70 results about "Radial distribution" patented technology

The invention relates to the technical field of cable manufacturing, in particular to cable insulation sheath extrusion molding equipment which comprises an extrusion device, and the extrusion device comprises an extrusion head and a rotating assembly. The plurality of convex surfaces are uniformly arranged on the outer wall of the extrusion head along the circumferential direction, so that the radial distribution of the molten material in the flow channel is adjusted, and the molten material is guided to supplement gaps among strands of the multi-strand stranded cable. Meanwhile, the extrusion head is driven by the rotating assembly to rotate, so that the convex surface can adapt to the outline of the outer surface of the cable in real time. Therefore, it is ensured that the thickness of the insulating layer is uniform, the surface of the insulating layer is smooth, the phenomenon that materials are excessively gathered towards gaps or are not evenly distributed is avoided, the electrical hidden danger of an over-thin area is eliminated, material waste of an over-thick area is reduced, and the insulating performance and the material utilization rate of the cable are improved.

A filling device (1) for filling a container with a particulate material (28) comprises a supply container (2) that can be filled with the particulate material (28), wherein the supply container (2) has a lower opening (2.2). Moreover, the filling device (1) comprises a radial distribution unit (3), which can be supplied with the particulate material via the lower opening (2.2) of the supply container (2) and which is connected to the supply container (2) in such a way that it can rotate about a rotational axis (A), in order to distribute in the container the particulate material (28) supplied from the supply container (2) to the distribution unit (3). The filling device is characterized in that the distribution unit (3) can be driven by a drive unit (4) that is arranged outside the supply container (2).

The invention relates to a self-powered detector on-pile test device and method.The device comprises an outer support fixed in a test dry hole channel and an inner support coaxially nested in an inner cavity of the outer support, the outer diameter of the outer support and the inner diameter of the test dry hole channel form micro-tight fit, and the inner support can rotate around the axis relative to the outer support; a first mounting position for mounting at least one standard self-powered detector is arranged on the outer support, a second mounting position for mounting at least one self-powered detector to be detected is arranged on the inner support, and a cross arm is arranged at the bottom of the outer support and used for being in contact with the lower end of the inner support so as to limit the axial insertion position of the inner support. According to the on-pile test device and method for the self-powered detector, single-point calibration errors caused by uneven radial distribution of neutron fluence rates can be effectively eliminated or greatly reduced, and the calibration precision and the representativeness of results are remarkably improved.

The utility model belongs to steam turbine equipment technical field, concretely relates to a steam turbine shaft seal rack assembly tool, and this tool includes: base, is equipped with the arc locating surface that matches with the curvature of shaft seal strip in its inner ring, a pair of support is arranged in both ends of base, the rotating drum is coaxially suspended in the above of arc locating surface with locating surface, the rotating shaft is through rotating drum and is rotatablely arranged on the support in both ends, drive assembly is connected with one end of rotating shaft, wherein, the rotating drum extends along the axial direction of rotating shaft, and there are multiple containing grooves in radial distribution, the containing groove extends along the circumference of rotating drum, covers the rack groove that shaft seal strip sets, and the depth of containing groove is adapted to the height of rack, when drive assembly drives rotating drum to rotate to the direction of arc locating surface, the lug of rack circumference is embedded in the rack groove.

The present application provides a turboprop engine power turbine blade and a design method thereof, the method comprising the following steps: Step 1: According to the design requirements of the power turbine at the design state point, the initial angle of attack is selected as zero, and a preliminary turbine blade shape design is carried out; Step 2: According to the preliminary turbine blade shape design results, a calculation model is built, and multi-state calculation analysis is carried out to obtain the radial distribution of the blade outlet airflow angle at the typical state point; Step 3: According to the radial distribution of the blade outlet airflow angle at the typical state point, the inlet angle of attack range is optimized, and the blade geometric modeling parameters are adjusted to carry out blade blade type optimization design; Step 4: The turbine characteristic calculation based on the optimized blade is carried out to obtain the assessment parameters at different state points; Step 5: The assessment parameters are judged, and the blade modeling parameters and the turbine characteristics are iteratively adjusted according to the judgment results until the blade meets all preset conditions. The present application can improve the turbine efficiency at non-design points and reduce the fuel consumption rate of the whole machine within the full envelope range.

