44 results about "Pointing error" patented technology

The invention relates to the technical field of space telescope calibration, in particular to a telescope pointing calibration method based on optical fiber interconnection, which comprises the following steps: providing reference light beams in different directions, enabling each lens to correspondingly receive the reference light beams by adjusting the lens pointing, splitting the reference light beams received by the lenses through an optical splitter, and obtaining a split beam; one beam is aligned and corrected through a camera, and the other beam is coupled into an optical fiber to record direction information; the calibration light beams are reversely emitted by the optical fiber through the optical switch and are emitted by the lens, each reference light beam in the known direction is reproduced, a reference light field is formed, the telescope to be calibrated is placed in the reference light field, the miss distance of each calibration light beam in the known direction on the mirror surface of the telescope to be calibrated is measured, and the pointing error is calculated and corrected according to the miss distance. The optical fiber network is used for establishing the unique mapping relation between the space direction and the optical fiber channel, miss distance measurement is carried out through dynamic time-sharing reproduction, and the problems of mechanical accumulative errors and the like existing in a traditional mechanical calibration method are solved.

The invention discloses a ground station antenna pointing error compensation method and related equipment. The method comprises the following steps: controlling an antenna driving shaft to sequentially rotate to a plurality of measuring points according to a preset angle step length in a preset angle range, and synchronously acquiring a command angle value output by an encoder and an actual angle value output by a gradienter at each measuring point; for each measurement point, an error value is calculated according to the relation that the error value is equal to the difference between the actual angle value and the command angle value, and an error sample set containing a plurality of data pairs is formed; and performing curve fitting processing on the error sample set to obtain a continuous and smooth error compensation function in the preset angle range, and performing ground station antenna pointing error compensation by using the error compensation function, the error compensation function being used for representing a mapping relationship between a command angle value and an error value. The problem that an existing ground station antenna pointing error compensation method is high in cost, complex in implementation or limited in compensation effect can be solved.

The application discloses a kind of mechanical hand eye automatic calibration method, device, equipment and medium, comprising: obtaining calibration board image and identifying feature point and camera field of view center, select target feature point and record first mechanical hand coordinates and initial pixel coordinates;Control mechanical hand moves fixed step along multiple directions and obtains tentative information, and determine target mechanical hand coordinates and step length adjustment mode accordingly;According to iterative update mechanical hand coordinates and fixed step according to alignment condition, establish the corresponding relationship of final mechanical hand coordinates and initial pixel coordinates;Repeat the above operation to the rest feature points, calculate hand-eye transformation relationship based on multiple sets of corresponding relationship.The application gradually corrects the position of mechanical hand by the iterative alignment mode driven by pixel error, and realizes stable convergence by combining step length adjustment, so as to reduce the point error of artificial, improve calibration accuracy, reduce repeated adjustment process, and improve calibration efficiency.

The invention discloses a horizon astronomical telescope pointing error correction method based on machine learning. The method comprises the following steps: recording fixed star data; constructing a telescope rack pointing model, calculating a model coefficient, performing coarse correction on a new observation target, accumulating observation data, and preprocessing the observation data; training the preprocessed training set data by using an XGBoost regression model, predicting condition parameters of a new observation target by using a trained error prediction model to obtain normalized azimuth angle deviation and elevation angle deviation predicted values of the new observation target, and carrying out reverse normalization processing on the predicted values to obtain an actual rack deviation angle; and superposing the rough correction deviation angle and the actual rack deviation angle to serve as a final offset to be injected into a telescope rack tracking program so as to realize correction of a pointing error. According to the invention, the pointing error can be within a very small range, and the pointing precision of the horizon telescope can be effectively improved.

The invention provides a pointing error correction method and device of a beam waveguide system, equipment and a storage medium, which can be applied to the technical field of antennas. The method comprises the following steps: acquiring laser incident to a beam waveguide system along a current beam transmission direction every time an antenna rotates to an angle; laser is reflected to the target through first to Sth plane mirrors in the beam waveguide system, a first laser point is obtained, and the first to Sth plane mirrors are plane mirrors which are closer to the target in sequence; determining an angle error according to the first laser point, the second laser point incident to the Sth plane mirror and the target point; rotating angles of waveguide reflectors are adjusted, angle errors are corrected, the waveguide reflectors are used for reflecting a current wave beam, and a plane mirror is placed in the center of each waveguide reflector; re-acquiring the first laser point, and determining a displacement error according to the re-acquired first laser point and the target point; and adjusting the displacement of the waveguide reflector, and correcting the displacement error.

