32 results about "Angular momentum" patented technology

Aspects of the present disclosure relate to a formula-based inter-circle precoding weight determination for an orbital angular momentum (OAM) communication system. Some aspects of the present disclosure relate to an apparatus and method for wireless communication, the apparatus including a processor, an antenna element including a first subset and a second subset of the antenna elements, and a memory coupled to the processor, the memory storing instructions that, when executed by the processor, cause the processor to transmit a first reference signal using a first OAM mode via the first subset of the antenna elements, transmit a second reference signal using the first OAM mode via the second subset of the antenna elements, and receive information indicating a subset of antenna elements of the plurality of antenna elements to use to transmit the first OAM mode. Other aspects, embodiments, and features are also claimed and described.

A satellite control system fault detection method based on cooperative monitoring of energy and angular momentum comprises the following steps: firstly, setting a detection statistical period value, calculating a satellite average energy value, a theoretical angular momentum change value and a measurement angular momentum change value of each statistical period, then comparing the satellite average energy value, the theoretical angular momentum change value and the measurement angular momentum change value with a satellite average energy value of a previous statistical period, and scoring; comparing and grading the consistency of the theoretical angular momentum change value and the measured angular momentum change value, comprehensively judging the grading value, giving a satellite attitude control abnormity mark, and when the satellite attitude control abnormity is confirmed, performing subsequent processing to enable the satellite to autonomously switch into an attitude control safety capture mode.

A method for controlling a set of gyroscopic actuators of a satellite, distributed into two coplanar subsets, is described, the method comprising: Receiving a setpoint angular momentum, Determining an angular momentum to be provided by each coplanar subset (, ), from a distribution parameter, between the two subsets, of a component of the setpoint angular momentum along an axis () common to the two planes, r being a scalar comprising the lowest admissible value and the highest admissible value of the contribution of one of the coplanar subsets to the component of the setpoint angular momentum along the axis common to the two planes, determining a tilt angle value of each gyroscopic actuator of a subset, from the angular momentum to be provided by said subset, and Issuing a command to each gyroscopic actuator comprising the respective tilt angle value determined.Figure from the summary: Figure 2.

The embodiment of the application discloses a kind of OAM mode determination method and device thereof, the method includes: sending the measurement reference signal corresponding to candidate OAM mode to receiving equipment;At least one measurement result of the measurement reference signal sent by receiving equipment is received;Target OAM mode is determined from candidate OAM mode based on measurement result, and it is indicated to receiving equipment.The embodiment of the application provides a kind of OAM mode determination method, by sending the measurement reference signal corresponding to candidate OAM mode, can make receiving equipment to measurement reference signal measurement, obtain measurement result, and then based on measurement result, the interference degree that signal on candidate OAM mode is judged, determines the most suitable target OAM mode, to reduce the interference between mode, improve system capacity.

This application relates to a satellite orbit prediction method. The method includes: constructing an expression for the gravitational force acting on the satellite based on its mass and distance from Earth; constructing a differential equation for the satellite's acceleration based on Newton's second law and the expression for the gravitational force; solving the differential equation based on the conservative force field characteristics of mechanics, calculating the gravitational potential energy function and its derivative with respect to time; transforming the derivative expression based on the mechanical conservation law that the sum of the derivatives of kinetic energy and gravitational potential energy with respect to time is zero, to obtain the derivative expression for acceleration; converting the time relationship in the derivative expression of acceleration to a radial position relationship based on the principle of conservation of angular momentum; integrating the radial position relationship to obtain the satellite's orbit equation. This method enables satellite orbit prediction.

The application discloses a LS+CNN combined UT1-UTC prediction method considering effective angular momentum, relates to the field of geophysics and related computer science technology, and comprises the following steps: acquiring a UT1-UTC basic data set and an effective angular momentum data set, constructing an LS model and a CNN model, combining an LS fitting extrapolation result with an output result of the CNN model, and obtaining a high-precision UT1-UTC prediction value. The model has high precision and reliability in long-term UT1-UTC prediction, can overcome the shortcomings of a traditional linear model in UT1-UTC parameter prediction, and improves the prediction precision and stability of UT1-UTC compared with the traditional method. The method realizes high-precision long-term UT1-UTC prediction, and provides a new UT1-UTC parameter prediction method for the fields of navigation satellite orbit determination, astronomical observation and geophysical research.

