158 results about "Meridian plane" patented technology

A ball-and-socket joint with integrated angle sensor for a motor vehicle, especially for the chassis of the motor vehicle is created. The ball-and-socket joint has a ball-and-socket joint housing (6) provided with a joint opening (7), a ball pivot (1) having a joint ball (2) and a pin (3), which is mounted, with its joint ball (2), rotatably and pivotably in a hollow-ball-shaped bearing surface in the ball-and-socket joint housing (6), and projects, with its pin (3), through the joint opening (7) out of the ball-and-socket joint housing (6). A two-pole field transducer (5) is provided at the end of the joint ball (2) facing away from the pin (3). The poles of the field transducer (5) are arranged on the ball surface. In this case, at least two field sensors (13) are arranged at a distance from one another with respect to the meridian plane defined by the large circle on the hollow-ball-shaped bearing surface running at right angles to the bearing longitudinal axis in the area or on the ball-and-socket joint housing (6) facing away from the joint opening, and interact with the field produced by the field transducer (5).

The invention discloses a method for constructing a turbine disc structure probability design system. The method comprises the following six steps of: 1, analyzing a turbine disc structure probability design flow, analyzing a failure mode, and determining a system functional model of the probability design flow; 2, extracting characteristic parameters of a turbine disc meridian plane and a mortise respectively to finish parametric modeling; 3, storing a common material for a turbine disc in a form of spreadsheet to form a material base tool; 4, integrating a rain-flow counting program, processing a standard loading spectrum, providing primary and secondary cyclic loading parameters for low cyclic analysis, integrating an MATLAB data processing function, and expressing fatigue-creep coupling by using a double-parameter characteristic function; 5, researching the heteroscedastic characteristic of a strain life model and providing a model to realize heteroscedastic recursive processing of fatigue test data; and 6, constructing a turbine disc structure probability design system database based on the principle of using a task as a basic unit and using the turbine disc probability design flow as a core. The method has broad application prospect in the field of aerospace engines.

A method for monitoring a tire during running includes acquiring and storing, at least temporarily, a first curve representing an acceleration profile of a first point of a tread area of the tire; acquiring and storing, at least temporarily, at least one second curve representing an acceleration profile of a second point of the tread area; and comparing the first curve and the at least one second curve, or parameters derived from the first curve and the at least one second curve, so as to determine a dynamic behavior of the tire. The first and second points are located substantially on a same meridian plane of the tire. A related tire, wheel for a vehicle, system for monitoring a tire during running, and method for controlling a vehicle are also disclosed.

The invention relates to a dark view field object lens device which illumines the observed objects at the dark view field and used in a dark view field microscope utilizing the scattering and diffraction of the objects to observe. More particularly, the invention relates to a lighting and mounting structure of the dark view field object lens device. The object lens contains an inner cylinder and an outer cylinder. A combination of lenses used for imaging is installed inside the inner cylinder; an LED illuminating apparatus which is arranged in a ring shape and takes an LED original piece as light source is arranged at the outer side of the outer cylinder. In addition, an optical element which is arranged between the LED original piece and the observed objects transforms the light of LED in a meridian plane into parallel light and leads the parallel light to light the observed objects in an inclined way. The light emitted by the LED original piece is transformed into parallel light to light the observed objects in the meridian plane. After the image of the light scattered and diffracted by the observed objects is formed by an imaging object lens, the image is processed after being observed by using an eyepiece and shot by a camera. Screw thread is arranged at the periphery of the end part of the inner cylinder of the dark view field object lens device, so that the dark view field object lens device can be directly installed on a change over panel of a bright field microscopical. Therefore, the bright field microscopical can be directly switched for the observation of the dark view field.

