48 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 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.

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 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 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 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 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.

This application belongs to the field of aero-engine testing technology, specifically relating to a method for estimating the thrust correction coefficient of an aero-engine indoor test stand, including: Step 1, determining the performance and structural parameters of the target aero-engine; Step 2, finding a reference aero-engine, wherein the performance and structural parameters of the reference aero-engine are of the same order of magnitude as those of the target aero-engine, and the thrust coefficient on the target test stand is already known; Step 3, calculating the ratio of the impulse of the target aero-engine to that of the reference aero-engine; Step 4, correcting the thrust correction coefficient of the reference aero-engine using the ratio of the impulse of the target aero-engine to that of the reference aero-engine, thereby obtaining the thrust correction coefficient of the target aero-engine.

This invention discloses a method for monitoring the comprehensive performance of ships, including: a speed performance monitoring process and a cost-effectiveness monitoring process. The speed performance monitoring process includes: constructing the ship's total resistance, torque coefficient, and thrust coefficient using three sets of polynomials containing unknowns to be identified; dividing the value ranges of the three sets of unknowns into several value intervals; using an improved genetic algorithm, finding the optimal solution in each value interval of the unknowns, and taking the smallest optimal solution as the final solution; calculating the ship's real-time parameters in the ship's mathematical model based on the values ​​of the three sets of unknowns corresponding to the final solution, thus completing the ship's speed performance monitoring; the cost-effectiveness monitoring process includes: calculating cost-effectiveness based on the degree of change in naval coefficients, the degree of change in monitoring system functional indicators, and the cost of the monitoring system. This invention can better obtain ship speed performance indicators and more accurately and dynamically obtain cost-effectiveness.

The application relates to the technical field of wind turbine wake calculation, in particular to a wind farm full-field full-domain wake analysis method based on yaw control, which comprises the following steps: acquiring wind turbine parameters and terrain and inflow parameters of an operating environment in a wind farm, including the position of the wind turbine, the rotor diameter, the hub height, the yaw angle and the thrust coefficient, the flat terrain inflow wind speed, the complex terrain inflow wind speed and the turbulence intensity; calculating the lateral offset of the wake generated by the yaw of the wind turbine based on the law of conservation of momentum and the law of conservation of mass; calculating the wake width downstream of the wind turbine based on the inflow parameters and the lateral offset of the wake, and determining the range of the wake area; calculating the initial speed loss of the full-field full-domain wake based on the law of conservation of mass and the cosine distribution function; and obtaining the full-field full-domain wake speed of the wind farm based on the inflow speed and the wake speed loss at the complex terrain. Through comprehensive consideration of factors such as complex terrain, wake yaw and wake interaction, high-precision prediction of the wake speed of the wind farm is realized.

The invention relates to a wind speed fine correction method and system based on a physical effect. The method comprises the steps that a double-Gaussian wake flow model is constructed, model parameters are determined based on a thrust coefficient and turbulence intensity of a wind turbine, and wake flow velocity loss distribution is represented by adopting a double-Gaussian function. The method comprises the steps that a CFD field machine integrated simulation model is established, a flow field model is established based on large vortex simulation, a wind turbine is modeled to be an actuator disc capable of being dynamically adjusted, and dynamic operation of the turbine is simulated by sensing local wind speed and wind direction in real time and updating aerodynamic loads and yaw angles. And inputting the speed loss output by the double-Gaussian wake flow model as a correction value into the CFD field-machine integrated simulation model for flow field solution, and obtaining corrected wind speed distribution. According to the method, wake flow velocity loss distribution characteristics are accurately described through the double-Gaussian wake flow model, and accurate prediction of wind speed distribution and power output of the wind power plant under complex terrains and dynamic working conditions is realized in combination with a dynamic response mechanism of CFD field machine integrated simulation.

The application discloses a large vertical axis fan wind tunnel scale model blade aerodynamic optimization design method based on a DMST theory, and comprises the following steps: determining scale parameters according to wind tunnel test similarity criteria; selecting an optimized airfoil with matched aerodynamic characteristics under low Reynolds number based on the lift-drag ratio characteristics of a prototype blade; constructing an aerodynamic performance model based on a double disk multi-flow management theory, calculating the theoretical thrust coefficient of the prototype and the optimized airfoil, and performing matching verification; carrying out a force-measuring and pressure-measuring test in a wind tunnel, stripping the pure thrust of the blade by subtracting the total thrust of the whole machine from the thrust vector of the tower column; and comparing and verifying the aerodynamic load matching degree by comparing the measured thrust coefficient with the theoretical thrust coefficient. The application combines airfoil optimization, DMST theory verification and wind tunnel test stripping verification, effectively eliminates the Reynolds number effect in the scale test, realizes high-precision matching of the aerodynamic load of the vertical axis fan scale model blade, and improves the reliability of the wind tunnel test data.