The present application relates to a kind of motion coupling under spaceborne laser communication terminal fixed time disturbance control method, for the periscope type laser communication terminal fast pointing control problem under the influence of multi-source disturbance such as space environment interference, floating satellite platform coupling moment and rotation shaft friction moment, first, the deep coupling model of spaceborne communication terminal containing above-mentioned multi-source disturbance is established, and multi-source disturbance is regarded as total disturbance moment by analyzing interference structure and characteristics;Second, fixed time disturbance observer is designed to quickly estimate the total disturbance moment suffered by communication terminal;Third, nominal fixed time controller is designed and combined with disturbance observer to form fixed time compound anti-interference controller;Finally, combined with the pointing time demand of communication terminal, observer and controller parameter selection are analyzed and guided, and fixed time anti-interference control of spaceborne laser communication terminal under motion coupling is completed.The control method of the present application has the characteristics of strong robustness, fast pointing speed and guaranteeing pointing error fixed time convergence.

The application discloses a target radar cross section estimation method and system, and relates to the technical field of radio and radar detection; the method comprises the following steps: forming a main scanning beam, a left accompanying beam and a right accompanying beam in a residence period, collecting echo samples to obtain an echo sample set, recording a beam serial number and a pointing angle to obtain a multi-beam pointing table, and obtaining a multi-beam power group from the echo intensity of three beams; obtaining a direction map deviation segment from the multi-beam power group and the multi-beam pointing table; aligning the direction map deviation segment with the echo sample set, and obtaining a channel consistency correction table according to a background echo segment; obtaining a de-drift echo power sequence and a maneuvering decoupling weight according to the channel consistency correction table and a tracking error sequence; the application can effectively solve the problems of the mixing of sidelobe energy caused by the beam pointing error in the prior art and the asymmetric drift of the radar cross section estimation caused by the change of the beam shape with the pointing.

A kind of full strapdown millimeter wave phased array radar system pointing calibration method, main steps include: to be calibrated system is installed on three-axis turntable, based on the set calibration range and calibration granularity, calculate t time antenna azimuth beam pointing angle and elevation beam pointing angle theoretical value, and corresponding turntable attitude angle theoretical value, control turntable turns to the angle;Adjust phased array antenna beam pointing, so that target is located in the antenna beam center, obtain the actual value of antenna azimuth beam pointing angle and elevation beam pointing angle at this time, with the difference between the beam pointing theoretical value and actual value as the pointing error of phased array at the angle, to complete the calibration test of all angles in calibration range.This is a kind of high-efficiency calibration test method at system level, without accurately determining the coordinate position of each array element of antenna, can take into account the influence of system each link error on beam pointing precision, realize the fast, high-precision high-speed full strapdown millimeter wave phased array test calibration.

The invention provides a spacecraft double-flywheel under-actuated sun safety control method and system, and the method comprises the steps: S1, calculating a sun quaternion according to the time of a GNC computer system of a spacecraft, and calculating a sun error quaternion according to the quaternion from a spacecraft inertial system to the system; s2, calculating a sun target angular velocity according to the sun error quaternion and the inertial angular velocity of the gyroscope of the spacecraft; s3, calculating a double-flywheel under-actuated sun control quantity according to the inertial angular velocity of the spacecraft gyroscope and the sun target angular velocity; and S4, open-loop processing is carried out on spacecraft double-flywheel under-actuated sun control according to the sun error quaternion, the control torque is prevented from exceeding the maximum torque provided by the flywheels, and low-pass filtering is carried out on the control torque. According to the invention, stable sun alignment under the double-flywheel configuration of the spacecraft actuating mechanism is realized, and the energy safety of the spacecraft is effectively guaranteed.

The invention belongs to the technical field of astronomical observation equipment, and particularly relates to a modeling and correcting method and system for static pointing errors of a horizontal telescope. The method comprises the following steps: S1, establishing a horizontal telescope static pointing model, and analyzing shafting error factors of the telescope; s2, deducing a telescope shafting static pointing error compensation model based on the static pointing model; s3, substituting experimental data, fitting the data by using a least square method, and determining each undetermined coefficient of the compensation model; and S4, correcting the static pointing error of the warp axis and the weft axis of the telescope by using the compensation model. The method has the characteristics that the observation precision can be improved, the calibration efficiency is improved, and the applicability is wide.

