the conversion mechanism configured to reversibly convert the translational motion of the manipulator connector to a rotational motion of the differential device; an adjustment member connected to the differential device; and a control member connected to the differential device; wherein the differential device is configured to enable the adjustment member to remain in position during an aircraft control process to permit: translation of the manipulator connector from a translational neutral position; and controlling the corresponding movement of the member to control the aircraft through the differential device; and wherein the differential device is configured to enable the control member to remain in position during the adjustment process to permit: translation of the manipulator connector; and adjusting the corresponding movement of the member by the differential device to adjust the translational neutral position.

A dispensing head for a fluid product is adapted to mount on a fluid product reservoir of a dispenser. The dispensing head includes a pump actuator, and a locking system. The pump actuator is capable of moving along a main longitudinal axis (X) from a rest position to a product dispensing position, and vice versa. The locking system for the actuator enables the actuator to be locked and / or unlocked. The locking system include an actuating means and a ring. The actuating means is capable of moving in a translational movement in a plane perpendicular to the main axis (X) from a locking position of the actuator to an unlocking position of the actuator, and vice versa. The ring capable of moving in a rotational movement about the main axis.

The utility model discloses an adjustable seat structure on a simulation aircraft. The adjustable seat structure comprises an oblique movement driving device, the seat is arranged on the oblique motion driving device and can do oblique upward or oblique downward translational motion under the action of the oblique motion driving device; a pad body; the horizontal sliding mechanism is arranged on the oblique movement driving device; and the manual locking mechanism is arranged on the horizontal sliding mechanism. According to the utility model, the seat moves up and down in the inclined direction through the inclined movement driving device, so that the height of the seat can be adjusted, and the leaning comfort of the seat is not influenced; the front-back translation movement of the seat can be controlled through the horizontal sliding mechanism, the seat can be stopped at the corresponding position by means of the manual locking mechanism, manual operation is convenient, and the situation that a tall pilot feels uncomfortable due to the fact that the legs cannot be bent normally during riding can be prevented; the range of sight of a short pilot can be prevented from being affected when the short pilot takes the vehicle, and the application range of the device can be expanded.

The invention discloses a novel liquid drop self-driving method based on Quincke rotation and a wall surface effect, and belongs to the field of microfluid machinery. The method comprises the following steps: placing a weak conductive liquid drop on a hydrophobic solid wall surface, and applying a uniform electric field; then, the liquid drops generate Quincke rotation under the action of the electric field, and the rotation effect can cause the liquid drops to be separated from and suspend on the wall surface; and finally, viscous stress caused by a liquid pad between the bottom of the liquid drop and the wall surface acts on the bottom of the liquid drop, so that the upper part and the lower part of the liquid drop generate a speed difference, and additional translational motion, namely liquid drop self-driving, can be generated due to the existence of the speed difference for rotating the liquid drop. According to the method, the complexity of a self-driven platform and the instability of liquid drop movement in an existing method are overcome.

Methods and systems are provided for nautical stationkeeping of free-floating objects. In one example, a method includes adjusting translational motion of a body freely floating in water by rotating the body. The translational motion may be adjusted, for instance, to maintain the body within a geographic area. In certain examples, the adjustment of the translational motion may be realized via a Magnus effect induced by rotating the body. The body may be configured as, for example, a free-floating object such as a wave engine.

A fluid conduit for aircraft, the conduit having a pipe made from thermoplastic material having a connection end which extends along a pipe axis and a connector which is intended to be mounted in the connection end by a translational movement along the pipe axis in a downstream direction, the connector having a joining portion which extends longitudinally along the connector axis and which is configured to extend into the connection end, the joining portion having a free longitudinal end which is chamfered, the free longitudinal end being configured to be radially deformed after the connector is mounted in the connection end, which has been thermally expanded beforehand, so that the conduit has an internal surface which has an internal radius which is substantially constant at the interface between the connector and the pipe.

A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.

Disclosed is an aircraft windshield wiper system, having: a wiper arm; a reversible motor that drives the wiper arm, the motor including: a stator; a rotor configured to rotate relative to the stator; a forward shaft segment that is driven by the rotor and being rotationally connected to the wiper arm; an aft shaft segment that is driven by the rotor, the aft shaft segment including a forward end and an aft end; a ball nut that translates along the aft shaft segment from rotation of the aft shaft segment; a forward stop at a forward end of the aft shaft segment, configured to stop forward translational motion of the ball nut along the aft shaft segment; and an aft stop at an aft end of the aft shaft segment, configured to stop aft translational motion of the ball nut along the aft shaft segment.