The invention belongs to the technical field of inclined shaft TBM anti-falling supporting, and particularly relates to an ABS supporting device suitable for a large-dip-angle inclined shaft TBM and a structure optimization method of the ABS supporting device, and the structure optimization method comprises the steps that a coordinate system is established with the center of a supporting shoe of the ABS supporting device as an original point; establishing a thrust equation of thrust required to be provided by a hydraulic cylinder and a connecting rod of the ABS supporting device; deducing a thrust coefficient and an integral value of the thrust coefficient according to the obtained thrust equation, and constructing a structure optimization function of the ABS support device; and solving the optimal structural size of the ABS supporting device by taking the horizontal distance between a supporting shoe of the ABS supporting device and a rack and the ratio of thrust coefficients of a hydraulic cylinder and a connecting rod as constraint conditions. The optimal structure size of the ABS supporting device is obtained by taking the horizontal distance between the supporting shoe of the ABS supporting device and the rack of the TBM main machine and the like as constraint conditions, the anti-falling supporting capacity of the ABS supporting device can be improved, the TBM falling risk of the inclined shaft can be reduced, and then serious casualties and property losses are avoided.

The invention relates to the technical field of aerodynamic design of helicopter rotors, and discloses a coaxial rotor blade aerodynamic configuration optimization design method, which comprises the following steps of: determining an optimization state and an optimization target: determining that a flight state needing to be calculated and analyzed is a hovering state, and correspondingly analyzing and evaluating the optimization target as hovering efficiency and a maximum tension coefficient; a reference model of the rotor wing type of the coaxial rotor aircraft is selected, and the datum blade aerodynamic configuration is constructed based on reference model parameters; determining an optimization parameter range and an optimization strategy: setting the optimization parameter range and the optimization strategy according to the aerodynamic configuration of the reference blade; and differential optimization of the aerodynamic configuration of the blade: based on a Kriging model, performing differential optimization on the aerodynamic configuration of the reference blade by adopting an NSGA-II multi-target genetic algorithm. The hovering efficiency of the coaxial rotor wings can be effectively improved, the influence of aerodynamic interference between the upper rotor wings and the lower rotor wings is avoided or reduced, and then the performance of the aircraft is improved.

The application provides an eight-valve solid attitude control engine interior ballistic design method, which provides effective guidance for the design method of the eight-valve solid attitude control engine interior ballistic. The idea of the application is to realize constant engine working pressure through the constraint conditions of grain burning surface and total throat area, to transform the valve number through rotational symmetry and mirror symmetry rules, to obtain the valve thrust calculation formula through sequentially deducing the zero thrust mode, single-valve effective thrust and adjacent 2-valve effective thrust and the like; under the condition of constant combustion chamber pressure, the working conditions of each needle valve nozzle are simplified, the efficiency of obtaining the corresponding thrust coefficient of the throat plug under different strokes is improved, and the valve total throat area calculation method for realizing constant combustion chamber pressure at any time is realized.

The invention provides an ejector nozzle wind tunnel test thrust measuring and calculating method under engine body streaming interference, and belongs to the technical field of nozzle wind tunnel tests. The method comprises the steps that a main jet flow air inlet channel and a secondary flow air inlet channel of an ejector nozzle are constructed, different main flow drop-pressure ratio and secondary flow drop-pressure ratio conditions of the injection spray pipe are simulated by adjusting main flow inlet conditions and secondary flow inlet conditions entering a main flow inlet channel and a secondary flow inlet channel of the injection spray pipe; the total pressure and the total temperature at an inlet of a main spray pipe of the injection spray pipe, the total pressure and the total temperature at an inlet of a secondary flow channel and the total pressure and the static pressure at an outlet of the injection spray pipe are obtained, and the actual thrust of the injection spray pipe in a given test state is calculated based on test measurement data of the total pressure and the static pressure at the outlet of the injection spray pipe; the ideal thrust of the injection nozzle in a given test state is calculated based on the total pressure and total temperature test measurement data at the inlet of the injection nozzle, and finally the thrust coefficient of the injection nozzle is obtained by calculating the ratio of the actual thrust to the ideal thrust of the injection nozzle.

