32 results about "In plane" patented technology

Data indicative of a line of sight to a target is obtained from a sensor mounted on an aircraft. Data indicative of an orientation of the aircraft relative to the Earth is obtained from a navigation system associated with the aircraft. An expression is generated that couples a first variable indicative of misalignment of an orientation of the sensor and the orientation of the aircraft and a second variable indicative of the location of the target relative to the Earth. The first variable and second variable are determined using the data indicative of the line of sight from the sensor to the target and the expression coupling the first variable and the second variable. The misalignment of the orientation of the sensor and the orientation of the aircraft is compensated for using the first variable. The location of the target relative to the Earth is determined using the second variable.

A method for landing an aircraft, which takes off and lands vertically, at a predetermined landing site defined by a circular marking that can be captured optically and has a circular outer contour utilizes a landing system. A camera arranged on the aircraft and directed to the landing site is used to capture images electronically, each of which represents a reproduction of the marking detected at least in sections. Each camera image is evaluated in a control device. The control device is used to fit a geometric object with at least one straight line, which has a predetermined line slope in relation to the camera image, into the reproduction in such a way that the line constitutes a tangent through a contact point to the marking detected at least in sections. The control device steers the aircraft in the direction of the contact point determined in this way.

Provided is a ventilation member that is suitable for improving the ease of elastic deformation of an insertion part when the insertion part is inserted into an opening of a housing. This ventilation member (10) is provided with a support body (4a) and a ventilation membrane (2). The support body (4a) includes a base portion (11) and a leg portion (12) that support the ventilation membrane (2). The leg part (12) has a plurality of insertion parts (21) and claw parts (23). In a plane (A) orthogonal to the central axis (O) of the support body (4a) and passing through the root portion of the insertion part (21), when an imaginary circle passing through both end portions (21p) in the width direction of the inner surface (21c) of the insertion part (21) and centered on the central axis (O) is defined as a first imaginary circle (C1), the inner surface (21c) of the insertion part (21) has a protruding part (21d) that protrudes further toward the central axis (O) than the first imaginary circle (C1). The ratio of the length in the radial direction of the claw section (23) to the length in the axial direction of the insertion section (21) is from 0.3 to 0.5 (inclusive). In the plane (A), the maximum length of the protruding portion (21d) in the radial direction is 0.1 mm or more and 1.5 mm or less.

The utility model relates to the technical field of steel structure connecting pieces, and particularly discloses a building steel structure connecting piece which comprises main connecting pieces, two sets of main connecting pieces are attached to form a mouth-shaped structure, inner grooves are formed in the inner sides of the main connecting pieces, the inner grooves are filled with the connecting pieces during use, the building steel structure connecting piece comprises connecting assemblies, and the connecting assemblies are installed on the outer sides of the main connecting pieces. The connecting assembly can be adjusted at any angle on the side edge of the main connecting piece, the end of the stabilizing assembly is connected with the side edge of the connecting assembly, the internal angle of the connecting assembly can be adjusted according to the required angle change of the connecting piece, and the connecting piece can be connected at any angle in a plane. And after the angle is fixed, the angle of the whole structure can be fixed through movement of the internal structure, the connection stability is guaranteed, and therefore the external steel structure can deflect at different angles, the requirements of different building structures can be met, the use range is wider, and the structure is more stable.

A mobile contact (20) is provided for an electric current switching device (50), comprising:a first conductor blade (1) and a second conductor blade (2), extending in planes (P1, P2) parallel to each other and distant from each other, the conductor blades (1, 2) being linked in rotation about a common rotational axis (R),a first and a second spacer (3, 4) configured to maintain a minimum distance between the first blade (1) and the second blade (2),in whicha cross section (S1, S2) of each blade (1, 2) is shaped so as to:have an area equal to the area of a reference cross section (S1′, S2′) of rectangular shape and of the same length (a), andhave a quadratic moment greater than the quadratic moment of the reference cross section (S1′, S2′), the quadratic moment being determined in relation to an axis parallel to the transverse axis (T1, T2) of the blades (1, 2).

