29results about How to "Verify correctness" patented technology

The invention relates to a request comparison method and device applied to UVM verification, computer equipment, a computer readable storage medium and a computer program product, and can be applied to the technical field of computers. The method comprises the following steps: creating a transaction class corresponding to a storage access operation; generating an instance message for storing the access operation according to the transaction class, and storing the instance message into an expected queue; under the condition that the to-be-compared storage access request message meets the protocol condition and the design specification condition, comparing the storage access request message with the instance message in the expected queue to obtain a comparison result of the storage access request message; the comparison processing comprises initial address comparison processing and message length comparison processing; the comparison result is used for determining an access verification result for storing the access request message. By adopting the method, the access verification efficiency can be improved.

The invention discloses an unmanned aerial vehicle group distributed management method based on a mobile active secret sharing technology, which supports off-line of a trusted institution and comprises the following steps: the trusted institution TA generates public parameters; a mobile base station MS and an unmanned aerial vehicle UAV participating in communication respectively register with a trusted mechanism in a registration stage, and acquire information such as a secret key and a certificate; the UAV joins the MS and is administered by the MS, and after mutual identity authentication, the MS distributes secret shares to the UAV; performing identity authentication on the unmanned aerial vehicle group; the unmanned aerial vehicles of the two groups share the share, group fusion is achieved, and after a new share is obtained, each unmanned aerial vehicle updates the certificate of the unmanned aerial vehicle. According to the method, the sub-secrets of the unmanned aerial vehicles are autonomously updated through a mobile active secret sharing technology, and fusion of completely decentralized unmanned aerial vehicle groups is realized. Secondly, an efficient certificate self-updating method is designed. The unmanned aerial vehicle can update the certificate only by calculating a threshold signature. Detailed safety certification and comprehensive experiments show that dynamic autonomous management of the distributed unmanned aerial vehicle group can be realized, and the method has good safety characteristics and relatively low calculation overhead.

The application provides a large-diameter slurry shield safety stability multi-objective online optimization method and system based on GAT-LSTM-MOMPA, and belongs to the technical field of shield tunnel construction parameter multi-objective online optimization. The method comprises the following steps: obtaining monitoring data of shield construction parameters and preprocessing, and establishing an original sample set; adopting a method combining knowledge driving and correlation analysis, input parameters and output targets of a prediction model are determined; a space-time deep learning network framework GAT-LSTM is built, the mapping relationship between the input and the output is determined, and accurate prediction of the future time step optimization value is realized; through connection with MOMPA and TOPSIS, the historical value of the model is constantly updated, and accurate and effective real-time online optimization is achieved. The GAT-LSTM-MOMPA multi-objective online optimization model established by the application effectively improves the safety and stability of the shield machine operation.

The application discloses a kind of multi-party privacy calculation method, device and system based on blockchain, and the method steps include: in task execution phase, task executor receives ciphertext proof sent by trusted third party, ciphertext proof is generated according to the data fingerprint generated by task executor and task publisher generated task ID, and chain is uploaded with task ID and ciphertext proof;In task result verification phase, task executor provides random sampling data to task publisher, to challenge randomly the data used in execution process, verify whether the execution data of task executor contains sampling data, in random challenge, the data fingerprint of the data participating in task by sampling in task publisher is sent to trusted third party with task ID, after obtaining ciphertext proof from blockchain, verify using challenge key to decrypt ciphertext proof.The application has the advantages of simple implementation method, high safety and reliability, verifiable correctness of task execution result, verifiable task work proof and the like.

The invention relates to the technical field of thermodynamic property testing, and particularly discloses a multipurpose thermodynamic property demonstration method and a body measuring instrument, the body measuring instrument comprises a steel shell and a heat insulation cavity sealing cover, the outer wall of the steel shell is provided with a parameter display screen and an input panel, and the steel shell is internally provided with a storage cavity; the portion, located on the outer wall of the containing cavity, of the interior of the steel shell is filled with a heat insulation filling material. The instrument designed by the invention adopts the principle of the Boyle's law, so that the defects of a method for measuring the volume of an object by a drainage method can be overcome, the volume of the object can be quickly and conveniently measured without using water, and the problem that the volume of an object which is difficult to be soaked in water cannot be measured by the drainage method is solved; therefore, the instrument can also be used as a demonstration instrument for verifying the correctness of the Boyle's law and exploring the relationship between the temperature, the pressure and the volume.