This invention proposes a method for decoupling and controlling the pointing of sub-beams in a laser array, belonging to the field of beam combining technology. The method includes: acquiring an initial spot image on the target surface as an initial reference image; acquiring the offset of each sub-spot relative to the target position based on the initial reference image; sequentially applying perturbations to each beam pointing correction device according to a preset order and acquiring the current perturbed spot image; performing pixel-by-pixel difference operations between the current perturbed spot image and the initial reference image to obtain a differential energy map and perform energy detection, thereby determining the sub-spot corresponding to the current beam pointing correction device; applying perturbations to each beam pointing correction device to establish the correspondence between all sub-spots and beam pointing correction devices; and calculating the control voltage to correct the offset of each sub-spot using a control model to achieve one-step correction of large pointing errors in each sub-beam. This invention is applicable to the rapid correction of large pointing errors in laser arrays.

The invention discloses an array joint likelihood detection method and system for air-ground unmanned aerial vehicle optical communication, and aims to solve the problem of communication reliability caused by atmospheric turbulence and pointing errors in a complex electromagnetic environment. The method comprises the steps that a multi-factor coupling channel model including turbulence attenuation and pointing error attenuation is constructed, a double-Gamma statistical model is adopted for turbulence attenuation, and pointing errors are quantized through a zero-bias Rayleigh jitter model; estimating emission signal amplitude, equivalent gain of each channel and noise statistical characteristics by using the training symbols; an M * N detector array is adopted to obtain multichannel signals, joint likelihood detection (JLD) is executed, and the bit error rate is reduced through multichannel fusion and adaptive threshold judgment. The system comprises a transmitting end, an air-ground optical transmission link and a receiving end, wherein the receiving end is integrated with a large-field-of-view array and a signal processing module. According to the invention, cooperative compensation of turbulence and pointing errors is realized, link stability and anti-interference capability are improved, and the method is suitable for unmanned aerial vehicle communication scenes such as urban low altitude and mountainous open space.

The invention provides a high-precision inter-satellite pointing control method fusing laser interference measurement, and relates to the field of spacecraft control. The method comprises the following steps: firstly, carrying out validity judgment and processing on an attitude error value provided by the measurement of the laser interferometer in the period, carrying out attitude angular velocity differential calculation, and when the attitude error value provided by the measurement of the laser interferometer in the period is valid, carrying out reference error calculation in combination with an attitude error value provided by orbit extrapolation and on-satellite attitude determination; then, according to attitude error value validity provided by measurement of the laser interferometer in the current period and the last period, on the basis of a reference introduction / direct introduction selection mark set on the ground, determining to implement reference introduction calculation or direct introduction calculation, calculating an attitude control quantity and an angular velocity control quantity, and finally, according to the attitude control quantity and the angular velocity control quantity, calculating the attitude control quantity and the angular velocity control quantity. An attitude control moment is calculated by using a control law and is implemented by an execution mechanism. According to the invention, high-precision pointing error measurement of the laser interferometer is introduced, so that high-precision inter-satellite pointing control of satellites is realized.

The invention discloses a laser communication terminal pointing error real-time compensation method based on orbit space-time characteristics and a satellite-borne laser communication terminal. According to the method, the orbit operation periodicity of a satellite is utilized, and a multi-orbit period and angle partition iterative learning and compensation mode is adopted; the method is used for systematically correcting the installation angle deviation caused by slow change factors such as thermal deformation of an installation surface, and specifically comprises the following steps: in a link establishment process of a first track period, when a terminal runs to a certain preset angle partition, a system synchronously records and calculates a pointing error of the interval; starting from a second track period, when the terminal runs to the learned angle partition again, the system automatically injects the installation angle deviation of the partition learned and stored in the previous track, and the installation angle deviation serves as a feed-forward compensation amount to pre-correct the current direction; and all common working angles of the terminal can be covered step by step through operation of a plurality of continuous track periods. The method ensures that the pointing precision of the terminal can be dynamically maintained and continuously optimized in a long-term on-orbit task.