The embodiment of the present disclosure relates to a single-frame control moment gyro group on-orbit singularity analysis method. The method comprises the following steps: obtaining an angular momentum vector of an SGCMG based on each frame angle of the SGCMG, and establishing an angular momentum output equation of the SGCMG group; obtaining an output torque equation of the SGCMG group and a torque matrix of the SGCMG group according to the angular momentum output equation; obtaining a singular standard of the SGCMG by using the torque matrix and a singular frame angle of a singular state, and judging whether the frame angle is a singular point; if the frame angle is the singular point, judging the type and the singular direction of the singular point; drawing according to the singular direction and the angular momentum output equation; constructing a PID control model of the SGCMG, and simulating and analyzing a singular influence mechanism of the SGCMG group. According to the embodiment of the present disclosure, the visual drawing and the mechanism simulation running can directly show the singular point space distribution and changes of the SGCMG after the abnormality, and the spacecraft attitude maneuvering performance changes of the SGCMG group under external force interference can be accurately obtained.

The application discloses a kind of unloading method and device of asymmetric configuration satellite angular momentum, the method includes: by solar sensor, the solar vector under satellite body system is acquired, and the solar vector is converted into the solar vector under orbit system;The included angle β of the solar vector under the orbit system and orbit plane is calculated, and the rotation angle of solar wing rotation axis and the preset angle of biasing axis are set according to the included angle β of the solar vector under the orbit system and orbit plane;The angular momentum of flywheel system is calculated and is converted into the angular momentum under satellite body system;According to the modulus of satellite to be unloaded angular momentum and preset unloading threshold value are compared, according to the comparison result, it is judged whether magnetic moment device unloading needs to be started, and according to the comparison result, the control instruction of magnetic moment device is output.The application effectively reduces angular momentum accumulation and space moment accumulation;With the advantages of saving fuel, low power consumption requirement and high attitude stability, it provides a theoretical basis for angular momentum unloading of weak magnetic field planet explorer.

The application discloses a kind of two-way spin angular momentum and momentum direction controllable single photon emitter and method thereof.The application independently controls the spin angular momentum of emitting photon by the internal structure of each nano scattering unit, and is irrelevant to the phase of scattered light;The momentum direction of emitting photon is controlled by the position of each nano scattering unit, and is related to the phase of scattered light, two kinds of control do not affect each other, and the control of the spin angular momentum and momentum direction of emitting photon can be independently designed;Two sets of super surface structures corresponding to two emitting photons are combined to form a two-way single photon emitter, and single photon emission is realized, and the spin angular momentum and momentum direction of each emitting photon can be independently controlled by the corresponding super surface structure;The maximum emission angle can reach 53°, and the phase-independent scheme makes the spin angular momentum insensitive to the accurate position of single photon source relative to the super surface, so high-precision single photon source positioning and alignment technology is no longer needed.

The invention discloses a plasma state active control platform and method based on an orbital angular momentum electromagnetic field, and belongs to the technical field of plasma control. The platform comprises an orbital angular momentum electromagnetic field generation module, an energy and mode coupling module, a plasma region, a plasma state sensing module and a feedback control module. All the modules jointly form a closed-loop control structure, and through angular momentum exchange between an orbital angular momentum electromagnetic field and plasmas, active regulation and control over the macroscopic state, spatial distribution or statistical characteristics of the plasmas are achieved. The method does not depend on a specific device structure, a working frequency band or an implementation mode, has the advantages of being high in response speed, high in control dimension, high in adaptability and the like, and is suitable for a magnetic confinement nuclear fusion device, industrial plasma processing equipment and other plasma systems.