The invention relates to the technical field of ship safe harbor-returning power, and discloses a cruise ship and ro-ro passenger ship safe harbor-returning power estimation method, which comprises the following steps of: obtaining corresponding sea wave spectrum information in combination with a ship route and a voyage period; the resistance of the ship is calculated and analyzed, and according to the analysis of resistance components, the resistance borne by the ship can be obtained through the following method: Fasis = fcalm + fwind + fadd + fapped; the forward speed coefficient of the propeller is reversely deduced through the load coefficient Ctot of the propeller, so that the rotating speed of the propeller is determined, the corresponding thrust of the propeller is obtained through resistance, the load coefficient of the propeller is calculated, the corresponding forward speed coefficient is obtained through the intersection point of the load coefficient and the thrust coefficient in the open water curve, and the corresponding open water efficiency eta o is obtained. According to the method, the safety harbor-returning power of the ship can be checked and calculated in the initial stage of ship design, the model selection work of main propulsion equipment such as a main engine is matched, the calculation theory is clear, and the method has good popularization value.

The invention discloses a turbofan engine nacelle flight thrust determination method, and relates to the field of aero-engine thrust measurement, and the method comprises the steps: S1, obtaining a curvilinear relation graph between the flow CFi and thrust coefficient CFGi of each corresponding outlet of a turbofan and a rotary core nozzle and the nozzle pressure ratio NPRi through a model test; s2, during ground testing, the average total pressure P * T13 required by the plane 13 under the condition of minimizing the residual error is obtained by adjusting the fan pressure ratio correction coefficient FPC; s3, acquiring an NPR corresponding to the average total pressure P * T13; and S4, the total thrust FG and the installation net thrust FNIN1 of the turbofan engine are calculated. According to the method provided by the invention, by combining the model test, the ground test and the flight test, the flight thrust of the turbofan engine nacelle can be more accurately determined, so that the accuracy and efficiency of engine performance evaluation are improved.

This invention relates to an aerodynamic optimization design method for propellers of multi-condition unmanned aerial vehicles (UAVs), and more particularly to an optimization design method for propellers of low Reynolds number and small advance ratio UAVs based on genetic algorithms and sheet theory. It belongs to the field of aerodynamic performance technology for micro fixed-wing UAVs. The method optimizes the thrust coefficient, hovering and cruise efficiency of the propellers of UAVs with low Reynolds number and small advance ratio under hovering and cruise conditions. The chord length and twist angle of the corresponding propeller blades are obtained through the optimized thrust coefficient, hovering and cruise efficiency, and the UAV propeller configuration is designed based on the chord length and twist angle of the propeller blades.

The invention discloses a fan cut-out control method and system based on air density and wind speed real-time fusion. The control method comprises the following steps of multi-source data real-time collection, air density and wind speed data processing, thrust coefficient matching, real-time load calculation and threshold value comparison and cut-out decision making. The control system comprises a sensor module, a data processing module, a storage module, a control module and a communication module. According to the control method and system, the safety of the unit can be guaranteed, and meanwhile the power generation efficiency is improved.

The application belongs to the technical field of the inclined shaft TBM anti-falling support, and particularly relates to an ABS support device suitable for a large-inclination-angle inclined shaft TBM and a structural optimization method thereof, which comprises the following steps: taking the center of a supporting shoe of the ABS support device as an origin to establish a coordinate system; establishing a thrust equation required by a hydraulic cylinder and a connecting rod of the ABS support device to provide a thrust; deriving a thrust coefficient and an integral value of the thrust coefficient according to the obtained thrust equation, and constructing a structural optimization function of the ABS support device; and taking a horizontal distance between the supporting shoe of the ABS support device and a rack and a ratio of the thrust coefficients of the hydraulic cylinder and the connecting rod as constraint conditions to solve optimal structural sizes of the ABS support device. The optimal structural sizes of the ABS support device are obtained by taking the horizontal distance between the supporting shoe of the ABS support device and the rack of a TBM main machine as a constraint condition, the anti-falling support capability of the ABS support device can be improved, the falling risk of the inclined shaft TBM can be reduced, and thus serious personnel casualties and property losses can be avoided.