539 results about "Aerodynamics" patented technology

The invention discloses a method for measuring an attitude angle of a free throwing object in a wind tunnel test through a binocular system, and belongs to the field of aerodynamics tests based on a photogrammetry technology. Comprising the steps that a binocular system is arranged in a wind tunnel, and internal and external parameters of the binocular system are calibrated through a cross scale; reconstructing the surface mark points of the calibration plate by photogrammetry outside the wind tunnel and establishing a local coordinate system; placing a calibration plate in the wind tunnel, wherein each vector of a local coordinate system is parallel or vertical to an incoming vector, and calibrating a wind tunnel coordinate system by adopting a resection method; carrying out photogrammetry and initial pose installation on mark points on the surface of a thrown object; acquiring each state image of the thrown object and reconstructing the three-dimensional coordinates of the surface mark points; taking the attitude angle of the thrown object as 0 degree as a reference state, and comparing the rigid body transformation relationship between the blowing state point cloud and the reference state point cloud to obtain attitude angle data. Alignment of a wind tunnel coordinate system and a binocular system coordinate system can be achieved, limitation of the appearance of the thrown object is avoided, and attitude angle data of the thrown object are calculated in a non-contact and high-precision mode.

The present invention comprises an aerodynamic profile body with an outer flow surface for flow by a fluid, wherein the aerodynamic profile body comprises: - an upper cover layer and a lower cover layer, which form at least part of the outer flow surface and are designed to be flexurally elastic in an end section of the aerodynamic profile body, and - an actuator device with at least one actuator provided in an interior of the aerodynamic profile body, which actuator interacts with at least one of the cover layers in the flexurally elastic end section in such a way that the cross section of the aerodynamic profile body in the flexurally elastic end section can be changed by the at least one actuator, characterized in that - the at least one actuator is fastened with a first actuator end to a first fastening point in the interior and with at least a second actuator end to a second fastening point in the interior, - wherein the second attachment point is arranged transversely to the span of the aerodynamic profile body at a distance from the first attachment point and on an inner side of one of the cover layers in the flexurally elastic end section, and - the at least one actuator is designed such that the linear distance between the first attachment point and the second attachment point can be changed in order to change the cross-section of the aerodynamic profile body.

The invention discloses a ramjet numerical simulation method, device and equipment and a storage medium, and relates to the technical field of aerodynamics, and the method comprises the steps: determining a dimensionless temperature corresponding to a gas component of an initial flow field; based on the dimensionless temperature, determining a molecular viscosity collision integral function of the gas component in a polynomial fraction fitting mode; determining the viscosity coefficient of the gas component according to the molecular viscosity collision integral function; and generating a computational grid of the ramjet based on the viscosity coefficient so as to perform numerical simulation operation on the ramjet. Therefore, in the numerical simulation process of the ramjet, the polynomial fraction is adopted to fit the viscosity collision integral function, the calculation time of the gas viscosity coefficient can be effectively shortened, and the calculation precision is kept to meet the use requirement; in addition, the method can adapt to the combustion flow field temperature requirement and the component requirement of the ramjet engine, and the numerical simulation efficiency of the ramjet engine can be improved.

The invention discloses a neural operator-based particle image velocimetry (PIVNO) method. Efficient mapping of a particle image pair to a flow field is realized through an end-to-end learning framework. According to the method, a neural operator normal form is adopted, cost volume construction with large calculation amount in a traditional method is avoided, and calculation efficiency and estimation precision are improved. The method comprises the steps of obtaining a synthetic data set and carrying out multi-scale down-sampling, constructing a PIVNO model to realize high-precision flow field prediction, supervising pre-training on the synthetic data set, self-supervising a fine-tuning optimization model on real data, finally predicting a real flow field, and supporting estimation of any resolution. According to the method, global feature aggregation, iterative optimization and high-resolution reconstruction technologies are combined, the flow field estimation precision is improved, and the adaptability of the model on real data is enhanced. The method is efficient in calculation, high in generalization ability and suitable for the fields of aerodynamics, turbulence research, biological fluid and the like, and provides technical support for high-precision flow field measurement.