According to the invention, a seating device, in particular an aircraft seating device, for mounting in an aircraft, comprises a mounting unit (14a; 14b) having two spaced-apart seat feet (16a, 18a; 16b, 18b), a seat base (30a; 30b) having a seat floor (32a; 32b) and a backrest (34a; 34b), wherein the seat base (30a; 30b) is connected to the two seat feet (16a, 18a; 16b, 18b) in side regions (36a, 38a; 36b, 38b), and a bearing unit (40a; 40b) which pivotably connects the seat base (30a; 30b) to the seat feet (16a, 18a; 16b, 18b) in an upper region. attaches and with which the seat base (30a; 30b) can be pivoted between an upright sitting position and a maximum comfort position, with a locking device (42a; 42b) which is intended to secure the seat base (30a;30b) to lock at least in the upright sitting position and in the comfort position, wherein the locking device (42a; 42b) has at least one actuator (44a; 44b) which is attached below the seat base (32a; 32b) of the seat body (30a; 30b) and is designed to assist an adjustment of the seat body (30a; 30b) towards the comfort position, is proposed.;

A mold mechanism for laterally pushing a slotting tool driving block through an ejector block comprises an upper mold (10) and a lower mold (20), and the upper mold (10) comprises the ejector block (14); the lower die (20) comprises a lower die base (21), a side push insert (22), a push block base (23), a slotting tool driving block (24) and a third nitrogen spring (25), the side push insert (22) is arranged on the side, away from the slotting tool driving block (24), of the push block base (23), the push block base (23) linearly reciprocates on the lower die base (21), the slotting tool driving block (24) is in plane contact with the ejector block (14), and the ejector block (14) is in plane contact with the ejector block (14). The slotting tool driving block (24) is in inclined plane contact with the push block seat (23), and the third nitrogen spring (25) is arranged between the lower die seat (21) and the slotting tool driving block (24). The driving device is stable in driving, improves the strength of the die, prolongs the service life of the die, and can ensure the precision and consistency of products.

The utility model provides a kind of self-locking joint that can be freely rotated in plane, belong to self-locking mechanism field, including fixed end;Mounting pad in fixed end;Rotary end is fixed in mounting pad;Bearing-latch seat is fixed on fixed end;Latch is inserted into fixed end by bearing-latch seat;Four stop pieces are installed in bearing-latch seat by bearing and screw respectively;The outer edge of four stop pieces is equipped with chamfered end and round corner;Two stop pieces chamfered end are connected by a spring, and the chamfered end of other two stop pieces is connected by another spring.The utility model can be freely rotated in the same plane, and self-locking can be realized at any position, with the advantages of modularization, stackable use, solves the problems that existing self-locking joint has high manufacturing cost, overall structure is too complicated, too dependent on motor and speed reducer to realize design function and cannot realize 360 degrees free rotation and self-locking.

The tool comprises an annular piece made of a magnetizer, a through hole matched with a sliding block blank is formed in the annular piece, a fastener is arranged on the side wall of the annular piece in the radial direction, and the blank is pressed through a gasket, so that the annular piece is fixed through a magnetic platform, and a stable clamping scheme is provided for a non-magnetic sliding block. Furthermore, the tool is additionally provided with a transverse positioning mandrel, and the thermal expansion coefficient of a mandrel material is controlled to be higher than that of a sliding block blank and an annular piece, so that heat generated in the grinding process can drive the mandrel to be subjected to thermal expansion, the fit clearance is dynamically eliminated, self-tightening type locking is achieved, and the rigidity of a machining system is enhanced. The problems that a non-magnetic workpiece is difficult to stably fix in plane grinding and is easy to generate micro-motion deformation are effectively solved, and the machining precision of the workpiece can be improved.