This invention discloses a ground-based experimental system and method for onboard autonomous maneuvering mission planning. It utilizes a ground-based telemetry, tracking, and command (TT&C) simulation module to manage TT&C resource constraints, satellite-ground status, and mission requirements based on the test scenario. An onboard computer equivalent module performs autonomous mission planning based on mission instructions generated by the ground-based TT&C simulation module, generating control commands or mission execution sequences. A spacecraft dynamics simulation module determines the satellite's orbit, attitude, and visibility based on the control commands. A space environment simulation module generates sensor simulation data based on the orbit and attitude. A navigation sensor simulation module initiates or terminates the mission based on control commands and generates measurement data based on the sensor simulation data, sending it to the onboard computer equivalent module. A payload execution simulation module simulates the payload's operation process based on the mission execution sequence. This allows for the simulation and comprehensive verification of the entire mission planning algorithm, from mission injection to execution feedback.

This invention provides a stable transmission method, system, and medium for high-concurrency industrial data streams, relating to the field of data transmission technology. The method includes: dynamically grouping industrial field devices to obtain multiple groups of edge autonomous devices, constructing multiple local self-organizing cell network topologies; forming a globally optimized topology based on inter-group logical coupling relationships; performing distributed collaborative verification to obtain multiple valid data streams; performing cross-cell network data association verification to obtain W verified compliant data packets; after time-series packet encoding, reassembling them into an asynchronous transmission channel sequence according to deterministic transmission delay requirements, transmitting them to a central computing platform, and then performing time-series packet decoding, restoration, and storage. This invention solves the technical problem in existing technologies where industrial data transmission typically employs a centralized architecture, which easily creates bottlenecks in the data transmission path, leading to increased data transmission latency or even data loss, thereby reducing the overall system's response speed and security.

The invention discloses a numerical calculation method and system for turbulent combustion difference diffusion of mixed multiple fuels, and belongs to the field of turbulent combustion numerical simulation. Comprising the following steps: establishing a small flame table based on a one-dimensional hedging flame equation, parameterizing a thermodynamic state space into a function of a mixed fraction and a reaction process variable through a mapping algorithm, deducing a difference diffusion term of a multi-fuel component, and establishing and solving a difference diffusion double-equation small flame model control equation suitable for the multi-fuel component under a large vortex simulation framework; discretizing the processing model and coupling a pressure-velocity field; in the process, the same method is used for comparing a small flame model simulation result which does not consider the difference diffusion effect so as to highlight the influence of the difference diffusion effect. According to the method, a difference diffusion two-equation model is expanded to a multi-fuel mixing working condition, dual-fuel turbulence diffusion flame of hydrogen-ammonia mixing combustion is taken as an example, the mass fraction and temperature distribution of main components are compared through a prior method and a posterior method, and the influence of the difference diffusion effect is quantitatively analyzed.

The invention relates to an execution mechanism program verification method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining an execution program of an execution mechanism, placing the execution program in a storage area, obtaining a storage program, carrying out verification calculation on the storage program, obtaining a calculation verification value of the storage program, and carrying out verification calculation on the calculation verification value. Obtaining a comparison verification value of the calculation verification value, and determining a verification result of the storage program according to a comparison result of the calculation verification value and a first preset verification value and a comparison result of the comparison verification value and a second preset verification value; according to the method, the accuracy and the reliability of verification of the storage program are improved, on one hand, the integrity and the correctness of the storage program can be verified, and on the other hand, the integrity and the correctness of the calculated verification value can be verified.

The invention discloses a non-contact sleep eye movement detection method and system based on a biological radar, and the method comprises the steps: transmitting a radar echo signal through a transmitter, receiving the radar echo signal through a receiver, and selecting two paths of time sequences in a target distance in the received radar echo signal through a computer, carrying out autocorrelation processing on the two paths of time sequences to obtain an eye movement periodic characteristic enhanced time sequence, solving a phase in the eye movement periodic characteristic enhanced time sequence to obtain a path of real number time sequence, carrying out fast Fourier transform on the real number time sequence to obtain a power spectrum of the time sequence, and meanwhile, carrying out time spectrum analysis on the power spectrum of the time sequence. The electrooculogram measuring platform is used for synchronous detection, the non-contact detection result is compared with the synchronous detection result of the electrooculogram measuring platform, and the correctness and feasibility of the non-contact detection result are further verified on the basis of achieving non-contact detection of the eye movement of the human body.