The invention discloses a method for path planning of an eVTOL unmanned aerial vehicle in a dynamic environment, and the method comprises the steps: S1, designing a reinforcement learning framework TDDPG, and employing an LSTM model as a strategy model; s2, solving exploration and path planning problems in a dynamic environment in combination with a continuous action space; s3, constructing a model based on kinematics and aerodynamics principles; s4, designing a composite reward function; s5, introducing an initialization exploration mechanism and a priority experience playback mechanism; the continuous action optimization capability of the DDPG and the time sequence modeling capability of the LSTM are utilized, so that the unmanned aerial vehicle can perform dynamic obstacle avoidance and dynamic end point planning based on historical states and action information, and the problem of three-dimensional path planning of the unmanned aerial vehicle in a dynamic obstacle environment is solved; a model based on kinematics and aerodynamics principles is designed, it is ensured that a simulation result truly reflects the flight trajectory of the unmanned aerial vehicle in a multi-obstacle environment, meanwhile, state changes of the unmanned aerial vehicle in different flight stages can be effectively simulated, and the accuracy of the motion trajectory of the unmanned aerial vehicle is ensured.

The invention provides an aerodynamic task processing method and device based on multiple agents, and relates to the technical field of aircraft simulation design, and the method comprises the steps: obtaining a task target and working condition parameters inputted by a user; based on the capability of each agent group in the multi-agent system, generating a plurality of sub-tasks based on the task target; distributing the plurality of sub-tasks to corresponding agent groups in the multi-agent system for task processing to obtain a calculation result corresponding to the task target; the multi-agent system comprises a first agent group, a second agent group and a third agent group. According to the multi-agent-based aerodynamic task processing method and device provided by the invention, the role of a person in a traditional CFD normal form is replaced by the agents, automatic execution of the whole process of the CFD task is realized, and the processing efficiency of the aerodynamic task is greatly improved.

The invention discloses a wind power prediction method and system based on mesoscale-microscale dynamics, and the method comprises the following steps: constructing a wind power plant microscale aerodynamic model, setting an inflow boundary condition, generating data according to the inflow boundary condition and the wind power plant microscale aerodynamic model, and constructing a database; constructing a mesoscale-microscale aerodynamic coupling model and a prediction network of the wind power plant; taking the mesoscale-microscale aerodynamic coupling model of the wind power plant as a system environment, training a prediction network by using a database, and inputting mesoscale meteorological prediction data and corresponding inflow boundary conditions into the trained prediction network to obtain a wind power prediction result; compared with an existing method, the method is more beneficial to meeting the requirement of wind power prediction, the reliability of wind power prediction is improved, and the speed and precision of wind power prediction are improved.

The invention discloses an aircraft aerodynamic parameter prediction method based on multi-view airfoil profile concept correlation learning, and belongs to the technical field of aerodynamics, deep learning and computer vision crossing, and the method comprises the steps: converting a three-dimensional model into a multi-view image sequence through a hybrid projection strategy combining orthogonality and surround view; utilizing an optimal transmission theory to map visual features to a learnable airfoil profile concept space to realize semantization and discretization of the features; in combination with flow field working condition coding, aerodynamic parameters are regressed under the constraint of aerodynamic physical laws; and finally, by displaying the matching relationship between the input sample and the airfoil profile concept, the inherent interpretability based on the instance is provided.

The invention discloses an explainable appearance feature learning and quantitative representation method for aerodynamic parameter prediction, and belongs to the technical field of aerodynamics and artificial intelligence crossing. The method comprises the following steps: constructing a collaborative network architecture comprising an aerodynamic prediction module, an airfoil concept learning module and a quantitative distillation agent module; while high-precision and high-efficiency aerodynamic parameter prediction is realized, a prediction result can be decomposed into the sum of quantitative contributions of different airfoil profile concepts, so that a direct explainable basis is provided for the prediction result, and expert users are assisted in understanding and verifying the prediction process of the model.

The invention relates to a multi-target aerodynamic-structure optimization method based on a deep neural network proxy model, and solves the problem that an existing method is insufficient in efficiency, feasibility and credibility, and the method comprises the steps: firstly, carrying out the sampling in a parameterized design target, building an aerodynamic-structure database through CFD / FEA high-fidelity simulation; the method comprises the steps that firstly, a multi-task neural network is used for predicting the lift-drag ratio, quality and stress at the same time, uncertainty is output, then, in NSGA-III multi-target optimization, a proxy model is used for rapidly evaluating and searching out a Pareto leading edge meeting constraints, finally, the precision of the model is gradually improved through high-fidelity checking and incremental updating, and an optimal design scheme is output. According to the method, sub-optimization and repeated iteration caused by'pneumatic first and then structure 'are avoided; the design universality and robustness are improved; a compromise scheme set of the system is directly obtained; and the optimization cost and the optimization period can be obviously reduced.

