65 results about "Power system design" patented technology

The invention discloses a spacecraft power system energy analysis simulation platform which comprises a data input module, a data processing module, a data display module, a power system energy balance analysis judging module and a power system energy balance analysis exception alarm module. A user directly sets the power system designing parameters through the data input module; the data processing module processes and operates the read-in data; and the data display module outputs a visual result. The data processing module is used as the core of the simulation platform, and performs quick and effective data processing through logic analysis; and without a complicated circuit, the simulation platform can be used to perform spacecraft on-track energy balance analysis after the design of power system parameters is finished. The spacecraft power system energy analysis simulation platform greatly reduces the design time of the developing designers, and can quickly correct errors in the power system design.

An approach to modeling the nonlinear steady-state behavior of an electrical power grid in terms of equivalent circuits with currents and voltages as state variables is provided. Current and voltage conservation equations are formulated with circuit-theoretic algorithms that offer demonstrably superior robustness relative to traditional approaches. Generalized bus and line models are accommodated by the equivalent circuit-based approach, allowing for simulation of physical models not compatible with traditional methods. Unbalanced three-phase systems are handled without loss of generality. The provided methods allow for robust, efficient power flow simulation for contingency analysis, power system planning, power system design, power system control, component configurations and operating conditions, real-time scheduling, and optimization, among other applications.

The invention discloses a method for automatically forming patterns in the design of a power system of a thermal power plant, and belongs to the technical field of thermal power plant engineering design department power system design. The method comprises the following steps of: 1, establishing an interaction interface under a computer aided design (CAD) platform; 2, establishing standard electric equipment blocks; 3, defining the attributes of all the electric equipment blocks; 4, establishing CAD patterns of single devices in a power system deployment diagram; 5, establishing the CAD patterns of the single devices of a power system device list; 6, establishing the CAD patterns of the single devices of a power system terminal board outgoing line; 7, defining the standard format of a power system cable inventory; and 8, generating a finished product. By the method, the technical problems of power supply device missing, writing errors, finished product format non-uniformity and the like in the conventional power system design methods are solved.

The invention discloses a solar PVT thermoelectricity co-supplying system driven by a refrigerant pump. The solar PVT thermoelectricity co-supplying system driven by the refrigerant pump comprises an electrical power system and a refrigerant mechanical circulation solar heat pump system, and the electrical power system and the refrigerant mechanical circulation solar heat pump system are relativelyindependent; the refrigerant mechanical circulation solar heat pump system comprises a water subsystem and a refrigerant subsystem; a circulating water pump is adopted as power drive for the water subsystem, and the water subsystem comprises a heat storage water tank, the circulating water pump and a plate type heat exchanger. The refrigerant subsystem is driven by a refrigerant pump, and comprises an efficient solar thermoelectricity co-generation component, a plate type heat exchanger, the refrigerant pump, and a liquid storage tank, the refrigerant pump sends liquid refrigerant in the liquid storage tank into a heat exchanging tube flow channel of the efficient solar thermoelectricity co-generation component, refrigerant vapor in the heat exchanging tube flow channel enters the plate type heat exchanger, and conducts heat exchanging with water in the plate type heat exchanger, when the refrigerant vapor is condensed into liquid, heat is released at the same time, and then the condensate refrigerant is converged into the liquid storage tank. The electrical power system is designed into a grid combining power generation system, a mains supply complementary off-grid power generation system and an energy storage and microgrid system, and the grid combining power generation system, the mains supply complementary off-grid power generation system and the energy storage and microgrid system are synergetically and cooperatively used and flexibly transformed and switched.

The invention relates to a connecting apparatus and a mounting method for a 110kV outdoor cable terminal, and belongs to the technical fields of design, mounting and overhaul of an electric power system. The connecting apparatus comprises a copper-aluminum transitional equipment wire clamp, wherein the copper-aluminum transitional equipment wire clamp comprises a compression-joint pipe and a copper-aluminum transitional plate below the compression-joint pipe; the copper-aluminum transitional plate comprises an aluminum substrate and a copper surface layer; a copper wing plate which is fitted with the side wall of one surface of a copper terminal is arranged on the copper-aluminum transitional plate of the copper-aluminum transitional equipment wire clamp; the copper-aluminum transitional equipment wire clamp and the copper terminal are fastened into one body through fastening parts; and the exteriors of the copper terminal and the copper-aluminum transitional equipment wire clamp are sleeved with a cylinder-type thermal shrinkage pipe for isolating air and fastening each part. The connecting apparatus is simple in structure and capable of effectively preventing the joint place between a wire-outlet terminal of the dry-type cable terminal and the copper-aluminum transitional equipment wire clamp from being subjected to oxidization, heating and blackening, so as to achieve a life cycle.

