82 results about "Thrust coefficient" patented technology

The invention discloses a ship maneuverability prediction method, a ship maneuverability prediction system and a ship maneuverability prediction device taking propeller performance changes into regular waves. The method comprises the following steps: firstly, calculating the motion response, the second-order wave drift force and the drift moment of a ship body under different regular wave conditions based on a potential flow theory, establishing a wave force fitting equation taking the wave direction and the navigational speed as variables, and performing ship manipulation motion numerical simulation in regular waves based on an obtained calculation result; acquiring an input parameter range of the propeller in a manipulating motion state; establishing a CFD numerical model of ship propeller performance in regular waves, simulating heaving and pitching motion of the propeller under motion response, determining the range of the heaving and pitching motion, and calculating propeller thrust data under different wave conditions and input parameters; and carrying out regression analysis on the propeller thrust data, and fitting to obtain a prediction formula of the propeller thrust coefficient in the regular waves. The formula couples the wavelength-to-length ratio, the advance speed coefficient and the wave direction angle, and quantifies the dynamic influence of the wave on the propeller thrust.

The invention relates to the technical field of wind turbine generator wake flow calculation, in particular to a wind power plant whole-field global wake flow analysis method based on yaw control, which comprises the following steps: acquiring wind turbine parameters in a wind power plant and terrain and inflow parameters of an operating environment; comprise the position of a wind turbine, the diameter of a wind wheel, the height of a hub, a yaw angle, a thrust coefficient, the inflow wind speed of flat terrains, the inflow wind speed of complex terrains and turbulence intensity; based on the theorem of momentum conservation and mass conservation, the wake flow transverse offset generated by yaw of the wind turbine is calculated; based on the inflow parameters and the wake flow transverse offset, the downstream wake flow width of the wind turbine is calculated, and the wake flow area range is determined; based on the theorem of conservation of mass and a partial cosine distribution function, calculating the initial velocity loss of the wake flow in the whole field and the whole domain; and on the basis of the inflow velocity and wake velocity loss at the complex terrain, obtaining the full-field and full-domain wake velocity of the wind power plant. By comprehensively considering factors such as complex terrain, wake flow yaw and wake flow interaction, high-precision prediction of the wake flow speed of the wind power plant is realized.

The invention discloses a wind power plant active yaw optimization method and system considering a fatigue load of a wind turbine, and relates to the technical field of wind turbine power generation, and the method comprises the steps: obtaining a wake flow model for calculating the equivalent inflow wind speed of a wind wheel surface of the wind turbine; determining a wind wheel surface equivalent inflow wind speed-yaw angle-thrust coefficient two-dimensional lookup table and a wind wheel surface equivalent inflow wind speed-yaw angle-power two-dimensional lookup table of each wind turbine in the wind power plant; constructing an equivalent fatigue load proxy model of the wind turbine based on a blade aerodynamic load and blade gravity coupling effect; and constructing an optimized objective function by taking power maximization and equivalent fatigue load minimization as objectives, solving the optimized objective function through an optimization algorithm according to the actually measured wind turbine-wind measurement data, the wake flow model, each two-dimensional query table and the equivalent fatigue load proxy model, and determining a target yaw angle combination. On the basis of the scheme, the fatigue load caused by the wake effect is reduced while the power improvement is guaranteed, and the active yaw optimization reliability is improved on the whole.

The invention relates to a polarization / inertial navigation integrated navigation method of an embedded unmanned aerial vehicle kinetic model, which comprises the following steps of: expanding a three-dimensional attitude error angle, a speed error, a position error, an angular speed error and a thrust coefficient error of the unmanned aerial vehicle kinetic model into inertial navigation state parameters as state quantities to form system state quantities; establishing a system state equation; taking the course angle calculated by the polarization sensor and the attitude, the speed and the position of the unmanned aerial vehicle kinetic model as quantity measurement, and establishing a system measurement equation; establishing a credibility discrimination function of polarization course measurement based on course angle innovation, and designing a combined navigation mode switching and thrust coefficient error feedback strategy; a Kalman filtering method is used for estimating system state quantities, namely an inertial navigation attitude misalignment angle, a speed error and a position error, and an attitude error angle, a speed error, a position error and a thrust coefficient error of an unmanned aerial vehicle dynamic model, so that correction of the attitude and the position of the unmanned aerial vehicle is realized.

