43 results about "Orbital ring" patented technology

The invention discloses a morning orbit computing power satellite, and belongs to the field of aerospace technology and space infrastructure. The satellite comprises a satellite platform and a computing force load arranged on the satellite platform. The satellite platform is provided with a condensation type energy system and a space pump drive fluid loop system. The condensation type energy system adopts an expandable condensation type solar cell array to generate power, switches a power supply mode according to an illumination period and an earth shadow period of a morning and night orbit, and supplies power to computing force loads and platform equipment. The space pump drive fluid loop system adopts an expandable flexible radiation cooling plate for heat dissipation, heat dissipation is conducted on computing force loads through a fluid loop, and a heating assembly is arranged to prevent a working medium from being frozen under the low-temperature working condition. Through the expandable structure and the orbit environment adaptability design, continuous energy supply and effective heat management are provided for the computing power load in the morning and night orbit environment, and high-power-consumption computing power load in-orbit stable operation is supported.

The utility model relates to the technical field of phased array ultrasonic detection, in particular to a phased array ultrasonic detection pipeline scanning device which comprises a detection equipment body, a detection probe and a track ring, and the track ring is provided with a movable assembly used for carrying the detection probe for automatic detection. The movable assembly comprises a movable frame arranged on the track ring and used for driving the detection probe to move, and two pulleys and a transmission part used for driving the movable frame to move are arranged between the movable frame and the track ring. By arranging the movable assembly, the motor can be started to drive the gear to rotate on the gear ring, the movable frame does circular motion on the track ring under the cooperation of the guide groove and the pulley, and the detection probe is driven by the long bolt and the electric push rod to move and scan on a welding seam on the surface of a pipeline, so that the welding seam is detected; the long bolt is arranged, so that the position of the detection probe is adjusted under the action of the guide rod and the electric push rod in the rotating process, and the position of the detection probe is located at the optimal welding seam detection position.

The invention discloses a satellite orbit space environment disturbance coping method and device and a computer program product, and the method comprises the steps: obtaining the current position data and current space environment data of a target orbit, the current space environment data comprises a first high-energy particle integral flux at a high-energy particle flux target position and a first upper atmosphere daily average atmospheric density; according to the current position data, querying a second high-energy particle integral flux and a second upper atmosphere daily average atmospheric density at the high-energy particle flux target position when the target orbit environment is quiet; calculating the relative disturbance quantity of the high-energy particle radiation environment of the target orbit and the maximum relative disturbance quantity of the atmospheric density of the upper layer; determining the current high-energy particle radiation environment disturbance degree and the current atmospheric environment disturbance degree in combination with the disturbance degree judgment range; and generating risk coping suggestions. According to the invention, the operation environment disturbance condition of the spacecraft can be accurately known, and the in-orbit operation safety of the spacecraft is improved.

The present invention relates to the technical field of mahjong card sorting, and discloses a lifting and supporting type mahjong card sorting tray device, including an iron plate. The lifting and supporting device includes an orbital ring, an orbital groove, a moving rod, a moving block, a supporting block and a connecting device. The upper side of the iron plate is fixedly connected with the orbital ring. The axial inner side of the orbital ring is provided with an orbital groove. The axial inner side of the orbital ring is provided with a moving rod corresponding to the orbital groove. The moving rod is fixedly connected with a moving block on the axial inner side of the orbital ring. The moving block is fixedly connected with a supporting block on the axial inner side of the orbital ring. Through the cooperation among the orbital ring, the orbital groove and the supporting block, the mahjong tiles moving to the outer edge of the shuffling tray are intermittently pushed by the supporting block to complete the operation of sending the tiles upward, realizing the simplification of the structure and solving the problem of high failure rate of the tile sending operation in this lifting and supporting type mahjong card sorting tray device.

