37results about How to "In line with the actual work situation" patented technology

The objective of the invention is to provide a high-precision attitude determination method for a spacecraft attitude motion simulation platform. Equipment used in the method comprises a laser tracker, an intelligent probe, a gyroscope and two industrial control computers, so a ground fully-physical simulation experimental facility is constructed. The method is an improved method for attitude determination based on extended Kalman filtering, acquires attitude information of the spacecraft attitude motion simulation platform by carrying out data-fusion filtering on output information of the laser tracker and the gyroscope, better accords with actual working conditions and has high instantaneity. Measurement equipment used in the invention is easy to install, has high measurement precision and can realize dynamic contactless measurement of the attitude angle and angular rate information of the spacecraft attitude motion simulation platform.

The invention provides a method for reliability modeling and evaluation of a dynamic cascade coupling electromechanical system. The method is based on a physical background of a complex electromechanical system and is capable of carrying out research on reliability of the electromechanical system based on a dynamics response model, and an established reliability network model of the electromechanical system is capable of more accurately describing the characteristics of dynamic, cascading and coupling of the complex electromechanical system, so that reliability of the electromechanical system, which is obtained based on the network model, is more accurate and credible; meanwhile, by utilizing a method of combining dynamics analysis and uncertainty analysis, transfer of uncertain information from a bottom layer to a top layer of the network model is described, and the difficulties that an aerospace mechanism system has a response uncertainty character and system reliability information cannot be obtained through experiment measures due to large experimental expenses, long period, large technical difficulty and expensive product cost are solved.

The present invention discloses a performance detection and analysis test stand of an engineering machinery transmission assembly. The performance detection and analysis test stand of the engineering machinery transmission assembly comprises a pedestal, a transmission to be detected, a torque converter to be detected, a driving motor, a first torque and rotational speed sensor, a second torque and rotational speed sensor, a third torque and rotational speed sensor, an accompanying gear case, a loading motor, a vibration sensor, a noise sensor, a data acquisition card, a controller and an upper computer. The driving motor, the first torque and rotational speed sensor, the transmission to be detected, the second torque and rotational speed sensor, the torque converter to be detected, the third torque and rotational speed sensor, the accompanying gear case and the loading motor are connected in turn, and the loading motor is in power supply connection with the driving motor; the first torque and rotational speed sensor, the second torque and rotational speed sensor and the third torque and rotational speed sensor are in data transmission connection with the upper computer; and the upper computer is in control connection with the driving motor and the loading motor. The performance detection and analysis test stand of an engineering machinery transmission assembly is characterized in that: a transmission and a torque converter are able to perform a performance test in the same working condition and perform a NVH detection to improve the quality of the transmission. The present invention further discloses a performance detection and analysis test method of an engineering machinery transmission assembly.

The invention provides a virtual training system and method for a collaborative operation of a shield tunneling machine for solving the technical problem that in the prior art, the training effect is poor as command data cannot be simultaneously controlled. The training system comprises a virtual scene construction module, a command input module, a command data processing module and a system service module. The training method comprises the following steps: a sensor acquires related data of the shield tunneling machine and transmits the same to the data server; the virtual scene construction module reads data of the data server and configures a virtual environment; the command input module transmits the command data of a programmable logic controller; the command data processing module simultaneously controls the command data; and the system service module imports the simultaneously processed command data into the virtual environment to train the shield tunneling machine and score, analyze and suggest the virtual training process. According to the system and method provided by the invention, a trainee can more directly and clearly understand the problem of his operation, so that the ability of collaboratively solving the problem by the operator is enhanced.

A centrifugal fan volute structure comprises a volute top plate, a volute bottom plate and a volute surrounding plate; a volute molded line comprises a starting line HA and a finishing line FG; the centrifugal fan volute structure is characterized in that the volute molded line between the starting line HA and the finishing line FG is a spiral line; the spiral line comprises a starting spiral line AB connected with the starting line HA, a finishing spiral line EF connected with the finishing line FG and a middle spiral line connected between the starting spiral line and the finishing spiral line; spiral angles of the starting spiral line AB and the finishing spiral line EF are smaller than a spiral angle of the middle spiral line. According to the centrifugal fan volute structure, the spiral line between the starting line and the finishing line is divided into the starting spiral line AB, the finishing spiral line EF and the middle spiral line, and the spiral angles of the starting spiral line AB and the finishing spiral line EF are smaller than the spiral angle of the middle spiral line, so that the designed volute structure meet the actual working conditions; the static pressure close to the starting line is improved and the efficiency close to an optimal working condition is improved, so that the pneumatic and noise performances of a fan are better.