The invention discloses a boundary layer cushion block leveling method suitable for a wind tunnel half-mode test, relates to the field of experimental aerodynamics, and aims to reduce interference of wind tunnel wallboards in the half-mode test and improve assembly efficiency. The method comprises the following steps: S1, measuring corresponding data according to an established three-dimensional model of a boundary layer cushion block and a balance adapter; s2, based on the data in the step S1, the sizes of the first tool, the second tool, the third tool and the fourth tool are determined; s3, a corresponding first tool, a second tool, a third tool and a fourth tool are manufactured; s4, a balance adapter is installed in the wind tunnel test section, and a balance is measured; and S5, a leveling tool is used for assisting in leveling of the boundary layer cushion block. By adopting the method, the leveling tool is simple and convenient to apply, measurement parameters are few, and the mounting and leveling operation of the boundary layer base plate is effectively simplified; meanwhile, the leveling precision is high enough, the requirement for the installation precision of the boundary layer cushion block of the half-mold test can be met, and labyrinth groove collision is avoided.

An aerodynamics control system for a vehicle may include a repositionable aerodynamic device disposed at a portion of the vehicle, a controller operably coupled to components or sensors of the vehicle to receive information including vehicle performance data and position information for the aerodynamic device, and a vehicle location sensor determining location information for the vehicle. The controller stores the vehicle performance data and the position information in association with the location information for each of a plurality of locations. Responsive to detecting an approach of the vehicle to one of the locations, the controller provides a control instruction to position the aerodynamic device based on recorded vehicle performance data and recorded position information associated with the one of the locations.

The invention belongs to the technical field of aerodynamic wind tunnel tests, and discloses a test device and method for a dynamic derivative wind tunnel test, and the device comprises an aircraft model which is formed by assembling a nose, a middle fuselage, a rear fuselage, a balance, wings and an empennage; the oscillation mechanism is provided with an adapter, and the adapter is connected with the balance; and one end of the wind tunnel strut is connected with the wind tunnel attitude control system and the other end is connected with the oscillation mechanism. The problem that an existing dynamic derivative wind tunnel test model and a test device are low in efficiency is solved, heaving, sidesway, yawing, pitching and rolling oscillation of the model are achieved by replacing the adapters, and the test efficiency of a dynamic derivative wind tunnel test can be effectively improved.

The invention discloses a multi-scale vortex recognition method based on topology analysis, and aims to solve the problems that an existing vortex recognition method depends on a single scale and is insufficient in adaptability, limited in generalization ability, poor in visualization effect and the like. According to the method, firstly, a merge tree is constructed to obtain a multi-scale topological structure of a flow field, candidate vortex regions are screened based on extreme point-saddle point branches, and multi-scale vortex extraction is carried out in combination with a scalar criterion, so that dependence of a traditional method on a fixed threshold is avoided. In order to adapt to unstructured grid data, the method enhances the applicability and robustness of the method in a complex flow environment through adjacency relation reconstruction. In addition, a region diffusion algorithm is adopted to identify the vortex region, and surface extraction and smoothing processing are combined to optimize the visualization effect, so that the boundary of the vortex structure is more continuous and natural. Experimental results show that the method can accurately extract vortex structures of different scales, shows good generalization ability on flow field data of different Reynolds numbers, and has higher adaptability on complex flow fields and unstructured grids compared with a traditional method. The method can be widely applied to turbulence research, aerodynamic optimization, meteorological analysis and engineering flow problems, and an efficient, robust and accurate vortex recognition technology is provided for fluid mechanics research.

The invention discloses a calibration board and wind tunnel feature point-based binocular system wind tunnel coordinate system calibration method, and belongs to the field of aerodynamic tests. Comprising the following steps: reconstructing surface mark points of a calibration plate by photogrammetry outside a hole and establishing a local coordinate system to obtain coordinates under the local coordinate system; a binocular system is arranged in the hole, and binocular internal and external parameters are calibrated through a special cross calibration ruler; arranging a plurality of circular feature mark points on the surface of the hole wall with overlapped visual fields of the binocular system; the calibration plate is correctly placed according to the geometrical relationship, so that each vector of the local coordinate system is parallel or perpendicular to an incoming vector, and the binocular system reconstructs global points of the calibration plate and registers the global points to achieve alignment of a measurement coordinate system of the binocular system and a wind tunnel coordinate system; reconstructing a three-dimensional coordinate of the fixed point in a wind tunnel coordinate system through a binocular system; and in a subsequent test, adopting resection to realize the recalibration of the wind tunnel coordinate system. According to the invention, high-precision and high-efficiency alignment requirements of a measurement coordinate system and a wind tunnel coordinate system of a binocular system can be met.

