34results about How to "Compatible with practical engineering applications" patented technology

The invention discloses a method of optimal configuration of a plurality of superconducting fault current limiter based on a sensitivity technology, which comprises the steps of: calculating the three-phase short-circuit current of all nodes in a whole system, and finding b nodes with the short-circuit current exceeding the standard value; determining braches for installation and reliable startup of the SFCLs (superconducting fault current limiter) according to startup conditions of the SFCLs; calculating the sensitivity of self-impedance of each station with the short-circuit current exceeding the standard value, sequencing the stations in a sensitivity descending order, and taking the top a branches as candidate braches for installation of the SFCLs; and taking c candidate braches as optimal branches for a multi-objective optimization algorithm NSGA-II (non-dominated sorting genetic algorithm-II) in next step, determining a scheme with the optimal installation positions of the SFCLs, the number of SFCLs to be installed and the impedance, thereby realizing global optimum configuration. By adopting the method, the search space to be understood is reduced greatly, the speed of calculation is increased, and optimization results are more suitable for actual applications. Meanwhile, the problem of weight selection resulting from conversion of multi-objective optimization to single-objective optimization can be avoided, and a decision-maker can make final decisions according to actual engineering needs.

The invention relates to a rapid high-precision relative pointing control method of a noncoplanar rendezvous orbit, in particular to a feedforward PID (proportion, integration and differentiation) control based rapid high-precision relative pointing control method of the noncoplanar rendezvous orbit, and aims to solve the problem that rapid high-precision tracking-pointing control methods related to satellite attitudes under the noncoplanar rendezvous orbit do not exist in the prior art. The feedforward PID control based rapid high-precision relative pointing control method including adopting an Euler angle for attitude description of a spacecraft, creating dynamical and kinematical equations of the spacecraft, and acquiring an precise expected angle theta according to a noise-containing expected angle z by a Kalman filtering algorithm of a spaceborne computer; designing an attitude control law of each axis according to a formula of ; selecting two parallelly-placed single-frame control moment gyroscopes to control a yaw axis, and selecting two flywheels to control a rolling axis and a pitch axis respectively; calculating gyroscopic moment T and flywheel actual output moment uw to complete rapid high-precision relative pointing control of the noncoplanar rendezvous orbit. The feedforward PID control based rapid high-precision relative pointing control method is applicable to rapid high-precision relative pointing control of the noncoplanar rendezvous orbit.

The invention discloses an optimal controlling method for boiler intelligent combustion based on big data. The method comprises the following steps that firstly, the DCS data of a unit is collected and processed to form neural network training samples, and then a combustion optimization neural network model is established according to the training samples; then combustion parameters are optimizedby using multi-objective non-dominated fast sorting genetic algorithm (NSGA) according to the combustion optimization neural network model; and finally, optimization bias is calculated according to the optimized combustion parameters and sent to a DCS for realizing closed-loop optimization control. According to the optimal controlling method for boiler intelligent combustion based on big data, because the big data is adopted and the data of boiler ash blowing conditions is eliminated, the quality of the combustion optimization neural network model is improved; the optimization performance andoptimization effect are improved by adopting the multi-objective genetic algorithm optimize combustion parameters, and the optimal controlling method can adapt to the various optimization requirementsin practical application; and in addition to the boiler efficiency and the flue gas NOx emission of the optimizing objectives, the temperature difference index of smoke on both sides of a chamber outlet is further considered, and the optimal controlling method is more suitable for practical application of engineering.