The invention provides a calculation method and a test system for thrust coefficients of a pintle nozzle, and mainly aims to accurately measure the thrust coefficients of the pintle nozzle under different working conditions. The method comprises the following steps: on the basis of a pintle nozzle test model, according to an engine balance pressure calculation formula, calculating a corresponding thrust coefficient under a specified combustion chamber pressure; the test system applying the thrust coefficient calculation method comprises an engine combustion chamber, an ignition device, a servo control system, a sealing connection structure, a static frame, a movable frame, a thrust sensor and a bearing pier, the pressure intensity of the combustion chamber and the throat area of an engine can be accurately controlled in the test process, and the thrust coefficient of the spray pipe under the concerned working condition is obtained.

The invention discloses a fan mechanism modeling and optimizing method and system based on a neural network, and the method comprises the steps: building a model of a wind energy utilization coefficient and a thrust coefficient of a fan, and carrying out the steady-state simulation, so as to obtain a two-dimensional relation table model of the wind energy utilization coefficient and the thrust coefficient, establishing a fan aerodynamic model based on the two-dimensional relation table model; respectively establishing a fan transmission chain system model and a fan blade and tower coupling model based on the nonlinear pneumatic torque Tr and the nonlinear air thrust Ft in the fan aerodynamic model to obtain a complete fan mechanism model; and collecting actual operation data of the fan, analyzing the deviation between the fan mechanism model and the actual operation data of the fan based on the neural network, and correcting the deviation through the neural network to obtain an optimized fan mechanism model. According to the invention, the precision of fan modeling can be improved.

The invention discloses a wind power plant arrangement optimization method and device, equipment and a storage medium, and relates to the technical field of wind power plant design and optimization, and the method comprises the steps: obtaining environment turbulence intensity and a fan thrust coefficient, and constructing an omnidirectional wind resource map; inputting the environmental turbulence intensity and the fan thrust coefficient into a TurbOPark wake flow model, calculating wake flow loss and obtaining the inflow wind speed of each fan under each wind direction and wind speed combination; taking the wind frequency in the omnidirectional wind resource map as a weight, and carrying out weighted summation processing on single-machine power obtained by converting the inflow wind speed through a power curve to obtain a target function of maximizing the total power generation of the whole field; and by taking the boundary polygon coordinates and the minimum spacing requirement as constraints, randomly disturbing the fan coordinates and comparing the target function before and after disturbance to iteratively update the fan position, the target fan coordinates and the whole-field total generating capacity corresponding to the target fan coordinates are obtained, and the optimization precision and the engineering efficiency are remarkably improved.

The invention discloses a wind power plant multi-target yaw control method considering power load comprehensive benefits, and belongs to the technical field of wind power generation. The whole wind power plant wake flow modeling considering the yaw state is carried out by analyzing the wake flow model, the inflow data of each fan in the wind power plant is determined, and the total power and the average life of the wind power plant are rapidly and accurately predicted by combining the fan power, the thrust coefficient curve and the S-N curve of the transition section pipe node. Single fan power optimization and fan fatigue life optimization with power constraint are integrated, a two-stage multi-target control optimization system is established, and positioning of an optimal yaw combination of each stage is accelerated by establishing a Bayesian machine learning network and utilizing efficient and accurate power and life prediction data. According to the method, the optimal yaw strategy considering the power load comprehensive benefit can be accurately and efficiently provided according to the real-time wind speed data, and the load is reduced to the maximum extent and the service life of the fan is prolonged while the power generation requirement of the wind power plant is met.

The invention discloses a flight state estimation method and system for a low-cost small propeller aircraft, and belongs to the technical field of navigation, guidance and control, and the method mainly comprises the steps: building parameterized models of aerodynamic coefficients and propeller thrust coefficients, the difference between the air speed and the ground speed and the derivative deviation of the normal force coefficient to the attack angle are used as system state quantities to be estimated, and the axial apparent acceleration measured by an accelerometer is used as a quantity for measurement; calculating a theoretical value of the quantity measurement by using a kinetic model; and estimating the flight state of the aircraft based on extended Kalman filtering recursion. According to the method, an existing navigation system is utilized, and a simple, practical and effective flight state estimation means is provided for the propeller propulsion aircraft on the premise that no hardware needs to be added.