The invention provides a method for manufacturing a spherical surface frame of an airplane body. The method comprises the following steps of: acquiring a spherical skin curved surface according to the design requirement of an airplane; dividing the spherical skin curved surface into a plurality of strip-type parts, and unfolding the strip-type parts to form a plane by an equal-area method; determining that gaps delta t between theoretical boundaries and actual boundaries of the strip-type parts are equal to R cos alpha(tg pi/n-pi/n), wherein R is the radius of a sphere in which the spherical skin curved surface is positioned, alpha is included angles between the gaps and a meridian plane of the sphere, and n is the number of the strip-type parts divided on the sphere; shearing a unidirectional tape prepreg material by combining the sizes of the gaps with the shape of the plane formed by unfolding the strip-type parts; paving the shorn unidirectional tape prepreg material on a die for the spherical surface frame; curing for forming by using an autoclave; and machining complementally. The invention also provides the spherical surface frame of the airplane body, which is manufactured by the method. The spherical surface frame can meet the requirements of light weight and high strength.

The invention discloses a laser for generating high-power axisymmetric polarized light, which comprises a total-reflection mirror, an output mirror, a laser working medium and a pumping source, wherein the laser working medium is located on all folding arms perpendicular to the total-reflection mirror; the pumping source is a radio frequency semiconductor laser or a flash lamp pumping source. Thelaser is characterized by also comprising 4*N turning mirrors, N equals to 1, 2 and 3, and the centers of the 4*N turning mirrors are all located on the optical axis of a resonator, wherein the normal lines of 2*N turning mirrors are parallel to the meridian plane, and an included angle between the normal lines of two adjacent turning mirrors is 90 DEG; and the normal lines of the rest 2*N turning mirrors are parallel to the sagittal plane, an included angle between the normal lines of the rest two adjacent turning mirrors is also 90 DEG, and the included angles between the normal lines of the 4*N turning mirrors and the optical axis are 45 DEG. The total-reflection mirror is a medium grating mirror or an inner axial-cone metal grating mirror. The laser provided by the invention has the characteristics of simple structure, high output axisymmetric polarized light power, high degree of polarization, good beam quality and the like.

A centrifugal compressor for which θ−α>0° and 0°<θ<34°, when the angle formed by a diffuser inlet hub-side line (5a) and the radial direction at a point B in the meridian plane is θ, and the angle formed by a tangent line (3b) and the radial direction at a point A of an impeller hub-side line (3a) nearest the inlet of the diffuser (5) is α. Thus, skewing of the velocity distribution of a gas within the diffuser of the centrifugal compressor is eliminated.

The invention discloses a computing method of a revolution section profile of a turbomachinery blade, which mainly comprises the following steps: reading in each section profile data of the blade; taking out a point at the corresponding position on each section profile and recombining the points to form a space curve l; projecting the curve to an XZ plane and a YZ plane to obtain a curve lXZ and a curve lYZ; presetting a function relational expression R=f(X) of the intersecting line of a revolution surface and a meridian plane; presetting an initial radius Rinitial to solve the coordinates of the intersecting point A of a cylindrical revolution surface the axes of which is the X-axis and the radius of which is the initial radius Rinitial and the space curve l; substituting the coordinate AX of the point A at the X-axis into the function relational expression R=f(X) of the intersecting line of the revolution surface and the meridian plane to obtain the magnitude of the radius RA which corresponds to the coordinate AX on the revolution surface; and then judging whether the point A is the intersecting point according to the absolute value of RA-Rinitial. Each solved intersecting point forms the revolution section profile of the blade. The computing method has the advantages of convenience, rapidness, high computing precision and the like.

The invention discloses a method for machining an encircling hole with a meridian plane group nozzle, which mainly comprises the following steps of: fixing the group nozzle on a rotatable locating ring with index locating holes, cutting the encircling hole through a wire cutting machine, and cutting the next encircling hole according to the pitch rotate locating ring of the encircling hole after each one encircling hole is cut. The method for machining the encircling hole with the meridian plane group nozzle adopts the wire cutting machine to cut the encircling holes and uses index locating holes on the locating ring for index location so as to ensure the machining accuracy. The method is convenient to realize, ensures the reliability and rationality in technology,g greatly improves the production levels of steam turbine nozzles, reduces the manufacturing cost of steam turbine and improves the work efficiency.