Embodiments of the present invention disclose systems and methods for the efficient conversion of solar energy into a useable form of energy using a solar collector subsystem and a heat conversion subsystem. The systems and methods transfer solar energy directly to an intermediate solution and a working solution and indirectly to and between a basic rich solution, a condensing solution, a lean solution and a rich vapor solution. The systems and methods also include condensing the basic rich solution using an external coolant. The systems and methods support a closed thermodynamic cycle.

The invention provides a DC / DC converter structure for a high-gain fuel cell vehicle and a control method and belongs to the field of power system design and application for new energy vehicles. The DC / DC converter structure comprises an upper bridge circuit and a lower bridge circuit which are symmetrically arranged in structure and are connected in parallel, wherein the upper bridge circuit comprises a first inductor, a second switch tube, a second inductor, a second conducting diode and a first capacitor connected in series; a positive electrode terminal of a fuel cell is connected with a first switch tube through the first inductor and then connected to a negative electrode terminal of the fuel cell; the positive electrode terminal of the fuel cell is connected to a midpoint of the second switch tube and the second inductor through a first conducting diode; and the midpoint of the second inductor and the second conducting diode is connected with the negative electrode terminal of the fuel cell through a third switch tube. According to the DC / DC converter structure, the disadvantage of a low boost ratio of a traditional boost topology is avoided, the disturbance of input voltageto output voltage during wide range variation is offset and the overhigh cost is avoided.

The invention discloses a shield optimization design method for loosening and stripping a sandy gravel stratum based on a wedge coulter. The method comprises the following steps of determining a shield wedge coulter form for loosening and stripping the sandy cobble stratum, and adopting a shell type wedge coulter; calculating the limit loads borne by the wedge coulter at different positions when the stratum is loosened and stripped, and determining the arrangement mode of the alloy blocks; determining the heights of the alloy blocks according to the stratum abrasiveness and interval characteristics; according to the limit loads borne by the wedge coulter, calculating the cutting force and the jacking force needed by the wedge coulter, and preferably selecting a cutter appearance characteristic parameter design scheme; performing targeted optimization design on the wedge coulter; and calculating the power required by the wedge coulter to loosen and strip the sandy gravel stratum, and configuring a power driving system of a shield tunneling machine according to the calculated required power. According to the method for loosening and stripping the small and medium particle size gravel-cobble stratums through the shield wedge coulter, the blank of stress research on the wedge coulter is filled up, and a theoretical basis is provided for the shield model selection and the shield power system design.

A process for supplementing steam reformation with hydrogen, oxygen and heat from dissociation of hydrogen peroxide (H2O2). Steam reforming suffers from starting the overall system in an endothermic manner which leads to long start times and limited turndown capability in delivering high quality hydrogen. Using a material such as hydrogen peroxide in a controlled manner allows for instant generation of oxygen-enriched steam, an essential state in reforming hydrocarbons. It additionally, offers the opportunity to relieve parasitic power requirements associated with compressing air to reach the O2 density required for the reforming process and eliminates, or minimizes (as a function of overall power system design requirements) post process cleanup of nitrogen-oxides.

The invention relates to electrical field and discloses a method for establishing a three-phase short-circuit current correction curve of a 380V power system. The method comprises: S1) computing resistance R and reactance X between the high-voltage side of a transformer and a short dot; S2) computing impedance Z between the high-voltage side of the transformer and the short dot according to the resistance R and the reactance X between the high-voltage side of the transformer and the short dot; S3) computing short-circuit current Id according to the impedance Z between the high-voltage side of the transformer and the short dot; and S4) establishing a three-phase short-circuit current correction curve according to a functional relationship between the length L of a cable from the initial end to the short dot and the short-circuit current Id. The three-phase short-circuit current correction curve established by the method is more accurate and the method contributes to more accurate computation of three-phase short-circuit current of the 380V power system for power system designers.

