98 results about "In plane" patented technology

The invention discloses an ocean engineering plane section construction welding quality detection method, and belongs to the technical field of ocean engineering equipment manufacturing, the ocean engineering plane section construction welding quality detection method comprises a transverse plate, the transverse plate is parallel to the surface of a ship body and is perpendicular to the side edge of a component, and one end of the transverse plate is provided with a moving assembly moving in the length direction of the top of the component. The size of a weld leg of a weld joint can be measured through the first laser displacement sensor and the sliding length of the measuring sliding rod, the width and the thickness of the weld joint are calculated according to the size of the weld leg, the distance from the second laser displacement sensor to a welding spot can be measured through the second laser displacement sensor, and the thickness of the weld joint is known. In addition, the device controls the device to move along the welding seam through the moving assembly, manual measurement is not needed, the width of the welding seam at each position of the welding seam, the thickness of the welding seam and the surplus height of the welding seam can be accurately measured, the functionality is higher, and the practicability is higher.

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.

[Problem] To provide a flying object, a control method, and a program capable of controlling to achieve an increase in the cruising distance of the flying object and the stability of the flying object during hovering and landing by providing rotatable auxiliary wings to the flying object and controlling the angle of attack. [Solution] Provided is a flying object comprising: a main body part; a plurality of rotary wing parts provided to the main body part; an auxiliary wing part provided to the main body part; and a control part for controlling the operation of the rotary wing parts and the auxiliary wing part. The control part executes a change control of the lift of the auxiliary wing part in accordance with a comparison result between an acquired thrust-related parameter and one or more reference parameters.

The invention relates to the technical field of MEMS (Micro Electro Mechanical System) gyroscopes, and discloses an in-plane rotating MEMS gyroscope, which comprises two driving frames distributed along a second direction; the driving connecting frame is located between the two driving frames; the two coupling frames are distributed in the first direction and are both located in the driving connection frame; each coupling frame is provided with four orthogonal correction electrodes which are symmetrically distributed relative to the first direction and are antisymmetrically distributed relative to the second direction; the two detection frames are located between the two coupling frames; each detection frame is provided with two detection electrodes which are distributed in an anti-symmetric manner relative to the first direction; and the first inclined U-shaped beam can drive the two detection frames to do reverse reciprocating motion along the second direction in the detection mode. According to the in-plane rotating MEMS gyroscope disclosed by the invention, the structure of the MEMS gyroscope is optimized to improve the consistency of motion in a driving mode and inhibit coupling errors, so that the detection performance of the gyroscope is improved, and the in-plane rotating MEMS gyroscope is suitable for application scenes with higher requirements.

The utility model discloses a clamping tool for assembling a transverse rib plate of a cable saddle. The clamping tool is provided with a positioning base plate and at least one group of horse plates, the width of the positioning base plate is larger than the thickness of the transverse rib plate, the bottom side of the positioning base plate is a supporting base surface, and the top side of the positioning base plate is a clamping base surface; the horse plate is connected to the clamping base surface of the positioning base plate to form a clamping groove capable of accommodating the outer side of the corresponding transverse rib plate; when the transverse rib plate of the cable saddle is assembled, the transverse rib plate is clamped at a set position close to the outer side edge of the transverse rib plate of the working platform through a clamping groove between the horse plates, the horse plates and the clamped transverse rib plate are in spot welding connection, and the positioning base plate is in plane contact fit with the working platform or an equal-height pad on the working platform through the supporting base plane. Aiming at the particularity of the cable saddle with a saddle body of a steel plate welding structure, the cable saddle supporting and clamping device can stably support and clamp the cable saddle horizontally arranged on a working platform, and has the technical characteristics of simplicity and feasibility in supporting and clamping and stability in supporting.

The high-speed direct-drive horizontal five-axis machining tool comprises a base, a base table, an X-axis linear motor, a Y-axis linear motor, a Z-axis linear motor, an orthogonal rotary table assembly, a stand column assembly, a spindle box assembly and a gravity center adjusting assembly, the orthogonal rotary table assembly comprises an A-axis rotary table, a B-axis rotary table and a rotary table box body, and the rotation axis of the A-axis rotary table and the rotation axis of the B-axis rotary table are arranged in an orthogonal mode; the vertical plane where the gravity center of the orthogonal rotary table assembly is located and the gravity center of the Z-axis linear motor are located in the same vertical plane, by arranging the gravity center adjusting assembly, when the B-axis rotary table rotates in the plane, the gravity center shifts, and the gravity center adjusting assembly can adjust the position of a sliding plate in a rotary table box according to pressure changes of two pressure sensors; the plane where the gravity center of the orthogonal rotary table assembly is located is close to a Z-axis linear motor to the maximum extent, vibration generated when the linear motor is driven is reduced, and the machining precision of a machine tool is improved.