The invention relates to a circumferential direction vorticity through-flow design method of an aero-engine gas compressor. The circumferential direction vorticity distribution has a significant influent on the overall performance of the gas compressor and acts as critical diagnostic parameters of vorticity dynamics; in the through-flow design stage, the important design parameter circulation distribution is optimized so as to control the circumferential direction vorticity in advance and realize the design of the gas compressor with high performance. The method obtains a circulation optimal iterative formula according to the optimal distribution criterion of the circumferential direction vorticity close to zero in the main flow area of a meridian plane and the close relation of the vorticity and the circulation on the basis of a Crocco equation, can conveniently and automatically optimize the circulation distribution from the initial circulation distribution, realizes the better distribution of the circumferential direction vorticity, increases the pressure ratio and efficiency of the gas compressor, and guides the air-powered design of the gas compressor.

The invention discloses a machining technique of a turbine blade ring. In the machining technique, the machining of a guide blade ring steam seal groove is characterized in that different tools are used to respectively process a straight flute, left and right step surfaces, left and right elbow grooves and an arc groove on the guide blade ring steam seal slot according to a certain sequence, so that the machining precision of the guide blade ring steam seal groove can be effectively ensured, and the machining quality of the guide blade ring steam seal groove can also be ensured. When a steam extracting opening is machined, small planes are respectively arranged at corresponding positions on an excircle inclined surface and a meridian plane curved surface, so that a drilling hole can be conveniently positioned, thus the machining precision of the steam extraction opening can be ensured. With the adoption of the machining technique of the turbine blade ring, the machining precision of the turbine blade ring can be effectively increased and the quality of the turbine blade ring can be improved, moreover, the production efficiency can be effectively increased and the machining time can be shortened.

The invention belongs to the technical field of optical imaging simulation, and relates to an imaging quality simulation method of a Fresnel diffraction optical system. The method includes the following steps that 1, based on the isoplanatic region block thought, an original image is divided into multiple image blocks with the similar same point diffusion function; 2, the meridian plane position of the center of each image block and the corresponding field angle are calculated; 3, a discretized Fresnel diffraction formula is constructed, and the point spread function of each image block is calculated; 4, MTF in different regions of the image are used for conducting lowpass filtering on all the image blocks, and random noise is added. The imaging quality simulation method is suitable for imaging quality simulation of an optical system with a diffraction lens as the main lens, capable of generating images with diffraction optical imaging characteristics including low MTF, low contrast, low SNR and large-size PSF spatial variability in a simulation mode, and provides support for optimal design of the Fresnel diffraction imaging system and image processing algorithm research and verification.

The invention discloses a polarization-insensitive space folding laser resonator which comprises a total-reflection mirror, 4*N turning mirrors, an output mirror and a laser working medium, wherein the total-reflection mirror and the output mirror are perpendicular to an optical axis, and the centers of the total-reflection mirror and the output mirror are located on the optical axis; and the 4*N turning mirrors are highly reflecting plane mirrors, and the centers of the 4*N turning mirrors are located on the optical axis, wherein the normal lines of 2*N turning mirrors are parallel to the meridian plane, and an included angle between the normal lines of two adjacent turning mirrors is 90 DEG; the normal lines of the rest 2*N turning mirrors are parallel to the sagittal plane, an included angle between the normal lines of the rest two adjacent turning mirrors is also 90 DEG, and the included angles between the normal lines of the 4*N turning mirrors and the optical axis are 45 DEG; and the laser working medium is located on all folding arms perpendicular to the total-reflection mirror. The laser resonator eliminates the polarization selection phenomenon of the turning mirrors in the same plane. The polarization property of output laser is decided by the polarization selection characteristic of the total-reflection mirror. The higher the output power is, the better the beam quality is. The laser resonator can be applied to medium-power and high-power gas or solid laser devices.

The invention provides an adjustment and design method for a lighting system matching multiple objective lens in an extreme ultraviolet lithography machine. The lighting system applicable to the method includes a light source, a condenser lens, a view field compound eye, a diaphragm compound eye and a relay lens group. The method specifically comprises the steps of: before replacing a projection objective lens of the extreme ultraviolet lithography machine: using ray tracing to calculate the aperture angles of the emergent rays of a relay lens A on a meridian plane and a sagittal plane; after replacing a projection objective lens of the extreme ultraviolet lithography machine: taking out the central point of pupil plane to serve as an object point to perform ray tracing; adjusting the tilt angles and positions of the relay lens A and relay lens B, and adjusting the tilt angles of central compound eye elements on the diaphragm compound eye and the view field compound eye till that the image plane of the current lighting system is close to an arc image plane corresponding to the projection objective lens. By adjusting the lighting system based on the adjustment method provided by the invention, the lighting system matching the projection objective lens system can be obtained, thus greatly reducing the design cost of a projection lithography machine.