The present application relates to a kind of virtual marshalling system station marshalling and test method of departure function, equipment and medium, the method respectively tests virtual marshalling system in station has waist branch's track and station marshalling function without waist branch's track, and in two kinds of scenes, respectively test train FS mode departure and ATO mode departure function;While in the testing process, respectively from the visual interface of vehicle-mounted DMI, dispatching centralized control system CTC, wireless block center RBC maintenance station and interlocking maintenance station observe each step test result in the process of station marshalling. Compared with prior art, the present application has the scene of station marshalling in virtual marshalling system, greatly improves test efficiency and the like advantages.

The invention provides an electromagnetic compatibility test method for a spaceborne synthetic aperture radar antenna and a data transmission antenna, and provides a method for fixing a waveguide slot unit module on a scanning frame in order to solve the problems that time and labor are wasted and repetition exists when a complete synthetic aperture radar antenna state is constructed in a scheme stage. By moving the scanning frame and adjusting the relative position relation between the data transmission antenna and the scanning frame, the electromagnetic compatibility test of the spaceborne synthetic aperture radar antenna and the data transmission antenna is completed. According to the method, the electromagnetic compatibility condition of the synthetic aperture radar antenna and the data transmission antenna can be obtained without constructing a complete synthetic aperture radar antenna, so that the development cost in a scheme stage is reduced; the electromagnetic compatibility test between the spaceborne synthetic aperture radar antenna and the data transmission antenna can be quickly completed, the correctness of electromagnetic compatibility simulation analysis of the two antennas is verified, and data support is provided for optimizing product design.

The space-time constraint intelligent collaborative guidance method and system based on BP neural network belong to the field of collaborative guidance. It solves the existing intelligent collaborative attack target scenario based on estimating the remaining flight time, which is limited to stationary targets. For the scenario of collaborative attack on highly maneuverable targets, there is a low accuracy of estimating the remaining flight time, which leads to low accuracy of highly maneuverable targets. The present invention takes the ballistic data of a single missile under proportional guidance as a training set, trains the neural network, establishes a mapping from the missile state, the target maneuverability characteristics to the remaining flight time, and inverts the trained neural network in the collaborative guidance law design to form a learning method for the initial scenario and can intelligently predict the remaining flight time online, construct the space-time collaborative guidance law of each missile according to the predicted remaining flight time of each missile flying to the maneuverable target, and realize the collaborative attack task of multiple missiles on the maneuverable target. It is mainly used in the game process between missile groups and maneuverable targets.

This application provides a method, electronic device, and storage medium for testing the correctness of vectorization processing. The method includes: automatically enumerating multiple parameter combinations of test condition items (such as data type, broadcast rules, transpose state, etc.) related to the type of the operator to be tested; automatically generating a corresponding input tensor for each parameter combination; and performing vectorization processing and sequential loop processing respectively. By comparing the differences in the outputs of the two processing methods, the correctness of vectorization processing under all parameter combinations can be systematically verified. This overcomes the limitation of manually writing test cases that cannot fully cover multi-dimensional test conditions, and can efficiently and automatically discover boundary errors and numerical instability problems caused by different parameter combinations, thereby more accurately and reliably determining the correctness of vectorization processing.

The invention relates to a full-system flow field performance simulation method for an engine high-altitude simulation test, and mainly solves the technical problem that the real performance of a test system cannot be accurately obtained by an existing method. The method comprises the following steps: (1) performing simulation calculation on the stability of high-altitude simulation work of the engine; (2) performing simulation calculation on high-altitude simulation cooling characteristic distribution of the engine; (3) simulation calculation of high-altitude simulation working characteristics of the engine under different working conditions is completed; and (4) optimizing the design scheme of the test system according to the simulation result, and realizing the simulation analysis of the flow field performance of the whole system of the high-altitude simulation test of the engine. Through the method, the accuracy and feasibility of the test system scheme can be comprehensively and accurately analyzed, so that the correctness of the overall scheme of the engine high-altitude simulation test system is verified, the performance requirements of the test system are ensured, and finally engine test task assessment is completed.