A method of determining a repair method for a defect in a bladed rotor can comprise comparing the defect in a three-dimensional model of an inspected integrally bladed rotor (IBR) to a plurality of known defects from a repair database; determining the defect is matching a known defect in the plurality of known defects in the repair database; and generating a repair process associated with the known defect in response to determining the defect is matching the known defect. A method can also comprise determining a potential repair process; performing a structural simulation of a finite element model for the inspected IBR with the potential repair; performing an aerodynamic simulation of an aerodynamic model for the inspected IBR with the potential repair; and generating the potential repair process for the defect in response to determining the inspected IBR with the potential repair meets structural and the aerodynamic criteria.

The invention discloses a multi-vortex system space energy evolution process analysis method, belongs to the field of fluid mechanics and aerodynamics, and aims to solve the problem of energy analysis errors caused by integral radius dependence and single-vortex hypothesis limitation in a traditional method. According to the method, a vortex core is positioned through a Liutex method, a vortex to be analyzed is translated to an original point, a pseudo time sequence is generated in combination with evolution direction slices, and a first modal energy distribution and evolution law is extracted through eigen-orthogonal modal decomposition. According to the method, the integral radius does not need to be manually set, the adaptability is high, the vortex global energy space change process can be comprehensively reflected, the method is particularly suitable for energy evolution analysis in complex vortex system scenes such as bird flight and complex aircraft wake flow, a brand new view angle is provided for vortex energy evolution, and the method has certain engineering practical value. The method can be used for quantitative analysis of complex vortex field scenes such as aircraft design, biological bionics and wind energy engineering, and has important engineering application value.

The invention relates to the technical field of wind power generation, in particular to a wind power generation prediction method and system based on digital twin energizing and computer equipment. Comprising the following steps: establishing a blade stress-strain physical model, and quantifying a blade load and fatigue damage by combining aerodynamics and a thin plate bending theory; integrating weather, equipment parameters and operation data, and building a digital twinborn platform of a multi-task learning framework; executing the main task and the auxiliary task in parallel; theoretical generating capacity is calculated through a wind energy conversion equation, and a predicted value is corrected by fusing RNN; and selecting an optimal predicted value based on a confidence interval, and dynamically adjusting a yaw angle and a pitch angle in combination with an extreme weather risk level to form closed-loop control. According to the scheme, the power generation prediction error is reduced by 18%, the service life of the blade is prolonged by 28%, extreme weather early warning is brought forward by 72 hours, and the power generation efficiency and the equipment safety are remarkably improved.

The invention discloses a side wall balance system and method for bionic flexible skin wing measurement, belongs to the technical field of aerodynamic wind tunnel tests, and aims to comprehensively and effectively identify the aerodynamic performance gain effect of a bionic flexible skin lift-augmentation and drag-reduction wing. The side wall balance system comprises a side wall balance, the side wall balance is installed in the side wall of the test section, the side wall balance comprises a floating disc and a fixed disc, the floating disc and the fixed disc are connected through three lateral force units, two longitudinal force units and a transverse force unit, and each force measuring unit comprises a tension-compression balance. The tested model is connected with the floating disc through the low-heat-flux heat insulation flange. Compared with a cantilever beam type side-wall balance, the assembled side-wall balance system of the tension-compression balance provided by the invention has the advantages that the overall rigidity is improved, and meanwhile, the interference among components is greatly reduced. In cooperation with an original measurement method, each element force and moment of force of a bionic flexible skin wing wind tunnel test can be accurately obtained.

The invention belongs to the technical field of flight control, particularly relates to a simulation control method and device for a control load system and a storage medium, and aims to solve the problem of limited effect during simulation control of the control load system in the prior art. The method comprises the following steps: acquiring manipulation input data; carrying out filtering processing on the joystick force / torque data, and carrying out dynamic simulation on the control load system through a pre-constructed digital twin system based on the filtered joystick force / torque data and the control position data so as to determine a virtual force / torque track of the control load system for responding to the control input data; acquiring current flight parameters of the flight simulator, and resolving according to a preset aerodynamic model to obtain a reference force / torque trajectory; and taking the reference force / torque track as a control target, performing optimization solution on the virtual force / torque track, and determining an actuator driving instruction. According to the method, the effect is better when the control of the control load system is executed.

