304 results about "Optical observation" patented technology

The invention relates to the technical field of spacecraft orbit control and space safety, and discloses a space debris orbit prediction and avoidance method, which comprises the following steps that: a ground computing center screens candidate targets and generates enhanced data packets for uploading; the spaceborne computer combines real-time navigation data to carry out geometric feature screening, and an instant high-risk target list is generated; controlling the star sensor to execute optical observation, and resolving an optical measurement relative orbit state by utilizing displacement superposition and Kalman filtering; selecting a high confidence coefficient or a conservative probability threshold according to the optical measurement state acquisition condition, and generating an avoidance instruction when the collision probability exceeds the limit; and the propulsion system responds to the instruction to execute avoidance, verifies the effect by confirming the semi-major axis variation and executes track recovery by selecting an aircraft. According to the method, the ground-air collaborative screening and shift superposition enhancement technology is adopted, the problems that the low-precision ephemeris false alarm rate is high and the detection capability of a satellite-borne sensor on a dark and weak target is insufficient are solved, and the accuracy of evasion decision making and the execution reliability are improved.

The invention relates to a method for determining an initial orbit of a satellite with an embedded physical knowledge neural network, which is used for determining an initial orbit of a short arc segment under an optical observation condition and providing support for subsequent precise orbit determination. The network comprises an encoder-decoder structure, an encoder predicts the motion state of a satellite in an orbit according to observation information, the decoder converts the predicted satellite motion state into an observation value, the prediction accuracy of the encoder is evaluated, physical information of satellite orbit dynamics is introduced into a loss function, and the prediction accuracy of the satellite orbit is improved. And satellite orbit determination based on the neural network is realized. The input of the encoder is the observation angle quantity (namely azimuth angle and pitch angle) of the satellite relative to an observer, the observation time and the position information (namely longitude, latitude and altitude) of the observer; the output of the encoder, namely the input of the decoder, is the absolute motion state quantity (namely the position and the speed of the satellite in a geocentric inertial coordinate system) of the satellite in the orbit and the position information of an observer, and the output of the decoder is the observed quantity of the satellite relative to the observer. When the network is trained, firstly, a decoder is trained by taking a mean square error between a predicted observation value and a real observation value as a loss function, and a transformation relation from a satellite motion state to the observation value is learned; fixing the structure and parameters of a decoder, training the whole encoder-decoder network, calculating the derivative of the predicted satellite absolute state quantity relative to the observation time, and calculating the physical information loss of a speed item and an acceleration item; adding the physical information item loss and the mean square error of the observed quantity, constructing a total loss function, and optimizing network parameters through error back propagation; in the reasoning stage, an encoder network is used for reasoning, and the absolute motion state quantity, predicted by an encoder, of the satellite is converted into an orbit element form, namely, the initial orbit is determined.

The invention discloses a long-distance rail identification and obstacle detection method and system, and the method comprises the steps: combining a long-focus optical system with an ultra-high-speed industrial camera at a hardware level, and building a high-collection-frame-rate and long-distance optical detection system; on the software level, a region of interest for obstacle detection is delimited according to recognition and visual segmentation of left and right rail lines of a rail, advanced visual tasks such as a rail obstacle intrusion detection algorithm based on target detection are executed, and finally high-frame-rate recognition and detection of long-distance rails and rail obstacles are achieved. According to the invention, a Schmidt-Cassegrain optical system with a focal length of 2000mm is used, and an ultra-high-speed industrial camera with a resolution of 1920 * 1080 and 3000 frames per second is combined to build a long-distance high-frame-rate optical detection platform which is erected on a driving position of a train to detect railway conditions within a range of 6km in real time; serious accidents caused by overlong braking distance due to high-speed running of the train can be prevented. Compared with a traditional train driver eye observation and laser radar-based scanning imaging mode, a farther detection distance, better detection and recognition robustness and a higher frame rate can be realized through the long-distance optical observation platform and the rear-end real-time detection system.