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.

The present invention relates to a method and system for actively controlling the center of gravity of an aircraft. The method comprises: obtaining the heading center of gravity of a rear water tank and a front water tank on the aircraft, and the heading center of gravity of a front waste water tank and a rear waste water tank on the aircraft before the aircraft takes off; setting the target heading center of gravity of the aircraft according to the flight characteristics of the aircraft; during the flight, when the center of gravity of the aircraft changes, calculating the center of gravity difference ΔX between the current heading center of gravity of the aircraft and the target heading center of gravity CG ;When ΔX CG <0, the water in the front water tank is consumed by the user, and the waste water in the user is discharged into the rear waste water tank; when ΔX CG >0, the water in the rear water tank is consumed into the user, and the waste water in the user is discharged into the front waste water tank. According to the above technical scheme, the present invention can achieve the following beneficial technical effects: the method and system are simple and reliable, and it is easy to keep the center of gravity of the aircraft within the expected ideal range.

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).

The utility model relates to the technical field of vermicelli production, in particular to a nozzle capable of adjusting the section shape of vermicelli, which comprises a body, the top of the body is provided with a pipe thread, and the bottom of the body is provided with a strip-shaped discharge slotted hole along the radial direction; an adjusting block is fixedly arranged on one side of the body, and a push rod with a rectangular section is arranged in the adjusting block in a sealed and sliding mode. One end of the push rod penetrates through the body in a sliding mode and slides in the discharging groove hole in the radial direction, and a screw is arranged at the other end of the push rod. The screw rod penetrates through the adjusting block in a sliding manner; a matched adjusting knob is arranged on the screw rod; a vertical limiting plate is arranged at the outer end of the top of the adjusting block; the inner end of the adjusting button is in plane sliding abutting connection with the adjusting block, and the outer end of the adjusting button is in plane sliding abutting connection with the limiting plate. The push rod is driven to move in the radial direction by screwing the adjusting knob, so that the vermicelli discharging section shape of the discharging groove hole is adjusted, and thick and thin vermicelli or wide vermicelli can be produced.

The invention relates to a method (100) and a computer program product for estimating the weight of an aircraft, in particular a passenger aircraft, during a flight, wherein the relationship between total aircraft weight, lift coefficient and angle of attack is known for the aircraft and the angle of attack and amount of fuel are determined during the flight, characterised by the following steps: a) determining at least two instantaneous total aircraft weights at different times during a flight based on the respective instantaneous angle of attack and the relationship between lift coefficient, angle of attack and total aircraft weight (step 110); b) determining the respective dry total weights by subtracting the weight of the respective instantaneous amount of fuel from the determined total aircraft weights (step 120); c) averaging the dry total weight across all dry total weights determined for the same flight (step 130); and d) estimating an instantaneous total weight at an arbitrary time in the flight by adding the weight of the amount of fuel at this time to the averaged dry total weight (step 140). The computer program product according to the invention is designed to carry out this method.

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 invention proposes a method for assisting operations to be performed during a ground movement phase at an airport. The method comprises: obtaining, for at least one ground movement phase performed at an airport by an aircraft in a fleet, information representing each event from a list of events, as well as a geolocation point for said event and a condition of the ground movement phase; determining (512), for at least one route, an occurrence rate for each event occurring on said route, and per geolocation point, solely from the information for which the ground movement phase condition satisfies a predefined criterion. The method includes providing information representing the determined occurrence rate and an associated geolocation point. Thus, it is possible to easily decide on a presumed ideal location to perform an operation based on previous events.Figure to be published with the abbreviation: Fig. 5B.

The present application relates to a kind of three-way change approach bridge model construction method, device, equipment and storage medium, belong to water transport engineering technical field, wherein, the method includes by approach bridge axis to the multiple row frames of approach bridge simulation model is carried out coordinate calculation to obtain the three-dimensional coordinates of each row frame, so that the change of the plane and the elevation of approach bridge can be determined;According to the preset cross section data corresponding to the horn mouth of wharf side, middle section and shore side horn respectively, the slope of three-dimensional coordinates is calculated, to obtain the height of each row frame on cushion stone, so as to determine the change of approach bridge in cross section;The approach bridge simulation model can also be optimized according to the height of cushion stone and the three-dimensional coordinates of each row frame, so as to construct three-way change approach bridge model according to the change of approach bridge in plane, elevation and cross section, realize the quick and accurate parameter adjustment of three-way change special-shaped approach bridge, without manual parameter adjustment, save a lot of human resources and cost.