The invention discloses a rotor aerodynamic performance improvement wind tunnel test method based on active gurney flap control, and belongs to the technical field of active control of aircrafts. The problem that in a traditional rotor active control method in the prior art, when a gurney flap oscillates at the frequency of 1 ohm, the tension coefficient of a rotor is affected is solved. The method comprises the following steps: carrying out dynamic characteristic test on a rotor test bed, and carrying out control matrix calibration on the rotor test bed to obtain the rotor test bed meeting requirements; rotor wing dynamic balance and rotor wing common taper measurement are carried out on a rotor wing model, the obtained rotor wing model meeting the requirement is subjected to a Gurney flap active control test, rotor wing aerodynamic force under all set conditions is obtained and subjected to data processing, and according to the processed data, vibration characteristics and aerodynamic performance of the rotor wing in different working states are obtained through analysis. According to the method, the rotor performance is effectively improved, the influence on rotor control is avoided, and the method can be applied to active gurney flap control rotor performance research.

The invention discloses a long flexible blade reduced scale model design method suitable for a large fan wind tunnel experiment. The method comprises the following steps: selecting a reasonable similarity criterion, selecting a section airfoil of a model blade, optimizing the distribution of chord length and torsion angle in the length direction of the blade, and optimizing a model rotor variable pitch control strategy; the design objectives that the thrust coefficient of the reduced-scale model rotor in the experimental wind speed range is equal to that of the original-size fan rotor in the corresponding original-size wind speed range, and the first-order inherent frequency in the flapping and shimmy directions of the blades of the reduced-scale model is equal to that of the original-size blades are achieved, and the long flexible blade reduced-scale model is provided for a large-scale fan wind tunnel experiment. According to the method, the first-order inherent frequency of the flapping and shimmy directions of the model blade and the blade of the original size is equal, the thrust coefficients are equal under multiple working conditions, the wind tunnel experiment similarity criterion is met, different airfoil choices are appointed for different design control sections, and the method has high optimization solution efficiency.

The invention discloses a composite propeller design method based on a regression neural network and a genetic algorithm, and belongs to the field of composite propellers. According to the method, the minimization of the distance from the pitch angle of the blade tip of the composite propeller to the optimal pitch angle of the propeller type under each working condition is taken as the optimization target of the propulsive efficiency, and the minimization of the absolute value of the difference value of the thrust coefficient KTA under the working condition of the low advance speed coefficient and the thrust coefficient KTB under the working condition of the high advance speed coefficient is taken as the optimization target of vibration and noise reduction; the constraint is that the strength of the structural performance of the composite material needs to meet a Tsai-Wu strength criterion, and constructing a ply pre-deformation optimization model; through combination of a regression neural network and a genetic algorithm, a layering angle sequence and pre-deformation geometric parameters of the composite material propeller are optimized, performance optimization of the composite material propeller in a full working condition range is realized under steady-state and non-steady-state working conditions, the balance between the minimum propulsion efficiency and vibration and noise reduction is realized, and the comprehensive performance of the composite material propeller is improved. Therefore, the working performance of the composite propeller is improved.

The invention provides a wind power plant electric quantity calculation method considering additional turbulence and blocking effect coupling influence. The wind power plant electric quantity calculation method comprises the following steps: step 1, acquiring wind power plant information and inflow wind data; 2, numbering the wind turbines in the field according to a front-and-back sequence along the inflow wind direction; 3, quantizing wake flow loss by considering the additional turbulence influence, and calculating the effective wind speed and thrust coefficient of each wind turbine by combining the wind speed variation under the influence of the blocking effect; 4, taking the result of the step 3 as input, and calculating the wind speed variation caused by the blocking effect at each wind turbine; 5, updating the wind speed variation in the step 3 according to the result of the step 4, and obtaining an effective wind speed meeting a convergence standard through iterative calculation; and 6, calculating the generating capacity according to the effective wind speed in the step 5. Decoupling of the additional turbulence and the blocking effect is achieved, the generating capacity calculation method capable of efficiently and accurately simulating the common influence of the additional turbulence and the blocking effect is proposed for the first time, and the calculation precision is remarkably improved.