The invention provides a ground simulation test method and device based on ground irradiation source combination parameter optimization. The method comprises the steps that an in-orbit space irradiation environment is simulated, an orbit environment particle energy spectrum of a to-be-tested space orbit is obtained through calculation, and an in-orbit PKA distribution spectrum in a to-be-tested material is calculated based on the orbit environment particle energy spectrum; based on the obtained on-orbit PKA distribution spectrum, determining optimal combination parameters of one or more groups of ground irradiation sources through a specified optimization algorithm and fitting calculation, so that a PKA energy spectrum generated by the ground irradiation sources in the to-be-measured space material is matched with the on-orbit PKA distribution spectrum, and an optimal fitting energy spectrum is obtained; and calculating and determining a critical dose rate, and calculating to obtain an acceleration fluence and a maximum acceleration multiplying power for guiding a ground acceleration test so as to carry out a ground simulation test of the to-be-tested space material. According to the application, the combined parameters of the ground irradiation source are optimized, and a more accurate ground simulation test is realized.

To provide a bearing hanging tool, configured at low cost and compactly, which can stably hang a large-sized bearing, and a bearing which can be stably hung by the bearing hanging tool and whose strength can be kept.SOLUTION: A bearing hanging tool, which can hang an assembly which has conical rollers or cylindrical rollers and a raceway ring in which a raceway surface on which the conical rollers or the cylindrical rollers are arranged in parallel using a holding tool is formed between flange parts arranged at both sides in an axial direction, in a hanging posture in which the axial direction is directed toward a vertical direction, comprises a base part opposing to an upper surface of the raceway ring, a locking part that extends downward from the base part and is locked to the flange parts, an eyebolt that is fastened to a bolt hole in the vertical direction formed in the base part, and a pressing part that is pressed against the upper surface of the raceway ring, where the locking part is locked to a step part formed on the upper flange part in the axial direction.SELECTED DRAWING: Figure 2

The invention belongs to the technical field of tunnel internal structure construction, and discloses multifunctional assembling equipment for prefabricated parts in a tunnel and a construction method. A track; an annular seat; a first driving member; a rotating mechanism; the mechanical arm can rotate along with rotation of the rotating mechanism, and the position of the tail end of the mechanical arm on the plumb surface can be adjusted through movement of the mechanical arm; a grabbing mechanism; and a transport vehicle. The prefabricated part is transported to the position below the frame vehicle through the transport vehicle, the grabbing mechanism is used for grabbing the prefabricated part, then the grabbing mechanism is driven to move to the to-be-assembled position through matched movement of the first driving part, the rotating mechanism and the mechanical arm, and the prefabricated part grabbed by the grabbing mechanism is further assembled at the to-be-assembled position; compared with traditional hoisting, the positions and the assembling postures of the prefabricated parts are adjusted through cooperation of multiple kinds of mechanical movement, the construction efficiency is improved, and the safety risk is reduced.

The invention relates to a pathfinder test satellite suitable for a deep space exploration flight mission, and the satellite orbit of the pathfinder test satellite is a non-near earth orbit which avoids the influence of a normal Airy radiation band, and is a low orbit inclination angle which is free from the influence of strong space radiation. The method has the beneficial effects that the satellite orbit is not influenced by the Nabelian radiation band and is consistent with the actual deep space orbit environment.

The invention relates to the technical field of track supporting set manufacturing, in particular to a track guiding assembly and a manufacturing device.A first conveying pipe and a second conveying pipe are oppositely arranged on the upper side of a device body in the left-right direction, the first conveying pipe is provided with a track ring, the track ring is rotationally connected with an outer gear ring, and a first servo motor is installed on the device body; an output shaft of the first servo motor is provided with a gear meshed with the outer gear ring; first telescopic rods are arranged on the right side of the outer gear ring, mounting blocks are arranged at the right ends of the two first telescopic rods, blocking pieces are arranged on the right sides of the two mounting blocks, and clamping blocks which move relatively are arranged on the opposite sides of the two mounting blocks and located on the left sides of the blocking pieces; a welding assembly is arranged on the upper side of the device body and between the first conveying pipe and the second conveying pipe in an up-down moving mode. The problems that in the prior art, in the welding process of the rail support assembly, manual welding is mostly relied on, the manual welding is prone to being influenced by human factors, and the welding quality is uneven are solved.