A rotary scale apparatus for an encoder apparatus including a planar disc on which at least one track including scale features is provided, in which the planar disc includes a hole through its centre for receiving a cylindrical shaft, and in which the rotary scale member includes at least three cantilevered spring members which are provided substantially in plane with the planar disc and spaced around the edge of the hole, for engaging with, and radially locating the disc on, a cylindrical shaft inserted therethrough.

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.

1. Name of the product of this design: Aviation tire (7). 2. Purpose of this design product: for installation on aircraft. 3. The design key point of this appearance design product lies in the shape. 4. The picture or photo that best illustrates the design points: Stereoscopic diagram 1.

A low-noise multifunctional rotor for centrifugal / axial fans, vertical wind turbines and hydromachines is disclosed. The rotor comprises at least two blades fixed around a central shaft (1) by fastening elements (6). Each blade incorporates a first helical plate formed from a convex-concave rotation surface (3) and a second helical plate formed from a concave -convex rotation surface (4). The rotation radii of surface points, measured in planes perpendicular to the rotor axis, are equal to the radii defined in the generating surfaces and increase progressively from the lower to the upper part of the rotor, establishing an ascending spiral flow path. Novelty resides in that one side of plate (3) is aligned at an acute angle towards the inner face of plate (4) and is spaced therefrom by a gap, which reduces turbulence, noise and vibration while improving flow efficiency.

Systems and methods are provided for installing ribs and / or spars to a wing panel while a contour is enforced. Methods include suspending a wing panel beneath a shuttle that enforces the contour, advancing the wing panel through work stations via the shuttle, and installing a rib or a spar (or another wing panel) at a work station, while the contour is enforced. Other methods include locating a wing panel beneath a shuttle, coupling adjustable-length pogos to the wing panel at locations distinct from those corresponding with an installation location, e.g. for a rib or a spar, and controlling the length of the pogos to enforce a contour to the wing panel. Some systems include a track, work stations disposed along the track, and a shuttle to advance along the track and convey a wing panel to each of the work stations while enforcing a contour onto the wing panel.

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.

To provide a drone for pipeline inspection that when flying and moving in a pipeline, suppresses that the drone got too close to a ceiling plane and is pulled toward the ceiling plane side of the pipeline by air stream occurring due to rotation of a propeller, and thus, cannot be controlled, and that can stably fly and move in the pipeline.SOLUTION: In a drone for pipeline inspection which flies and moves in a pipeline 20 by rotation of a propeller 2 provided on an airframe 1 and inspects the interior of the pipeline 20, the airframe 1 comprises a contact part 3 contacting a ceiling plane 21 of the pipeline 20. The contact part 3 is provided above the airframe 1 with a prescribed clearance therebetween, this clearance is configured as a clearance capable of avoiding such a situation that when the contact part 3 contacts the ceiling plane 21, the airframe 1 pulled toward the ceiling plane 21 side of the pipeline 20 by air stream occurring due to rotation of the propeller 2 and cannot be controlled.SELECTED DRAWING: Figure 1

The utility model provides a mounting seat of a portable emergency positioning transmitter, and aims to solve the technical problem that the portable emergency positioning transmitter cannot be mounted at a pre-designed mounting position on an airplane due to technical update and iteration of the portable emergency positioning transmitter. The mounting base comprises a supporting plate; each supporting leg is of an L-shaped structure, one end of each supporting leg is detachably connected with the end of the supporting plate, and the L-shaped end of each supporting leg is far away from the supporting plate; the mounting plate is detachably arranged on the supporting plate, the mounting plate and the supporting legs are located on the two side faces of the supporting plate respectively, one end of the mounting plate tilts in the direction away from the supporting plate to form a positioning part, and a notch is formed in the middle of the positioning part; wherein at least one supporting leg is arranged at the four corners of the mounting plate, the position of the supporting leg on the supporting plate is adjustable, and the portable emergency positioning transmitter is arranged on the mounting plate. According to the mounting seat, a special mounting seat is designed, so that the updated and iterated portable emergency positioning transmitter can be mounted at a pre-designed mounting position on an aircraft.

The utility model belongs to the technical field of installation of valve positioners, and relates to an installation part which is used for connecting and installing a positioner and an adjusting valve and mainly comprises a plane L-shaped structure or concave structure installation plate or a combination of the plane L-shaped structure installation plate and the plane concave structure installation plate. A plurality of connecting holes with certain lengths are respectively formed in the two ends, connected with the regulating valve and the positioner, of the plane L-shaped structure mounting plate or the concave structure mounting plate along the central axis direction; and the concave edge of the plane concave structure mounting plate is matched with the convex shape of the fixed position of the positioner. The tool can be used for mounting valve positioners and regulating valves of different types, different sizes and different strokes, an additional auxiliary structure is not needed, the mounting difficulty of the valve positioners is reduced, the maintenance work efficiency is improved, and the cost is saved.

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).