32 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 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 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).

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 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.

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.

. 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.

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.

A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device 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 connected to the differential device; and a control member 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.

A passenger seat, for instance an aircraft passenger seat, including a seat pan, a backrest frame coupled to the seat pan, a backrest supported by the backrest frame, and an adjustment mechanism coupling the backrest to the backrest frame, the adjustment mechanism operable to translate the backrest forward or aft relative to the backrest frame to change a position of the backrest relative to the seat pan. In use, translation motion of the backrest is independent of pivoting motion of the backrest frame and the backrest position is adjustable relative to the seat pan to provide seat ergonomics commensurate with the stature of the seat occupant. In embodiments, the adjustment mechanism is manual and accessible from above the backrest.

A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device 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 connected to the differential device; and a control member 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.

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 utility model discloses a device and a system for measuring pitching and floating and sinking states of a wing, and the device comprises a pedestal which is horizontally disposed on the ground; the supporting frame is vertically arranged on the base; the test wing is vertically arranged in the support frame; the top end sliding frame is horizontally and slidably connected to the upper end of the supporting frame; the fixed seat is arranged on the top end sliding frame and is connected with the upper end of the test wing; the bottom end sliding frame is horizontally and slidably connected to the lower end of the supporting frame; the rotating seat is arranged on the top end sliding frame and is connected with the lower end of the test wing; the driving mechanism is used for controlling the top end sliding frame and the bottom end sliding frame to slide synchronously. According to the utility model, the fixed seat and the rotary seat which can slide horizontally are arranged, so that the floating and sinking motion of the wing, namely the translational motion, can be tested, the pitching motion of the wing, namely the rotary motion, can also be tested, and the floating and sinking motion and the pitching motion of the wing can be tested at the same time, so that the practicability of the measuring device is improved; and the measurement precision is ensured.

The invention discloses a power generation system and device capable of performing intermittent push-pull motion on a plane, and belongs to the technical field of power generation. The device comprises a bracket platform, a driving motor, a connecting rod, a rack structure and a power generation device, power generated by the driving motor is transmitted to the rack structure through the connecting rod, the rack structure is driven to do constant-speed reciprocating circular motion or translational motion on the plane, then the rack structure drives the power generation device to operate, and mechanical energy generated by constant-speed motion is converted into electric energy. The constant-speed translational motion enables the generated current and energy to be more stable, and the output power can reach more than four times of the input power; in addition, the device fully utilizes the rotation of the inertia wheel of the electric energy conversion device, so that the electric energy conversion device continuously generates electricity at a constant speed, and the continuous energy consumption is reduced.

The invention relates to a dispensing head for a fluid product dispenser and an associated dispenser. The invention in particular relates to a dispensing head for a fluid product and a dispenser comprising such a dispensing head. The invention relates to a dispensing head (10) configured to be mounted on a fluid product reservoir (12) of a dispenser (14), the dispensing head (10) comprising:-a pump actuator (16) movable along a main longitudinal axis (X) from a rest position to a product dispensing position, and vice versa,-a locking system (18) for the actuator (16) enabling the actuator (16) to be locked and / or unlocked, the locking system (18) comprises:-actuating means (30) which can be moved in a translational movement from a locking position of the actuator (16) to an unlocking position of the actuator (16), and vice versa, in a plane perpendicular to the main axis (X),-a ring (32) which can be moved in a rotational movement about the main axis.

The invention provides an imaging system for airplane bottom detection and a control method thereof, the imaging system comprises a controller, a box body, a lifting mechanism and a cover plate mechanism, the lifting mechanism and the cover plate mechanism are located in the box body, and a camera is installed at the top of the lifting mechanism. The lifting mechanism pushes the shear fork mechanism to move through a ball screw or an electric push rod so as to achieve lifting of the camera. The cover plate mechanism drives the parallelogram mechanism to do translational motion through a ball screw or an electric push rod, and opening and closing of a top cover of the box body are achieved. A pressure sensor is arranged on the cover plate device and used for detecting the pressure borne by the cover plate mechanism so as to judge whether the cover plate can be opened or not, and cover opening safety is guaranteed. When images need to be shot, the cover plate mechanism moves to open the hatch cover, and the camera rises to shoot the bottom images of the airplane; after shooting is completed, the camera descends, the cover plate mechanism moves to seal the hatch cover, and collision between the camera and the airplane is avoided. While the position of the camera is adjusted, the ground flatness of the parking shed and the sliding safety of the aircraft are not influenced, and high-quality aircraft bottom images can be obtained.

To provide a reaping blade-driving device capable of readily ensuring the safety of operation by suppressing the generation of scattered materials during the operation and suppressing the generation of vibration and noise while suppressing the nipping of foreign materials by the reaping blade.SOLUTION: A base unit that supports the plurality of cutting blade units in a stacked state, and a driving mechanism that is supported by the base unit and performs a cutting operation by driving at least one of the cutting blade units, the cutting blade unit includes a plurality of cutting blades that protrude in different directions around the base unit, and the drive mechanism performs a cutting operation in which the cutting blade of one cutting blade unit and the cutting blade of another cutting blade unit overlap each other by causing at least one of the cutting blade units to perform a translational movement in an orbital path having no dead point.SELECTED DRAWING: Figure 1