The invention discloses a passive self-adaptive magnetic TOFD flaw detection mechanism of a detection robot and the flaw detection robot, and relates to the technical field of ultrasonic flaw detection control. The suspension device comprises a suspension plate, the top end and the bottom end of the suspension plate are each rotationally connected with a parallel connecting rod assembly, the other end of each parallel connecting rod assembly is rotationally connected with a connecting rod, and a spring is arranged between each connecting rod and the suspension plate; and a deflection bracket is fixedly mounted at the bottom end of the connecting rod. Through the synergistic effect of the parallel connecting rod assembly, the spring, the deflection support and the square support, a passive force-position coupling compensation mechanism is constructed, and the unstable problems of contact pressure fluctuation, instantaneous separation and the like of a probe and the surface of a workpiece are solved; a cross shaft structure formed by the deflection support and the square support endows the probe with two independent rotational degrees of freedom in a plane, the probe can dynamically adjust the posture along with a complex curved surface in real time, and the spring and the parallel connecting rod assembly are linked to ensure that the contact pressure is constant during obstacle crossing.

The application discloses a kind of handheld laser welding repair defect process protection methods, comprising the following steps: S1: measurement;Part is placed on platform, and the structure state around defect position is clear, defect is in plane, circular surface (inner / outer), corner, corner and so on Position, and the size of defect position is measured, and according to the size of different defect position, it is divided into point defect and surface defect;S2: prepare adaptive repair protection sample plate;According to the size obtained by measuring different defects, prepare repair protection sample plate;S3: assembly;Repair protection sample plate is fixed in defect to be repaired position using fixing piece etc.;S4: defect repair;The way of welding while feeding wire is used to repair defect, to ensure that repair height is higher than surrounding matrix;S5: machining;Remove excess filler metal, and the filling position meets the size requirement of drawing;S6: appearance inspection;Further improve repair quality and repair efficiency.

The invention relates to a piston (10) having a front end (12) and a rear end (14), with an outer wall (16) connecting the front end (12) to the rear end (14), wherein the outer wall (16) comprises a sealing seat (18) configured for receipt of an O-ring (20), and wherein the sealing seat (18) has a non-uniform cross-section in plane parallel to a longitudinal axis (26) of the piston (10), and with the cross-section at any axial height of the sealing seat (18) being circular in a plane perpendicular to the longitudinal axis (26) of the piston (10).

The invention relates to an aircraft seating device, in particular an aircraft pilot seating device, for mounting in an aircraft, comprising a mounting unit (14a; 14b) having two spaced-apart seat feet (16a, 18a; 16b, 18b), a seat base (30a; 30b) having a seat floor (32a; 32b) and a backrest (34a; 34b), wherein the seat base (30a; 30b) is connected to the two seat feet (16a, 18a; 16b, 18b) in side areas (36a, 38a; 36b, 38b), and a height adjustment device (100a; 100b) by means of which the seat base (30a; 30b) can be adjusted in height on the seat feet (16a, 18a; 16b, 18b). 18a; 16b, 18b) is attached.It is proposed that the height adjustment device (100a; 100b) has a gear unit (102a; 102b) by means of which the seat base (30a; 30b) can be continuously adjusted between a lower position and an upper position, wherein the gear unit (102a; 102b) has at least one adjustment gear (104a, 106a; 104b, 106b) which is functionally arranged between the seat base (30a; 30b) and the stand unit (14a; 14b).

A cage nut assembly includes a nut, a base, and a cage. The nut includes a hollow elongate body and an annular flange. The elongate body has a first end, a second end, a first portion, and a second portion. The annular flange protrudes radially outward from the elongate body. The base has a hole extending therethrough. The cage includes a plate having a hole extending therethrough and sidewalls extending from opposite sides of the plate. The elongate body of the nut extends through the hole in the cage, the second portion of the nut is disposed within the hole in the base, and the second end of the elongate body is at least one of flared radially outward and welded to the base such that the nut is secured to the base and the nut is secured within the cage.

