320 results about "Aerodynamic load" patented technology

The invention relates to the technical field of turbomachinery monitoring, and discloses a cross-dimension turbomachinery dynamic risk prediction and visualization system. A dynamic data acquisition module of the system acquires multi-source heterogeneous sensing data such as a vibration spectrum sequence, an aerodynamic load distribution matrix, a rotor axial displacement time sequence and a surface temperature field thermodynamic diagram in real time; the service degradation evaluation module extracts a vibration characteristic spectrum based on a historical degradation mode library, calculates an instability risk level in combination with an aerodynamic load deviation value, and fuses a displacement sudden change gradient and a temperature difference abnormal area to generate a service degradation track matrix; the multi-dimensional risk prediction module inputs the degradation track matrix into a space-time coupling prediction network, and outputs a dynamic risk assessment vector including time-varying fault probability distribution, a residual life prediction value and a risk propagation path set; and the risk visualization engine module constructs a three-dimensional risk thermal field model and generates a dynamic thermal grid layer superposed on the digital twinborn body.

The invention discloses a floating type offshore wind turbine aerodynamic load calculation method based on a frequency domain method. The method comprises the steps that a state derivative is determined based on a blade element momentum theory quasi-steady-state assumption, and a dynamic inflow model is used for correction; establishing a pneumatic-elastic coupling two-degree-of-freedom linear dynamic model; establishing a wind wheel kinetic model; establishing a control model according to a floating type offshore wind turbine pitch angle control strategy, a torque control strategy and a floating body motion feedback control strategy; based on the pneumatic-elastic coupling two-degree-of-freedom linear dynamic model, the wind wheel dynamic model and the control model, pneumatic additional mass and pneumatic additional damping are obtained; pneumatic exciting force acting on the hub when the position of the cabin is fixed is obtained; and based on the pneumatic additional mass, the pneumatic additional damping and the pneumatic exciting force, an overall linear dynamic model of the fan is established and solved, and overall response is obtained. According to the method, the calculation result precision can be improved while the calculation efficiency is ensured, and a technical support is provided for accelerating the simulation efficiency of the offshore wind turbine.

The invention discloses a wind turbine blade semi-coupling aeroelastic modeling method considering nonlinear deformation, and belongs to the technical field of fan simulation calculation. In combination with calculation parameters used by three-party software, establishing a blade structured load model and a blade correction aerodynamic model, calculating an aerodynamic load and a structural load, and superposing: superposing the aerodynamic load, the gravity load and the centrifugal force load of the blade as an external load of a nonlinear structure control equation of the blade, and taking the external load as a calculation parameter; according to the method, the blade nonlinear structure model and the semi-coupling simulation process of the three-party wind turbine simulation software are constructed, and under the same simulation environment and load conditions, the blade nonlinear structure model and the three-party wind turbine simulation software can be subjected to semi-coupling simulation, so that the blade nonlinear structure model and the three-party wind turbine simulation software can be subjected to semi-coupling simulation calculation. The higher-precision non-linear motion response characteristics of the super-long flexible wind turbine blade are calculated, and a good effect can be achieved in the aspects of initial structure design and response evaluation of the large wind turbine blade.

The invention provides a strong nonlinear simulation method and device suitable for a large floating fan, and the method comprises the steps: dividing a target floating fan into a plurality of body structures according to the model parameters of the target floating fan, so as to construct a multi-body model containing a plurality of degrees of freedom, and building a whole machine load and a motion transmission path; the aerodynamic load input of each body structure is calculated, and the nonlinear dynamic response of the blade is calculated according to the aerodynamic load input of each body structure; according to the coordinate transformation relation, the nonlinear dynamic response of the blade is converted into a whole coordinate system and input into a multi-body dynamic model of the whole machine, generalized active force and generalized inertia force of each body structure in the target floating type draught fan are obtained through calculation, and the motion response of each body structure of the target floating type draught fan is obtained through simultaneous solution. According to the scheme, the motion response of each body structure of the target floating fan can be accurately determined, so that the running state of the floating fan in the deep and far sea complex environment can be accurately evaluated.