A friction transmission device 100 according to an embodiment of the present invention includes: a planetary rolling element 20 disposed about a rotation axis La; a first support raceway ring 26 and a second support raceway ring 28 in contact with the planetary rolling element 20; and a pressing force application mechanism 7 for pressing the second support raceway ring 28 to generate a pressing force on a contact surface between the second support raceway ring 28 and the planetary rolling element 20. The friction transmission device 100 has a cover 67 for covering this friction transmission device 100 from the axial direction. The pressing force application mechanism 7 has a pressing part 72 for pressing the second support raceway ring 28. The pressing force application mechanism 7 has an abutment part 56b in abutment against the cover 67 at a position overlapping the pressing part 72 in the axial direction or is formed integrally with the cover 67.

The application discloses a satellite orbit space environment disturbance coping method, equipment and computer program product. The method comprises the following steps: acquiring current position data and current space environment data of a target orbit, wherein the current space environment data comprises a first high-energy particle integrated flux at a target position of a high-energy particle flux and a first high-altitude atmospheric daily average atmospheric density; querying a second high-energy particle integrated flux at the target position of the high-energy particle flux and a second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm according to the current position data; calculating a high-energy particle radiation environment relative disturbance amount and a high-altitude atmospheric density maximum relative disturbance amount of the target orbit; determining a current high-energy particle radiation environment disturbance degree and a current atmospheric environment disturbance degree in combination with a disturbance degree discrimination range; and generating a risk coping suggestion. The application can accurately understand the disturbance situation of a spacecraft operating environment and improve the safety of the spacecraft in-orbit operation.

To provide a bearing hanging tool, configured at low cost and compactly, which can stably hang a large-sized bearing, and a bearing which can be stably hung by the bearing hanging tool and whose strength can be kept.SOLUTION: A bearing hanging tool, which can hang an assembly which has conical rollers or cylindrical rollers and a raceway ring in which a raceway surface on which the conical rollers or the cylindrical rollers are arranged in parallel using a holding tool is formed between flange parts arranged at both sides in an axial direction, in a hanging posture in which the axial direction is directed toward a vertical direction, comprises a base part opposing to an upper surface of the raceway ring, a locking part that extends downward from the base part and is locked to the flange parts, an eyebolt that is fastened to a bolt hole in the vertical direction formed in the base part, a recessed part for positioning recessed on the upper surface of the raceway ring, and a pressing part provided between the eyebolt and the upper surface of the raceway ring, where the pressing part fits to the recessed part.SELECTED DRAWING: Figure 2

This invention discloses an inlaid, patch-type, dual-track screening machine and a dedicated cylinder, comprising a frame, a power control box, an air source control box, a cylinder, a chassis, a rotating track ring, a pressure ring, a main motor, a main reducer, an auxiliary motor, an auxiliary reducer, an inclined base, air pipes, and a compressed air source. The cylinder is characterized by being composed of an upper ring and a lower ring. The lower ring has an annular outer track groove, a flat-blowing pipe mounting hole, a guide groove, and a conveyor track mounting groove. The inner wall of the lower ring has a flat-blowing hole adapted to the flat-blowing pipe mounting hole. The guide groove is connected to the first end of the outer track groove. The end of the outer track groove is connected to the track groove of the conveyor track fixed on the conveyor track mounting groove. A guide plate is provided on the inner side wall of the upper ring, with the inner end of the baffle at the bottom of the guide plate inserted into the inner track groove. A cover plate is provided on the top of the outer track groove. This invention features two annular track grooves, ensuring smooth operation and normal production of high-speed production lines.

The present invention provides a method for real-time calculating the radiation effect of a satellite in its on-orbit operating environment, belonging to the technical field of satellite space environment analysis. The method includes: S1. Import an orbit environment file into an environment solver to obtain corresponding parameters; S2. Select a time period N, a particle type, and a vehicle in the orbit environment file, set a minimum cumulative radiation simulation calculation time k, integrate the particle flux within the k time to generate an energy spectrum file, and the number of energy spectrum files is the ratio of N to k; S3. Set analysis parameters and the number of running particles, select a target structure, generate a corresponding script file according to the energy spectrum file, and input the script file into the solver for sequential solution; S4. Perform summation and normalization processing on the solution results to generate a final result. The present invention can real-time simulate and calculate the radiation damage degree of a spacecraft caused by different types of radiation particles during any period of operation in different orbit environments, and supports simultaneous calculation by multiple solvers, greatly improving the calculation efficiency.