The invention discloses an icing flashover influencing factor evaluation method for overhead lines under surge and power frequency superimposed voltage. The icing flashover influencing factor evaluation method for overhead lines under surge and power frequency superimposed voltage applies the power frequency voltage to an overhead line through a power frequency voltage generating unit, and then applies the surge voltage to the overhead line through a surge voltage generating unit, to simulate the situation that the overhead line is subjected to lightning and the operation is overvoltage so asto reproduce the actual complex condition for operation of the overhead line. The icing flashover influencing factor evaluation method for overhead lines under surge and power frequency superimposed voltage can not only preferably simulate the icing situation of an insulator in a natural environment, but also can simulate the icing flashover fault of the overhead line under the pollution level condition in different areas, so as to obtain the relationship between the surge flashover voltage and the conductivity of the salting liquid of an ice layer of the surface of the ice-covered insulator to evaluate the influencing factors of icing flashover to find the weakest link and provide the basic data and opinions for power system design with the flashover voltage that is the easiest to flash.

The invention discloses a spacecraft power system multi-objective optimization design method, system, and a storage medium. The method comprises the following steps of establishing an objective function based on a spacecraft power system pre-optimization objective; determining design variables of the objective function; determining constraint conditions of the objective function; according to theobjective function, building a power model and an external environment model of a spacecraft power system; by using an optimization algorithm, calling the power model and the external environment model of the spacecraft power system to perform simulation, and under the design variables and the constraint conditions, performing multi-objective optimization design by taking the objective function asan objective, thereby obtaining Pareto optimal solutions; and in combination with preference information of a power system designer, from the Pareto optimal solutions, selecting one as a final spacecraft system design scheme. The method lowers the difficulty in comprehensive quantitative analysis of spacecraft power system design, and realizes the multi-target optimization of the spacecraft powersystem.

The invention relates to a device for preventing a 110kV outdoor full-prefabricated dry type cable terminal from being heated and a mounting method of the device, and belongs to the technical field of design, mounting and maintenance of power systems. The device comprises two copper-aluminum transitional equipment wire clamps, wherein the copper-aluminum transitional equipment wire clamps comprise pressure connection pipes and copper-aluminum transitional plates arranged below the pressure connection pipes; the copper-aluminum transitional plates comprise aluminum base plates and copper surface layers closely attached to copper wiring terminals; a copper wing plate is arranged on the copper-aluminum transitional plate of one copper-aluminum transitional equipment wire clamp; a copper wing plate attached to the other side wall of the copper wiring terminal is arranged on the copper-aluminum transitional plate of the other copper-aluminum transitional equipment wire clamp; the two copper-aluminum transitional equipment wire clamps are fastened with the copper wiring terminals through fasteners to form a whole; fork type heat shrink tubes are arranged outside the copper wiring terminals and the two copper-aluminum transitional equipment wire clamps in a sleeving manner. The device is simple and effective in structure, can prevent joints of a wire outlet terminal of the dry type cable terminal and the copper-aluminum transitional equipment wire clamps from being oxidized, heated and blackened, and can realize a total life cycle.

The invention belongs to the technical field of helicopter power system design, and discloses an engine mechanical accelerator operating system for a helicopter, which comprises an accelerator ring, atotal distance rod, a first elastic pull rod, a rotor rotating speed adjusting executing mechanism, a total distance accelerator connecting rocker arm, an output elastic pull rod, a second elastic pull rod and a total distance linkage mechanism, the total distance rod and the total distance linkage mechanism form a total distance pre-input adjusting structure; the rotor rotating speed adjusting executing mechanism and the second elastic pull rod form a rotor rotating speed feedback input adjusting structure; the accelerator ring and the first elastic pull rod form an accelerator ring manual input adjusting structure; the rotor rotating speed feedback input adjusting structure and the manual input adjusting structure are connected in series and connected with the total distance pre-input adjusting structure in parallel through the total distance accelerator connecting rocker arm. The total-pitch accelerator connecting rocker arm is connected to an engine accelerator rocker arm throughan output elastic pull rod, so that the power of an engine output shaft is balanced with the supply and demand of required power of a helicopter, and the rotor rotating speed is kept constant.

The invention discloses a layered progressive design optimization method for a power system of an electric vertical take-off and landing aircraft. The method comprises the following steps: extracting task profile power and energy consumption requirements based on the electric vertical take-off and landing aircraft (eVTOL); designing parameters of the electric power system based on static optimization; and optimizing parameters of the electric power system based on power matching. According to the method, based on hierarchical progressive design of energy conversion and power matching, the defects of a traditional model selection and design method in the aspects of model precision and electrodynamic force performance improvement are broken through, the power system design optimization problem of eVTOLs of different configurations under the condition of a given flight task is solved, the output performance of a power system is improved, the total mass of the eVTOLs is reduced, and the cruising ability of the eVTOL is improved, and the application scene is expanded.

