403results about How to "Suitable for engineering applications" patented technology

The invention discloses a method for analog computation of concentration of a pollutant in a sensitive area. The method is as follows: 1) establishing a coordinate system according to the position of a predicted point of the sensitive area, and determining the position of a non-point source pollution source and coordinates of the predicted point; 2) determining the surface source height of the pollution source; determining the wind speed at a discharge site according to the surface source height; 4) determining diffusion parameters; 5) establishing a diffusion model, and inversely calculating emission source intensity of the pollutant according to the concentration of the pollutant at a monitoring point; 6) positively calculating the concentration of the pollutant at the predicted point according to the emission source intensity, and superimposing environmental background value to obtain the actual concentration value of the predicted point; and 7) comparing the positively-calculated concentration, obtained in the step 6), of the pollutant at the predicted point and a environmental standard to judge whether the concentration of the pollutant exceeds the standard. The concentration of the pollutant can be in real time monitored by means of an air automatic monitoring station built in the periphery of an industrial park. By setting up of the pollutant diffusion model, a calculation scheme for the concentration of the pollutant in the sensitive area can be formed, and diffusion of the pollutant in the industrial park can be forecasted and warned when emission source intensity is unknown.

A structure fatigue life calculation method based on the non-linear cumulative damage theory comprises the following steps: firstly, performing a stress analysis on a metal structure through the finite element technology and determining a large-stress-value area as a dangerous area, secondly, determining initial damage of the structure according to a served age and surface quality detection of the structure, thirdly, measuring a stress spectrum of the structure in a certain period through a stress detector, fourthly, calculating cumulative damage of the structure under the stress spectrum through the non-linear cumulative damage theory, and fifthly, calculating a fatigue life of the metal structure through the cumulative damage. According to the method, the multi-stage load loading sequence and an influence of the size of a load on the cumulative damage are taken into account, and precision of the fatigue life is higher than the precision of a fatigue life calculated according to the linear cumulative damage theory. The method only needs a small amount of material performance data such as a cyclic stress-strain curve and a constant-amplitude strain life curve, calculation is simple, and the method is suitable for engineering applications.

The invention discloses a coupling filler autotrophic denitrification biofilter and application and belongs to the technical field of sewage treatment. Pyrrhotite, sulfur and a carbon source are utilized to be mixed and coupled according to certain proportion; then the materials are put into a reactor, and the autotrophic denitrification biofilter can be formed after inoculating biofilm formation;sewage flows through the biofilter, and nitrogen and phosphorus in the water are removed. The biofilter disclosed by the invention has the advantages of simpleness, easiness, practicability and shortbiofilm formation time; when the biofilter is utilized to treat nitrogen and phosphorus containing sewage, hydraulic retention time is only 0.5 to 3 h, and yielding water can meet a requirement; furthermore, the biofilter has the advantages of excellent nitrogen and phosphorus removal effect, low cost and suitability for engineering application.

The invention discloses a method for calibrating fixed errors of an inertial sensor in an inertial navigation system in real time. The method comprises the following steps of: firstly, establishing a fixed error model of the inertial sensor during the dynamic flying process of an aircraft, wherein the fixed errors include installation errors and scale factor errors; secondly, establishing a state equation and a position, speed and attitude linear measurement equation of a filter, with the fixed errors of the inertial sensor included, on the basis of a random error model of a traditional IMU (Inertial Measurement Unit) and the established fixed error model; and finally, carrying out real-time dynamic calibration and correction to the fixed errors of the inertial sensor during the dynamic flying process of the aircraft, so as to obtain the navigation result of the inertial navigation system after the fixed errors of the inertial sensor are compensated and corrected. The method can realize the calibration and correction of installation errors and scale factor errors of the inertial sensor used in the inertial navigation system during the dynamic flying process of the aircraft, effectively enhances the performance of the inertial navigation system, and is suitable for engineering application.

The invention discloses a multi-level embedded integrated navigation system and a navigation method, belonging to the technical field of integrated navigation. The method comprises the following steps: firstly establishing an aviation airborne inertial navigation system (INS) error state value equation and an inertia/satellite integrated measurement model, then defining a navigation error state value of an embedded inertia/satellite integrated system and establishing an inertia/star sensor integrated measurement model; on that basis, carrying out embedded inertia/satellite integrated system internal integrated navigation resolving and close-loop filtering correction, and finally carrying out external inertia/star sensor integrated navigation resolving and open-loop filtering correction to obtain multi-information fusion navigation results. According to the invention, the complete independent integrated structure of the embedded inertia/satellite integrated system can be kept, and simultaneously the multi-level fusion of inertia/satellite/astronomy asynchronous multi-sensor information and the step-by-step correction of the inertial navigation system are realized, the integrated navigation performance is effectively raised, and the invention is suitable for engineering application.