The invention belongs to the technical field of numerical simulation and analysis of unmanned aerial vehicles, and relates to a rigid-flexible coupled variable-camber-range deformable wing optimization design method, which comprises the following steps of: obtaining working conditions of an aircraft, determining wing types and basic parameters of wings of the aircraft, and establishing a three-dimensional aerodynamic model of the wings; variable-attack-angle pneumatic simulation is carried out on working conditions of the aircraft in take-off and cruise, optimal camber values and corresponding pneumatic loads of wings under multiple working conditions are determined, and the positions of rotating joints of the deformed wing ribs are adjusted to obtain the deformed wing ribs after primary optimization; dividing the optimization range of the deformed wing rib after primary optimization into a fixed area and an optimizable area, loading an aerodynamic load under the optimal camber value in the optimizable area to perform aerodynamic simulation to obtain a deformed wing rib after secondary optimization, and optimizing the structure; and a deformed wing rib sample is made, performance testing is conducted, and the optimizable area is adjusted till the wing performance meets the preset requirement. The aerodynamic efficiency of the full flight envelope can be improved.

The invention discloses a floating fan aerodynamic load real-time mixing test method and system based on AI enhancement, and the method comprises the steps: calculating the six-degree-of-freedom motion information of a floating foundation through a numerical calculation model based on a real-time floating foundation kinetic equation; the method comprises the following steps: carrying a reduced-scale fan model on a six-degree-of-freedom motion platform, placing the six-degree-of-freedom motion platform on a wind tunnel atmospheric boundary layer, controlling the six-degree-of-freedom motion platform based on floating foundation six-degree-of-freedom motion information, driving the reduced-scale fan model to move, generating an aerodynamic load in a simulated wind environment, measuring an original load signal, and correcting the original load signal. Synchronously recording the actual pose of the six-degree-of-freedom platform; and AI correction is carried out on the corrected load signal and the actual pose of the six-degree-of-freedom platform to obtain a net aerodynamic load, the net aerodynamic load is fed back to the numerical calculation model, and closed-loop updating is carried out to realize coupling circulation. According to the method, the problem of interaction between numerical values and physical boundaries is solved, and the test precision of the large floating fan under the complex environment load can be remarkably improved.

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 discloses an intelligent variable pitch control method, system and equipment for a wind generating set, and relates to the technical field of wind generating set control, and the method comprises the steps: synchronously collecting multi-source data in real time through a multi-source heterogeneous sensor array, constructing a dynamic load spectrum matrix, and carrying out nonlinear optimization; an optimal pitch angle sequence is generated to drive a variable pitch execution mechanism, meanwhile, the blade stress change rate is monitored in real time, and an aerodynamic load-structure response coupling factor is calculated; when the factor exceeds a safety threshold, the pitch angle command is reconstructed and the pitch angle is forcibly adjusted to a preset safety angle. The technical problems that the power generation efficiency and the structure safety are difficult to consider under the complex turbulence condition and a safety protection mechanism under the over-limit working condition is lacked in the variable pitch control of the existing wind generating set are solved, and the aim that the power generation efficiency and the structure safety are effectively improved through nonlinear optimization control and introduction of an over-limit triggered standby control path is achieved. And the technical effect of dynamic unification of power generation efficiency and structural safety in a complex turbulence environment is achieved.

An intelligent unmanned aerial vehicle pneumatic structure reduced-order analysis model comprises a pneumatic reduced-order model and a structure reduced-order model. The aerodynamic structure order reduction analysis process comprises the steps that an aerodynamic order reduction model and a structure order reduction model are initialized; under the given calculation working condition, the aerodynamic load acting on the intelligent unmanned aerial vehicle structure is obtained through calculation of the aerodynamic reduced-order model; transmitting the load on the pneumatic grid to the structural grid through a force interpolation algorithm; solving deformation response by the structure order reduction model under the action of aerodynamic load; the structural deformation is fed back to the pneumatic grid through displacement interpolation, and the pneumatic configuration is updated; and performing iterative calculation until a convergence criterion is met, finally obtaining a pneumatic structure analysis result in an equilibrium state, and outputting a pneumatic coefficient and structural deformation and stress. According to the method, the CFD / CSD model is replaced by the equivalent model, so that the calculation efficiency is remarkably improved on the premise of ensuring the calculation precision.