The invention discloses a method for determining intersection coordinates of a satellite wave beam and the earth. The method comprises the following steps of: (1) seeking a unit vector rfs of the satellite wave beam in a satellite body coordinate system; (2) calculating a conversion matrix of the satellite body coordinate system and a satellite track coordinate system by a yaw angle, a pitch angle and a roll angle of a satellite; (3) calculating the conversion matrix of a geographic coordinate system and an earth coordinate system by longitude lambda and latitude I of the satellite; (4) calculating the conversion matrix of an auxiliary coordinate system and the geographic coordinate system by an included angle beta of a meridian plane on which the satellite is and an instantaneous orbit plane of the satellite and an included angle alpha between a movement direction of the satellite and a geographic horizontal plane; (5) converting the unit vector rfs into the earth coordinate system to obtain rfe by coordinate system conversion; (6) associating a linear parameter equation of satellite beam incidence with an earth ellipsoid equation, and calculating two groups of coordinates [xje, yje and zje]T, wherein a group of coordinates near the satellite are coordinates of an intersection point of the satellite wave beam and the earth.

The invention provides a turbine stator and rotor combination piece for linear projection blade and a turbine motor. The turbine stator and rotor combination piece comprises a stator and a rotor which are coaxially sleeved, wherein the stator comprises a stator body, a stator blade and a stator shroud; the rotor comprises a rotor body, a rotor blade and a rotor shroud; the inner wall of the stator shroud and the outer wall of the rotor body are coaxially sleeved; points on an outer outline line of the stator blade and an intersection line of the corresponding equivalent meridian plane form a first intersecting line; the first intersecting line is vertically intersected with a first projection straight line passing through the inside of the stator shroud; points on the outer outline line of the rotor blade and an intersection line of the corresponding equivalent meridian plane form a second intersecting line; the second intersecting line is vertically intersected with a second projection straight line passing through the inside of the rotor shroud. The turbine stator and rotor combination piece provided by the invention has the advantages of high hydraulic efficiency. The turbine motor provided by the invention has the advantages of simple structure and large torque, and is applicable to drilling boreholes with various sizes.

The invention provides a unit magnification multi-pass system optical path astigmatism compensation method and a system thereof, and belongs to the field of astigmatism compensation of a unit magnification multi-pass system. The method is characterized in that: a compensation spherical mirror is introduced behind an output aperture of a UMS (unit magnification multi-pass system) optical path which at least comprises a White optical path, various improved White optical paths and an MMS (multi-pass matrix system) optical path, the compensation spherical mirror and the whole astigmatism of the UMS optical path are compensated by adjusting the radium of the compensation mirror and the beam full divergence angle adjustment parameters, the output beam of the UMS optical path is reflected on the compensation spherical mirror, the transmission meridian plane of the compensation spherical mirror is possibly superposed with the sagittal plane of the output beam of the UMS optical path, and the astigmatism of the compensation spherical mirror is the same as that of the output beam of the UMS optical path with opposite directions, so that the astigmatism is compensated, and the divergence angle of the output beam can be further adjusted to match with the numerical aperture of a subsequent optical path.

The invention discloses a type line design and check method for an impeller meridian plane of a radial-axial turbine expander. The type line design and check method comprises the following main steps of reading in basic parameters of the impeller meridian plane; selecting a two-dimensional coordinate system of the meridian plane; calculating point coordinates of an input and an exit of a hub and shroud curve; giving an initial equation index value by adopting a generalized elliptic equation according to known parameters and solving a hub and shroud curvilinear equation; solving the arc length of the curve from the input to the output, dividing the arc length of the curve into N equal parts, solving the coordinates of equal diversion points according to the curvilinear equation, thus calculating the through-flow area at constant current contour position, and drawing with the flow line position as a horizontal coordinate and the through-flow area of the flow line position as a longitudinal coordinate; judging whether a flow channel meets the requirement or not, if so, outputting the point coordinates of the hub and shroud curve of the meridian plane, and if not, adjusting curvilinear equation indexes ph and qh or ps and qs and recalculating. According to the method provided by the invention, the design process is simpler, more convenient and quicker; the reference for checking smoothing changes of the flow channel is more visual and reliable; in addition, the processing and the manufacturing of subsequent impellers are facilitated.