A centrifugal fan volute structure comprises a volute top plate, a volute bottom plate and a volute surrounding plate; a volute molded line comprises a starting line HA and a finishing line FG; the centrifugal fan volute structure is characterized in that the volute molded line between the starting line HA and the finishing line FG is a spiral line; the spiral line comprises a starting spiral line AB connected with the starting line HA, a finishing spiral line EF connected with the finishing line FG and a middle spiral line connected between the starting spiral line and the finishing spiral line; spiral angles of the starting spiral line AB and the finishing spiral line EF are smaller than a spiral angle of the middle spiral line. According to the centrifugal fan volute structure, the spiral line between the starting line and the finishing line is divided into the starting spiral line AB, the finishing spiral line EF and the middle spiral line, and the spiral angles of the starting spiral line AB and the finishing spiral line EF are smaller than the spiral angle of the middle spiral line, so that the designed volute structure meet the actual working conditions; the static pressure close to the starting line is improved and the efficiency close to an optimal working condition is improved, so that the pneumatic and noise performances of a fan are better.

The invention provides a virtual training system and method for a collaborative operation of a shield tunneling machine for solving the technical problem that in the prior art, the training effect is poor as command data cannot be simultaneously controlled. The training system comprises a virtual scene construction module, a command input module, a command data processing module and a system service module. The training method comprises the following steps: a sensor acquires related data of the shield tunneling machine and transmits the same to the data server; the virtual scene construction module reads data of the data server and configures a virtual environment; the command input module transmits the command data of a programmable logic controller; the command data processing module simultaneously controls the command data; and the system service module imports the simultaneously processed command data into the virtual environment to train the shield tunneling machine and score, analyze and suggest the virtual training process. According to the system and method provided by the invention, a trainee can more directly and clearly understand the problem of his operation, so that the ability of collaboratively solving the problem by the operator is enhanced.

The embodiment of the invention discloses a path optimization method and system for garbage collection and transportation. The method comprises the steps of acquiring the position information and garbage weight information of all garbage cans in a target area and garbage collection and transportation related information of all garbage collection and transportation vehicles; obtaining a plurality of pieces of path optimization scheme information according to given limiting conditions, the position information and the garbage weight information of all the garbage cans and the related garbage collection information of all the garbage collection vehicles; calculating the garbage clearing cost of the multiple pieces of path optimization scheme information according to a preset garbage clearingcost rule; and performing the ascending sorting on the garbage collection costs of the multiple pieces of path optimization scheme information, and a preset number of pieces of path optimization scheme information are displayed according to the sorting. According to the path optimization method, the operation cost of the garbage collection vehicle is considered according to an algorithm, and the operation cost of the sanitation vehicle can be effectively reduced.

The invention relates to a method for testing and measuring modal parameters of a ship propeller rotor under real prestress. The method comprises the following steps: designing a whole test flow, namely deducing a test principle, selecting and arranging test facilities and instruments, arranging the test flow, processing test data and the like, and finally, the purpose of measuring the modal parameters of the ship propeller rotor under the real prestress is achieved. According to the method provided by the invention, with the help of test facilities such as a circulating water tank or a towing tank commonly used in the ship and ocean engineering field, the rotor is enabled to be in a stress state the same as that in a real working state by setting the inflow speed and the rotation speed of the rotor of the propeller in a flow field, and meanwhile, modal parameters are measured, so that the modal parameters of the rotor in a real stress state can be accurately obtained. Compared with a common marine propeller rotor modal parameter test at present, the measurement method provided by the invention better conforms to the actual working condition of the rotor, and the measurement result has higher accuracy and practicability.