The invention discloses an operation control method and device for a vertical axis wind turbine generator, and belongs to the technical field of wind power generation. The method comprises the steps that a pitch angle of a lower blade is driven to be gradually increased to a preset angle at a preset angular speed through a variable pitch controller; when the rotating speed of the wind wheel reaches the cut-in rotating speed, the optimal tip speed ratio is tracked until the rotating speed of the wind wheel rises to the rated rotating speed; when the rotating speed of the wind wheel reaches the rated rotating speed, the rotating speed of the wind wheel is stabilized at the rated rotating speed; when the driving torque under the action of the aerodynamic load continuously exceeds the rated torque of the generator and the rotating speed of the generator reaches an early-warning rotating speed threshold value, a shutdown control strategy is triggered; and under the shutdown control strategy, the connection between the generator and the power grid is cut off, and mechanical braking is applied, so that the wind wheel stops rotating. According to the technical scheme, smooth starting of the wind wheel, stable operation at the rated rotating speed and safe shutdown in the fault state are achieved, the starting and stopping capacity and power stability of the unit are effectively improved, the wind speed application range is expanded, and it is guaranteed that the whole-process operation of the unit is safe and reliable.

The invention relates to the technical field of wind power generation. The invention provides an emergency yaw and automatic crosswind method and system for a wind turbine generator. The method comprises the following steps: monitoring the on-off state of a safety chain in real time, and activating an emergency power supply switching module when detecting that the safety chain is disconnected; synchronously acquiring unit vibration spectrum, impeller rotating speed, environment wind speed and cabin load distribution data, and generating dynamic risk assessment parameters based on a multi-source signal fusion algorithm; inputting a hierarchical control instruction to a yaw driver according to a comparison result of the risk assessment parameter and a preset threshold value; and in the automatic crosswind control stage, the yaw rate and the angle offset are dynamically adjusted based on the blade root bending moment real-time feedback and the wind speed change rate, so that the unit maintains the aerodynamic load balance in the non-windward state. The problems that after a safety chain of an existing wind turbine generator is disconnected, yaw capacity is completely lost, emergency crosswind protection or fault recovery cannot be achieved, and a traditional emergency yaw scheme is high in cost, complex in maintenance, slow in response, difficult to adapt to complex working conditions and the like are solved.

The invention provides a high aspect ratio wing topological optimization method considering pneumatic-structure coupling. The method comprises the following steps: establishing a pneumatic-structure strong coupling topological optimization model; performing finite element analysis to obtain an original variable field of the high aspect ratio wing; generating a filtering variable field and a projection variable field; deformation displacement of each finite element unit is obtained based on a UMMI material interpolation model; establishing information transmission, structure displacement response, aerodynamic load transmission and aerodynamic load updating strategies under pneumatic-structure coupling, and analyzing and updating the aerodynamic load; according to the method, manufacturing constraints such as geometric nonlinearity, multi-material layout and wing rib orientation size are comprehensively considered, design variables in an original variable field are subjected to iterative optimization solution, a wing optimization configuration is obtained, the three core problems of calculation distortion, performance deviation and manufacturing difficulty in lightweight design of the high aspect ratio wing are successfully solved, and the method is suitable for the lightweight design of the high aspect ratio wing. And the comprehensive performance and economical efficiency of the aircraft are remarkably improved.

The invention discloses a brush type sealing fluid-solid-heat-grinding multi-physics field efficient coupling method, and particularly relates to the field of aero-engine sealing. Comprising the following steps: establishing an interdigitated tube bundle solid model, taking the interdigitated tube bundle solid model as a first model, and executing a division step; cFD simulation is carried out on the first model after grid division, and flow field distribution is obtained; determining a three-dimensional aerodynamic load of the brush wires based on the flow field distribution; determining the three-dimensional pneumatic deformation result of the brush wires according to the three-dimensional pneumatic load, and determining the wear volume of each brush wire; according to the pneumatic deformation result of the brush wires and the abrasion volume of each brush wire, the forked row tube bundle solid model is updated, and a deformation geometric model under aerodynamic force is obtained; and taking the deformation geometric model as a first model, starting to execute a division step, and stopping iteration until a brush wire three-dimensional pneumatic deformation result reaches a first condition, so as to finish accurate simulation of a fluid-solid-heat-grinding coupling effect.