This invention relates to the field of marine propulsion device manufacturing, specifically a design method for a fully azimuth-controlled adjustable-pitch ducted propeller. This method extracts the basic parameters of the ship's main engine and existing rudder propeller, and establishes an integrated arrangement scheme to replace the fixed-pitch propeller with an adjustable-pitch propeller while maintaining the original power parameters unchanged. Based on the theoretical diagram of the fixed-pitch ducted propeller, a hydrodynamic calculation program is executed, introducing correction factors for increased shell diameter ratio and slightly reduced disk area ratio, and forcibly lowering the theoretical thrust coefficient by 5%, to obtain the corrected target open-water characteristic curve. The overall rotational characteristics of the fully azimuth-controlled rudder propeller are utilized to provide thrust for reversing and steering, strictly limiting the pitch adjustment authority to adaptability requirements for low-speed navigation and providing maximum drag under multiple operating conditions. A single-crank slider mechanism is configured inside the propeller hub as the core rotor component, and a three-dimensional spatial layout is completed. An electro-hydraulic integrated servo control system, dominated by a PLC and incorporating a dual-pump parallel architecture and a built-in hydraulic lock, is established. This significantly reduces the frequency and physical amplitude of the propeller blade rotation angle.

The invention belongs to the technical field of aero-engines, and particularly relates to an air film cooling two-dimensional nozzle thrust coefficient loss rapid calculation method which comprises the steps that the total flow of a nozzle is determined, and the total flow comprises the inner culvert flow, the flow flowing through an air film plate, the flow flowing through an impact-air film plate and the outer culvert leakage flow; based on the gas film hole inclination angle and the local loss factor, the speed v of the gas flow passing through the gas film plate is determined; based on the sectional area of the cooling channel and the hole area of the baffle, the speed v25 of the airflow passing through the baffle is determined; calculating the energy loss of the air flow passing through the impact-air film plate, and determining the speed v3 of the air flow passing through the impact-air film plate based on the inclination angle of the impact-air film hole; and substituting each airflow velocity into a thrust coefficient calculation formula to calculate the thrust coefficient loss.

This invention discloses an aerodynamic optimization design method for scaled-down model blades of large vertical axis wind turbines based on DMST theory. The method includes: determining scaled-down parameters according to wind tunnel similarity criteria; selecting an optimized airfoil for aerodynamic characteristic matching at low Reynolds numbers based on the lift-to-drag ratio characteristics of the prototype blades; constructing an aerodynamic performance model based on dual-disk multi-flow theory, calculating and verifying the theoretical thrust coefficients of the prototype and optimized airfoils; conducting force-pressure tests in a wind tunnel, extracting the pure thrust of the blades by subtracting the total thrust of the turbine from the tower thrust vector; and comparing the measured thrust coefficients with the theoretical thrust coefficients to verify the aerodynamic load matching degree. This invention effectively eliminates the Reynolds number effect in scaled-down tests by combining airfoil optimization, DMST theory verification, and wind tunnel test verification, achieving high-precision matching of aerodynamic loads on scaled-down model blades of vertical axis wind turbines and improving the reliability of wind tunnel test data.

The present application discloses a dynamic modeling method for a vector-propelled AUV, which relates to the field of vector-propelled AUVs. The method uses a CFD simulation method to respectively obtain the vector propulsion performance of a vector propulsion device in a vector-propelled AUV when subjected to different fluid parameters under different operating conditions, and then obtains a relationship between the thrust coefficient of the vector propulsion device and the fluid parameters by fitting. The hydrodynamic parameters of the vector-propelled AUV and the thrust coefficient of the vector propulsion device are used to construct a six-degree-of-freedom dynamic equation. The six-degree-of-freedom dynamic equation can fully consider the coupling effects of various factors on the vector propulsion to accurately characterize the vector propulsion characteristics. The constructed six-degree-of-freedom dynamic equation can more accurately describe the dynamic characteristics of the vector-propelled AUV. Combined with the kinematic equation, a dynamic model for the vector-propelled AUV is established, and the motion process of the vector-propelled AUV can be accurately predicted.