The application relates to the technical field of building walls, and particularly discloses a shock insulation viscous damping wall, which comprises a wall body; the wall body comprises an upper wall body and a lower wall body; a movable wall body is connected with the upper wall body; clamps are embedded on the two sides of the movable wall body; a supporting plate is arranged in the movable wall body; the supporting plate is in sliding connection with the clamps; an adjusting assembly is arranged between the supporting plate and the clamps; a limiting wall body is connected with the lower wall body; a base is arranged in the limiting wall body; and a centripetal assembly is arranged in the base. The inner side surface of the movable wall body is arranged as a wedge surface; the adjusting assembly can be relatively moved horizontally to extrude the wall surface of the movable wall body, so that the pressure between the movable wall body and the limiting wall body is changed, and the viscous force is changed; on the basis, the centripetal assembly capable of generating angular momentum is arranged in the limiting wall body, so that the stability of the limiting wall body can be further improved.

The application discloses a kind of orbital angular momentum entanglement measurement method, system and equipment, it is related to quantum state chromatography technical field.High-dimensional orbital angular momentum entangled state is acquired;The high-dimensional orbital angular momentum entangled state includes: signal photon and idler photon;Signal photon and idler photon one-to-one correspondence;Signal photon is projected on first superposition state and second superposition state in turn, simultaneously, with the idler photon corresponding to signal photon collapse, and get collapse state;According to the collapse state, two spatial mode images are obtained by ICCD camera;Two spatial mode images are input into quantum state chromatography model respectively for calculation, and the representation result of orbital angular momentum entanglement is obtained.The application improves the efficiency of orbital angular momentum entanglement measurement.

The application discloses an orbital angular momentum beam detection method based on quantum weak measurement technology, and the method comprises the following steps: setting a suitable polarization state preparer and a polarization state selector, preparing a virtual weak value, and using a differential distribution of the orbital angular momentum beam obtained by quantum weak measurement differential effect to realize detection of the orbital angular momentum beam and measurement of angular momentum quantum number. The application realizes measurement of the orbital angular momentum beam in a natural state by using optical differential based on quantum weak measurement technology, and reduces energy consumption to a certain extent, thereby providing a simple and low-energy consumption orbital angular momentum detection method for engineering and laboratory related fields, and having important application value in multiple technical fields such as optical communication, transmission and manipulation.

The application discloses a flywheel unloading method and device based on PID control and a storage medium. The method comprises the following steps: determining an angular momentum deviation between an angular momentum of a flywheel arranged on a satellite and a reference angular momentum; determining a PID control item for angular momentum unloading of the flywheel according to the angular momentum deviation; determining a control torque corresponding to the angular momentum deviation in a PID control mode based on the PID control item; determining an unloading magnetic moment for angular momentum unloading of the flywheel according to the control torque; determining weight information between a plurality of magnetic moment devices according to an included angle between a magnetic moment magnetic moment of the plurality of magnetic moment devices and the unloading magnetic moment, wherein the weight information is used for indicating a magnetic moment distribution ratio between the magnetic moment devices; determining the magnetic moment magnetic moment of the plurality of magnetic moment devices according to the unloading magnetic moment and the magnetic moment distribution ratio; and performing angular momentum unloading on the flywheel by the plurality of magnetic moment devices according to the determined magnetic moment magnetic moment.

The invention relates to the technical field of vacuum, and discloses a molecular pump and a dynamic balance debugging method.The molecular pump comprises a shell, a rotor, a first driving structure, a rotating body, a second driving structure and a balance weight structure. And the rotation directions of the second driving structure and the first driving structure are opposite. On the basis, the rotating directions of the rotating body and the rotor are opposite, the angular momentum of the rotating body and the angular momentum of the molecular pump are opposite in direction, and the angular momentum value of the rotating body can correspond to the angular momentum value of the molecular pump, so that the angular momentum of the rotating body and the angular momentum of the molecular pump can be partially counteracted; the total angular momentum of the molecular pump reaches the required range, meanwhile, the balance weight structure is matched, the stability of the rotor in the rotating process is improved, influences on a bearing in the molecular pump and a downstream structure of the molecular pump in the related technology are avoided, and therefore the technical effect of improving the use reliability of the molecular pump is achieved.

The device includes a body and a first torque generator, like an electromagnetic coil or a motor with a flywheel. The first torque generator is attached to the body. The first torque generator applies an angular movement to the body around an axis of rotation of the body. The angular movement takes place either in a first direction with a first angular acceleration value or in a second direction with a second angular acceleration value to thereby transform the angular movement into a translational movement. Applying the angular movement in the first direction and in the second direction repeatedly and in a consecutive manner applies a movement force onto the object.