The utility model relates to a clutch positioning mechanism, a clutch and an engine. The clutch positioning mechanism comprises a retainer, a first pressing plate and a second pressing plate, the retainer is provided with evenly-distributed installation parts in the circumferential direction of the retainer, the installation parts are used for installing wedge blocks, the first pressing plate and the second pressing plate are used for abutting against the two sides of the wedge blocks respectively, and pressing protruding tongues and positioning protruding tongues are evenly distributed on the first pressing plate in the circumferential direction of the first pressing plate. The radial distribution diameter of the positioning protruding tongues is larger than that of the pressing protruding tongues, the positioning protruding tongues and the pressing protruding tongues are staggered in the axial direction, a compression interval is formed between the positioning protruding tongues and the pressing protruding tongues, and the pressing protruding tongues can conduct compression deformation relative to the positioning protruding tongues in the axial direction. According to the clutch positioning mechanism, due to the fact that the distribution diameter of the positioning protruding tongues in the radial direction is larger than the distribution diameter of the pressing protruding tongues in the radial direction, radial positioning of the retainer is achieved through the fact that the positioning protruding tongues are matched with the second pressing plate, axial positioning of the wedge blocks is achieved through the pressing protruding tongues, and deflection of the retainer is prevented.

The invention discloses a gas distribution device and semiconductor film equipment, the gas distribution device is arranged above a spraying plate, the gas distribution device comprises a gas distribution piece and a gas distribution valve island, the gas distribution piece is internally provided with a plurality of annular flow channels which are distributed at intervals in the radial direction and are concentrically arranged, and the annular flow channels are communicated with the spraying plate. A plurality of air outlet holes axially penetrating through the air distribution piece are uniformly formed in each annular flow channel in the circumferential direction; the air distribution valve island comprises a plurality of air distribution valve sets connected with the annular flow channels in a one-to-one correspondence mode, and each air distribution valve set independently controls connection and disconnection of the corresponding annular flow channel. According to the invention, the gas distribution piece with a plurality of independent controllable annular flow channels is arranged above the spraying plate above the wafer, so that the on-off and gas flow of the corresponding annular flow channels can be accurately controlled through the gas distribution valve island according to the radial distribution requirement of the wafer film thickness in the technological process; independent adjustment of reaction or diluent gas flow in different radial intervals is realized, so that the film thickness uniformity of each area of the wafer is adjusted in a targeted manner, and the increase or decrease of the film thickness in the specified radial interval is realized.

The utility model discloses a karting boat relates to karting boat technical field. The karting boat includes the hull and the propeller, and the propeller includes the casing, the motor, the connecting rod, the impeller, the first flow guide and the second flow guide, and the motor drives the rotation of the impeller, and the water flow is inhaled from the casing side wall water inlet, and the water flow is formed after the acceleration of the impeller and is rotated jet. Rotating water flow first hits the first flow guide piece, and the first flow guide piece of radial distribution divides the water flow into multiple sub flow channels, and forces the water flow to discharge along the axial direction. Subsequently, the water flow enters the second flow guide area, and the taper structure makes the flow passage cross section area gradually reduce, and the water flow speed improves, and finally the water flow is sprayed from the water outlet in the approximate straight line form. Through the first flow guide, the preliminary rectification is realized, and the second flow guide carries out secondary despinning to the central vortex, and the synergistic effect is formed, and the second flow guide piece produces the reverse moment, converts the rotation energy into the additional thrust, and can improve the power of the propeller.

The present disclosure relates to the technical field of flow tube calibration, and particularly relates to a flow tube calibration data processing method. The flow tube calibration data processing method comprises: determining a piecewise linear function of radial distribution of boundary total pressure P s and total pressure P t within a boundary layer based on measured static pressure P tbl_cri and total pressure P tbl at a measurement section of a flow tube; and determining a thickness δ of the boundary layer based on the determined piecewise linear function of radial distribution of boundary total pressure P tbl_cri and total pressure P tbl within the boundary layer. Thus, the deviation caused by the distance between adjacent measurement points can be reduced, the thickness of the boundary layer can be more accurate, and the accuracy of the flow tube calibration result can be effectively improved.