A friction transmission device 100 comprises: an input raceway ring 14; a planetary rolling element 20 that is disposed around a rotation axis La of the input raceway ring 14 and comes into contact with the input raceway ring 14; an output raceway ring 30 that comes into contact with the planetary rolling element 20 and is connected to an output member 32; and a first support raceway ring 26 and a second support raceway ring 28 that come into contact with the planetary rolling element 20. The friction transmission device includes a speed ratio changing mechanism 6 that changes the speed ratio by changing the relative positions of two outer raceway rings. The gear ratio changed by the speed ratio changing mechanism 6 is configured such that the maximum amount of an absolute value of the gear ratio on the positive side and the maximum amount of an absolute value of the gear ratio on the negative side are different from each other, and shapes of a first contact surface 20d and a second contact surface 20c that come into contact with the two outer raceway rings of the planetary rolling element 20 are different from each other.

This invention discloses a precision bearing grinding device, relating to the technical field of bearing grinding equipment. It includes a feeding assembly for carrying bearing blanks; and a positioning and stamping assembly, comprising a positioning part and a stamping part. The upper surface of the positioning part is at the same horizontal plane as the bearing surface of the feeding assembly, while the stamping part is fixed to a stamping worktable directly above the positioning part, forming a vertical suspension relationship with the positioning part. This invention employs a dynamic mating and positioning mechanism consisting of an electric bidirectional telescopic actuator, a limiting track ring, and a track arm. This mechanism allows for flexible adaptive adjustment based on the inner ring size and tolerance deviations of different bearing blank models. Compared to traditional rigid positioning structures, it allows the limiting track ring to perform slow calibration and bidirectional fine-tuning before contacting the inner ring. During mating, the track arm guides the downward pressing path, effectively compensating for positioning offset problems caused by manufacturing errors and assembly posture deviations in the bearing blank.

A cycloid speed reducer is disclosed. The accommodation space required for the sealing component is integrated into the track ring to save the material costs and significantly reduce the overall volume. Moreover, a spacer ring is placed between the front bearing and the rear bearing, and the thickness of the spacer ring can be used to adjust the clearances of the front bearing and the rear bearing to facilitate the quantitative production and control the yield. On the other hand, the initial shape of the output plate is adjusted through mass production molding, and the thickness next to the protruding structures of the output plate is increased, so that the supporting plane can be milled through a lower-cost lathe processing, and the accuracy of bearing plane can meet the requirements. There is no need to perform full-circle milling on the output plate, and the processing hours are reduced significantly.

The invention relates to the technical field of aerial tracks, in particular to a track transfer device of an inspection robot, which comprises a first track and a plurality of second tracks and further comprises an annular track transfer seat, the first track and the plurality of second tracks are annularly distributed on the periphery of the outer side of the annular track transfer seat, and a track transfer assembly is movably arranged in the annular track transfer seat. The track transfer assembly comprises a connecting track, a driving assembly is arranged on the annular track transfer seat, and the track transfer assembly is driven by the driving assembly to rotate by a set angle, so that the track transfer assembly is in butt joint with the first track or the multiple second tracks, and track transfer operation is achieved; through the arrangement of the rail transfer assembly, rapid butt joint passing of the crossed rails can be achieved, and path switching can be achieved without depending on a large-curvature bent rail.

The present invention provides a constant temperature control device for a relative gravimeter, which relates to the technical field of relative gravimeters and includes a gravimeter housing, a U-shaped positioning frame welded to the outer periphery of the rotating ring, a bevel gear rotatably mounted in the middle portion of the U-shaped positioning frame, a threaded positioning shaft threadedly mounted on the bevel gear, the tail end portion of the threaded positioning shaft passes through the peripheral wall of the rotating ring and is in contact with the track ring; a U-shaped limiting frame is welded to the head end of the threaded positioning shaft, and the two long side rods of the U-shaped limiting frame are slidably engaged with the long side rods of the U-shaped positioning frame. Through the meshing transmission of the bevel rack and the bevel gear and in conjunction with the spring pushing effect on the arc-shaped sliding shaft, the tightening operation of the rotating ring on the four steel wire ropes and the positioning operation of the rotating ring by the threaded positioning shaft can be driven and executed at one time by the simple operation of sliding the L-shaped driving rod, which helps to improve the tightening and positioning efficiency of the circulation fan.