The present application relates to the technical field of satellite attitude control, and particularly relates to a maximum angular momentum determination method of a wheel system with non-zero initial angular momentum. The maximum angular momentum envelope surface of the momentum wheel combination can be obtained through analytical calculation, which can effectively improve the angular momentum output capacity of the momentum wheel combination, thereby improving the rapid maneuvering capability of the whole satellite and the momentum wheel anti-saturation capability, and there is no numerical iterative search process, compared with the search method, the calculation efficiency is high, the storage amount is small, and the on-board calculation is easy to realize; in addition, the obtained maximum angular momentum envelope surface has a clear boundary, and the momentum wheel output angular momentum with the maximum envelope characteristic can be accurately obtained according to the envelope surface, compared with the pseudo-inverse method, the angular momentum output capacity of the wheel system can be more fully utilized.

The application belongs to the technical field of communication, and specifically relates to an antenna for generating multiple mode orbital angular momentum waves. The antenna is composed of three spiral phase plates; the first spiral phase plate is circular and solid, and is located at the center; the second spiral phase plate is annular, and is located at the periphery of the first spiral phase plate; the third spiral phase plate is annular, and is located at the periphery of the second spiral phase plate; the three spiral phase plates are coaxial; the three spiral phase plates are respectively composed of eight gradient surfaces with synchronous increment, each gradient surface has the same area, and adjacent gradient surfaces are sequentially increased by the same height; the three spiral phase plates are separated by metal rings. The super material surface can simultaneously convert the linear polarization mode incident plane wave into three mode orbital angular momentum waves, and different mode orbital angular momentum waves can be formed by changing the height of the spiral phase plate, and the application has the advantages of multi-mode multiplexing, flexible design, simple structure, low cost and the like.

The invention provides a teaching gyroscope for demonstrating the law of conservation of angular momentum and a display device thereof, and relates to the field of teaching gyroscopes, the teaching gyroscope comprises a device main platform, a plurality of supporting legs are fixedly arranged at the bottom of the device main platform, the supporting legs play a supporting role, the positions of the supporting legs form a group, and the supporting legs are distributed in an annular array; the top of the device main platform is provided with a gyroscope containing cavity with an outward opening, the interior of the gyroscope containing cavity is of a radian, a mounting support is fixedly arranged on the side face of the device main platform, and an L-shaped support is fixedly arranged at the top end of the mounting support. Through the synergistic effect of the air flotation limiting groove in the bottom of the gyroscope containing cavity and the annular airflow nozzle, a uniform air flotation layer is formed, the friction resistance during rotation of the demonstration gyroscope is remarkably reduced, an ideal experiment environment is provided for the condition that the resultant external torque required by the law of conservation of angular momentum is approximate to zero, and the scientific accuracy of demonstration results is ensured.

The invention discloses a device for generating an orbital angular momentum-adjustable broadband terahertz vortex beam, and the device comprises a vacuum target chamber which is used for providing a vacuum environment for the interaction of laser and a substance; the laser system is used for providing driving light pulses; the gas target generation device is arranged in the vacuum target chamber, provides a plasma channel along the propagation direction of the driving light pulse, guides the driving light pulse to be transmitted in the plasma channel and generates a broadband terahertz vortex light beam; the light path adjusting element is used for adjusting the position and angle of the driving light pulse when the driving light pulse enters the plasma channel, so that the driving light pulse is transmitted in the plasma channel along a spiral linear track after entering the plasma channel, and then the transverse net current is driven on each section of the plasma channel; and broadband terahertz radiation is generated at different positions of a spiral linear track in the plasma channel, so that a broadband terahertz vortex beam with adjustable orbital angular momentum is formed. The device obtains the broadband terahertz vortex beam with the adjustable orbital angular momentum.