The invention relates to a device for adjusting (80) an air stream for an air inlet of a motor vehicle, comprising a housing (81) defining a flow duct (82) into which an air stream flows and in which a cooling unit comprising at least one heat exchanger (83) is at least partially arranged, the housing comprising a flap (85) designed to be placed in an open position providing access to the heat exchanger, said flap being designed to close the access in the closed position, said access (86) being designed in particular to enable removal of the heat exchanger through a substantially translational movement.

. The invention relates to an ultrasonic testing system (600) designed for the automated non-destructive testing of large composite structures, particularly in the aeronautical field. Traditional ultrasonic inspection requires precise positioning of the probe, which can be affected by deviations between the CAD model used for programming and the actual part. The proposed system comprises a probe holder moved by an effector (650), ensuring constant alignment of the ultrasonic probe (150) despite these deviations. The probe holder incorporates a double compliance mechanism: an upper system allowing limited translational movement with an elastic return to maintain alignment, and a lower system offering angular adjustments thanks to two intersecting rotation axes. Rolling elements ensure a constant distance and orientation between the ultrasonic probe and the surface to be inspected.Suitable for complex geometries, this system enables reliable automated ultrasonic testing, compensating for positioning variations, thus improving the accuracy and repeatability of defect detection Figure 6.

The invention provides a posture adjusting assembly, a bearing device and a vehicle, and relates to the technical field of automobile parts. The posture adjusting assembly comprises a guiding unit, a rotating unit and a rotating matching structure. The rotating unit is movably connected with the guiding unit in a guiding mode in the first direction, and the rotating unit is used for being connected with an adjusted structure; the rotating matching structure is arranged on the guiding unit and located on the moving path of the rotating unit, and when the rotating unit moves towards the set end in the first direction and passes through the rotating matching structure, the rotating unit rotates under the interaction force with the rotating matching structure; when the rotating unit moves towards the end opposite to the set end in the first direction and passes through the rotating matching structure, the rotating unit keeps translational motion. The adjusted structure rotates in the process of moving in the first direction, the requirement for the size of the peripheral space of the initial mounting position of the adjusted structure in the posture adjusting process can be lowered, and the space applicability of the adjusted structure can be improved.

A control mechanism for an aircraft comprising: a conversion mechanism (104a) having a translatable part (105a) and a rotatable part (103a), the translatable part being reversibly translatable and being connectable to an inceptor (108a); an inceptor connector (102a) connected to the translatable part of the conversion mechanism; a differential device (112a) connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device; an adjustment member (116) connected to the differential device; and a control member (114) connected to the differential device; wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit: translation of the inceptor connector from a translational neutral position; and corresponding movement of the control member, to control the aircraft through the differential device; and wherein the differential device is configured such that the control member is maintainable in position during an adjustment process to permit: translation of the inceptor connector; and corresponding movement of the adjustment member through the differential device, to adjust the translational neutral position.

To obtain a vehicle that does not cause flow interference, does not impose unsteady aerodynamic forces on the aircraft, can improve the accuracy of guidance to the rendezvous point, and can also be miniaturized as a propulsion system. [Solution] The vehicle 1 includes a sensor 2 that obtains tracking information of the rendezvous point, an inertial device 3 that obtains inertial information of the vehicle 1, a cluster engine 4 provided at the rear of the aircraft body 60 and including a plurality of nozzles 6 to 9 that impart translational motion and rotational motion to the aircraft body 60, and an autopilot 5 that calculates an acceleration command for guiding to the rendezvous point based on the tracking information and inertial information, and controls the thrust of the cluster engine 4 including the plurality of nozzles 6 to 9 based on the acceleration command.

A locking mechanism situated in an inner zone and comprising at least one component that is adjustable in a longitudinal direction and that is linked to a support by a link having a rod secured to the adjustable component. The link includes a guideway link, linking the rod and the support, and an adjustment system. The adjustment system comprises a pivoting control pivoting on itself and having a first end accessible from an outer zone, an intermediate piece configured to pivot on itself, an angle transmission converting a pivoting movement of the pivoting control into a pivoting movement of the intermediate piece, and a helical link converting a pivoting movement of the intermediate piece into a translational movement of the rod. The locking mechanism allows for adjustment from the outer zone. An aircraft comprising at least one such locking mechanism is also provided.