The invention discloses a windshield type head up display and a method for weakening a double image. The windshield type head up display includes an image source and a projection group. The image source is projected to a windshield through the projection group, and forms a first virtual image and a second virtual image on the same side of the windshield. The first virtual image approaches the areaof an eye box with respect to the second virtual image. The distance between the first virtual image and the area of the eye box is an imaging distance. When the imaging distance changes, the value of the first virtual image and the second virtual image is detected. If the imaging distance increases, the value of the double image of the first virtual image and the second virtual image that are projected to the same side of the windshield through the projection group is lowered. According to the invention, by reasonably adjusting the astigmatism of an optical system, meridian plane imaging relative to human eyesight is greater than sagittal surface imaging, which can further weaken the phenomenon of double images. By increasing imaging distance and reasonably adjusting astigmatism, the phenomenon of double images can be also weakened. Therefore, either way or the combination of two ways can be conducive to the weakening of the phenomenon of double images.

This invention is a small type turbine axis manufacturing method. The turbine is welded with axis; stress is eliminated through heat treating. Weld zone is sanded, then tension test is done. Burr is done first and then axis is processed t needed length, and central hole is punched at end of axis. Outer circle and R slot are processed to needed dimension, then liquid penetrant test, Central hole and turbine outer circle are grinded, then turbine end face is processed to needed dimension, then each outer circle is processed to needed dimension. Penetration testing and high frequency hardening and alignment are done. Stress is eliminated through heat treating and central hole is grinded, turbine end face is grinded to needed dimension, then each outer circle on the axis is grinded. Screw thread is roll extruded, turbine outer circle is precise grinded. Turbine end face is grinded, then each outer circle on the axis is precise grinded, sealing slot is grinded, turbine meridian plane is grinded, burr is eliminated, then dynamic balancing experiment is done for testing.

This invention is a small compression impellor manufacturing method. First, big excircle, big end face and hole are processed through small end excircle is clamped and is relied on advection road plane. Secondly, big excircle is clamped by three claws and big end face is done to plane to process meridian plane and small end face, all procedures are finished. The consistency of small end excircle and passage is fully used in the first processing to make position reference coincide design reference, so the processing error brought from non coincidence of reference in traditional technique is effectively avoided, and the passing percent is raised to more than 97%. The advantages are simple technology, low cost and high production efficiency.

The invention discloses an ultra-wide field-of-view off-axis three-reflector optical imaging system which comprises a main reflector with positive focal power, a second reflector with negative focal power, and a third reflector with positive focal power. The reflecting surface of the main reflector is a spherical surface. The reflecting surfaces of the secondary mirror and the third reflector are flat spherical secondary curved surfaces. The curvature radii of top points of the three reflectors approximately satisfy a flat image field condition. The main reflector generates a real image of a far scene between the main reflector and the second reflector. The second reflector and the third reflector perform relay imaging of the real image on an image plane. An aperture diaphragm is placed on the front focal plane of the third reflector, thereby realizing an image-side telecentric optical path. The main reflector inclines along an X-axis relative to incident main light of a central field-of-view. The second reflector is coaxial with the third reflector. After the main light of the central field-of-view in a meridian plane is reflected by the main reflector, an included angle is formed between the reflected main light and the common symmetric axis of the second reflector and the third reflector. The ultra-wide field-of-view off-axis three-reflector optical imaging system has advantages of ultra-wide field-of-view, intermediate relative aperture, wide working wave band, no image-side telecentric barrier, small object-side distortion, high imaging quality, etc. The ultra-wide field-of-view off-axis three-reflector optical imaging system is suitable for earth imaging observation field of a spatial camera, an imaging spectrometer, etc.