The invention discloses a real-time electrovalence-based household appliance control device and a control method thereof, and belongs to the field of intelligent power system design the technical field of Internet of things. The device comprises an interactive terminal and a receiver, wherein the interactive terminal comprises a microprocessor, a key, a liquid crystal display (LCD), a data memory, a Bluetooth module and a power supply; and the receiver comprises a microprocessor, a Bluetooth module and a switch socket driver. The method comprises that: when a power enterprise issues real-time electrovalence, a user can refer to the specific real-time electrovalence of the other day through the interactive terminal, select a low electrovalence time interval, set the time interval as the working time interval of the interactive terminal and set the highest acceptable value of the electrovalence, and then the user can carry on other activities; and when the real-time electrovalence is lower than the highest acceptable electrovalence value, the receiver of electrical appliance equipment is connected with the electrical appliance power supply, and the electrical appliance starts working. The device and the method have strong pertinence and simple application, and have strong practical significance for guiding residents to intelligent utilize power and reducing power fare expenditure.

The invention relates to the technical field of ship power system design, in particular to a multi-objective optimization design method for a propulsion system, and electronic equipment. Multi-target comprehensive optimization analysis is carried out by taking shafting transmission efficiency as a key point and taking improvement of shafting alignment quality and improvement of vibration characteristics as targets, shafting power consumption can be reduced, and meanwhile, the shafting alignment quality and the vibration characteristics are both improved; by establishing a calculation model of thrust bearing friction power consumption, radial bearing friction power consumption, sealing friction power consumption and rotating shaft friction power consumption, the transmission efficiency of the propulsion system can be accurately and efficiently calculated; and by adopting the finite difference method and mathematical induction, the calculation result of the friction power consumption is more accurate, and the calculation time of the friction power consumption can be effectively shortened.

The invention discloses a new type of passenger car chassis power platform, which includes a lower body frame and a power battery pack. Drive axle. Based on lightweight technology and integrated design ideas, the present invention adopts an integrated design power system and four-wheel independent suspension to realize the light weight of the chassis power platform of a medium-sized bus. The passing performance under the attached road surface enhances the driving safety of the bus on the rainy and snowy road. It not only has a simple structure, compact size, small size, good handling stability, ride comfort and NVH performance, but also simplifies the production and assembly steps of the bus, effectively Increased production efficiency.

The invention discloses a novel cyclone drying device which comprises a drying chamber and a cyclone separator. The novel cyclone drying device is characterized in that the drying chamber is provided with two or more air intakes and an air outlet, the cyclone separator is provided with an air inlet and two exhaust fans, the air inlet is connected with the air outlet, and rotatable air intake barrels are arranged on the air intakes. The novel cyclone drying device is novel in structure, and has unique air power system design, the air-drying efficiency of materials is greatly improved, and the novel cyclone drying device is worthy of application and popularization.

A method for operating a wind turbine power system connected to an electrical grid includes collecting data relating to one or more parameters of one or more electrical components of the wind turbine power system. The method may also include performing a statistical analysis of the data relating to one or more parameters of the one or more electrical components. Further, the method includes predicting future behavior of the electrical component(s) based on the statistical analysis. Moreover, the method includes determining set points for the electrical component(s) using the predicted future behavior. In addition, the method includes operating the wind turbine power system at the determined set points for the electrical component(s) so as to optimize at least one characteristic of the electrical component(s).

The invention belongs to the technical field of helicopter power system design, and discloses a large-overload shock absorber. The large-overload shock absorber comprises a nut, a force bearing connector, a shock absorber upper positioning piece, a shock absorber outer shell, a shock absorber lower positioning piece, a special bolt, first disc springs, second disc springs and a compression spring;the shock absorber lower positioning piece is fixed to a helicopter body structure frame, and the lower portion of the special bolt penetrates through the shock absorber lower positioning piece; andgrooves are formed in the corresponding positions of the shock absorber upper positioning piece and the shock absorber lower positioning piece correspondingly, and the compression spring sleeves the lower portion of a first boss of the special bolt and is positioned through the grooves in the shock absorber upper positioning piece and the shock absorber lower positioning piece. The large-overloadshock absorber has a good shock absorption effect, can bear large overload, and meets the crash resistance.