The invention provides a construction method of a wind turbine wind speed prediction model and a wind speed prediction method and system. The construction method of the wind turbine wind speed prediction model comprises the steps of obtaining first simulation operation data of a first wind turbine and second simulation operation data of a second wind turbine under preset wind condition parameters; extracting a first dynamic characteristic parameter of the first wind turbine from the first simulation operation data, and extracting a second dynamic characteristic parameter of the second wind turbine from the second simulation operation data; based on the first dynamic characteristic parameter, the first thrust coefficient and the second dynamic characteristic parameter, a preset wake flow model and the distance between the first wind turbine and the second wind turbine are adjusted, and a target wake flow model is obtained; the target wake flow model is used for acquiring the predicted wind speed of the second wind turbine. The wake flow attenuation is calculated by using the impeller diameter after blade deformation and the thrust coefficient, the calculation error of wind power plant data is effectively reduced, and the wind power plant wake flow evaluation level is improved.

The invention relates to a polarization / inertial navigation combined navigation method with an embedded unmanned aerial vehicle (UAV) dynamics model. The method comprises the following steps: taking the three-dimensional attitude error angle, velocity error, position error, angular velocity error and thrust coefficient error of the UAV dynamics model as state quantities and expanding them into inertial navigation state parameters to form system state quantities, and establishing a system state equation; taking the heading angle solved by a polarization sensor and the attitude, velocity and position of the UAV dynamics model as quantity measurements to establish a system measurement equation; establishing a credibility discriminant function of the polarization heading vector measurement based on heading angle innovation information, and designing a combined navigation mode switching and thrust coefficient error feedback strategy; and using a Kalman filtering method to estimate the system state quantities, namely the inertial navigation attitude misalignment angle, velocity error and position error, and the attitude error angle, velocity error, position error and thrust coefficient error of the UAV dynamics model, to achieve correction of the UAV attitude and position.

This invention belongs to the field of electronic digital data processing and discloses a propulsion modeling method for FPSOs based on Modelica, comprising the following steps: S1: Modeling the propulsion coefficient model of the propeller, including calculating the following parameters: thrust coefficient, thrust torque coefficient, thrust gain coefficient, and thrust torque gain coefficient; S2: Modeling the propeller performance model, including calculating the following parameters: wake coefficient, advance number, thrust loss coefficient, and relative rotational efficiency; S3: Based on the results of steps S1 and S2, outputting the thrust and thrust torque of the propeller, thereby obtaining the propulsion efficiency of the propeller. This method can comprehensively simulate the thrust and torque variation characteristics of the propeller under different operating conditions through a discrete dynamic modeling approach, thus providing accurate simulation support for the dynamic response of FPSO systems in complex marine environments.

The invention provides a pit structure wind turbine airfoil design method and device, equipment and a medium, and relates to the technical field of wind power generation new energy, and the method comprises the steps: generating a plurality of groups of different target circular pit parameters, and arranging a plurality of pit structures to a smooth wind turbine airfoil model according to the plurality of groups of different target circular pit parameters, the first target pit structure wind turbine airfoil is obtained, simulation of the pit structure wind turbine airfoil can be achieved, then the first target pit structure wind turbine airfoil is simulated and operated, a target function value composed of the lift-drag ratio parameter and the thrust coefficient is obtained, and therefore the target function value can be used for evaluating the target circular pit parameter. According to the method, the optimal circular pit parameters are determined, and finally the second target pit structure wind turbine airfoil is generated according to the optimal circular pit parameters, so that automatic design and optimization of the pit structure wind turbine airfoil are realized, the influence of various parameters on the airfoil is considered, and the aerodynamic characteristics of the pit structure wind turbine airfoil can be effectively improved.