The invention relates to a mirror image rehabilitation training device and a using method, the mirror image rehabilitation training device comprises a platform and a plane mirror which is arranged in the middle of the platform and extends along the width direction of the platform, two supporting seats are slidably connected to the top surface of the platform and located on two sides of the plane mirror respectively, and a transmission assembly connected with the two supporting seats is arranged in the platform. The other supporting seat is driven by the transmission assembly to slide in the opposite direction; feedback assemblies are arranged on the two supporting seats, a linkage assembly is further arranged in the platform, and the linkage assembly responds to movement of the supporting seats to trigger the feedback assemblies. Tactile stimulation is provided for the uninjured hand and the injured hand, so that a patient does not completely depend on'imagination 'that the injured hand is moving by the patient in the training process, the injured hand is more easily substituted into the uninjured hand in the plane mirror, the degree of dependence on consciousness and concentration of the patient in mirror image therapy is reduced, auxiliary movement is provided for the injured hand of the patient, and the training effect is improved. And the experience of the patient in the mirror image therapy is enhanced.

The present invention relates at least one payload (B) positioned on an aircraft by a user and / or manufacturer; at least one body (2) that allows for the transport of the payload (B) on the aircraft; at least one hook (3), pivotally mounted on the body (2), onto which the payload (B) is attached for transport on the body (2) and / or jettisoning from the body (2); at least one main rotating element (4), pivotally supported on the body (2) so as to be connected with the hook (3), and which, upon being triggered, is rotatable about its pivot axis, thereby enabling the actuation of the hook (3); a plurality of triggering rods (5), pivotally connected at one end to the hook (3) and at the other end to the main rotating element (4), for transmitting motion to the hook (3) and causing its rotation upon the triggering of the main rotating element (4); at least one shaft (M), positioned within the body (2) and arranged to be actuated together with the main rotating element (4), and which, by being rotated by a user about its longitudinal axis, allows for the actuation of the main rotating element (4); a first connection point (6), located on the main rotating element (4), where the triggering rod (5) is mounted to the main rotating element (4); a second connection point (7), where the triggering rod (5) is pivotally supported on the hook (3); a first axis (F), on which the shaft (M) is located and which is the direction in which said shaft (M) extends on the body (2) and a second axis (S), which is substantially perpendicular to the first axis (F) and parallel to the longitudinal direction of the body (2).

The invention refers to an aerodynamic construction attached to the tip of an aircraft's wing, used to recover redundant energy that can be used in the aircraft's consuming systems and discharged. The construction according to the invention is mounted on an aircraft (A) at wing tip, fastened with help of clamps (1) that fix a flange (2) to which is attached two casings (3 and 4) outer and funnel, between which some ribs (5) are fixed, the outer casing (3) having an aerodynamic shape, with two connecting radius (r1) and (r2), frontal and upper, and the funnel casing (4) having two radius (r3 and r4), upper and lower, with two inlet and outlet sections (a and b), the air from the outlet section (b) it is taken with the help of a collar (6) to an installation inside the wing of the aircraft (A) on which an air filter (7) with automatic drainage, an amplifier (8) and a pressure distributor (9) are mounted, from where the pressure is used as a source of energy for several consumer systems (C) of the aircraft (A) and for discharge (E) directed to the distributor (10) from where the pressure is successively or combined redistributed in several directions in the branched tubing (11), provided at the exit sections with flap (12).

Provided are a tank capable of individually accommodating a plurality of substances using a single design, and a flying device with the same.　A tank 10 is mounted on a flying device 30. The tank 10 comprises: a tank main body portion 11; and a protruding portion 12 that protrudes downward from the tank main body portion 11. The protruding portion 12 comprises a cutting portion 13 and discharge portions 14. The cutting portion 13 is defined in an intermediate section of the protruding portion 12, and is a part that allows the protruding part 12 to be cut from the intermediate section. The discharge portions 14 are disposed in the protruding portion 12 below the cutting portion 13, and are configured to allow a substance 15 stored in the tank main body portion 11 to pass to the outside.