The application discloses a distortion generator arranged in an engine case, which comprises a plurality of threaded rods arranged between an inner case and an outer case of the engine case along the radial direction of the engine case, nuts arranged on and engaged with the threaded rods, distortion members respectively connected to the nuts of different threaded rods at two ends along the length direction, the distortion members being elastic along the length direction, and a driving mechanism connected to the threaded rods and used for driving the threaded rods to rotate. When the driving mechanism drives the threaded rods to rotate, the position of the nut arranged on the threaded rod in the engine case can be changed, the distortion member connected to the nut is stretched or shrunk, and the position of the distortion member in the engine case is changed, so that the adjustment of the position of the distortion structure in the case is realized, different total pressure radial distribution rules are simulated, and the experimental period of an air intake experiment is shortened.

The invention discloses an underground engineering rock mass cutting and replacing device and method in the field of underground engineering rock mechanics, the cutting and replacing device comprises a high-pressure steel pipe, the front end of the high-pressure steel pipe is communicated with a high-pressure spray pipe, and the rear end of the high-pressure steel pipe is communicated with a water conveying pipe, a slurry conveying pipe and a slag discharging pipe; a plurality of high-pressure nozzles are symmetrically arranged on the left side and the right side of the side wall of the high-pressure spray pipe, and the high-pressure nozzles on the same side face different directions. The high-pressure spraying pipe is used for sequentially achieving hole forming, slag discharging and grouting filling replacement on the same station, accurate grouting of the cutting hole is guaranteed, slurry loss is avoided, the construction efficiency is greatly improved, the high-pressure spraying nozzles with different angles are symmetrically arranged on the left side and the right side of the high-pressure spraying pipe, and the construction efficiency is greatly improved. The radial distribution of the cutting holes in the space can be realized, and the replaced grouting body can form a net-shaped structure in combination with the distance between the drill holes, so that the surrounding rock is reinforced by using less grouting materials, and the stability of the surrounding rock of the deep engineering rock mass is ensured.

A controller of a magnetic disk device obtains, for each of a plurality of first position sets, a first distribution that is a radial distribution of differences between a target orbit of the magnetic head and an actual position of the magnetic head while correcting a disturbance synchronized with rotation of the magnetic disk by using correction amounts at a plurality of positions included in one of the plurality of first position sets. The controller performs weighting the first distribution according to a position in the radial direction and calculating an evaluation value based on the weighted first distribution for each of the plurality of first position sets. The controller selects a second position set from the plurality of first position sets based on the evaluation value. The controller records correction amounts at a plurality of positions included in the second position set by the magnetic head.

The utility model discloses a caliber-adjustable silage bagging device, which belongs to the technical field of silage filling, and realizes dynamic adjustability of connecting caliber by arranging caliber adjusting devices with the same structure at two ends of an elastic connecting pipe and combining a plurality of radially distributed telescopic rods and driving mechanisms matched with the telescopic rods. The telescopic rod drives the elastic connecting pipe with flexible deformation capacity, the caliber of the elastic connecting pipe expands or contracts along with the telescopic rod in the telescopic process, the telescopic rod can be effectively attached to the outlines of the filling machine and the ensiling bags, and the device is simple in structure, convenient to adjust, capable of adapting to the ensiling bags with different calibers and high in practicability. And the connecting sealing performance and the filling stability are improved, and the silage filling device is suitable for various silage filling working conditions.

The application provides a heavy gas turbine air-cooled turbine aerodynamic layout design method and system, electronic equipment and a storage medium. The method comprises the following steps: step 1: obtaining the design requirements of the heavy gas turbine air-cooled turbine, and determining the turbine stage number; step 2: determining the enthalpy drop and load distribution scheme of each turbine stage; step 3: performing preliminary evaluation on the stress of the blade and the disc, if the requirement is not met, adjusting the load coefficient and the flow coefficient, if the requirement is met, entering step 4; step 4: initial meridian flow passage design, evaluating the strength of the blade and the disc after the meridian flow passage design is completed, if the requirement is not met, repeating steps 2 to 4 to perform parameter optimization, if the requirement is met, entering step 5; step 5: determining the radial distribution law of the turbine stage reaction degree; step 6: determining the radial distribution law of the aerodynamic parameter according to the one-dimensional average parameter design result; step 7: S2 inverse problem calculation; and step 8: aerodynamic performance analysis and optimization. The scheme provided by the application shortens the turbine engineering design cycle.