The invention provides a radar and optical observation segmental arc correlation method and system for space debris. A joint probability density function is obtained through a kernel density estimation algorithm. A radar observation arc section and an optical observation arc section are input. And converting the observation data into a geocentric celestial coordinate system. And acquiring system parameters of the observation equipment. Radar observation data and optical observation data are unified to the same dimension, and a distance measurement value weight and an angle measurement value weight are set. And calculating an initial orbit by the radar observation arc section. And calculating a joint objective function corresponding to the current orbit position speed. And if the convergence condition is met, outputting the minimum value of the joint objective function and the orbit position speed corresponding to the minimum value. Otherwise, updating the track position speed, and repeating until the convergence condition is met. And according to the minimum value of the joint objective function and the joint probability density function, judging whether association is carried out, and outputting confidence during association. The method is easy to implement and can be effectively applied to association of the space debris radar and the optical observation arc section.

An imaging device for capturing images through an eyepiece of an optical viewing device. The imaging device includes a camera that aligns with the eyepiece for capturing the images viewed through the eyepiece, and a display for displaying the images captured by the camera. The imaging device determines a type of the optical viewing device. The imaging device presents a workflow on the display based on the type of the optical viewing device. The imaging device captures metrics related to user interactions with the workflow presented on the display and the images captured by the camera during the workflow.

The invention provides a comprehensive photoelectric platform method and system for unmanned aerial vehicle detection, electronic equipment and a storage medium, and relates to the technical field of unmanned aerial vehicle detection and localization. Synchronously triggering a photoelectric platform to capture a suspicious airspace high-definition video stream and establishing a space-time corresponding database of the two; synchronizing each radio frequency receiving node by taking a high-precision atomic clock as a time reference, and processing multiple paths of signal data to obtain a time-aligned basic signal; basic signal radio frequency features are extracted and associated with equipment identification, a mapping relation between the basic signal radio frequency features and remote controller models is established, and a hardware feature library is constructed; and finally, in combination with the library identification result, the signal time difference and the optical data, correcting a multipath error by using particle filtering, predicting and updating the position of an operator, and realizing comprehensive detection and positioning of the unmanned aerial vehicle after iterative convergence, thereby realizing comprehensive detection and positioning of the unmanned aerial vehicle in combination with radio frequency detection and optical observation.

A scope mount assembly for attaching an optical scope having first and second eyepieces to an electronic accessory having a lens. The scope mount assembly broadly comprises a scope mount and a target attachable to the electronic accessory. The scope mount is configured to engage the first eyepiece. The scope mount includes an aperture for viewing through the first eyepiece when the optical scope is not attached to the electronic accessory and a magnet positioned near the aperture. The target includes a body formed of a structural material and a powder particulate. The powder particulate is distributed throughout the structural material and includes a material configured to be attracted to the magnet. The target is positionable on the electronic accessory so that the second eyepiece aligns with the lens of the electronic accessory when the scope mount magnetically engages the target.

The invention provides an objective lens system and optical observation equipment. The objective lens system comprises a fourth lens with positive focal power, a third lens with positive focal power, a second lens with negative focal power and a first lens with positive focal power which are sequentially arranged on the same optical axis from the object side; the first lens and the third lens are biconvex lenses, the second lens is a biconcave lens, the fourth lens is a balsaming lens, and the image side surface of the fourth lens is a convex surface; the focal length f of the objective lens system and the focal length f1 of the first lens satisfy the relationship. According to the invention, during assembly, the tolerance requirement is low, installation and adjustment are more facilitated, the field of view is larger, the vignetting is smaller, the number of lenses is smaller, and the cost performance is higher.

The invention belongs to the technical field of optical observation equipment, and relates to a space observation optical technology, in particular to a space telescope on-orbit assembly method, a computer program product and a system. A space telescope on-orbit assembly method comprises the steps that a target sub-lens module is determined based on an installation sequence, and the target sub-lens module is locked in a storage module; after a mechanical arm module is controlled to move to a first set area where the target sub-mirror module can be grabbed, a visual mark on the target sub-mirror module is recognized, and the visual mark comprises pose information and identity information of the target sub-mirror module; calculating a first relative pose of a butt joint interface fixed between the target sub-mirror module and the mechanical arm module relative to the mechanical arm module based on the visual mark; and after the mechanical arm module is controlled to grab the target sub-mirror module based on the first relative pose, the target sub-mirror module and the storage module are unlocked. The technical problem that the precision requirement of a visual camera is high is solved.