The invention discloses an aerodynamic load determination method and device of a train and the train, and relates to the field of aerodynamics. The method comprises the steps that geometric shape data of the train with the load to be determined are obtained; inputting the geometric shape data of the train with the to-be-determined load into the prediction model to obtain the pressure and shear stress of the train with the to-be-determined load, which are output by the prediction model; and according to the pressure and the shear stress of the train with the to-be-determined load, determining the resistance, the lift force and the lateral force of the train with the to-be-determined load. The prediction model is trained through the data of the train with the known load, the trained prediction model only needs to input the geometric file of the train object to be calculated, the pressure and the shear stress can be obtained, the threshold in the professional field is not involved, and therefore all workers have the operable ability. Simulation calculation is replaced by the prediction model, the prediction model does not need to be subjected to simulation calculation again, the pressure and the shear stress are directly output, the calculation time is shortened, and the calculation efficiency is improved.

The invention discloses a full-coupling numerical simulation system and method for a wind and wave hybrid energy obtaining system, and relates to the field of data analysis, and the method comprises the steps: generating an aerodynamic load of a current period based on incoming flow wind speed and coupling dynamics response data of a previous simulation period; based on preset mooring system parameters and the coupling dynamics response data of the previous simulation period, generating a mooring load of the current period; in the random wave field, determining the hydrodynamic force of the floating foundation entity and the wave energy power generation entity, and generating a wave load; determining a PTO force based on the relative motion between the power generation platform and the wave energy power generation entity; and taking the aerodynamic load, the mooring load, the wave load and the PTO force as external force terms in the same time domain kinetic equation for unified solution, and obtaining a coupling kinetic response of the current simulation period. According to the full-coupling numerical simulation system and method for the wind and wave hybrid energy obtaining system, the simulation precision of the simulation system can be improved, and the overall calculation efficiency of the system is improved.

The invention discloses a system-level coupling modeling method, system, equipment and medium for a multi-wind-wheel multi-tower-drum floating type wind turbine generator set, and relates to the field of simulation modeling, and the method comprises the steps that parameter information of the multi-wind-wheel multi-tower-drum floating type wind turbine generator set is obtained, and a multi-system structural dynamics model is obtained based on the parameter information of the multi-wind-wheel multi-tower-drum floating type wind turbine generator set; the unsteady aerodynamic model, the hydrodynamic model and the mooring structure dynamic model are used for outputting aerodynamic loads, hydrodynamic loads and mooring cable tension, the aerodynamic loads, the hydrodynamic loads and the mooring cable tension are fed back to the multi-system structure dynamic model, and based on a Lagrange framework, the models are subjected to joint simulation operation through a joint simulation interface, so that the mooring cable tension is obtained. And the multi-wind-wheel and multi-tower-drum floating type wind turbine generator is designed. According to the method, a complete system dynamics model can be established, and complete machine level rapid evaluation and engineering iteration under multiple working conditions can be supported.

A method for reducing aerodynamic loads on an aircraft located on the ground includes moving a wing tip relative to a fixed wing to an on-ground configuration in which the span of the wing is reduced. The wing tip includes an airflow channel, which is in an open configuration in which airflow through the channel between upper and lower surfaces of the wing tip is enabled, when the wing tip is in the on-ground configuration. This has been found to reduce aerodynamic loads on the wing tip and / or parts of the aircraft connected thereto during this phase of the aircraft's use.

The invention belongs to the technical field of unmanned aerial vehicle aircraft design, and particularly relates to a longitudinal aerodynamic parameter identification calculation method in a closed-loop state and a large angle-of-attack range, and the method comprises the steps: building a flight simulation model; performing aerodynamic characteristic simulation based on a flight simulation model to obtain an aerodynamic load value, comparing the aerodynamic load value with data tested in an actual flight experiment, and calculating and minimizing an error sum of squares; dividing the whole angle-of-attack range into a plurality of sub-intervals, respectively obtaining the optimal aerodynamic parameters of each sub-interval based on the minimum sum of squares of errors, inputting each optimal aerodynamic parameter into the flight simulation model, and carrying out model accuracy verification; and drawing an aerodynamic characteristic curve according to each optimal aerodynamic parameter, and verifying the applicability of the flight simulation model. The method has universality and is suitable for longitudinal aerodynamic coefficient parameter identification of different types of unmanned aerial vehicles, the parameter identification efficiency is improved, and meanwhile the applicability of the model under the complex flight working condition is enhanced.