The application discloses a novel connecting structure for large-span steel-bamboo buildings, and belongs to the technical field of large-span buildings. The connecting structure comprises a supporting body which is formed by mutually splicing a plurality of connecting units, long steel-bamboo poles are connected to the periphery of the supporting body, a central lifting point is arranged directly above the supporting body, and a plurality of lifting pieces are connected between the supporting body and the central lifting point. The connecting unit comprises a plurality of short steel-bamboo poles which are in equal-angle radial distribution and are connected at the ends, and the ends of the short steel-bamboo poles are fixed through connecting nodes. Two adjacent connecting units are connected through the connecting nodes or through a shared short steel-bamboo pole. The novel connecting structure for large-span steel-bamboo buildings fully utilizes the initial vertical form of natural steel bamboo, and combines the novel connecting node to form a novel building structure system, which is characterized by low cost, structural safety and building aesthetics, and can be used for large-span steel-bamboo buildings.

The present invention relates to a flow distributor for a parallelized microfluidic chip system, adapted for the individual feeding of a large number of microfluidic channels. In particular, the invention proposes a distributor comprising at least one radial flow distribution channel, said channel having a central opening leading into peripheral openings distributed circularly around an axial center of said distributor, characterized in that: - the distributor comprises a support in the form of a regular cylinder, preferably circular, in which said at least one radial distribution channel is integrated, and such that - the peripheral openings are distributed on vertical walls of said support to convey a flow into or out of said distributor along a horizontal flow plane.

A chemical mechanical polishing system includes a chuck assembly that has a chuck to hold a substrate, a motor to rotate the chuck about a first axis, and a pad carrier assembly. The pad carrier assembly includes a support that is movably along a radial direction relative to the first axis, a lateral actuator coupled the support to cause the support to move along the radial direction, a support arm extending from the support over the chuck, a pad carrier suspended from the support arm, the pad carrier configured to receive and hold a polishing pad, and a flexible membrane secured to the support arm to form a plurality of individually pressurizable chambers between the pad carrier and the support arm such that variation of a pressure difference between the chambers adjusts a radial distribution of pressure on the pad carrier.

The present application provides a method for determining the radial distribution requirements of the combustion chamber outlet temperature, which belongs to the field of aero-engine technology, including: determining the radial temperature distribution coefficient RTDF max and radial height H max range, and divide it into RTDF according to the predetermined step size max Dataset and H max A data set is generated and elements in the data set are combined; one combination is selected from multiple combinations, and the distribution form of the RTDF along the radial height H when the requirement is met under this combination is determined based on the performance and structural parameters of the main combustion chamber; the surface temperature distribution of the turbine blade is calculated based on the distribution form, and the strength coefficient of the key area under the main failure mode is calculated based on the structural parameters and operating parameters of the turbine blade; a functional formula of the comprehensive strength coefficient of the turbine blade and the strength coefficient of the key area is constructed to calculate the comprehensive strength coefficient of the turbine blade; the comprehensive strength coefficient of the turbine blade under all combinations is obtained, and the combination corresponding to the maximum value of the comprehensive strength coefficient of the turbine blade is selected as the radial distribution requirement of the combustion chamber outlet temperature.

The invention provides an aerodynamic layout design method and system for an air-cooled turbine of a heavy-duty gas turbine, electronic equipment and a storage medium, and the method comprises the following steps: 1, obtaining the design requirement of the air-cooled turbine of the heavy-duty gas turbine, and determining the stage number of the turbine; 2, determining an enthalpy drop and load distribution scheme of each turbine stage; 3, preliminarily evaluating the stress of the blade and the wheel disc, if the requirement is not met, adjusting the load coefficient and the flow coefficient, and if the requirement is met, entering the step 4; 4, primary meridian flow channel design is conducted, the strength of the blades and the strength of the wheel disc are evaluated after the meridian flow channel design is completed, if the requirements are not met, the second step to the fourth step are repeated for parameter optimization, and if the requirements are met, the fifth step is conducted; 5, determining the radial distribution rule of the reaction power of the turbine stage; step 6, determining a radial distribution rule of the aerodynamic parameters according to a one-dimensional average parameter design result; step 7, S2, inverse problem calculation; and step 8, analyzing and optimizing aerodynamic performance. According to the scheme, the design period of turbine engineering is shortened.