To provide a technique capable of suitably mitigating an influence when an end effector mounted on a flying body comes into contact with a structure or the like.SOLUTION: In an attachment structure of an end effector attached to a tip end portion of a shaft extending in a forward direction of a flying object, there is provided a connecting member that connects the tip end portion of the shaft and the end effector, that is bent and deformed in a first direction orthogonal to an axial direction of the shaft and in a second direction opposite to the first direction in response to receiving an external force, and that is restored to an original shape in response to being released from the external force. The coupling member is configured such that a bendable amount in the first direction is smaller than a bendable amount in the second direction.SELECTED DRAWING: Figure 5

Integrated functional component foam inner frame for aircraft windows, window module and associated manufacturing method. In a frame (20) for a window (6) equipping a passenger cabin (4) of an aircraft (2), said window (6) comprises, considered in a viewing direction (8), an outer pane (10) integrated into a fuselage (12) of the aircraft (2) and extending transversely with respect to said direction (8); an inner pane (14) located on the cabin side and extending parallel to said outer pane (10), at a distance (A), along said direction (8); a window funnel (22) that can be fixed in the aircraft (2), extending between said inner pane (14) and said outer pane (10) in the assembled state (M), along said direction (8), and made of foam (24); and at least one functional component (26) fixed to said funnel (22) of the porthole. Figure to be published with the abbreviation: Fig. 1

An acoustic reproduction method includes: obtaining information indicating sounds that reach a listener in a sound reproduction space and direction information indicating a direction in which the head of the listener is oriented; judging whether a first direction in which a first sound reaches the listener and a second direction in which a second sound reaches the listener are in plane symmetry with respect to a predetermined plane that passes through both ears of the listener and is perpendicular to the direction in which the head of the listener is oriented, the first and the second sounds being included in the sounds indicated in the information obtained; performing processing on sound information indicating the second sound when the first and the second directions are judged to be in plane symmetry, the processing being change processing of changing the second direction; and outputting the sound information subjected to the change processing.

The utility model discloses a right-angle workpiece positioning device convenient to adjust, which relates to the technical field of machining, and comprises a right-angle frame, two connecting frames are arranged on the surface of the right-angle frame, clamping blocks are arranged in the two connecting frames, and screw rods are sleeved in the two connecting frames in a threaded manner. The datum plane of the right-angle frame is tightly attached to the right-angle side of the workpiece, the two degrees of freedom of the workpiece in the plane are limited, it is ensured that the workpiece is located at the preset right-angle position, when the position of the connecting frame needs to be adjusted, the push block is pushed to drive the fixed limiting block to move together, the reset spring is compressed, and at the moment, the limiting block is disengaged from clamping with the limiting groove; when the limiting device is opened, the connecting frame can be disassembled, the position of the connecting frame can be adjusted according to requirements at the moment, overall disassembly is convenient, the position of the connecting frame can be adjusted conveniently, the later maintenance cost is reduced through the modular design, the use requirement is met, and the overall applicability and flexibility are improved.

The invention relates to a piston (10) having a front end (12) and a rear end (14), with an outer wall (16) connecting the front end (12) to the rear end (14), wherein the outer wall (16) comprises a sealing seat (18) configured for receipt of an O-ring (20), and wherein the sealing seat (18) has a non-uniform cross-section in plane parallel to a longitudinal axis (26) of the piston (10), and with the cross-section at any axial height of the sealing seat (18) being circular in a plane perpendicular to the longitudinal axis (26) of the piston (10).

To provide a system for changing a vertical position of one or a plurality of objects such as a wire bundle arranged in an aircraft.SOLUTION: The lift system 100 includes a first clamping assembly 102, a second clamping assembly 104, and a gear assembly 106. The lift system 100 includes a lift housing 126 having a housing cavity 140 with a spool assembly disposed within the housing cavity 140. The spool assembly is coupled to the gear assembly 106, which controls the direction of rotation of the spool assembly. A first strap 112 extends between a first end 116 coupled to the first clamping assembly 102 and a second end coupled to the spool assembly. A second strap 114 extends between a third end 120 coupled to the second clamping assembly 104 and a fourth end coupled to the spool assembly.SELECTED DRAWING: Figure 1

This utility model relates to a device for the mechanical joining of metal structural profiles, designed to facilitate rapid installation and provide a robust connection against dynamic stresses or seismic movements, without the need for screws, welding, or additional fixings. It comprises a toothed metal wedge body (1) with an elongated prismatic geometry, provided with an inclined upper face (2) with a toothed surface (6) composed of transverse undulations, and a lower face (3) arranged in planes diverging from the former. The wedge body (1) is inserted into a slotted housing (7), shaped as a rigid piece with a central longitudinal groove delimited by parallel lateral edges and a semicircular upper surface.In a preferred embodiment, the holder (7) passes through a through-hole (8) in the lower wall of the first structural profile (9), without being fixed to it, and rests its lower base on a second structural profile (10), to which it is fixed. The interaction between the wedge (1), the holder (7), and the profiles (9, 10) creates a friction lock that ensures the structural connection without the need for additional elements.