The invention relates to a blade reconstruction method of a floating vertical axis fan model for a scaling test, aerodynamic parameters of a real-scale fan comprise an actual thrust coefficient and an actual lateral force coefficient, and the blade reconstruction method comprises the following steps: determining a scaling proportion of the fan model according to test conditions; the initial blade chord length c0 and the torsional angle beta0 of the fan model are obtained through calculation according to the Froude similarity law; calculating to obtain a Reynolds number of a fan model blade, and selecting a low Reynolds number airfoil; determining a thrust coefficient calculation expression CT (c, beta) and a lateral force coefficient calculation expression CS (c, beta) of the fan model; performing expansion processing on CT (c, beta) and CS (c, beta) at (c0, beta0) by adopting a Taylor expansion formula, taking an actual thrust coefficient and an actual lateral force coefficient as target values, and substituting the target values into an expression subjected to expansion processing to obtain a binary linear equation set; the target chord length and the target torsion angle of the fan model blade are solved, effective blade reconstruction is achieved, and the two-degree-of-freedom aerodynamic load borne by the fan is accurately simulated.

The invention discloses a bimodal afterburner structure and a modal adjusting method thereof.The bimodal afterburner structure comprises an inner duct structure, an outer duct structure, a combustion chamber and a spray pipe, a partition plate is arranged between the inner duct structure and the outer duct structure, and a change-over valve is connected to the partition plate; one end of the combustion chamber is connected with the inner duct structure and the outer duct structure, and the other end of the combustion chamber is connected with the spray pipe. Through the design of a slow combustion / deflagration dual-mode inner and outer ring parallel structure, autonomous dual-mode switching and a dual-mode shared combustion chamber, efficient energy conversion and dynamic adjustment of the power device in a wide speed domain range are achieved, the thrust coefficient of a slow combustion mode is 0.3-0.5, the detonation mode is improved to 0.6-0.8, the flight requirement of Mach number 1-Mach number 5 can be met, and the flight speed of the power device is improved. And meanwhile, the detonation combustion heat efficiency is improved by 15% compared with a slow combustion mode, and the fuel power ratio is reduced by 15%-20%.

The invention relates to controlling a wind turbine. A predefined power coefficient data structure and a predefined thrust coefficient data structure respectively comprise values of a power coefficient and a thrust coefficient as functions of blade pitch angle and tip speed ratio. The invention includes using an iterative search algorithm to determine values of pitch angle and tip speed ratio that maximise the power coefficient value in the predefined power coefficient data structure subject to a constraint that the thrust coefficient value in the predefined thrust coefficient data structure is no greater than a maximum threshold thrust coefficient value. A rotor speed reference is determined based on the determined tip speed ratio value and on a received wind speed. The determined pitch angle value is set as a pitch angle reference. The wind turbine is controlled in accordance with the pitch angle and tip speed ration references.

The invention belongs to the technical field of aero-engine double-duct nozzle thrust coefficient determination, and particularly relates to an aero-engine double-duct nozzle thrust coefficient determination method which comprises the following steps: step 1, constructing a double-duct nozzle calculation model; 2, setting an air inlet condition and outlet back pressure of the double-duct spray pipe, and calculating to obtain flow field distribution and inlet and outlet parameters of the double-duct spray pipe according to a calculation model of the double-duct spray pipe; 3, based on the inlet and outlet parameters of the double-duct spray pipe, the theoretical thrust of the inner duct spray pipe and the theoretical thrust of the outer duct spray pipe are obtained through calculation; step 4, based on the theoretical thrust of the inner duct spray pipe, the theoretical thrust of the outer duct spray pipe and the real thrust of the double-duct spray pipe; 5, on the basis of the inlet and outlet parameters of the double-duct spray pipe, the one-dimensional isentropic complete expansion thrust of the double-duct spray pipe is calculated; and 6, calculating the thrust coefficient of the double-duct nozzle based on the real thrust and the one-dimensional isentropic complete expansion thrust of the double-duct nozzle.

The present application belongs to the field of aero-engine nozzle aerodynamic optimization, and discloses a discrete-adjoint nozzle thrust coefficient surface sensitivity calculation method and system. The surface sensitivity algorithm and system capture the response of the flow field to the nozzle thrust coefficient through the discrete-adjoint equation, take the spatial sensitivity as an intermediate bridge to separate the geometric direct effect and the flow field indirect effect, combine the radial basis function RBF-transfinite interpolation TFI to calculate the mapping derivative, and transfer the nozzle spatial structure grid deformation, so that the whole solving process is independent of the number of design variables, and high-precision and high-efficiency sensitivity calculation of the nozzle thrust coefficient to the surface parameters is realized. The surface sensitivity algorithm and system solve the problems of low optimization efficiency, poor precision and weak adaptability of the nozzle, realize accurate and efficient analysis of the influence of the nozzle thrust coefficient on the surface parameter sensitivity, provide key technical support for improving the nozzle thrust coefficient, and have engineering practical value.