The invention discloses an online Gaussian process regression-based model prediction control method and device for a precise air-drop system, and the method comprises the steps: processing a dynamic model of a parafoil system into a transverse lateral motion linear time-invariant nominal model through the aerodynamic analysis of the parafoil system, and considering the flexibility of the parafoil and a residual part of the nominal model of wind disturbance; designing an online Gaussian process regression algorithm to learn a (potential) time-varying nominal model residual part; a new performance functional is designed for tracking error weighting based on posterior prediction variance of a Gaussian process regression algorithm, a random optimal control problem is constructed and solved in two parts, one part is used for controlling a nominal model, a suboptimal strategy of an off-line solving Riccati equation is adopted, and the optimal control problem is solved. And the other part is used for controlling the residual error and disturbance of the model obtained by online Gaussian process regression learning, and solving to obtain an optimal control sequence so as to obtain an optimal control law. The invention provides a novel and efficient solution for accurate homing control of the air-drop system.

The invention discloses a physical feature perception large language model construction method for flow field understanding and generation, and belongs to the technical field of intelligent aerodynamics, multi-modal deep learning and computer vision crossing. High-level aerodynamic semantics and bottom-level physical feature learning of a flow field are decoupled through a double-codebook sharing mapping mechanism, and alignment of the high-level aerodynamic semantics and the bottom-level physical feature learning is kept at the same time. The discrete unified representation obtained through the token device is combined with a large language model, high-precision physical reconstruction and deep aerodynamic semantic understanding of the flow field image can be achieved at the same time under a single model framework, and the core problems that in the prior art, perception and generation tasks are split, and the fidelity of physical characteristics is low are effectively solved.

The invention discloses a high-speed train head type aerodynamic optimization design method, device and equipment and a storage medium. The optimization design method comprises the steps that a high-speed train aerodynamic simulation model is constructed; performing free-form surface fitting on the front end surface of the high-speed train aerodynamic simulation model to form a grid surface; according to the train head deformation requirement, key spline control molded lines are added to grid lines of the grid face, and grid points are selected from the key spline control molded lines to serve as control points; defining control point parameters and an optimization target; based on the control point parameters and the optimization target, an intelligent optimization algorithm is adopted to carry out optimization solution, and each control point parameter under the optimal target is obtained; and performing high-speed train head optimization design according to the parameters of each control point under the optimal target. According to the method, the free-form surface modeling technology is combined with high-precision computational fluid mechanics and an intelligent optimization algorithm, and the problems that a traditional method is low in design freedom degree, long in period and difficult in global optimization are solved.

The invention relates to the technical field of aircraft design, in particular to an aircraft cost-efficiency optimization system construction method based on collaborative optimization. The method comprises the steps of carding design variables and constraints of engine, pneumatic and structural subjects, constructing a collaborative optimization framework and defining a hierarchical relationship between a system-level optimizer and a subject-level optimizer; constructing a BP neural network agent model for each subject, configuring a unified network structure and training to a precision requirement; integrating an agent model on an Isight platform, and constructing an automatic workflow to realize parameter transfer and iterative optimization; and on the basis of a QT development user interface, parameter setting, workflow calling and result visualization are supported. According to the method, traditional simulation is replaced by proxy model accelerated evaluation, and multidisciplinary coupling conflicts are solved; manual coordination cost is eliminated through automatic workflow; the integrated system improves the optimization efficiency and the research and development automation level, and effectively reduces the research and development cost of the aircraft.

An apparatus is provided that has a skirt (18) that has an inner surface (32). A bending member (14) is present that engages the skirt (18) and is located inboard from the skirt (18) in a lateral direction. The bending member (14) has a vertical length that extends in a vertical direction. A connection is present between the skirt (18) and the bending member (14) that is a sliding connection. The connection has a slot (44) and a fastener (54) that is disposed through the slot (44). Relative movement between the skirt (18) and the bending member (14) causes the fastener (54) to slide along the slot (44).

The invention discloses a fan blade icing monitoring method based on mechanism analysis, and the method comprises the steps: 1, constructing a dynamic mechanism model of "pneumatic-thermal-quality" three-phase strong coupling, local micrometeorological conditions and water drop impact characteristics of each airfoil section and feedback effects of icing growth on aerodynamic configuration and subsequent icing in the blade rotation process are calculated in real time; 2, performing icing prediction based on the constructed dynamic mechanism model, wherein the icing prediction comprises local microenvironment calculation, dynamic icing growth calculation and pneumatic feedback calculation; step 3, judging an icing state; step 4, outputting an icing state and early warning information; the problems that a data-based driving method needs to depend on a large amount of high-quality annotation data, when the data size is insufficient or data distribution changes, the generalization ability and prediction precision of a prediction model can be greatly reduced, the internal mechanism of icing cannot be explained, and the reliability requirement in engineering application is difficult to meet are solved.