The invention discloses a dynamic modeling and fault simulation method for an RV reducer with a rolling bearing, and belongs to the technical field of mechanical transmission. According to the method, complete three-dimensional modeling and assembling are carried out on all parts in the RV reducer, a tapered roller bearing, an angular contact ball bearing, a needle bearing and other full-class rolling bearings are introduced, and based on Adams multi-body dynamics software, a high-precision dynamics simulation model is established by adopting an IMPACT contact model and a friction model; verifying the working frequency of the model through theoretical calculation, test bed vibration signal acquisition and spectral analysis; on the basis, the difference between the bearing and the traditional model neglecting the bearing is compared, analyzed and considered, and the influence of different types of bearings on the output rotating speed, the gear meshing force and the transmission error is further studied. Meanwhile, a pitting corrosion defect is introduced into the tooth surface of the gear, a gear pitting corrosion fault model is constructed, and simulation and experimental verification of the fault characteristic frequency of the RV reducer are achieved. According to the method, the actual running state of the RV speed reducer can be reflected more truly, the dynamics simulation precision is improved, and an effective technical means is provided for structural design, performance evaluation and fault diagnosis of the RV speed reducer.

The invention discloses an automatic process equipment simulation device based on industrial PLC control, which comprises a main body structure and an electrical control cabinet, and is characterized in that the main body structure comprises a gantry support frame, linear modules, a servo motor, a vernier block, a measuring scale and a measuring seat, and the top of the gantry support frame is provided with a plurality of linear modules with sliding platforms; a servo motor is arranged at one end of each linear module, a vernier block and a measuring scale are arranged on the linear modules, and a laser tracker is mounted in the measuring seat; the electrical control cabinet is installed on the outer side of the gantry supporting frame, a control system is arranged in the electrical control cabinet and comprises an interaction layer, a control layer and an execution layer, and the servo motor controls the start and stop states of the servo motor through the execution layer under the action of the control layer. By adopting the simulation device, the control program is debugged and verified in the design stage, the project development period can be shortened, the manufacturing cost can be reduced, and the simulation device is suitable for popularization and application.

The invention discloses a power distribution network risk assessment and avoidance method considering electric vehicle charging load access. The method comprises the steps of 1, performing prediction and scene division on an electric vehicle charging load by using a long short-term memory network and a K-means clustering algorithm; step 2, based on a complex network theory and a risk theory, establishing a risk assessment index system including a comprehensive risk index of a node and a comprehensive risk index of a line; step 3, establishing an objective function by adopting the minimum risk assessment index as an optimization objective; and 4, according to the established objective function, carrying out iterative optimization on the charging facility site selection scheme by adopting a binary particle swarm optimization algorithm to obtain a new charging facility site selection scheme, and completing risk avoidance. According to the method, the power distribution network risk assessment indexes are established, the site selection scheme of the charging facilities is optimized, the operation risk of the power distribution network is effectively reduced, and the toughness and reliability of the power distribution network are improved.

The invention discloses a detection device and a detection method for the size of a rotor pitch rocker arm, which is used for a foldable coaxial twin-rotor UAV, comprising: a structural support; a torque measuring device, comprising a transmission shaft and a torque detection device, wherein the transmission shaft is horizontally arranged and rotationally connected to the structural support, and the torque detection device is transmission-connected to one or both ends of the transmission shaft to measure the roll control torque or pitch control torque of the UAV; a clamping device, which is fixedly arranged on the transmission shaft and suspended in the air, and a clamping cavity is provided on the clamping device, and the axis of the clamping cavity is perpendicular to the axis of the transmission shaft, and is used to install the UAV to be measured. The device can directly measure the size of the rotor control torque of the coaxial twin-rotor UAV, and verify whether the size of the actual control torque is consistent with the size of the theoretical control torque, which is more conducive to verifying the size parameters of the rotor pitch mechanism, the correction of the theoretical calculation results, and the design and parameter optimization of the control rate of the later flight control system.