The invention belongs to the field of design of internal combustion engines and relates to a cam rotor internal combustion engine power system design method, in particular to a cam rotor internal combustion engine design method. In the design method, according to cam lift and size changes, caused by the cam lift, of the contour surface of a cam; other surfaces of the cam are wrapped through the inner surface of an inner cavity rotation surface component, the outer surface of an outer rotation surface component and corresponding end components in a contact sealing mode, and then an unsymmetrical annular gap is formed; the cam is made to do fixed-axis rotation along with one of the inner cavity component and the outer rotation surface component relative to the other one; a set of cam driven parts are mounted on the inner cavity component or the outer rotation surface which is not fixed to the cam. According to the design method, the four classic procedures of the otto cycle are realized through volume change, and the influence on the rotational speed is little. A control system is used in cooperation to realize flexible transformation of various working modes. The adaptability is high. The system is good in designability and especially suitable for being used in cooperation with computers to conduct flexible automatic control.

The invention belongs to the field of helicopter power system design, and discloses a single-engine failure training method for a three-engine helicopter. Compared with a single-engine failure OEI training function of a current helicopter, on the premise that the flight safety is further improved, more real simulation of the real OEI flight state can be achieved. Therefore, a pilot can be trainedto handle the OEI flight state more accurately, the training function can be used for replacing a real OEI flight subject in the test flight process, the test flight evidence obtaining period is greatly shortened, the test flight evidence obtaining cost is greatly reduced, and the flight safety of risk subjects is improved. The method can be applied to three-engine helicopters, and the design logic of the method can also be applied to double-engine helicopters or multi-engine helicopters.

The invention discloses a ship shore power parameter design and performance evaluation method and device, and the method comprises the steps: respectively designing a corresponding grid structure, a boarding mode, a grounding mode, a corresponding power system, an optimal voltage grade selection and a filter after port features and ship features are obtained through port feature analysis, and obtaining a port shore power system design scheme; starting from the electrical design of the shore power system, the parameter design method of the ship shore power system is provided from four aspects of voltage grade selection, grounding system design, wire system design and filter as well as a shore power system design process and a typical shore power system design scheme.

The invention discloses a communication power supply system and an application method thereof. Among them, the system includes an AC power distribution module, a plurality of rectifiers, a DC power distribution module and a monitoring module. The monitoring module includes: a phase wire information acquisition unit, which is used to obtain the phase wire information of the respective phase wires of multiple rectifiers; The information acquisition unit is used to obtain the grid standard information of the power grid connected to the AC power distribution module; the control strategy generation unit is used to generate according to the grid standard information obtained by the grid standard information acquisition unit and the phase line information obtained by the phase line information acquisition unit. A control strategy; a control unit, configured to control the working state of the corresponding rectifier according to the control strategy generated by the control strategy generation unit. The present invention solves the problems of narrow design and use range and poor configuration flexibility of the communication power supply system in the related art.

A propeller retractable integrated cross-media aircraft power system belongs to the technical field of cross-media aircraft. In the present invention, the nose telescopic mechanism is connected to the electromagnetic clutch I on the left side of the power mechanism through a connecting shaft; It is fixedly connected with the aircraft shell, and its left side forms a sliding connection with the secondary transmission rod in the nose telescopic mechanism through a sliding sleeve II; the power mechanism is connected with the aircraft shell through a dual-shaft stepping motor, and its right side is connected by an electromagnetic clutch II. It is connected with the propeller transmission mechanism for water use. The invention can be used for the design of the power system of the cross-medium aircraft. On the premise that the air-use propeller can be retracted, the air-use propeller and the water-use propeller can share a stepping motor, and the integrated design of the power system is completed. The medium aircraft has a good shape and tightness under water, and makes the trans-medium aircraft lighter and lower energy consumption.

The invention provides a module screening method applied to energy storage of a power system, and the method comprises the following steps: S1, starting a program, carrying out the matching calculation of the voltage of the power system, and defining a first input packet; s2, performing installation matching calculation on an energy storage cabinet body of the power system, and defining a second input packet; s3, designing matching calculation for the power system, and defining a third input packet; s4, when the output result of the third input packet is unique, ending the process, and realizing optimal module screening of energy storage of the power system; according to the invention, by setting the input parameters, the energy storage module suitable for a plurality of voltage levels can be calculated.

The invention discloses a spacecraft power system energy analysis simulation platform which comprises a data input module, a data processing module, a data display module, a power system energy balance analysis judging module and a power system energy balance analysis exception alarm module. A user directly sets the power system designing parameters through the data input module; the data processing module processes and operates the read-in data; and the data display module outputs a visual result. The data processing module is used as the core of the simulation platform, and performs quick and effective data processing through logic analysis; and without a complicated circuit, the simulation platform can be used to perform spacecraft on-track energy balance analysis after the design of power system parameters is finished. The spacecraft power system energy analysis simulation platform greatly reduces the design time of the developing designers, and can quickly correct errors in the power system design.