The invention provides a transparent bulletproof ceramic composite structure with an electric heating function and a preparation method of the transparent bulletproof ceramic composite structure. The composite structure comprises an anti-splashing layer (1), a first middle layer film (2), a multi-layer stacked structure (3) of glass sheets and films, a first transition layer (4), an electric heating film layer (5), a second transition layer (6), a ceramic layer (7), a first antireflection film layer (8), a second antireflection film layer (9), a third antireflection film layer (10), a second middle layer film (11), an inorganic glass layer (12), a third transition layer (13) and an anti-static layer (14) which are arranged in sequence. The composite structure provided by the invention has excellent impact resistance and bulletproof grade, can effectively resist the damage of high-speed elastic sheets or impact objects, and meets the requirements of high-safety application scenes such as weapon armors, armed airplanes and high-speed trains; and the anti-static film has clear optical observation capability, high transmissivity and anti-static property.

The invention discloses a method for carrying out correlation and orbit determination on a space target based on a double-star optical observation result, and the method comprises the steps: obtaining the observation vectors of two observation stars for a certain space target in the respective visual fields, calculating the shortest distance between the observation vectors, and if the distance is always smaller than a threshold value in a time sequence, determining that the space target does not exist. And if not, determining that the two observation stars observe the same space target, calculating a midpoint of two observation vector common vertical lines of the same space target by the two observation stars as an orbit determination point, and performing orbit determination on the space target based on an orbit determination point sequence. According to the method, a low-cost space-based optical orbit determination mode is adopted, space target association is completed through an algorithm with low calculation cost, target consistency is judged based on observation vector distance constraints, a complex model or a large amount of calculation power is not needed, efficient processing can still be performed when the number of targets is large and the data size is large, and the cost and efficiency advantages are remarkable.

The invention discloses an intelligent segmental arc correlation method based on a minimum optical admissible domain, belongs to the field of intelligent calculation optimization of space target monitoring, solves the problem of large calculation amount of segmental arc correlation, and comprises the following steps: constructing the minimum optical admissible domain by a first observation segmental arc; uniformly sampling in the minimum optical tolerance domain, performing orbit propagation on each sampling point under a J2 perturbation model to obtain theoretical optical observation data of a second observation arc section, and calculating an angle root-mean-square error of the second observation arc section to obtain an angle loss function; using a DBSCAN clustering algorithm to identify wave troughs; selecting an initial value of a simplex method in each wave trough to obtain an angle optimal solution; a probability loss function is obtained through Bayesian theorem calculation; substituting the angle optimal solution into a probability loss function, and obtaining a probability optimal solution by using an LM algorithm; a threshold value is set according to the probability loss function obeying chi-square distribution, and when the probability optimal solution is smaller than the threshold value, the two arc segments are associated successfully; according to the invention, the calculation cost is saved, and the space target observation accuracy is improved.

A measurement apparatus for the braking distance of a mine fall arrester, the measurement apparatus comprising a housing (1), wherein a display screen (2) is provided on the housing (1); an optical observation window (3), indicator lights (5), functional operation buttons (6), a mode switch (7), a memory card slot (8), and a data transmission interface (9) are provided on the front face of the housing (1); a cubic neodymium magnet (10) is provided on the back face of the housing (1); an optical glass column (11), a laser ranging module (13), a measurement LED fill light module (14), an imaging module (15), and an outwardly-flared metal shielding cover (16) are provided at the lower portion of the housing (1); and a central control module (17), a GPS module (18), an active ceramic GPS antenna (19), a wireless receiver module (20), a wireless transmitter module (21), a 315MHz control module (22), a 433MHz communication output module (23), a nine-axis accelerometer and gyroscope module (24), a power supply module, and a loudspeaker module (26) are provided in the housing (1). Further provided is a measurement method for the braking distance of a mine fall arrester.

An intervertebral disc surgical system has at least one optical cannula configured with a working channel and an optical channel, wherein the working channel and the optical channel are positioned parallel to one another. The working channel is configured to receive the elongated tubular member of an electrosurgical instrument and the optical channel is configured to receive an optical scope. The optical cannula has an optical cannula operative end for entering an operative field of a patient.