An electromechanical actuator architecture is provided for a cowl door of an aircraft engine nacelle. The electromechanical actuator architecture includes a first clutch, a no-back unit including a friction clutch and a one-way clutch and a ball screw with two coaxial external cylinders. Torque generated for actuator extension is transferable to the ball screw and the coaxial external cylinder via the first clutch. During actuator retraction, cowl door weight and an aerodynamic load compress the coaxial external cylinder and the ball screw with loads that are transferred to the no-back unit, which is configured to maintain actuator position in an event generation of the torque ceases.

The invention discloses an aerodynamic load loading method, device and equipment and a medium, relates to the technical field of ocean engineering, is applied to a processor, and comprises the following steps: receiving scale motion data currently acquired by a scaling model of a floating wind turbine generator, and amplifying the scale motion data to obtain full-scale motion data; determining a first expected aerodynamic load borne by the floating wind turbine generator based on the full-size motion data; reducing the first expected aerodynamic load to obtain a second expected aerodynamic load borne by the scaling model; decomposing the second expected aerodynamic load into output thrust of each propeller in the loading device, and converting the output thrust into a PWM control signal; the loading device regulates and controls the rotating speed of each propeller based on the PWM control signal, and loads a target aerodynamic load generated by rotation to the scaling model; and skipping to the step of receiving the scale motion data again until a preset stop condition is met. And the loading of the aerodynamic load on the scale model is accurately realized.

The invention discloses a self-coupling PID (proportion integration differentiation) flight control method of a rudder-controlled transverse-row type rotor unmanned aerial vehicle based on dynamic multi-dimensional heterogeneous fuzzy logic, and belongs to the technical field of flight control of rudder-controlled transverse-row type rotor unmanned aerial vehicles. A flight control system architecture of the self-coupling PID flight control method is composed of three core modules: (1) a dynamic multi-dimensional fuzzy logic coupling PID controller (DMHFL-SCPID); (2) control instruction distribution; and (3) a six-degree-of-freedom dynamical model of the rudder-controlled transverse rotorcraft. According to the control algorithm, input and output dynamic parameters of a system are analyzed in real time, and four-dimensional flight control quantities (roll, pitch, yaw and height instructions) are generated. A control distribution strategy based on the aerodynamic characteristics of the rotor converts the instructions into actuating quantity of an actuating mechanism, and flight attitude adjustment is realized by changing aerodynamic load distribution of a rotor system, so that the unmanned aerial vehicle is guided to realize accurate tracking along a predetermined flight path.

The invention provides a friction stir tunnel forming device and method for enhancing bearing performance, relates to the field of machining and inner flow channel forming, and aims to overcome the defects of an inner flow channel prepared through an existing friction stir tunnel forming technology in the aspects of structural bearing and fatigue performance. The non-rotating part is of a hollow structure, the rotating part is coaxially arranged in the non-rotating part, the non-rotating part comprises a clamping part, a step part and a shaft shoulder part, the bottom of the shaft shoulder part is provided with a reinforcing rib manufacturing part, the reinforcing rib manufacturing part is used for containing an inner runner surface material and providing forging pressure, and an inner runner surface with a reinforcing rib structure is manufactured. And a rounded rectangular inner flow channel is manufactured at the stirring needle part of the rotating part, so that the bearing efficiency and rigidity of the rotating part in an aerodynamic load and vibration environment are remarkably improved. And through different sections of the stirring needle part, the manufacturing requirements of the aerospace field on the lightweight and integrated heat management structure in the aspects of complex forms and multifunctional integration can be met.

The invention discloses a semi-physical simulation system and method for an aircraft with variable wings, and belongs to the technical field of semi-physical simulation of variant aircrafts. The method comprises the steps that a PC upper computer builds a model and monitors the process; the real-time simulation computer is connected with all the devices through the optical fiber reflection memory network and executes trajectory calculation, pneumatic processing, airfoil profile reconstruction and deformation control strategy generation. The three-axis servo turntable loads inertial navigation equipment and tracks pose information; the wind tunnel applies an aerodynamic load to the deformed wing; the STM32 driving system realizes multi-stage motor cooperative control; the measuring system acquires deformation data in real time through a laser displacement sensor, a strain gauge array and a coding disc; the flight control system generates a rudder control and deformation instruction; and the annular cascade optical fiber network realizes multi-protocol conversion. Physical deformation wings are integrated into semi-physical simulation, collaborative testing of flight control, deformation control and an aircraft body structure is achieved, deformation interference resistance and flight safety research are supported, and a foundation is laid for optimization and test flight of the wing-variable-bending aircraft.