The invention discloses a high-order nonsingular terminal slip mode control method applied to a two-stage magnetic head positioning system of a hard drive. The method comprises the following steps of: establishing a kinetic model of a flexible access arm system under the consideration of a flexible mode and the uncertainty of model parameters; and putting forward a three-order nonsingular terminal slip mode control method for permodeing one-time low-pass filtration on a control signal to effectively weaken the phenomenon of buffeting. In the method, a Lagrange method and an assumed mode method are used for deriving a dynamical equation of a flexible access arm two-stage system, and an output redefinition method is adopted for decomposing the flexible two-stage system into an input-output subsystem and an internal subsystem. Specific to the input-output subsystem in combination with two-order nonsingular terminal slip mode control and linear slip mode control, a three-order nonsingular terminal slip mode controller is designed, the converging characteristic of the system within limited time is proved through a Lyapunov stability theory, and the effectiveness of the method is verified by emulating with Matlab/Simulink software.

The invention discloses an input-limited finite time attitude cooperative tracking fault-tolerant control method, and belongs to the technical field of multi-spacecraft formation flight. In order to reduce communication paths and avoid resource waste, a communication topological structure which has less communication traffic, comprises a directed spanning tree taking a navigator as a root node andonly has a part of followers capable of obtaining navigator information is adopted among spacecraft formation members. In order to enable a following spacecraft which cannot obtain pilot informationto obtain reference information, a distributed finite time state observer is designed to observe the pilot information. Considering communication bandwidth limitation, actuator fault and saturation, system uncertainty and external interference, based on a finite time algorithm, a redundant fault-tolerant algorithm, an adaptive algorithm and a saturation function, a finite time attitude cooperativetracking fault-tolerant control strategy is perfected, and the robustness and practicability of the control system are further improved.

The invention discloses a segmentation-based super-low altitude flight control method for a pilotless aircraft. The method comprises the steps of: judging the flight mode of the pilotless aircraft according to a preset flight mode judging condition of the pilotless aircraft, wherein the flight mode is divided into super-low altitude flight mode, super-low altitude level-off flight mode, and super-low altitude quitting flight mode; determining the longitudinal segmented flight control strategy of the pilotless aircraft in the super-low altitude flight mode according to the judgment result, anddesigning the longitudinal segmented control law of the pilotless aircraft; and refining specific control logic and control law parameters. According to the segmentation-based super-low altitude flight control method for the pilotless aircraft, the pilotless aircraft can enters super-low altitude flight mode in a relatively stable posture under a small disturbance environment; the flight range isshortened, and the oil consumption is reduced; and after the pilotless aircraft quits the super-low altitude flight, the pilotless aircraft can climb at the maximum dynamic pressure with an allowed overload, and then enters a second super-low altitude flight or returns.

The invention discloses an attitude cooperative tracking control method for a distributed spacecraft, and relates to the technical field of spacecraft formation flight. A communication topological structure which has few communication paths and only enables a part of followers to obtain pilot information is adopted among spacecraft formation members, and in order to obtain the pilot information, adistributed finite time state observer is designed to observe the pilot information; a rapid nonsingular terminal sliding mode control algorithm is adopted to enable the attitude of a formation spacecraft to be rapidly coordinated and tracked, a saturation function is input to limit the amplitude of a control moment, and a self-adaptive algorithm is adopted to perform self-adaptive compensation on inertia change and external disturbance. A distributed spacecraft formation adaptive finite time attitude cooperative tracking control method is designed. According to the method, the considerationof communication resources, input saturation, rapid convergence, external interference and inertia uncertainty is more perfect, the formation spacecraft attitude cooperative tracking error system canbe rapidly converged, and the robustness and practicability of the system are improved.

The invention belongs to the technical field of automobile engineering, and particularly relates to a method for predicting the fatigue life of a wide-body mining vehicle frame. The prediction methodcomprises the following steps: 1, extracting an acceleration signal on an axle head of the wide-body mining vehicle through a test; 2, establishing a whole vehicle rigid-flexible coupling model; 3, performing virtual iteration on the acceleration signal to convert the acceleration signal into an axle shaft head displacement signal; 4, inputting the axle head displacement signal into the whole vehicle rigid-flexible coupling model, and calculating and obtianing a change curve of the load at each connection point of the vehicle frame and other structures along with time; 5, performing static simulation analysis on the frame flexible body model, namely a finite element model; and 6, inputting the S-N curve of the frame material, the frame static analysis result file and the change curve of the load of each connection point along with time into software nCode for calculation. According to the method, the dangerous position with the short fatigue life of the frame can be accurately found through simulation analysis according to the axle shaft head acceleration measured by the test, and the fatigue life of the frame of the wide-body mining vehicle is predicted.

