161 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 wide-width off-axis three-reflection-mirror optical system adopting a free curved surface, and belongs to the technical field of optics. A conventional off-axis three-reflection optical system adopting a free curved surface has a small field angle, and the adopted totally unbalanced free curved surface has large processing difficulty. The system is a wide-width off-axis three-reflection mirror optical system taking a primary reflection mirror as a free curved surface, and comprises the primary reflection mirror, a secondary reflection mirror, a third reflection mirror and a aperture diaphragm, wherein the aperture diaphragm is overlapped with the secondary reflection mirror; incident light is reflected to the secondary reflection mirror through the main reflection mirror, reflected to the third reflection mirror through the secondary reflection mirror, and then reflected through the third reflection mirror, so that an image is formed; the main reflection mirror is a free curved surface which is symmetrical to a meridian plane, so that the manufacturing difficulty of the system can be reduced; and at the same time, the system has a lager rectangular view field, so that wide-width imaging can be realized.

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.

The invention provides a single rotor minitype turbofan engine adopting an axial flow oblique flow serial composite compressing system. The structure of the single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system is that airflow of an outer duct of a turbofan engine and the airflow which enters into a combustor of an inner duct are both supplied by the axial flow oblique flow serial composite compressing system, the axial flow oblique flow serial composite compressing system adopts a combination of both an axial flow fan rotor and an oblique flow compressor rotor, and provides pressure boosting airflow for both the inner duct and the outer duct. The serial axial flow fan rotor is relative to the portion of the inner duct, and directly forms an oblique flow compressor impeller to a serial blade lattice form; a row of stator impellers is arranged on the axial flow fan rotor corresponding to the portion of the outer duct, the air flow is adjusted to the rear direction of the meridian plane through rectification deceleration, and flows into a turbofan engine outer duct bypass along the outer surface of an intermediary cartridge receiver. The single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system has the advantages of being capable of realizing to provide the pressure boosting airflow for the inner duct and the outer duct by the needs of the turbofan engine, lowering an oil consumption rate of the engine, improving windward side thrust of each unit of the engine, and effectively improving voyage and enhancing load when the single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system is applied in carriers of unmanned planes, loitering munitions, and the like.

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 three-dimensional design method for a turbomachinery impeller with castability. The method comprises the following steps of 1) determining meridian plane profiles of an impeller disk and an impeller cover of an impeller according to design demands; 2) on a meridian plane obtained in the step 1), constructing a first meridian streamline, a second meridian streamline and a third meridian streamline for controlling spatial twisted shapes of blades of the impeller, wherein the first meridian streamline is an impeller cover streamline and coincides with the meridian plane profile of the impeller cover, the third meridian streamline is an impeller disk streamline and coincides with the meridian plane profile of the impeller disk, and the second meridian streamline is a middle streamline and is arranged between the first meridian streamline and the third meridian streamline; 3) designing profiles of the blades of the impeller, wherein distribution of a blade mounting angle and blade thickness on the third meridian streamline is determined according to the castability of the formed three-dimensional spatial twisted blades; and 4) forming the three-dimensional turbomachinery impeller with the castability.

A centrifugal multi-blade blower includes an impeller, and a casing that accommodates the impeller, and draws in air at least from an inlet port of the casing which opens on one end side of a rotation shaft and blows out the air radially outward of the rotation shaft. The impeller includes a main plate that is joined to the rotation shaft, vanes which are arranged around the axis of the rotation shaft and the other end sides of which in the rotation axis direction are connected to the main plate, and a side plate that connects together the vanes on their one end sides in the rotation axis direction. The vanes are characterized in that an inlet angle on a cross-sectional surface crossing each inner peripheral edge part of the vanes on a meridian plane of the impeller in a predetermined direction is evenly made in the entire region from the side plate-side through the main plate-side, and that outer peripheral edge parts of the vanes are configured to be away from the axis of the rotation shaft from the main plate-side toward the side plate-side.

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 relates to a fan / compressor casing treatment device. In the internal structural design of an arc slot casing treatment, the radial projecting line of a meridian plane is a non-orthogonal smooth curve, so that flow loss inside the casing treatment is reduced, and the efficiency of the fan / compressor is improved.

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 relates to a linear density measuring method for an optical grating. Laser sent out by a laser light source is coupled through an optical fiber coupler, is coupled by a single-mode 2*2 optical fiber coupler, is collimated by an optical fiber collimator, and is then illuminated onto the surface of the optical grating to be tested to generate diffraction; different levels of diffraction light is generated; an irradiation area illuminated by the laser onto the optical grating is reduced by using the optical fiber, the conditions that zero stage diffraction light and first stage diffraction light of optical grating measuring points return in an incidence direction, the angle difference between the zero stage diffraction light and the first stage diffraction light is just a first stage diffraction angle alpha are respectively measured; the calculation is performed according to the angle difference of the measured two beams of diffraction light; groove density is obtained. The measuring stability is high; the light spot dimensions are small; the collimation performance is good; the measuring precision is high. In the practical operation process, the optical grating to be measured only needs to be put onto an electric displacement table; by regulating the angle position of an electric rotating table, the groove density of each measuring point on the meridian plane of the optical grating to be tested can be obtained. The linear density measuring method has the advantages that the higher-precision linear density measurement can be performed on the optical grating; the method can be used for a plane optical grating or a concave surface optical grating with greater curvature radius.

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 provides a wide flow range surge control turbocharger compressor which comprises a compressor casing and a compressor impeller, wherein an outer ring and an inner ring which are coaxial with the compressor impeller are arranged on the inner side of the compressor casing; a C-shaped circulation channel is formed between the outer ring and the inner ring; vanes are arranged at the end, away from the compressor impeller, of the C-shaped circulation channel; the back half part, where the C-shaped circulation channel vanes are positioned, of the C-shaped circulation channel forms a vaned diffuser inside the circulation channel; the front half part of the C-shaped circulation channel forms a vaneless diffuser inside circulation channel; the front edges of the C-shaped circulation channel vanes are positioned at the highest points of the C-shaped circulation channel; the rear edges of the C-shaped circulation channel vanes are flush with the outlet of the C-shaped circulation channel; and the meridian plane of the C-shaped circulation channel is divergent. Relative to the prior art, the wide flow range surge control turbocharger compressor has the advantages that a universal vaned diffuser is embedded in the cavity of the compressor casing, so that the treatment effect of the casing is optimized, and the casing can be widely applied to centrifugal compressors.

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.

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.

The invention concerns a double-chamber device for mixing at least two viscous substances, comprising: cylindrical and coaxial first and second communicating vessels, each hermetically sealed at one end by a mobile piston, and provided at its second end with a slightly conical bottom end, the two vessels being arranged, preferably vertically, in mirror symmetry relative to a meridian plane perpendicular to their common axis; a central mixing element connecting the two vessels at the two slightly conical bottom ends; and a high pressure hydraulic device for automatically activating the pistons in a coordinated reciprocating movement. A worm screw injection device in communication with one of the vessels or with the mixing element may be used to inject the substances. Mixing of substances may include driving the pistons in a coordinated reciprocal motion to collapse one vessel while expanding the other, forcing the substances through the central mixing element.

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.