The invention discloses a CBCT craniojaw median sagittal plane automatic fitting method based on deep learning, and the method comprises the following steps: data preprocessing: obtaining CBCT image data, carrying out the format conversion, resampling and data enhancement processing of an original CBCT image, and obtaining standardized training data, verification data and test data; the method has the advantages that a two-stage network structure combining 3D U-Net and LSTM is adopted, high-precision automatic positioning of key anatomical points is achieved, the average positioning error is only 0.9671 mm, the errors of all the points are smaller than 1.2 mm, the detection success rate under the threshold value of 2 mm reaches 98.03%, the precision reaches the labeling level of high-age doctors, and the accuracy of median sagittal plane fitting is guaranteed; the TLS algorithm is introduced to carry out median sagittal plane fitting, discrete points or abnormal points can be automatically eliminated, the method has high robustness for outliers, excellent performance can be kept in complex cases such as symmetric cases and jaw deflection cases, the angle average errors of a symmetric group and a jaw deflection group are 0.4717 degrees and 0.47599 degrees respectively, and the method is superior to a traditional fitting method.

The application discloses a kind of mark point error identification and elimination method, device, equipment and storage medium, method is by obtaining the observation ray set of target mark point under multiple camera visual angle, establish local three-dimensional coordinate system with target mark point as origin, and according to the included angle distribution of observation ray relative to the main shaft of local three-dimensional coordinate system, observation ray set is divided into at least two direction regions;According to the ray number distribution in each direction region divided out, the overall observation quality of target mark point is judged, when overall observation quality satisfies preset condition, the comprehensive score of each observation ray is carried out, and the observation ray that comprehensive quality score does not satisfy preset screening condition is eliminated, and the ray set after screening is obtained;According to ray set, the three-dimensional coordinates of target mark point are calculated by preset space front intersection algorithm;It can realize the deep evaluation of mark point overall observation geometric quality, and the precision, stability and algorithm robustness of mark point three-dimensional coordinate reconstruction are improved.

The application discloses a Q / V frequency band low-orbit three-axis antenna pointing mark calibration method based on an MPA algorithm and belongs to the field of satellite communication antenna servo control. The method comprises the following steps: defining to-be-optimized parameters representing a plurality of error sources of a three-axis antenna; defining an error index function for evaluating pointing deviation; acquiring tracking data of a multi-orbit satellite as a training data set; establishing a pointing error correction model with a measurement angle as input and the defined parameters for correction; iteratively optimizing parameters in the model by using a marine predator algorithm (MPA) to minimize the error index function and obtain an optimal parameter set; and configuring the optimal parameter set to a servo control system for real-time tracking error correction. The application utilizes on-orbit data, does not need additional equipment, and can realize fast calibration only by using 1-2 orbit data, significantly improves pointing precision and high-elevation tracking stability, and is suitable for large-scale and rapid deployment.

The invention discloses a space laser communication method and system based on a cascade liquid crystal polarization grating device, and relates to the technical field of space laser communication. A cascade liquid crystal polarization grating module is used for executing discrete deflection based on an electric control liquid crystal phase to output a coarse pointing light beam, and a fine tracking deflection module is used for executing continuous angle compensation. The control module generates a state code based on the coarse tracking error, looks up a table and outputs a grating driving signal; and a precise tracking deflection module is driven based on the precise tracking error, and when the continuous compensation angle reaches the upper limit or the pointing error exceeds the limit, a state code is updated based on the continuous compensation angle or the pointing error, the grating is driven to discretely deflect, and the precise tracking deflection module is reset to zero. According to the method, large-range, high-precision and stable pointing control is realized through cooperation of non-mechanical discrete coarse pointing and continuous fine tracking in combination with table look-up driving, saturated unloading and pointing monitoring mechanisms. And further, multi-channel waveform pre-emphasis driving and Gray code coding are combined, so that transient disturbance of state switching is effectively inhibited.

The invention discloses a guide star data-based rack residual error adaptive pointing correction method and system, which are applied to a telescope with a height axis and an azimuth axis. The method comprises the following steps: establishing and initializing a rack model; guide star data acquisition and mass filtering; the sky grid coverage degree is judged; judging a sample number threshold value and removing abnormal samples; carrying out residual feature construction based on rack item contribution and meteorological features; training a rack residual regression model; performing new and old model effect comparison and online updating; and correcting the pointing error on line. Under the condition that extra calibration overhead is not increased, automatic updating of the pointing model is achieved through daily guide star data, the pointing precision and stability under the complex weather and long-term drift condition are improved, the manual calibration burden is relieved, and the method is suitable for a high-automation telescope long-term operation scene.