The invention discloses an adaptive terminal dynamic sliding mode control method based on active disturbance rejection. ESO is introduced, the ESO can estimate the state and the total disturbance of the system in real time only according to input and output information of a controlled object, more model information is provided for the design of sliding mode control, the total disturbance of the system is estimated in real time by using ESO, the total disturbance is compensated through a control law, the control gain can be reduced, and the control energy consumption can be reduced. In addition, the control precision can be improved by adding the information of the total disturbance into the design of the controller. In combination with a dynamic sliding mode control idea, the buffeting problem existing in traditional sliding mode control can be reduced to a great extent; in combination with a terminal sliding mode control idea, it can be ensured that the state of the controlled objectconverges to a balance point within limited time; actual conditions are fully considered, the upper bound of unknown part information of the system does not need to be acquired in advance by designingadaptive gain, and the problem that the upper bound of disturbance information in an actual system is difficult to acquire is solved.

The invention discloses a waveguide invariant estimation method based on a deep sea vertical array, which relates to the technical field of underwater acoustic parameter estimation, can estimate waveguide invariants under two conditions of known and unknown target distances, and is simple and convenient. The waveguide invariant estimation method is characterized by comprising the following steps of: S1, establishing a function relationship among a waveguide invariant beta, a multipath time delay parameter bv, a signal arrival glancing angle theta, an arrival time delay t and a target distance R; S2, utilizing a target radiation sound signal received by a vertical hydrophone array deployed at a deep sea bottom, and carrying out short-time frequency domain beam forming processing on the target radiation sound signal to obtain a beam time delay diagram; S3, carrying out clustering on the wave beam time delay diagram and extracting a wave beam peak point and a corresponding time delay value; S4, carrying out curve fitting by using a least square method aiming at the head of the extracted wave beam peak so as to solve multipath time delay parameters; and S5, aiming at different target distance prior information, combining actual measurement multipath time delay parameters to estimate waveguide invariants.

The invention discloses a mixed composite material layering method considering multi-scale uncertainty. The method comprises the steps of selecting an alternative material set, obtaining the microscopic attributes of the alternative material set, and obtaining the distribution type of macroscopic attributes of the alternative material set through a multi-scale analysis model; determining a macroscopic finite element model of the alternative material set by utilizing the macroscopic attributes and the distribution types of the macroscopic attributes; constructing a neural network model of the microscopic attributes of the alternative material set and the mixed composite material parameters, calculating a mean square error MSE for the trained neural network model, and judging the accuracy ofthe trained neural network model according to the mean square error MSE; and optimizing the selection of the alternative material set and the selection of the layer stacking sequence by using a genetic algorithm. According to the method, multiple optimization algorithms are used, so that the burden of designers and computers is greatly reduced, the calculation speed is greatly increased, the optimization accuracy is also improved, Meanwhile the method is more suitable for engineering practical application.

The invention provides a multi-channel adaptive beam forming method based on an LCMV criterion, is suitable for radar communication sidelobe anti-interference application, and belongs to the field of array signal processing. Compared with a traditional beam forming algorithm, the method has the advantages that sub-array division is carried out on the array plane according to the actual array plane structure and engineering requirements of the radar, the multi-channel signal model is generated, adaptive beam forming is carried out by using the LCMV criterion, and the method is high in real-time performance and easy to implement. Compared with a traditional beam forming algorithm, the method has the advantages that the operation speed is higher under the multi-channel condition.