This invention provides a positioning device and method for a surveying instrument used in engineering surveying, relating to the field of surveying instrument technology. In this invention, a first frame and a second frame are rotatably connected by a shaft. An extension frame is slidably connected to the outer surface of the second frame to extend its length. Fasteners are provided between the second frame and the extension frame for fixation. A target positioning component and an inclination sensor are provided on the first frame. The target positioning component also has a protective component to protect the positioning element. In this invention, the protective component, through the cooperation of a track ring, gear transmission, and baffle structure, can be unfolded and folded by rotating a handle. When unfolded, it forms a complete circular protective surface that wraps around the positioning prism, effectively preventing damage to the positioning prism from collisions, dust corrosion, etc., during transportation or when not in use. When folded, it does not affect the signal reception of the positioning prism, thus balancing protection and practicality.

The utility model belongs to the field of driving assemblies, and particularly relates to an adjustable driving assembly which comprises a main frame, the inner wall of the main frame is fixedly connected with a supporting shaft, the outer wall of the supporting shaft is rotatably connected with a rotating frame, the main frame is provided with an adjusting assembly, the rotating frame is provided with a driving assembly, and the adjusting assembly is connected with the driving assembly. The adjusting assembly comprises a first hinge rod, the inner wall of the main frame is fixedly connected with the first hinge rod, and the outer wall of the first hinge rod is hinged to a hinge base. According to the adjustable driving assembly, through a linkage structure of the cylinder base, the hinge block and the hinge rod, linear stretching of the electric cylinder base drives the rotating frame to rotate around the supporting shaft, the driving wheel is driven to move up and down, and the adjustable driving assembly is rapidly adaptive to sliding rails with different thicknesses and angles. According to the flexible adjusting mode, the tedious operation that a traditional driving device needs to manually replace accessories or reinstall the accessories is avoided, the applicability of the device in diversified track environments is remarkably improved, and the debugging cost and time are effectively reduced.

A kind of multi-group independent lifting rotating show device, it is related to performance stage prop technical field, including fixed truss, rotating truss, a certain number of rotating components and a certain number of lifting components, fixed truss is fixed in the top of show stage, a certain number of first support is arranged in the bottom of fixed truss, first support bottom is provided with hanging wheel, rotating truss top is provided with annular hanging track and annular friction track, annular hanging track is hung on hanging wheel, rotating component includes rotating drive motor and rotating friction wheel, rotating friction wheel and the side of annular friction track are in abutment, lifting component includes lifting winch group fixed on rotating truss, steering pulley, hanging point pulley, traction rope is sequentially through steering pulley and hanging point pulley, then vertically downward passes through rotating truss.The utility model can be used for the rotating movement and lifting movement when multiple actors perform in the air, realize the multidimensional position change of multiple actors in the air performance.

This invention discloses a device and method for detecting the water vapor composition and wind field occultation of planetary atmospheres, belonging to the field of planetary atmospheric detection technology. It includes a sealed mounting housing, a modular control unit, and an all-fiber optic unit. The device adopts a layered sealed structure of "upper-layer optics + lower-layer control." The optical unit receives sunlight passing through the planetary atmosphere via a solar telescope, mixes it with one laser beam split by a laser to generate a water vapor absorption spectrum, and extracts the peak wavelength λ'. Another laser beam passes through a built-in calibration gas cylinder to generate a standard absorption spectrum, and extracts the peak wavelength λ. Based on the Doppler frequency shift principle, the line-of-sight wind speed is inverted using the wavelength drift. This invention features strong adaptability to orbital environments, high integration, and high measurement accuracy. It can achieve synchronous in-situ detection of water vapor composition and wind speed in planetary atmospheric orbits, meeting the requirements of lightweight, radiation-resistant, and long-life interplanetary orbit detection, and is suitable for on-orbit occultation detection scenarios in planetary atmospheric orbits.