The invention provides a coarse and fine switching method and device in satellite top-crossing tracking and pointing, and the method comprises the steps: carrying out the state estimation and uncertainty quantification based on the instantaneous pointing error of a satellite top-crossing tracking and pointing system at a satellite top-crossing stage, generating and dynamically updating the two-dimensional probability density distribution describing the position of a light spot, and carrying out the dynamic updating of the two-dimensional probability density distribution; fusing with a light intensity distribution diagram influenced by atmospheric turbulence to obtain an effective receiving index, and determining a region of interest for fine aiming detection from probability distribution; performing spatio-temporal clustering analysis on multiple frames of detection data continuously collected by the fine aiming equipment, and calculating the coordinates of a fine aiming tracking point and the identification confidence of the fine aiming tracking point; and predicting the tracking interruption probability based on the atmospheric turbulence prediction data and the probability distribution, performing judgment in combination with the confidence coefficient, and if the judgment is passed, switching the control system to a fine aiming closed-loop tracking mode. According to the invention, rapid, reliable and anti-interference automatic switching from coarse aiming to fine aiming can be realized in a high dynamic scene in which a satellite rapidly passes through the top, so that rapid establishment and stable maintenance of a free space optical communication link are ensured.

Systems and methods disclosed herein for pointing a steerable antenna system onboard a satellite exploit advantageous image-processing techniques that provide a computationally efficient and accurate way of determining the pointing error of the steerable antenna system and determining corresponding pointing corrections. Received-signal power measurements for individual array elements in an antenna array of the steerable antenna system provide the basis for forming a power-distribution image that reveals where an uplink signal falls on the array, which in turn provides a basis for determining the appropriate pointing correction.

The application discloses a periodic template compensation wave control algorithm for improving beam pointing accuracy of a phased array antenna. u 、 v The quantization error of the four-round wave control algorithm digital phase shifter in the four-round wave control algorithm is derived for a phased array antenna wave control system, and is recorded as P u 、 P v Then, a two-dimensional beam pointing area is divided into units of u v P u P v In the first phase quantization error period u , v}∈{[0, P u ),[0, P v}, a compensation matrix template is constructed by using a sequential phase feeding method based on a minimum beam pointing error criterion. In the PTC algorithm, a corresponding compensation vector is periodically selected from the compensation matrix template according to the beam pointing, a wave control code of the four-round wave control algorithm is added to the compensation vector to obtain a wave control code of the PTC algorithm, and the method can effectively reduce the beam pointing error of the phased array antenna, has low calculation amount and is easy to implement.​​​

The application provides a light splitting detection system and a light beam pointing detection and stabilization system. The light splitting detection system is used for detecting the properties of a light beam emitted by a light beam pointing control component, and comprises a light splitting detection component and a controller. The light splitting detection component comprises a light splitting component and a detection component. The light splitting component is used for reflecting and transmitting the light beam, and the detection component is used for receiving a reflected light beam formed by the reflection of the light beam and detecting the properties of the reflected light beam. The controller is connected between the detection component and the light beam pointing control component. The controller is used for determining a light beam adjustment amount according to the properties of the reflected light beam, and controlling the light beam pointing control component to modulate the light beam emitted by a light source according to the light beam adjustment amount. The light splitting detection system provided by the application can control the light beam pointing control component to modulate the light beam emitted by the light source according to the properties of the light beam detected by the detection component, reduce the deviation of the light beam in the process of long-distance propagation and the pointing error introduced by optical devices, and improve the stability of the light beam.

A laser communication terminal pointing error real-time compensation method based on track space-time characteristics and a satellite-borne laser communication terminal, the method uses the periodicity of satellite orbit operation, through multi-orbit period, angle partition iterative learning and compensation, the installation angle deviation caused by slow-changing factors such as installation surface thermal deformation is systematically corrected, specifically comprising: in the first orbit period, when the terminal runs to a preset angle partition, the system synchronously records and calculates the pointing error in the interval; from the second orbit period, when the terminal runs to the angle partition that has been learned again, the system automatically injects the installation angle deviation of the partition learned and saved in the last orbit as a feedforward compensation amount to pre-correct the current pointing; through the operation of multiple continuous orbit periods, all commonly used working angles of the terminal can be gradually covered. The application ensures that the pointing accuracy of the terminal can be dynamically maintained and continuously optimized in long-term on-orbit tasks.