The present application relates to a method, an apparatus, a system, and a storage medium for extracting a field enhancement factor. The method comprises: collecting an electrode spacing of an electrostatic transducer and the corresponding current between the electrodes at each deformation time, wherein the deformation time is a moment during deformation of the movable electrodes of the electrostatic transducer under a bias voltage; and fitting a linear relation obtained according to each electrode spacing and each current between the electrodes to obtain a fitting relation, and obtaining thefield enhancement factor of a field electron emission effect of the electrostatic transducer according to the fitting relation. According to the method for extracting the field enhancement factor, itcan be fully considered that after the bias voltage is applied, the electrodes of the electrostatic transducer will be deformed and each electrode spacing will gradually become smaller during the deformation, so that the error caused by each electrode spacing is regarded as a fixed value is avoided. The field enhancement factor obtained by the method is more consistent with the actual working condition of the electrostatic transducer, thereby improving the accuracy of acquiring the field enhancement factor.

The present invention provides a superconducting high-frequency testing system and method, which firstly receives a trigger pulse signal, outputs a periodic high-frequency clock signal; controls the continuity of the high-frequency clock signal, and outputs a high-frequency control clock signal; receives the initial The signal is a linear feedback shift register with a non-zero initial state, and based on the high-frequency control clock signal, multiple periodic pseudo-random sequences with preset cycle lengths are simultaneously output; the circuit to be tested receives multiple pseudo-random sequences and outputs multiple test signals ; receiving the multi-channel test signal, and outputting a multiplexed signal based on a low-frequency clock signal; comparing the multiplexed signal with an expected output result to determine whether the circuit to be tested works normally. The circuit structure of the invention is relatively simple; the input signal is a pseudo-random sequence generated based on a linear feedback shift register, which can realize continuous high-frequency testing and is more in line with the actual working conditions of the circuit to be tested.

The objective of the invention is to provide a high-precision attitude determination method for a spacecraft attitude motion simulation platform. Equipment used in the method comprises a laser tracker, an intelligent probe, a gyroscope and two industrial control computers, so a ground fully-physical simulation experimental facility is constructed. The method is an improved method for attitude determination based on extended Kalman filtering, acquires attitude information of the spacecraft attitude motion simulation platform by carrying out data-fusion filtering on output information of the laser tracker and the gyroscope, better accords with actual working conditions and has high instantaneity. Measurement equipment used in the invention is easy to install, has high measurement precision and can realize dynamic contactless measurement of the attitude angle and angular rate information of the spacecraft attitude motion simulation platform.

The invention aims at the impeller of a turboexpander in a large-scale air separation equipment, and in particular relates to a structural optimization design method of a blade of a large turboexpander considering defects. On the basis of the original impeller stress analysis, the present invention adds defect factors, uses the generalized regression neural network and the multi-objective optimization algorithm based on the genetic algorithm to perform genetic optimization operations on the impeller parameters, and finally obtains evenly distributed Pareto optimal solutions as the impeller blade optimization parameters , the optimization process integrates the actual working characteristics of the impeller, the overall strength and structural rigidity of the impeller are high, and the practicability is strong. Under the condition of satisfying the strength requirement of the impeller, the method reduces the stress concentration under the action of defects, improves the working life of the impeller, reduces the weight and moment of inertia of the impeller, and saves materials.

The invention provides a method for reliability modeling and evaluation of a dynamic cascade coupling electromechanical system. The method is based on a physical background of a complex electromechanical system and is capable of carrying out research on reliability of the electromechanical system based on a dynamics response model, and an established reliability network model of the electromechanical system is capable of more accurately describing the characteristics of dynamic, cascading and coupling of the complex electromechanical system, so that reliability of the electromechanical system, which is obtained based on the network model, is more accurate and credible; meanwhile, by utilizing a method of combining dynamics analysis and uncertainty analysis, transfer of uncertain information from a bottom layer to a top layer of the network model is described, and the difficulties that an aerospace mechanism system has a response uncertainty character and system reliability information cannot be obtained through experiment measures due to large experimental expenses, long period, large technical difficulty and expensive product cost are solved.