The invention discloses a dust explosion flame free radical testing system and a testing method, belongs to the technical field of dust explosion testing, and solves the problem that existing testing equipment cannot realize visual testing of combustion flame free radicals at the initial stage of dust explosion ignition and in the development process. According to the solution, the test system comprises an explosion generation assembly used for generating single-side open type dust cloud explosion, an optical observation assembly used for observing flame free radicals, a control system, a computer and an air compressor, and semi-open type dust cloud is formed through the explosion generation assembly and is ignited and detonated; images of different free radicals changing along with flame are collected through the optical observation assembly, and visual observation, recording and analysis are carried out through the computer. The system has the advantages of being high in functionality, integrated in system, easy to operate and safe and reliable in experiment process and is suitable for various kinds of combustible dust, collected data can promote dust explosion mechanism research, and data support is provided for development of dust explosion optical early warning protection measures.

The invention discloses a point cloud intersection-based space target optical segmental arc rapid association method. The method comprises the following steps: 1, acquiring optical segmental arc data and constructing a constraint admissible domain; 2, generating a track point cloud; 3, forecasting parallel orbit point cloud; 4, fast point cloud intersection is carried out; and 5, determining an initial orbit based on point cloud intersection. Through the above process, the space target rapid segmental arc correlation method based on point cloud intersection is provided, an admissible domain is constructed by two optical observation segmental arcs and orbit point clouds are generated, and then the point clouds of the two segmental arcs are forecasted to the same moment through a parallel orbit point cloud forecasting technology. Quickly locking an overlapping region of the two point clouds by adopting a minimum bounding box method, and judging the relevance between the point clouds through a mahalanobis distance; and finally, based on the Bayesian estimation principle, carrying out initial orbit determination on the successfully associated arc segments.

An optical viewing system includes an optical viewing device having an eyepiece. The system further includes an imaging device that includes a housing having a bracket that is configured to removably attach the imaging device to the optical viewing device. The imaging device includes a camera configured to capture images viewed through the eyepiece and a display screen configured to display the images captured by the camera. The system further includes a secondary display screen physically separate from the optical viewing device and the imaging device. The secondary display screen pairs with the imaging device to display the images viewed through the eyepiece of the optical viewing device. The pairing between the imaging device and the secondary display screen expires when a condition is satisfied.

The invention provides a space-based optical observation high-orbit space debris short arc initial orbit determination method and system. The method comprises the steps that S1, angle measurement information of imaging of the same unidentified space debris by a space-based optical observation platform is acquired; s2, acquiring observation data according to the observation capability of the space-based optical observation platform, and setting the upper limit and the lower limit of the distance between the high-orbit space debris and the space-based optical observation platform; s3, calculating an actual observation distance upper limit and an actual observation distance lower limit corresponding to the current observation arc section according to the observation data; s4, randomly initializing a plurality of groups of particles within the upper limit and lower limit range of the actual observation distance; s5, calculating a loss function corresponding to each group of particles; s6, updating each group of particles, calculating a loss function corresponding to the updated particles, and recording each group of optimal particles and global optimal particles; and step S7, repeating the step S6 until the cycle quitting condition is met. The method is easy to implement, and the success rate of determining the high-orbit space debris short arc initial orbit can be increased.

The invention relates to a sea ice remote sensing identification method based on ultraviolet reflection difference, and the method achieves the quick and accurate identification of sea ice in a multi-source remote sensing image through the unique optical signal difference of sea ice, cloud and other confusion targets under the reflection of an ultraviolet band. And estimating the sea ice concentration and the sea ice coverage area of the sea ice image after the cloud mask. According to the method, timely and efficient guidance information can be provided, the used multi-source remote sensing image only needs to be subjected to radiometric calibration and atmospheric correction to obtain an optical band apparent reflectivity and a thermal infrared band brightness temperature image, and sea ice can be accurately identified and extracted; compared with a traditional optical observation means, the method is suitable for the situation that an optical remote sensing image is prone to cloud coverage interference, and cloud interference information can be recognized and removed at the same time; the method can meet the requirements of sea ice business monitoring and improve the working efficiency of sea ice observation.

A diagnostic device with an improved optical system is disclosed. The disclosed in vitro diagnostic device has a housing with an inner bottom surface having an arc shape that rises upward from one side where the light source is arranged to the other side where the cartridge sensing surface is arranged. This device may include light sources with different wavelengths arranged on one side of the lower housing. Additionally, it may include an upper housing that is coupled to the upper surface of the lower housing and has a cartridge insertion space for a cartridge with a plurality of wells. The upper housing includes an observation window that covers at least the plurality of sensing hole areas to allow optical observation of the inside of the wells.