A nanometer reinforcing method belongs to the technical field of multipurpose use of building wastes and manufacture of building materials. The nanometer reinforcing method of completely-regenerative concrete aggregate mainly comprises the steps of: immersing regenerative coarse aggregate in a nanometer calcium carbonate solution for 30-60 minutes to perform aggregate reinforcement; and mixing the concrete by completely replacing the natural coarse aggregate with the reinforced aggregate. The reinforcing method which combines a reinforcing process with a mixing process effectively reduces procedures and cost, saves time and is suitable for engineering application. The nanometer reinforcing method of completely-regenerative concrete aggregate is mainly characterized in that: the mixing process is changed and nanoparticles are introduced; the micro-fissure and open pores of the regenerative aggregate are filled up with nanometer materials due to the fine particles and high penetrability , thus the strength of the regenerative aggregate is improved; and an interfacial strength between the regenerative aggregate and cement stone is improved and strengthened by a secondary mixing process and the introduction of the nanoparticles, so that the strength and the durability of the completely-regenerative aggregate concrete are improved under the condition of no change of peaceability. The 3-day strength of the completely-regenerative concrete aggregate can be improved by about 30% and the 28-day strength of the completely-regenerative concrete aggregate can be improved by about 20%.

The invention discloses a method for forecasting public building air conditioner short-time base wire load with consideration of real-time weather factors. The method comprises the following steps: S1, calculating correlation between temperature, humidity, air speed, rainfall amount and the air conditioner load by using a Pearson correlation coefficient formula, and selecting strong linear correlation parameters as the real-time weather factors considered during forecasting of the public building air conditioner short-time load base wire; S2, respectively calculating the daily temperature-humidity index THI and a weighed temperature-humidity index THI of the forecasting date and two months before the forecasting date and selecting a typically-similar date of the forecasting date; and S3, calculating the air conditioner load value of 24 hours of the forecasting date by using a BP neural network method. The method can be used for forecasting the public building air conditioner short-time base wire load on a national scale and can also be used for providing theoretical support and data support for applying the typical public building air conditioner load to the regulation of power grid load.

An embodiment of the invention provides an electric-power-system robust state estimation method based on a subsection nonlinear weight function and an apparatus thereof. The method comprises the following steps of constructing a node admittance matrix of an electric power system, a measurement amount measurement equation and a zero injection equality constraint; calculating a jacobian matrix and a measurement-amount residual error of the electric power system and acquiring a weight of each measurement amount; and updating a state variable, determining whether an iteration algorithm reaches a convergence threshold, and if the iteration algorithm reaches the convergence threshold, acquiring a final node voltage amplitude and a phase position of the electric power system. In the invention, bad data detection and identification, and state estimation are simultaneously performed; state estimation calculating is performed, and simultaneously a measurement amount weight can be changed; a bad data weight in iteration is continuously reduced and an influence brought by the bad data is restrained; a calculation amount is effectively reduced and work efficiency is increased; a residual error of the measurement amount is directly introduced into a subsection nonlinear weight function, and standardized residual error calculating is avoided so that a calculating speed can be greatly increased and calculating time is saved; and the method and the apparatus are suitable for an engineering application.

The invention relates to a parameter simulation method for an inertial navigation system of an aircraft. The method can effectively realize separation of dynamic calculation errors in the process of dynamic simulation of the inertial navigation system, eliminates influence of the dynamic calculation errors in simulation on inertial navigation simulation precision, corrects and compensates the dynamic calculation errors of navigation parameters in the navigation simulation process at a simulation output terminal of the inertial navigation system, improves navigation simulation precision of the inertial navigation system, provides bases for type selection of inertial navigation sensors and has a good engineering application value.

The invention discloses a multi-integrated navigation processing device under a launch inertial system and a navigation method of the multi-integrated navigation processing device and belongs to the technical field of integrated navigation of aircraft. The device comprises a sensor module, a navigation processing device and a display module. The navigation method comprises steps of firstly, directly establishing an integrated navigation system state model and measuring model of a guided missile under the launch inertial system, developing an SINS/GPS/CNS (Strapdown Inertial Navigation System/Global Position System Central Nervous System) integrated navigation method under the launch inertial system, carrying out multi-information optimal fusion processing by adopting federal filtering, and finally directly outputting attitude, position and speed parameters of the guided missile under the launch inertial system. According to the device and the method, the SINS/GPS/CNS multi-information fusion processing can be effectively realized under the launch inertial system, a high-precision navigation result is obtained, meanwhile, an efficient support is provided for the engineering implement and application of an SINS/GPS/CNS integrated navigation system.