This invention relates to a method for verifying a structured startup module for spaceborne software, belonging to the field of space technology. The invention verifies the structured startup module of spaceborne software, checking whether the software's operating state is consistent with the design under conditions such as initial power-on, reset, system disconnection, and power-off, whether it can transition to the normal operating process, and whether it can guarantee the normal operation of the spacecraft. This invention verifies, on the one hand, the rationality of the software design and whether it can achieve the expected results; on the other hand, it verifies the correctness of the software logic, verifying the operating logic of the computer upon initial power-on, as well as the correctness of fault logic and process jumps, ensuring the stable operation of the spacecraft in orbit.

The invention particularly relates to a sodium-cooled fast reactor core power measurement method, which comprises the following steps of: replacing a component at a reactor core power measurement position with a test component loaded with a group of detection foils, and carrying out a reactor entry irradiation test on the test component to obtain the power at the reactor core power measurement position; calculating the reactor core power according to the power of the reactor core power measurement position; and taking the average power value of each reactor core power measurement position as the reactor core power. According to the invention, the reactor core power measurement during the low-power period of the sodium-cooled fast reactor is realized.

This invention discloses an automated design method, system, device, and storage medium for spacecraft nominal plans. The method includes: automatically converting the spacecraft's flight program into an initial nominal plan based on an instruction and injection database; selecting a corresponding nominal plan from a pre-established set of nominal plans according to the spacecraft's actual operating conditions, and fusing it with the initial nominal plan to generate a fused nominal plan; reading the spacecraft's telemetry, tracking, and command (TT&C) arc segments and arc segment obstruction times, and automatically generating instruction transmission times within the TT&C and TT&C arc segments based on the instruction transmission intervals and instruction attributes in the fused nominal plan, while avoiding arc segment obstruction times, to obtain an updated nominal plan; and verifying the correctness of the instruction codes, instruction names, and offsets in the updated nominal plan. This invention improves the efficiency and accuracy of nominal plan design, better meets the needs of spacecraft flight control missions, and provides strong technical support for the stable operation of spacecraft.

This invention discloses a photothermal multilayer film device with a dual-aperture structure, its fabrication method, and its applications, belonging to the fields of photothermal conversion devices and micro / nano fabrication technology. The device consists of an array of unit pixel structures, each a dual-aperture structure supported by silicon microbridges, with a pixel line spacing greater than 2 μm. From top to bottom, the unit pixel structure comprises an aluminum black film, a polyimide film, a silicon microbridge, and a silicon substrate, excluding a metal thermally conductive layer. The dual-aperture structure reduces etching stress concentration and improves fabrication success rate by increasing the line spacing; omitting the metal thermally conductive layer allows heat to be retained in the upper film, enhancing infrared emission performance. This device can achieve a 3200×3200 pixel array on a 4-inch silicon wafer, with a photothermal conversion efficiency of 16.32%. This invention solves the problems of low yield and complex structure in existing photothermal thin-film devices, and can be used for infrared scene generation, infrared imaging, and infrared decision-making training for autonomous driving.

The invention discloses an ASC log analysis system and method based on a multimode CAN bus protocol, and the system comprises an obtaining module, an analysis module and a storage module, the obtaining module is used for obtaining an ASC log file, the analysis module is used for analyzing the format of the ASC log file, verifying the ASC log file, carrying out the standardized field conversion of the ASC log file, generating an analysis result list, and storing the analysis result list in the storage module. And the storage module is used for configuring a data storage environment, generating a database, inserting the data of the analysis result list into the database in batches, performing transaction management and counting the data increment of the analysis result list. The method can be compatible with analysis of the ASC logs in multiple formats, the large file processing efficiency is greatly improved, and the query time for positioning a specific CAN ID or a time period is shortened.

The application relates to the technical field of rotor aerodynamics and computational fluid dynamics, and discloses a CFD simulation method for rotor disc chamfering, which comprises the following steps: obtaining a damped flapping dynamics equation according to a flapping dynamics equation of a blade; converting the damped flapping dynamics equation into a second-order ordinary differential equation; obtaining a flapping dynamics response under ideal simple harmonic vibration excitation according to the second-order ordinary differential equation; converting the second-order ordinary differential equation into a first-order ordinary differential equation group; solving the first-order ordinary differential equation group to obtain a flapping angle of the blade and a first time derivative of the flapping angle; performing fast Fourier transform on the flapping angle to obtain a periodic flapping solution; obtaining an aerodynamic moment of the blade on a flapping hinge through flow field calculation; substituting the aerodynamic moment into the second-order ordinary differential equation; solving the second-order ordinary differential equation to obtain a new flapping angle; and obtaining a final flapping angle according to harmonic components of the flapping angle in each rotation period. The application improves the simulation precision of rotor disc chamfering.