A sound production system is provided. The sound production system includes a handpiece for adjusting the depth of penetration. In a preferred embodiment, adjustment of the penetration depth is achieved by adjusting between a fixed part of the handpiece and an adjustable part of the handpiece. In a more preferred embodiment, adjustment of the penetration depth is accomplished by a plurality of interchangeable adjustable members, each of which is configured to provide a different penetration depth when coupled to a stationary member. Preferred embodiments also include an optical system that provides imaging of the treatment surface and is adjustable to continue imaging the treatment surface according to variations in penetration depth. In some embodiments, an interface between a fixed member and an adjustable member of the handpiece passes through a chamber containing a liquid acoustic coupling medium.

The invention provides an astronomical positioning navigation method based on optical observation, which comprises the following steps: screening and sorting observation targets to be observed according to initial conditions of a platform and ephemeris of the observation targets to serve as an observation task list; driving the optical telescope to steer and collect observation images according to the observation task list; matching astronomical images in the observation image with a fixed star catalogue so as to calculate observed celestial coordinates of each astronomical image; extracting a moving target as an observation target through star change of the multiple frames of observation images, and obtaining a motion track of the observation target; and carrying out platform position calculation. According to the astronomical positioning and navigation method disclosed by the invention, the attitude and position calculation of the platform is completed by integrating optical observation data of a fixed star and an observation target, and the autonomous navigation and positioning of the platform under the condition of no GNSS signal are realized.

The invention discloses a sunshading and demisting system matched with an optical observation instrument. The sunshading and demisting system comprises two supports; the first framework, the second framework and the third framework are rotationally connected between the two brackets, are in semi-arc shapes and rotate in corresponding shaft holes of the brackets; a fourth framework, a fifth framework and a sixth framework which are the same are arranged at positions symmetrical to the first framework, the second framework and the third framework and are rotationally connected between the two brackets; the innermost first framework and the innermost fourth framework serve as active frameworks, and driving shafts are additionally arranged on the innermost first framework and the innermost fourth framework close to the root of the support and used for being in shaft connection with push rods of the stepping motors respectively; the two stepping motors are connected to the corresponding supports through shafts respectively. The two pieces of foldable sunshade cloth are respectively fixed on the frameworks on the two sides; the controller is electrically connected to the stepping motor and used for controlling the first framework and the fourth framework to rotate so as to unfold or fold the sunshade cloth; the air heater is electrically connected with the controller and used for supplying hot air into the skylight of the optical observation instrument through the air pipe.

Provided in the present application is a culture apparatus. The culture apparatus comprises: a housing, inside which a closed culture space is formed, the direction from one end of the housing to the other end thereof being defined as a first direction. In the culture space, assemblies are provided in sequence in the first direction: a first assembly, which comprises a light source and a gas supply assembly, the gas supply assembly being configured to provide a gas required by the culture space; and an optical observation assembly, which comprises a shell and a functional portion, the functional portion being arranged inside the shell. A light path structure is provided by the culture apparatus, and by means of the light path structure, a light beam is emitted from the light source, penetrates cultured specimen and a light-transmitting area of the shell, and is received by the functional portion, such that an observation image of the cultured specimen is formed and the observed image is outputted.

Acoustic generating systems are provided. The acoustic generating systems include a handpiece that provides for adjustment of the penetration depth. In preferred embodiments, the adjustment of the penetration depth is provided by adjustment between a fixed part of the handpiece and an adjustable part of the handpiece. In even more preferred embodiments, adjustment of the penetration depth is provided through a plurality of interchangeable adjustable parts each configured to provide for a different penetration depth when coupled to the fixed part. Preferred embodiments further include an optical system that provides imaging of the treatment surface and is capable of adjusting to the change in penetration depth to continue to provide imaging of the treatment surface. In some embodiments, the interface between the fixed part and adjustable part of the handpiece passes through a chamber that holds a liquid acoustic coupling medium.