The utility model discloses a fan framework which comprises a main body, and the main body is provided with a center installation position used for being connected with a motor driving shaft. The mounting parts and the main body are integrally and uniformly arranged in the circumferential direction of the central mounting position at intervals, and the mounting parts approximately extend in the radial direction and are used for being connected with blades; wherein the main body and the plurality of mounting parts jointly form a first extension surface and a second extension surface which are approximately distributed along the radial direction, and the first extension surface sinks relative to the second extension surface. According to the technical scheme, the common surface of the main body of the fan framework and the mounting part integrated with the main body is divided into two extension surfaces, and one extension surface sinks relative to the other extension surface, so that the strength of the framework with the same material and the same thickness can be obviously improved at the joint of the two surfaces, damage to the framework can be reduced, and the service life of the framework is prolonged. Therefore, the purposes of reducing the fan blade cost and improving the fan efficiency are achieved while the thickness of the framework is reduced.

The present invention provides a multi-degree-of-freedom vibrating screen control method and system based on the distribution state of the sieved material. A plurality of rows of grain counting sensors are arranged below the vibrating screen to monitor the number of grains passing through the vibrating screen. The controller inputs the output signals of α, β and the grain counting sensors into the BP neural network prediction model to obtain the radial distribution coefficient V of the screen surface, substitutes V into the horizontal attitude angle fuzzy control model to obtain the horizontal attitude angle rotation amount Δβ, substitutes the amount d of the grains passing through the screen tail into the inclination angle fuzzy control model to obtain the inclination angle rotation amount Δα, and the controller controls the inclination angle and attitude angle of the vibrating screen according to the horizontal attitude angle rotation amount Δβ and the inclination angle rotation amount Δα. The present invention monitors the sieved grain flow rate in a certain area below the screen, predicts the distribution state of the material on the vibrating screen surface through a model, and proposes a quantitative description index, respectively constructs fuzzy control strategies for the horizontal attitude angle and the inclination angle of the screen surface, realizes the automatic control of the attitude of the vibrating screen surface, and improves the real-time performance and stability of the control system.

The application relates to a thread tool grinding method, device and numerical control equipment. The method comprises the following steps: determining the intersection between the chip flute edge line on the outer cylindrical surface of a blank and a thread guide line; determining the circumferential machining range of a machining track section from the intersection based on a machining range parameter; determining the axial distribution of the thread guide line along the tool axis within the circumferential machining range as the axial distribution of the machining track section along the tool axis from the intersection; decreasing the bottom surface circle radius of the blank along the circumferential deflection angle relative to the intersection based on a radial clearance angle parameter to obtain the radial distribution of the machining track section along the tool radial direction from the intersection; and determining the grinding track of a grinding wheel on the blank when grinding thread teeth based on the geometric parameters of the grinding wheel and the radial distribution and axial distribution of the machining track section. The method can ensure the grinding efficiency of the thread tool.

The present invention relates to a flow distributor for a parallelized microfluidic chip system, adapted for the individual feeding of a large number of microfluidic channels. In particular, the invention proposes a distributor comprising at least one radial flow distribution channel, said channel having a central opening leading into peripheral openings distributed circularly around an axial center of said distributor, characterized in that: - the distributor comprises a support in the form of a regular cylinder, preferably circular, in which said at least one radial distribution channel is integrated, and such that - the peripheral openings are distributed on vertical walls of said support to convey a flow into or out of said distributor along a horizontal flow plane.

The utility model relates to the technical field of semiconductor manufacturing equipment, specifically disclose a tray structure for silicon carbide epitaxial equipment, including tray base, the concentric circle arrangement of multiple wafer bearing positions is provided with in the upper end surface of circular tray base, each wafer bearing position is the recessed structure of ladder, including embedding setting bottom support ring in the upper end of circular tray base, the inclined transition surface is connected with the upper surface of tray base the outer edge of bottom support ring's upper end surface, through recessed bearing position structure of ladder, the risk of wafer thermal deformation breakage is reduced significantly, radial flow guide groove optimizes reaction gas radial distribution uniformity, and the composite structure of graphite matrix and silicon carbide coating and the processing of round corner edge are matched, effectively improve the anti -peeling ability of coating and equipment service life under high temperature working condition, finally realize the synchronous improvement of epitaxial layer thickness consistency and production yield.

The present invention relates to a flow distributor for a parallelised microfluidic chip system, which is suitable for individually supplying a large number of the microfluidic channels. In particular, the invention proposes a distributor including at least one radial flow distribution pipe, the pipe having a central opening leading into peripheral openings distributed circularly around a radius about an axial centre of the distributor, characterised in that: - the distributor includes a support in the form of a regular cylinder, preferably of circular shape, into which the at least one radial distribution pipe is integrated, and such that - the peripheral openings are distributed on vertical walls of the support in order to convey a flow at the inlet or at the outlet of the distributor according to a horizontal flow plane.