The utility model belongs to the technical field of plane printer devices, and particularly relates to a plane printer device with a lifting platform structure, which comprises a plane support, a placing mechanism is arranged on the plane support, and the placing mechanism comprises a platform assembly, a lifting mechanism and a lifting mechanism, the transverse tops of the concave pieces are connected with the bottom of the plane support through guide rods, a downwards-concave support is connected to the pair of guide rods in a sliding mode, and protruding parts at the two ends of the bottom of the downwards-concave support are connected with the transverse tops of the pair of concave pieces through springs respectively. The problems that in the prior art, the height of a printing plane needs to be manually adjusted, a rotary knob needs to be manually rotated or other manual mechanisms are used for adjusting the height of the printing plane, operation is tedious, and printed objects are prone to being damaged or the printing plane is prone to shifting due to misoperation are solved.

The present invention relates to an aircraft frame preform, particularly for unmanned aircraft, comprising a central member (1) and at least two arms (2) extending from the central member (1) in an outward direction, wherein the central member (1) and / or the at least two arms (2) are formed of an inner wall (6) and an outer wall (7) made of a metal sheet, wherein the inner wall (6) and the outer wall (7) are arranged in planes relative to each other while retaining a gap, wherein the edges of the inner wall (6) and the outer wall (7) are connected and sealed by means of a seal (12), forming a closed hermetic empty inner space (3) of the aircraft frame preform, wherein a valve (8) is arranged on at least one wall (6, 7). The present invention also relates to a method for manufacturing an aircraft frame, particularly for unmanned aircraft, from the aircraft frame preform and an aircraft frame manufactured by this method, particularly for unmanned aircraft.

The invention relates to a seat device, in particular an aircraft seat device, for mounting in an aircraft, comprising a stand unit (14a; 14b), which has two mutually spaced seat feet (16a, 18a; 16b, 18b); a seat main part (30a; 30b), which has a seat base (32a; 32b) and a backrest (34a; 34b), the seat main part (30a; 30b) being connected, in lateral regions (36a, 38a; 36b, 38b), to the two seat feet (16a, 18a; 16b, 18b); a bearing unit (40a; 40b) which pivotally connects the seat main part (30a; 30b), in an upper region, to the seat feet (16a, 18a; 16b, 18b) and by means of which the seat main part (30a; 30b) can be pivoted between an upright sitting position and a maximum comfort position; and a locking device (42a; 42b), which is designed to lock the seat main part (30a; 30b) at least in the upright sitting position and in the comfort position, the locking device (42a; 42b) having at least one actuator (44a; 44b), which is connected below the seat base (32a; 32b) of the seat main part (30a; 30b) and is designed to support an adjustment of the seat main part (30a; 30b) in the direction of the comfort position.

The application discloses a kind of hanging column mounting bolt pull-out test device and its using method, belong to tunnel construction technical field.It includes: general frame, rotating mechanism, XY horizontal displacement mechanism, swing mechanism, feed mechanism, pull-out mechanism, control system, the three-dimensional space position of the feed mechanism adjustable pull-out mechanism;XY horizontal displacement mechanism is not limited in the moving direction on the plane parallel with the base of rotating mechanism;The end face formed in the top of general frame is adapted with the inner wall arc surface of tunnel.The application solves the limitation that pull-out device can only work in plane, realizes the pull-out work on the inner arc structure surface of tunnel, can simultaneously carry out batch testing to multiple bolts, and is suitable for the distribution working condition of multiple bolts, improves the efficiency of tunnel installation bolt pull-out test, high flexibility, wider application range, improves the safety of tunnel construction.