This invention discloses a method, system, and fluorescent mixed-spray device for detecting and evaluating inclined roadways in open-pit mines. The method includes: performing fluorescent material spraying and optical observation in at least two boreholes along the target exploration line; determining the spatial connectivity of roadway cavities between boreholes based on the observation results; acquiring roadway profile area data perpendicular to the exploration line at each borehole location for roadway sections determined to be connected; calculating a quantitative index characterizing the degree of profile morphology change based on the profile area data; and adaptively selecting a corresponding volume calculation model to calculate the volume of the roadway cavity based on a comparison of the quantitative index with a preset threshold. This invention combines rapid qualitative assessment of spatial connectivity based on fluorescence with accurate adaptive volume calculation based on morphological variation coefficients, using a single integrated technical process to simultaneously solve the problems of high exploration costs and low calculation accuracy in traditional methods.

The invention discloses an optical observation correlation method based on mixed multi-hour ephemeris, and belongs to the technical field of space target monitoring. Aiming at the problem that the correlation performance is reduced when the ephemeris quality is unstable due to dependence on a single ephemeris in the prior art, the method comprises the following steps of: firstly, constructing a mixed set containing multi-source ephemeris; secondly, intelligently selecting a leading ephemeris and a lagging ephemeris which are closest in time for each observation arc section and each target; then, the two ephemeris are used for association respectively, and union sets of results are obtained, so that an initial association set is expanded; and for the generated fuzzy correlation, performing primary disambiguation based on the comprehensive confidence, and performing secondary accurate disambiguation on the residual fuzzy condition by comparing the weighted angular distance residual error root-mean-square value of the whole arc section. According to the method, the dependence on single-term and single-source ephemeris precision is effectively reduced, available information is fully utilized, and the correlation robustness and accuracy of optical observation data under the complex ephemeris condition are remarkably improved.

The present invention discloses an intelligent arc segment correlation method based on the minimum optical tolerance domain, belonging to the field of intelligent computing optimization for space target surveillance, which solves the problem of large computational volume of arc segment correlation, and includes: constructing a minimum optical tolerance domain from the first observation arc segment; uniformly sampling in the minimum optical tolerance domain, and propagating the orbit of each sampling point under the J2 perturbation model to obtain the theoretical optical observation data of the second observation arc segment and calculating the root mean square error of the angle of the second observation arc segment to obtain an angle loss function; using the DBSCAN clustering algorithm to identify the wave valleys; selecting the initial value of the simplex method in each wave valley to obtain the optimal angle solution; calculating the probability loss function by the Bayesian theorem; substituting the optimal angle solution into the probability loss function and using the LM algorithm to obtain the optimal probability solution; setting a threshold according to the chi-square distribution of the probability loss function, and when the optimal probability solution is less than the threshold, the two arc segments are successfully correlated; the present invention saves computational costs and improves the accuracy of space target observation.

The invention discloses a single-particle electrode material rate capability characterization method based on optical imaging. Comprising the following steps: constructing an electrochemical test configuration allowing optical observation, executing constant-current charging and discharging under a controlled magnification, synchronously acquiring optical data, defining characterization parameters related to the magnification based on the optical data, and evaluating the magnification performance of the single-particle electrode material. According to the method, the real-time response of the particles in the charging and discharging process is obtained through optical imaging, quantitative analysis of the magnification response under the single particle scale is achieved, the problem of particle behavior averaging in a macroscopic test is solved, and the accuracy and the resolution capacity of material performance evaluation are improved. The method is easy and convenient to operate, high in testing efficiency and suitable for high-throughput and high-spatial-resolution characterization of the rate performance of the electrode material.

The invention discloses a crystal growth synthesis furnace which comprises a composite furnace body, a heating and temperature control system, an optical observation window assembly and a growth monitoring and control system. A furnace chamber of the composite furnace body is of a multi-layer gradient composite lining structure composed of a pressure-bearing water-cooled jacket, a carbon fiber reinforced silicon carbide composite material layer, a foam silicon carbide ceramic heat insulation layer and high-purity graphite paper. The heating and temperature control system adopts a distributed design and comprises a main heater, an upper auxiliary heating ring, a lower auxiliary heating disc and a lateral compensation heater. The optical observation window assembly is fixed to the center of the upper furnace cover and matched with the high-speed imaging unit to achieve in-situ monitoring of the growth process. According to the crystal growth synthesis furnace provided by the invention, accurate regulation and control of a three-dimensional temperature field and real-time visual monitoring of a growth interface in a silicon carbide crystal growth process are realized, and the crystal quality, the growth success rate and the process repeatability are remarkably improved.