The invention relates to the technical field of engineering, and discloses a high-speed train stability fluid-structure interaction numerical simulation method and system under wind shear, and the method comprises the steps: building a high-speed train system dynamics model based on system dynamics data, and determining a train body accompanying mark point in the high-speed train system dynamics model; loading the time-varying aerodynamic load input function through a No.93 force element, and outputting motion state parameters of a train body and key components to a high-speed train system dynamic model to obtain a high-speed train system dynamic model after loading; outputting the high-speed train system dynamics model loaded with the load in the form of an FMU format file; an aerodynamic model is established based on the aerodynamic data, a model moment point is determined in the aerodynamic model, and the position of the model moment point is made to be consistent with the vehicle body accompanying mark point; establishing two physical continuums in the aerodynamic model; and synchronously outputting aerodynamic performance parameters and dynamic performance parameters.

A system for controlling at least one active aerodynamic appendage of a road vehicle is described, comprising an actuation control unit operating to implement a predictive control of the active aerodynamic appendage, based on an estimation, performed dynamically while the road vehicle is in motion, of an aerodynamic load demand of the road vehicle in a route section subsequent to one currently travelled.

The invention relates to the technical field of fan equipment management, in particular to a wind turbine gearbox fault diagnosis method and system based on multi-modal data fusion, and the method comprises the steps: carrying out the key structure recognition of a wind turbine gearbox, and marking the key structure as a gearbox key structural part; vibration signals of key structural parts of each gearbox and impeller strain signals of a wind turbine are collected; extracting aerodynamic load characteristics from the impeller strain signal; inputting the aerodynamic load characteristics into a pre-constructed load transmission evaluation model to obtain a load influence transmission coefficient set; performing impeller influence correction on each vibration signal based on the load influence transfer coefficient set to obtain a vibration signal correction data set; performing multi-dimensional feature extraction on the vibration signal correction data set, and converting extracted vibration features into a three-dimensional vibration feature matrix; and performing fault identification on the three-dimensional vibration characteristic matrix by using a preset gearbox fault identification model. The pneumatic load interference can be eliminated, and the fault diagnosis accuracy is improved.

The invention discloses an inflatable returner structure safety analysis method and system considering a thermo-pneumatic elastic effect, and the method comprises the steps: building a structural dynamics sub-model, a fluid domain calculation sub-model and a structural thermodynamics sub-model of an inflatable returner, and comprehensively considering the structural thermal deformation caused by aerodynamic heat and the thermal expansion effect of an internally inflated gas; and a bidirectional coupling relationship among aerodynamic force, aerodynamic heat, structural deformation, temperature and internal charging pressure is constructed through the feedback effect of structural deformation on a flow field and an aerodynamic load. And carrying out multi-physics field simultaneous solution by adopting a time step propulsion method, and finally realizing comprehensive safety evaluation of the temperature, stress and deformation characteristics of the structure. According to the method, aerodynamic load distribution, temperature field change, stress response and vibration characteristics of the inflatable returner in the reentry process can be accurately predicted, so that the thermal protection performance and structural safety of the inflatable returner are comprehensively evaluated, and reliable analysis means and engineering basis are provided for optimization design and structural stability improvement of a thermal protection system.

This invention discloses a dynamic pressure-based method for testing and analyzing hammer shock waves in aero-engines, belonging to the field of aero-engine testing and structural strength design. The method first uses a surge-induced pressure method to generate hammer shock waves at the engine inlet. Based on the flow field characteristics of the air intake outlet section (AIP section) during surge, dynamic total pressure and static pressure measuring points are arranged in a combination of circumferential and radial directions. Pressure signals are synchronously recorded using a high-speed data acquisition system, and four characteristic parameters—surge overpressure, overpressure ratio, loading time, and pressure rise rate—are defined to quantitatively analyze the intensity, spatial distribution, and dynamic process of the hammer shock waves. This invention achieves rapid, accurate, and comprehensive characterization of the aerodynamic load of hammer shock waves, providing reliable input loads directly for the strength design of complex structures such as S-curve air intakes, thereby improving aircraft safety.