The invention discloses an unmanned aerial vehicle speed self-adaptive variable overload half-rolling inversion control method, which comprises the following steps: dividing half-rolling inversion maneuver into a rolling stage and an inversion pull-up stage, setting a switching logic, and adopting different control strategies in each stage, such as attack angle control in the rolling stage, rolling angle rate control based on a robust servo theory and the like, so that the speed self-adaptive variable overload half-rolling inversion maneuver of an unmanned aerial vehicle is realized. Overload control in the reverse pull-up stage and the like. Meanwhile, various technical means such as real-time updating of an aerodynamic model, introduction of machine learning auxiliary parameter estimation, multi-model fusion, a high-precision sensor, sensor data fusion and filtering, real-time compensation of measurement delay, an adaptive robust control algorithm, a multi-modal control strategy and interference suppression based on model prediction are adopted; the control precision, robustness and adaptability of the unmanned aerial vehicle in the semi-rolling inversion process are improved, and the application range of the unmanned aerial vehicle in a complex environment is expanded.

The invention belongs to the technical field of aviation electric propulsion, and provides a power and thermal management parameter optimization integrated framework suitable for a high-power hydrogen electric propulsion aircraft, which mainly comprises an overall design and parameter optimization module, a power distribution and control module and a comprehensive thermal management analysis module, the overall design and parameter optimization module realizes optimal balance of thrust, energy efficiency and stability of the aircraft through aerodynamic design, mission profile analysis, propulsion system configuration and weight estimation; the power distribution and control module dynamically distributes power output of power sources such as a lithium battery, a hydrogen fuel cell and a hydrogen turbine engine based on a model predictive control method and by means of cooperative work of a top energy management controller and component control units, and the optimal power utilization rate of different flight stages is ensured. The comprehensive heat management analysis module integrates a low-temperature cooling loop, a non-low-temperature heat management system and a temperature monitoring and heat recovery unit, accurately controls and adjusts the temperature and heat consumption of key components, and ensures that the key components always run in a safe temperature range; through parameter transmission and feedback iterative optimization between the modules, the energy efficiency and stability of the aircraft under the high-load condition are remarkably improved, and the development requirements of future high-power hydrogen-electric propulsion aircrafts for high efficiency, low carbon emission and multi-working-condition adaptability are met.

The invention relates to the technical field of high-speed railway tunnel aerodynamics, in particular to a railway tunnel micro-pressure wave pneumatic analysis and evaluation management system which comprises the following steps: S1, speed verification: acquiring the current train speed; s2, track type judgment: obtaining the track type of the tunnel; s3, tunnel length judgment: obtaining the tunnel length; s4, micro-pressure wave evaluation: calculating a micro-pressure wave peak value, comparing the micro-pressure wave peak value with a control standard, and judging whether the micro-pressure wave peak value meets the standard or not; s5, mitigation measures: when the micro-pressure crest value exceeds the standard, adopting the mitigation measures, and updating the input parameters to perform modeling simulation and evaluation again; and S6, outputting a result: generating a report. According to the method, the automation level and the intelligent degree of tunnel pneumatic safety design are effectively improved, and the risk of environment and safety problems caused by micro-pressure waves is reduced.

The invention discloses an electric aircraft cross compass attitude control system, and relates to the technical field of unmanned aerial vehicle attitude control, the electric aircraft cross compass attitude control system comprises # imgabs 0 # rotor motors and further comprises an annular base frame, and # imgabs 1 # rotor motors form an annular array based on the annular base frame; a controller; and the driving mechanism is used for receiving the driving electric signal of the controller and adjusting the position of the rotor motor. According to the cross compass attitude control system of the electric aircraft, when the function of the rotor motor is abnormal or damaged through automatic monitoring, the abnormal or damaged rotor motor is abandoned, and the position or the rotating speed of the rotor motor is correspondingly adjusted based on a corresponding strategy, so that the rotor motor annularly moves relative to the annular base frame; according to the invention, the attitude basis conforming to aerodynamics is reconstructed to optimize lift distribution to compensate imbalance, so that the aircraft can stably fly to the maximum extent in an extreme environment, high controllability is kept, and a better use prospect is brought.