The utility model relates to a cooling structure, turbulence unit and turbine blade relates to aircraft technical field to solve the problem of turbine blade trailing edge cooling performance is poor, radial distribution uneven in the prior art. The cooling structure of the utility model, including turbulence rib and turbulence column, the periphery of turbulence rib sets at least 2 turbulence columns. The utility model can increase the contact area between turbine blade pressure side wall surface and suction side wall surface, thereby enhancing the pressure -bearing capacity of turbine blade, and promoting structural strength.

The present invention discloses a distortion generator, which includes: a plurality of positioning rods arranged radially between the inner casing and the outer casing of the engine casing along the radial direction of the engine casing; a first magnetic member sleeved on the positioning rods and movable along the length direction of the positioning rods; a distortion member, both ends of the distortion member along the length direction are respectively connected to the first magnetic members of different positioning rods, and the distortion member has elasticity along the length direction; a second magnetic member arranged on the outer casing or the inner casing, and the second magnetic member can drive the first magnetic member to move on the positioning rods in a magnetic induction manner. This distortion generator not only overcomes the defects in the prior art that the structure of the distortion grid is fixed, the compatibility of the distortion grid is poor, and the design, manufacturing and installation costs are high, but also can simulate different total pressure radial distribution laws according to the requirements of different oncoming flow conditions of the engine, which is beneficial to shortening the experimental period of the intake experiment.

The invention discloses a variable geometry turbine guider blade combined winglet structure and a design method and application thereof, the variable geometry turbine guider blade combined winglet structure comprises a blade body and a combined winglet arranged on the blade body, and the blade body is divided into a front edge section, a gap section and a tail edge section by taking the axial start-stop position of a rotating shaft local gap as a reference. The combined winglet is composed of a front side leakage control module and a rear side leakage control module which are arranged on the blade surface main control areas of the front edge section and the tail edge section correspondingly, and cooperative control is carried out on leakage sources on the front side and the rear side of the rotating shaft. Each leakage control module comprises a main section offset curve and a bridging transition curve in a two-dimensional plane, and the bridging transition curve is used for smoothly connecting the offset curve with the prototype molded line. The design method comprises the steps of blade modeling, section division, leakage analysis, configuration selection, molded line design, radial distribution and the like. The problem of leakage suppression of a local gap formed by the rotating shaft and the end wall is solved, leakage jet flow and induced vortex interference can be effectively weakened, and the method is suitable for leakage control of a wide-working-condition high-load variable geometry turbine.

The application discloses a kind of linear defect depth's ray detection calculation method, comprising the following steps: special positioning mark is made;Special positioning mark includes several with the same point as center outward radial distribution branch;Part is once penetrated, and once penetrated negative is obtained, and the object distance f and focal length F are determined;Linear defect fitting line is obtained by linear fitting to linear defect on once penetrated negative, according to the direction of linear defect fitting line, the branch of special positioning mark is selected and is parallel to linear defect fitting line, and the vertical distance L1 of the branch of special positioning mark and linear defect fitting line is measured;According to the normal direction of linear defect overall trend, part is parallelly displaced, and the parallel displacement distance W is displaced;Part after parallel displacement is twice penetrated, and twice penetrated negative is obtained, and linear defect fitting line is obtained by linear fitting to linear defect on twice penetrated negative, the branch of special positioning mark is selected and is parallel to linear defect fitting line, and the vertical distance L2 between the branch of special positioning mark and linear defect fitting line is measured;Linear defect depth is calculated according to the following public demonstration:。

The present application belongs to the field of measuring the plume divergence angle of the gasification product of a thruster, and particularly relates to a method for measuring the plume divergence angle of the gasification product of a solid propellant after ignition, comprising the following steps: obtaining a background image before ignition of the solid propellant and a gasification product inflation movement image during the ignition process; comparing the background image and the gasification product inflation movement image to obtain a gasification product image; solving the radial distribution of radiation intensity on N cross sections of the gasification product image; determining the maximum intensity value on each cross section and calculating the position of 98% maximum intensity value on each cross section; using the least square method to perform linear regression on the positions of all 98% maximum intensity values, calculating the slope of the regression straight line, and calculating the plume divergence angle of the gasification product according to the slope of the regression straight line. The plume divergence angle measurement method provided by the present application ensures measurement efficiency and high measurement accuracy.