The present application discloses a parameter selection method and device for simulating wind, solar and water resources elements in river valley areas, belonging to the field of wind power generation. The method includes: without correcting the thrust coefficient in the WRF model, simulating the wind field and turbulent kinetic energy distribution in the dry hot river valley area with a first resolution grid spacing to obtain a first simulation result; simulating the wind field and turbulent kinetic energy distribution in the dry hot river valley area with a second resolution grid spacing to obtain a second simulation result; comparing the first simulation result with the second simulation result, determining the correction coefficient value at the second resolution; correcting the thrust coefficient according to the wind direction wind turbine angle and the correction coefficient value to obtain a target thrust coefficient, which is used in the simulation process of the WRF model.

The invention discloses a wind turbine generator group wake flow optimization method and system suitable for generating power synergy. The method comprises the following steps: establishing an engineering wake flow model considering wake flow delay; in the wake flow area, the equivalent wind speed of the downstream wind turbine generator is calculated; acquiring a sensitivity coefficient of the wind speed with respect to the thrust coefficient based on an engineering wake flow model; acquiring a wind speed sensitivity coefficient according to the fact that the equivalent wind speed is a polynomial about an upstream unit thrust coefficient, namely a multivariate nonlinear function about a tip speed ratio and a pitch angle; establishing a wind turbine generator group increment state-space equation based on the wind speed sensitivity coefficient; establishing an optimization target for improving the generated power; and based on the wind turbine generator group increment state equation of the wind speed sensitivity coefficient, an optimization value is solved, and an optimization instruction of the optimized active power and the pitch angle is sent to a wind turbine generator controller.

The invention belongs to the technical field of aircraft design, and particularly relates to a ducted fan power aircraft numerical simulation aerodynamic force and torque correction method. The correction method comprises the following steps: carrying out a ducted fan ground test; converting the ground test data to the sea level; determining a flow boundary condition of the numerical simulation working condition, and converting the numerical simulation working condition to a sea level reference point; performing interpolation to obtain a sea level fan disc thrust coefficient, and converting the sea level fan disc thrust coefficient into a numerical simulation working condition; carrying out numerical simulation aerodynamic force data correction; and carrying out numerical simulation aerodynamic torque data correction. According to the numerical simulation aerodynamic force and torque correction method for the ducted fan power aircraft, the lift force, the resistance and the pitching torque of the ducted fan power aircraft under the low-speed incoming flow condition are corrected on the basis of the fan disc thrust in combination with calculation and testing; the aerodynamic performance of the ducted fan power aircraft under different power working conditions can be evaluated efficiently and precisely, and the method has engineering practical value.

The invention belongs to the technical field of aero-engine exhaust nozzle pneumatic optimization, and discloses an exhaust nozzle thrust coefficient surface sensitivity algorithm and system based on discrete accompanying. According to the surface sensitivity algorithm and system, response of a flow field to a thrust coefficient of the exhaust nozzle is captured through a discrete adjoint equation, a geometric direct effect and a flow field indirect effect are separated by taking space sensitivity as an intermediate bridge, and grid deformation of a mapping derivative transfer exhaust nozzle space structure is calculated in combination with a radial basis function (RBF)-over-limit interpolation (TFI); the whole solving process is irrelevant to the number of design variables, and high-precision, high-efficiency and high-sensitivity calculation of the thrust coefficient of the exhaust nozzle on the surface parameters is achieved. According to the surface sensitivity algorithm and system, the problems of low optimization efficiency, poor precision and weak adaptability of the exhaust nozzle are solved, accurate and efficient analysis of the influence of the thrust coefficient of the exhaust nozzle on the surface parameter sensitivity is realized, key technical support is provided for improvement of the thrust coefficient of the exhaust nozzle, and the surface sensitivity algorithm and system have engineering practical value.