This invention discloses a method for preparing the compressed internal state of large-spin atoms based on reinforcement learning and its application in magnetic field measurement. The method includes: constructing environmental observations, an evolutionary action set, and a reward function based on the quantum state and total angular momentum operator of the large-spin atom; an actor network selecting an action from the evolutionary action set based on the environmental observations of the large-spin atom system at the current time step, executing the action, calculating the reward value at the current time step, and updating the environmental observations for the next time step; a critic network obtaining a state value estimate based on the environmental observations experienced by the actor network at each time step, calculating the advantage function by combining it with the expected cumulative reward at the current time step, and training both the actor network and the critic network; inputting the environmental observations constructed from the quantum state and total angular momentum operator of the large-spin atom into the trained actor network to generate an optimal control pulse sequence for preparing and maintaining the compressed state of the large-spin atom.

The invention discloses an operation state monitoring method and system for a vertical-horizontal dual-purpose five-axis turntable, and belongs to the technical field of industrial control systems, and the method comprises the following steps: S1, carrying out the analysis to obtain a swing frame angular velocity prediction value used for representing that a swing frame is overturned to a final position; s2, obtaining a residual kinetic energy prediction value and a residual swing amplitude prediction value, and analyzing in combination with a swing frame angular velocity prediction value to obtain a dynamic convergence criterion; s3, if the dynamic convergence criterion is convergence closure, maintaining the current state, otherwise, performing servo motor operation correction processing to obtain an initial dynamic convergence criterion; and S4, if the initial dynamic convergence criterion is convergence closing, servo motor operation correction processing is completed, vertical-horizontal mode switching continues to be executed, otherwise, hydraulic correction processing is executed until vertical-horizontal switching processing is completed, and the problems that in the prior art, due to the fact that a swing frame carries non-zero angular momentum, residual swing cannot be completely attenuated, and the stability of the swing frame is poor are solved. And therefore, the five-axis linkage machining precision and the surface quality are influenced.

The application discloses a device for measuring orbital angular momentum of vortex particles based on a gradient magnetic field, which is integrated in a beamline system of a particle accelerator or an electron microscope and used for measuring the orbital angular momentum of a vortex particle beam in real time. The device comprises a vortex particle source, a gradient magnetic field device, a detection system and a processing system. The vortex particle source is used for providing a vortex particle beam. The gradient magnetic field device is used for exerting a transverse deflection force related to the orbital angular momentum on the vortex particle beam. The detection system is used for receiving the particle beam after a certain longitudinal movement and obtaining an intensity distribution image of the particle beam. The processing system is used for calculating the orbital angular momentum of the vortex particle beam according to the intensity distribution image and magnetic field gradient parameters. The device for measuring the orbital angular momentum of vortex particles based on the gradient magnetic field has the characteristics of simple structure, fast response and integration in the beamline system, and is suitable for various equipment environments such as particle accelerators, electron microscopes and the like.

The application discloses a method for calculating the collision force of a large modulus friction plate inner hub core plate, and specifically comprises the following steps: S1: physical parameters of a to-be-tested friction plate core plate and an experimental friction plate core plate are respectively acquired, whether the two are geometrically similar, kinetically similar and dynamically similar is judged, if yes, S2 is entered, and if not, the method is ended; S2: an angular momentum model of the to-be-tested friction plate core plate and the experimental friction plate core plate is established, and the angular velocity ratio of the to-be-tested friction plate core plate and the experimental friction plate core plate is calculated; S3: inner parameters of the to-be-tested friction plate core plate and the experimental friction plate core plate are respectively acquired, and a collision tooth root stress model of the to-be-tested friction plate core plate and the experimental friction plate core plate is established; and S4: when the tooth root stress of the to-be-tested friction plate core plate and the experimental friction plate core plate is equal, the collision force ratio of the to-be-tested friction plate core plate and the experimental friction plate core plate is calculated. Through the collision of the large modulus core plate equivalent to the small modulus core plate, the collision force of the large modulus core plate is obtained on the basis of the calculation of the collision force of the small modulus core plate.