The invention relates to a beam pointing error correction method and device and a storage medium, and the method executed by network equipment comprises the steps: determining a first beam used for successfully paging a terminal, and enabling the first beam to be a beam used for expanding a paging area under the condition that the terminal is failed to be paged by using a second beam; a first message is sent to the terminal, and the first message is used for indicating the terminal to report beam error information; a second message sent by the terminal is received, the second message comprises the current first position and the elevation angle of the terminal, and the elevation angle is determined by the terminal according to the position of the network equipment and the second wave beam; and correcting the coverage range of the first cell to which the first beam belongs according to the first position and the elevation angle. Therefore, the network equipment can correct the coverage range dislocation of the cell caused by the beam pointing error, so as to accurately provide business service for the terminal.

The application discloses a two-dimensional galvanometer visual axis pointing coupling correction method, and mainly solves the problem that the visual axis pointing error calculated by the prior art is in the order of milliradians, and it is difficult to meet the high-precision correction requirement.The method comprises the following steps: step 1, establishing a visual axis pointing model for a two-dimensional galvanometer to be corrected; step 2, acquiring a linear model between the rotation angle of the two-dimensional galvanometer and the visual axis pointing angle of a two-stage stable pointing system based on the visual axis pointing model by using a linear approximation method; acquiring a pointing error based on the visual axis pointing model and the linear model; performing nonlinear correction on the pointing error by using a Volterra series to acquire a nonlinear correction relationship; step 3, acquiring a corrected pointing error by using the nonlinear correction relationship; and step 4, acquiring the control angle of the two-dimensional galvanometer based on the corrected pointing error.The application can reduce the visual axis pointing error from the order of milliradians to the order of microradians, the pointing calculation precision is improved by about 75 times, and the visual axis pointing calculation precision is significantly improved.

This invention relates to a dual-wedge scanner calibration system and method based on the principle of directional decoupling. The system comprises a dual-wedge scanner, an imaging detector, a target, and a reference screen. The implementation method includes assembling the calibration system, adjusting the imaging line of sight pitch, adjusting the imaging line of sight azimuth, and calibrating the dual-wedge rotation angle error. Compared with existing technologies, this invention detects the optical pointing error of the dual-wedge scanner by combining the imaging detector and the target. Simultaneously, it utilizes the optical scanning characteristics of the dual-wedge scanner to establish a decoupled adjustment strategy for pitch and azimuth, transforming the dual-wedge calibration problem into an imaging line of sight pointing adjustment problem. This allows for large-scale, high-precision calibration of the dual-wedge main cross-section position using a simple and compact system composition and flexible and efficient implementation methods, providing technical support for the application of dual-wedge scanners.

The present application relates to error calibration method, more particularly to a kind of correction method of rotating double-prism pointing error based on search and rescue optimization algorithm, the method based on rotating double-prism system, SARO (SARO) algorithm is introduced into the parameter estimation of rotating double-prism system error, the deviation between actual pointing position and theory pointing is constructed search and rescue optimization fitness function, finally proposes assembly error parameter estimation model and is applied to pointing error correction.The present application realizes the comprehensive identification of assembly error parameter in system, effectively corrects rotating double-prism system pointing error.

The utility model relates to machine tool machining original point correction device technical field discloses a machine tool machining original point correction device, including base, the outer surface of base is equipped with two symmetrical clamping grooves, and the outer surface of base is equipped with rotary groove, the inside rotation of rotary groove is connected with rotating shaft, the angle of rotating block is adjusted through knob, realizes the fine adjustment and balance of positioning block, guarantees the levelness of elastic plug -in post further, through the level auxiliary leveling of top setting, has guaranteed that the device can reach accurate point in different installation state, besides, the laser pen that device sets can mark position after the position of original point is determined, finds the point error that leads to because clamping deviation through visual identification, and the position correction of convenient operator is carried out, thereby secondary ensures the positioning accuracy, the reasonable cooperation of spring and sliding slot structure makes elastic plug -in post can rebound homing after pressing, has strengthened the repeated use performance of device.

A laser processing system for processing a workpiece is adapted to predict a thermal response of at least one of a number of beam path components to a laser energy beam during a predetermined processing interval as the workpiece is being processed, generate one or more commands based at least in part on the predicted thermal response, and output the one or more commands to one or more components of the system to process the workpiece during the processing interval.