The invention relates to a rapid calibration and correction method and a TOF camera thereof, and the method comprises the following steps of (1), collecting the related data of the TOF camera at a fixed frequency, including a depth value image, an integral time value, and real distance value data; (2) processing the data obtained in the step (1), and generating related calibration parameters including a global deviation value, a weight lookup table and an FPPN lookup table; and (3) according to the related calibration parameters generated in the step (2), performing distance correction on theTOF camera, including preprocessing, lighting correction and FPPN correction. The method is simple in principle and simple and convenient to operate, can ensure that the TOF camera has higher measurement precision, can meet the speed requirement in the correction process, and is very suitable for engineering application.

The invention discloses a method for calibrating gyro errors online based on star light information assistance in an inertial system, comprising: first, establishing a gyro error model, including a gyro installation error model, a scale factor error model and a random drift error model; then, expanding gyro errors to system state variables, and establishing a combined inertial/start light navigation Kalman filtering state equation and a measurement equation in the inertial system; finally, subjecting the gyro errors to online calibration and real-time correction during dynamic flight of an aerial vehicle to obtain inertial navigation system navigation results with the gyro errors corrected. The method enables effective utilization of star sensor high-precision altitude information during dynamic flight of an aerial vehicle so as to provide online calibration and correction of the gyro errors, improving the performance of the inertial navigation system and adapting to engineering application.

The invention discloses a device and a treating method for treating organic waste gas through concerted catalysis of dielectric barrier discharge and low-temperature plasma and belongs to the technical field of organic gas treatment. Organic waste gas enters a reaction cavity through a gas inlet device after being filtered by a filter bed layer, a low-temperature plasma generation device inhales external air through a fan at the same time, high-energy active particles and ozone generated by dielectric barrier discharge stimulation enter the reaction cavity to oxidize and decompose the organic waste gas, gas flow in the reaction cavity passes through an absorbing catalytic bed layer at the upper portion of the device to be further reinforced and decomposed under catalyst action to generate harmless gas of CO2, H2O and the like which can be emitted on standard. The device disclosed by the invention has the advantages that the low-temperature plasma generation device is separated from waste gas, so that the problems of discharge device corrosion and the like caused by direct contact are avoided, and low-temperature plasma and catalysis are effectively combined to reinforce organic waste gas treatment.

The invention relates to a preparation method of a gas diffusion electrode for producing formic acid by electrochemical reduction of CO2. The preparation method comprises the following steps: 1) adding anhydrous ethanol into powdery conductive carbon black till the powdery conductive carbon black is completely immersed, adding a polytetrafluoroethylene emulsion, performing reaction in a water bath, stirring till the formation of a lump, and then pressing by a roller to form a film, namely a diffusion layer film; 2) deoiling, acid-washing, tinning and drying a copper net to obtain a tinned copper net current collector; and 3) covering the diffusion layer film on the tinned copper net current collector, pressing by the roller, then cutting for formation, placing into a muffle furnace and calcining at the temperature of 3400 DEG C for 20-30min to prepare a target object. The preparation method provided by the invention has the advantages that according to the preparation method of the gas diffusion electrode, CO2 diffusion and mass transfer are strengthened by changing a CO2 transmission path and way of electrochemical reduction reaction of the CO2; and the preparation method has the advantages of simple process and low cost of raw materials, the prepared gas diffusion electrode has high mechanical strength, the electrochemical reduction efficiency of the CO2 is high, and the preparation method is suitable for engineering applications of electrochemical reduction of the CO2.

The invention discloses an online adaptive calibration method for inertial sensor errors of an aerospace vehicle. The method comprises the following steps: establishing an error of an inertial sensor in the high dynamic flight process of the aerospace vehicle, wherein the errors comprise an installation error, a calibration factor error and a random constant value error; establishing a high-order online calibration filter state equation comprising error parameters of the inertial sensor and a measurement equation; and finally, performing online adaptive calibration and real-time compensation on the errors of the inertial sensor in the high dynamic flight process of the aerospace vehicle, thereby obtaining the navigation result of the inertial navigation system subjected to error compensation correction of the inertial sensor. According to the method, the real-time calibration and compensation of the installation error, the calibration factor error and the random constant value error of the inertial sensor of the inertial navigation system can be realized in the high dynamic flight process of the aerospace vehicle, the performance of the inertial navigation system in an aerospace flight environment is effectively improved, and the method is applied to engineering application.