The application discloses a kind of self-adapting angular momentum amplitude adjustment attitude maneuvering methods, comprising: obtaining the attitude quaternion deviation and angular velocity deviation of satellite body;According to the attitude quaternion deviation of satellite body, three-axis attitude maneuvering angular velocity amplitude value is obtained;According to the three-axis attitude maneuvering angular velocity amplitude value of satellite body, satellite body three-axis quaternion deviation amplitude value is obtained;According to satellite body three-axis quaternion deviation amplitude value, the attitude quaternion deviation of satellite body after vector amplitude limiting is calculated;According to satellite body three-axis quaternion deviation after vector amplitude limiting and angular velocity deviation, three-axis command control moment is obtained.The application can guarantee that the execution mechanism angular momentum does not exceed the premise of output capacity during maneuvering process, and simultaneously realize three-axis simultaneous maneuvering to place to the greatest extent using execution angular momentum.

The application discloses a satellite sun-oriented flywheel angular momentum dynamic adjustment method and device and a medium. First, the orbit position of the satellite after the next control step is predicted, so that the azimuth information of the sun relative to the satellite after the next control step is determined according to the predicted orbit position, and the target attitude angle after the next control step is determined according to the azimuth information. Then, the difference between the target attitude angle and the current attitude angle is determined, a linear smoothing strategy is adopted, and the smoothed attitude angular velocity is determined. Based on the angular momentum conservation principle, the attitude angular velocity is converted into a target angular momentum change amount, and the target angular momentum change amount is distributed to each flywheel to adjust the satellite attitude by controlling the angular momentum change amount of the flywheel. Therefore, the application can stably adjust the satellite attitude by avoiding the angular velocity mutation and uniformly distributing the angular momentum change amount of each flywheel, thereby reducing the energy consumption.

The invention belongs to the technical field of optical communication, and particularly relates to an orbital angular momentum pattern recognition method based on deep learning. According to the OAM pattern recognition method, the efficiency and precision of model training are remarkably improved by introducing the adaptive learning rate scheduling and gradient cutting technology. In the experiment, the Two Phase Scheduler and Dynamic Range SGD optimizers provided by the invention can ensure the steady convergence of the model in different initial learning rate ranges, so that the training process is obviously accelerated, and the common convergence oscillation problem is effectively avoided. According to the method, a high-precision recognition result can be provided in an OAM speckle classification task, good generalization ability is shown in the face of various different scattering environments, and an efficient and robust solution is provided for the OAM mode recognition problem.

The application discloses a kind of space multibody system dynamics modeling method based on Lagrange multiplier method, first establish the coordinate conversion matrix of local to global coordinate system of each component in space;With centroid coordinates and Euler angle definition active component pose, determine generalized coordinate;Position constraint equation is established to kinematic pair, after first and second derivative, obtain the numerical expression of velocity, acceleration constraint equation;Through the cross product property of space angular velocity matrix and vector and the symmetry of vector cross product, the velocity constraint equation is converted, and the numerical expression of Jacobian matrix and time partial derivative term is obtained;Based on the modified Lagrange multiplier method, the cross product term of angular velocity and angular momentum of space component rotation is considered, the dynamics equation is established and solved;The correlation law of Euler angle and space angular velocity is established, the conversion of both is realized.Therefore, the method of the application is suitable for various space multibody systems, solves the problem of existing modeling method when dealing with complex constraints, fills the gap of prior art.

The invention discloses a method for regulating and controlling a spin-orbit entangled state through spin-orbit angular momentum conversion efficiency. The light may carry three types of angular momentums. The invention relates to an intrinsic orbital angular momentum (EOAM), which is characterized in that the intrinsic orbital angular momentum (IOAM) is used as an intrinsic orbital angular momentum (ANM), the spin angular momentum (SAM), the intrinsic orbital angular momentum (IOAM), and the intrinsic orbital angular momentum (EOAM) are used as a main orbital angular momentum (EOAM) of the main orbital angular momentum (ANM) of the main orbital angular momentum (ANM) of the main orbital angular momentum (ANM) of the main orbital angular momentum. The SAM and the IOAM of the light can be mutually converted, and a spin-orbit entangled state can also be formed between the SAM and the IOAM. The SAM-IOAM mutual conversion efficiency of light is closely related to the spin-orbit entangled state of the light. Based on the relevance, the invention provides a method for regulating and controlling the spin-orbit entangled state by regulating and controlling the spin-orbit angular momentum conversion efficiency.