37 results about "Transient response analysis" patented technology

Wellbore wireless thermal conductivity quartz transducer comprising a thermal conductivity quartz transducer and a wireless communication system comprising an external device and an internal device, a cable, and a surface device. The thermal conductivity quartz transducer comprises a first quartz resonator, a heat dissipation element, a second quartz resonator, an electronics circuit and heat guiding means arranged for transferring a heat generated by said electronics circuit to said heat dissipation element, so that said dissipation temperature is higher than said ambient temperature. The invention is also a method for wirelessly performing transient response analysis of a formation in a wellbore with such transducer.

A computer-executed method for determining the earthquake safety prediction of a super-large project in the field of computer technology, using finite element pre-processing software to establish a finite element model, and inputting the parameters required for the time history of earthquake motion; the parameters are transferred to a supercomputer, and artificial earthquake motion is used to The time-history parallel simulation hybrid task assignment method is used to obtain the seismic excitation dynamic time history; the seismic excitation dynamic time history is returned to the finite element pre-processing software for constraint loading, and the task file of the finite element analysis software is obtained and submitted to the finite element analysis software to obtain The mathematical model, the mathematical model and the time step are transferred to the supercomputer, and the parallel processing method of transient response analysis and modal analysis or the parallel processing method of modal analysis is used for parallel calculation; the data is returned to the finite element analysis software for subsequent calculation; limited The meta-post-processing software reads in the calculation results and performs visual processing. The present invention is realized by means of software, which greatly saves manpower, material resources and financial resources for system implementation.

The invention provides an evaluation method of an auxiliary information delay effect in a GNSS / INS deep combination. The method comprises the following steps: (1) establishing the INS auxiliary tracking loop mathematical model of a Laplace domain according to the principle structure of an INS auxiliary tracking loop, (2) according to the INS auxiliary tracking loop mathematical model, establishing the error transmission model between INS auxiliary delay and a loop tracking error, (3) transmitting the error transmission model into a time domain, using a transient response analysis method to simulate the change of the loop tracking error brought by the INS auxiliary delay of the INS auxiliary tracking loop under a dynamic excitation signal. The method can be used for evaluating the effect of the auxiliary information delay to the INS auxiliary GNSS tracking loop performance, and thus the real-time performance design and tracking loop optimization in GNSS / INS deep combination system development are guided.

This disclosure discloses a fast prediction method for the instability limit of a steam turbine rotor system based on shroud zero damping. By establishing a three-dimensional geometric model of the steam turbine rotor system, the modal analysis module and the transient response analysis module of the finite element software are used to obtain the maximum vibration of the system. The adjacent peak value of the transient displacement response of the blade is read from the displacement response curve (A 1 、A 2 ), calculate the logarithmic damping δ and damping ratio ξ of the rotor system considering the shroud friction under the rotational speed and harmonic excitation loads of each order, and quantitatively calculate the shroud damping C at different speeds s . The present invention uses the FFT multi-harmonic balance method to extend the existing modeling of the surrounding band damping considering the influence of the simple harmonic excitation and the quantitative solution method based on the envelope of the transient response to the multi-frequency excitation. The operation process is clear and the calculation is simple. It has high efficiency, provides theoretical basis and methods for the design and manufacture of steam turbine rotor system, and has important theoretical significance and engineering application value for ensuring the safe operation of steam turbines.

The invention belongs to the technical field of structural dynamics and finite element simulation and particularly relates to a dynamic load nonlinear analysis method for a flexible solar cell wing. The invention discloses the following technologies: 1, a finite element modeling method of tensioning mechanisms, a guide mechanism and hanging steel wire ropes of the flexible cell wing; 2, a method for applying a pre-tightening force of the tensioning mechanisms and the guide mechanism in the nonlinear transient response analysis process; 3, simulation of a mechanical property that the hanging steel wire ropes only can bear a pulling force and cannot be pressed in the NASTRAN solving process; 4, a method for improving nonlinear iteration convergence by compensating difference in lengths of the hanging steel wire ropes, which is caused by deformation of storage boxes; and 5, a nonlinear transient response analysis technology under the combined action of a static pre-tightening force and a dynamic inertial force. The dynamic load nonlinear analysis method for the flexible solar cell wing has the beneficial effects of simple method and ingenious design.

The dynamic measurement time domain compensation method includes approximating the measured parameter curve into sectional broken lines and recursion calculation to obtain measured parameter based on the kick point and slope of the broken lines. In determining the kick point and slope of a broken line, the discreet value of sensor output is calculated through analysis and recursion based on the instantaneous response of inertial link, the broken line model is then determined dynamically based the difference between the discreet value and the practical value, and the broken line signal value is finally calculated through recursion calculation based on the broken line model. The said method can raise the dynamic measurement response speed and precision, and the simple time domain recursion algorithm is simple, timely, suitable for realizing with microcomputer assemble language, low in cost, flexible and intelligent, and is suitable for measurement of various physical quantities with sensor being inertial link.

The present invention proposes a thin-walled structure thermal aeroelasticity dynamic response analysis method, according to the thin-walled structure and boundary conditions, the thin-walled structure is discretized into shell elements with seven degrees of freedom, and the ribs are discretized into beam elements with seven degrees of freedom. The thin-walled finite element model is used to obtain the structural finite element grid; the temperature field of the thin-walled structure is applied to the structural finite element grid, and the linear flutter analysis is performed on the finite element model to obtain the unsteady gas corresponding to each reduction frequency k Power matrix Q k , to fit the time-domain expression of the unsteady aerodynamic matrix; iteratively calculate the time-domain expression of the unsteady aerodynamic matrix, analyze the nonlinear transient response of the thin-walled structure, and obtain the nonlinear thermal Aeroelastic dynamic response. The method of the invention can solve the calculation problem of the nonlinear thermal aeroelastic dynamic response of the complex thin-walled structure.

The present invention discloses a carrier transient response indication method based on a star satellite load couple analysis result. The method comprises the following steps of taking carrier or satellite interface time domain acceleration data obtained in the star satellite load couple analysis process as an agreed boundary between the carrier and the satellite in a certain research stage and loading the data to a carrier or satellite docking point in a combined body physical model of the carrier and effective load in a forced acceleration manner, and performing transient response analysis and calculation on the combined body physical model so as to obtain desired carrier or an effective load interface and response data of internal nodes of the carrier. According to the carrier transient response indication method based on the star satellite load couple analysis result, the large difference between boundary impedance and actual flying condition of the frequency response analysis method in response indication is prevented, and calculation number of times are not limited by whole satellite load couple analysis number of times, so that the local improvement effect of the carrier structure can be indicated and evaluated.