This invention provides an autonomous tracking control method for unmanned surface vessels (USVs) that integrates Kalman filtering and deep reinforcement learning, belonging to the field of intelligent ship and autonomous navigation control technology. Addressing issues such as increased drift angle and frequent steering in real-world marine environments, it constructs a control framework that combines Kalman filtering-assisted line-of-sight guidance with deep reinforcement learning. By introducing a Kalman filtering-based line-of-sight guidance algorithm to predict and compensate for drift angle in real time, a target heading is generated, ensuring the USV's speed and direction align with the desired path. A deep reinforcement learning controller learns and outputs the optimal rudder angle control strategy based on state information such as the deviation between the target heading and the actual heading. A composite reward function is designed that considers heading error, drift angle changes, and rudder angle stability, significantly suppressing the frequent steering issues found in traditional control methods. This invention outperforms existing traditional control technologies in terms of track tracking accuracy, rudder angle adjustment smoothness, and robustness under complex sea conditions.

The invention provides a verification test device and method for a radiation noise simulation algorithm, and belongs to the technical field of ship vibration noise control. The verification test device comprises a test model, an actuator, a vibration acceleration sensor, a hydrophone, a signal generator, a power amplifier, a data acquisition instrument and a computer; the actuator is arranged on the test model; the vibration acceleration sensors are distributed on the test model and are used for measuring the vibration response of the test model; the hydrophone is arranged in the water pool and is used for measuring radiation noise generated by vibration of the test model; and the data acquisition instrument and the computer are used for acquiring and processing data of the vibration acceleration sensor and the hydrophone, comparing target radiation noise with actually simulated radiation noise, and verifying the effectiveness of a radiation noise simulation algorithm. The effectiveness and correctness of a radiation noise simulation algorithm are verified, and the problem that the consistency and voiceprint similarity between an underwater radiation noise result simulated through structural actuation and a target spectrum are difficult to verify through an existing method is solved.

The invention discloses an intramedullary nail far-end positioning hole alignment system and method, and relates to the technical field of medical instruments. Comprising a probe, a sensor, a bougie, a controller, a magnetic field generating device and a guide mechanism, the magnetic field generating device is electrically connected with a controller with a display and provides a magnetic field with preset characteristics for the sensor; the sensor is a magnetic sensor, is electrically connected with the probe, is mounted on the probe and is used for acquiring magnetic field induction data; the probe is located at the top of the bougie; the two ends of the bougie are electrically connected with the sensor and the controller respectively, and magnetic induction data obtained by the sensor are transmitted to the controller. The controller generates a magnetic induction curve according to the received magnetic induction data and displays the magnetic induction curve on the display; and the operation device is aligned with the intramedullary nail positioning hole in vitro through the guide mechanism. The posture position of the magnetic field generating device is adjusted to enable a magnetic induction curve to reach a preset curve, and alignment of the positioning hole can be completed. The invention relates to a few components, is low in cost, and can quickly, stably and reliably realize high-precision positioning hole alignment operation.

This disclosure relates to a method for testing the phase of relay protection on a no-load line, comprising the following steps: providing a predetermined current required for testing to the line under test and the line capable of carrying a load through a current booster; measuring whether the voltage wiring and the secondary circuit wiring of the current transformer of the corresponding relay protection device are consistent with those of the line under test and the line capable of carrying a load; after the line capable of carrying a load is energized, measuring whether the phase of the relay protection device of the line capable of carrying a load is correct; if the results of the above measurements are all correct or consistent, it indicates that the phase of the relay protection device of the line under test and the line capable of carrying a load is correct. This method solves the problem that in the past, due to insufficient load current or the inability to connect a load to the line, the phase of the relay protection device could not be tested, resulting in the relay protection device failing to perform normal line protection and affecting the commissioning of primary equipment.