A friction transmission device 100 includes: an input raceway ring 14; a planetary rolling element 20 disposed about a rotation axis La of the input raceway ring 14 and in contact with the input raceway ring 14; an output raceway ring 30 in contact with the planetary rolling element 20 and connected to an output member 32; and a support raceway ring 28 in contact with the planetary rolling element 20. The friction transmission device 100 includes: a casing 37 surrounding the planetary rolling element 20 and the output raceway ring 30; a thrust bearing 33 supporting the output raceway ring 30 on a side opposite from the planetary rolling element 20; and a support member 31 independent of the casing 37. The support member 31 is in abutment against the thrust bearing 33.

This invention discloses a lunar orbit space solar power station system, belonging to the field of spacecraft structure and energy system technology. Addressing the problems of traditional solar power generation failure in the lunar polar shadow regions and the inability of existing space power station structures to adapt to the lunar orbit environment, a novel system is proposed, comprising: a double-layered box-type central truss made of carbon fiber composite material; 12 thin-film solar subarrays, achieving independent solar tracking via a first conductive rotary joint; 5 laser transmitting antenna subarrays, achieving precise pointing via a second conductive rotary joint; and a rotary connection module. The system adopts a tree-like topological multibody structure, allowing independent attitude adjustment of the solar energy collection and laser transmitting modules, achieving decoupling between solar tracking and laser pointing. This invention offers advantages such as modular on-orbit assembly, lightweight and high rigidity, and flexible vibration suppression, providing continuous wireless energy transmission to the lunar polar regions.

The utility model provides an annular track centripetal force analysis experiment device comprising a track assembly which comprises a release track, an annular track and a recovery track; a small ball runs on the track assembly; the releasing mechanism comprises a sliding base, an electromagnetic assembly and a guide rod unit arranged on a releasing track, the electromagnetic assembly is arranged on the sliding base, and in the initial state, the electromagnetic assembly generates magnetic force to adsorb and fix the small ball; a driving screw rod is arranged on the guide rod unit, a driving plate arranged below the sliding base is nested on the driving screw rod, and a supporting bolt arranged on the driving screw rod is screwed in to adjust the height of the sliding base. According to the utility model, the supporting bolt is screwed on the driving screw, so that the tedious disassembly and assembly process in the height adjustment process is simplified, the preparation and disassembly and assembly work before and after an experiment is reduced, the experiment time is shortened, and the experiment progress is accelerated.

The present invention provides a method and device for collaborative quantitative characterization and simulation of the multi-orbital environment of the Earth's radiation belt, which relates to the field of spacecraft simulation technology. The method for collaborative quantitative characterization and simulation of the multi-orbital environment of the Earth's radiation belt described in the present invention includes: initializing parameters, wherein the parameters include the mission start time, the mission end time, the simulation step length, the orbital parameters of the navigation satellite constellation, and the radiation belt model control parameters; from the mission start time to the mission end time, successively accumulating the simulation step lengths to obtain each simulation moment, traversing each navigation satellite in turn at each simulation moment, and updating the on-orbit motion state data of the navigation satellite; determining the corresponding radiation environment quantitative characterization data according to the spatial position data of the navigation satellite at each simulation moment and the radiation belt model control parameters. The present invention can quantitatively characterize the space radiation environment in which the navigation satellite is located.

The utility model discloses a detachable winding gear which comprises a detachable gear baffle, a first gear positioning ring and a second gear positioning ring. Wherein the first gear positioning ring and the second gear positioning ring are fixedly connected to form a track ring groove, the gear baffle is arranged on the track ring groove in a sleeving mode, and accurate positioning and smooth operation are achieved. Furthermore, the first gear positioning ring comprises a fixed part and a movable part, and the fixed part and the movable part are detachably connected. Through the interaction and rotation mechanism between the gear baffle and the first gear positioning ring, high-adaptability disassembly and assembly of the winding gear are achieved. According to the utility model, not only is the complex winding process simplified, but also the overturning operation is obviously reduced, so that the risk that the coil is possibly damaged due to overturning is effectively avoided, and the safety and the efficiency of production operation are greatly improved.