The invention relates to a method and device for realizing the lasting and stable accumulation of nitrite nitrogen under a low-temperature condition. The lasting and stable accumulation of the nitrite nitrogen is completed in two stages of biological aerated filter systems. The method comprises the following steps: step a. starting a first-stage biological aerated filter and a secondary-stage biological aerated filter, cleaning a filter material, soaking, forming a biofilm, commissioning and operating; b. preparing testing wastewater, and maintaining water temperature at 6 to 10 DEG C; c. enabling wastewater to flow out from a head tank and enter the first-stage biological aerated filter from below; and d. enabling yielding water of the first-stage biological aerated filter to enter the secondary-stage biological aerated filter from bottom to top in the same way. The nitration types of the two stages of biological aerated filter are nitrous acid-type nitration, the stable accumulation of NO2--N in the yielding water is shown, the accumulation rate is 63.2% to 79.8%, and the accumulation time is up to 30 to 35 days. The method has the advantages that the biofilm process adopting the two stages of biological aerated filters can be used for solving the problems of high energy consumption at a high temperature (30 to 40 DEG C), and sludge bulking under a low DO (Dissolved Oxygen) condition, and the effective removal of organic matters in wastewater with a low C/N ratio (less than 3) and the lasting and stable accumulation of NO2--N are realized.

The invention discloses a heterodyne full-coherent-terahertz three-dimensional high-resolution imaging system and a method. The system comprises a reception-and-transmission-shared lens antenna, a terahertz linear frequency modulation wave emission module, a terahertz linear frequency modulation wave reception module, an X-Y two-dimensional scanning platform, a signal full-coherent module, a data acquiring and processing module, an image processing module and an image display unit. The system and the method of the invention are provided with a frequency on the terahertz frequency band. The overall system adopts a heterodyne full-coherent design, and a single antenna is adopted. Therefore, the structure of the system is simple and occupies less space. The planar and depth imaging resolution is high in millimeters; and the system frequency and the power stability are both advantageous.

The invention discloses an oil product storage tank safety protection device and protection method. The oil product storage tank safety protection device comprises a gas analyzing unit, an inhibitor supply unit and a control unit, the gas analyzing unit is connected with a mixed gas space formed above the liquid surface of oil product in the oil storage tank, the inhibitor supply unit is connected with the oil storage tank through an inhibitor supply pipe, and the control unit is respectively connected with the gas analyzing unit and inhibitor supply unit. The oil product storage tank safety protection device and protection method are mainly used for flammable and combustible spaces formed by oil evaporation in crude oil storage tanks and product oil tanks, the gas analyzing unit detects the concentration of the mixed gas in the space above the liquid surface of the oil product in the oil storage tank, the inhibitor supply unit fills inhibitor to the surface of the oil product in the oil storage tank, and the filled inhibitor can form a liquid film protection layer at the surface of the oil product and reduce the oil gas evaporation and volatilization of the oil product; the oil gas concentration is reduced through the evaporation of the liquid film, and accordingly the inactive protection for the oil gas space is realized.

The invention discloses a combination weight similarity day selection-based photovoltaic power prediction method and belongs to the photovoltaic power generation technical field. According to the method, based on the basic value point errors of similarity variables, similarity errors are obtained through using a combination weight method, so that similarity days can be determined; the output power of the similarity days is weighted according to different weight coefficients, so that predictive power can be obtained; based on the principle of minimum discrimination information, a subjective weight and an objective entropy weight are combined effectively, so that a combination weight coefficient for similarity day selection can be obtained; and the power weight coefficients are generated according to similarity indexes. As indicated by measured data example simulation of a certain photovoltaic power station, the method can select similarity days with high similarity, improve the prediction precision of photovoltaic output power and benefit grid-connected operation of a photovoltaic power generation system and safe and economic dispatch of a power grid.

The invention discloses a Hough transformation based ground penetrating radar target extraction method and device. According to the method, a target echo signal is collected by using an independently-developed ground penetrating radar model machine, zero alignment is carried out according to the features of radar echo, and then a sliding translation filter is adopted to lower echo image noise caused by power supply noise of the radar model machine; and one the basis, wavelet transformation is adopted to analyze the noise features of the echo, important information including the wave crest and wave trough of the target echo can be detected by setting the threshold, and finally Hough transformation is adopted to extract the hyperbolic curve of the target, thus obtaining the spatial position information of the target. According to the invention, the radar echo signal is processed by adopting wavelet transformation, so that useful information in the signal can be strengthened and guarantee is provided for the reliability of subsequent processing fundamentally; furthermore, the improved hyperbolic Hough transformation effectively improves the extraction precision, greatly reduces the calculated quantity and is suitable for engineering application.