78 results about "Flight height" patented technology

The invention relates to the technical field of electric power, in particular to an unmanned aerial vehicle route automatic planning method and system for a complex space of a transformer substation. Analyzing at least one inspection task instruction input by a user to obtain a task type corresponding to each inspection task instruction and a data acquisition requirement corresponding to the task type; according to a preset three-dimensional semantic map of the transformer substation and the data acquisition requirement of each inspection task instruction, a flight route of at least one unmanned aerial vehicle is automatically generated by adopting a path planning algorithm, and the flight route comprises a waypoint sequence, a flight height, a shooting angle and a holder action instruction; the three-dimensional semantic map comprises no-fly zone information in the transformer substation, a plurality of devices, the position of each device, the device type, the electrification attribute and the safety rule label. And controlling the corresponding unmanned aerial vehicle to inspect target equipment in the transformer substation according to the flight route of each unmanned aerial vehicle. And large-scale and standardized inspection operation is realized.

The invention belongs to the technical field of unmanned system intelligent control and path planning, and discloses a multi-unmanned aerial vehicle path planning method based on a multi-population grey wolf optimization algorithm, and the specific technical scheme comprises the steps: 1, building an environment model and constraint conditions of unmanned aerial vehicle three-dimensional path planning; 2, constructing a multi-target cost function including fuel consumption cost, flight height cost, threat area cost, time cooperation cost and space cooperation cost; 3, optimizing the multi-target cost function by adopting a multi-population grey wolf optimization algorithm to obtain an optimal flight path; according to the method, the global search capability is remarkably enhanced, and the multi-group clustering strategy and the periodic convergence factor act together, so that the algorithm can effectively jump out of local optimum, a path scheme closer to global optimum is found in a complex solution space, the convergence speed and the calculation precision are greatly improved, the collaborative planning effect is excellent, and the method is suitable for large-scale popularization and application. The method shows strong environmental adaptability and robustness, and has a very high practical application value.

The invention discloses an anti-explosion method and system for a vertical fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle and a medium, and the anti-explosion method comprises the steps: monitoring the operation conditions of motors of all rotor assemblies in real time, and determining a fault motor when an abnormality occurs; performing first stability control on other motors without faults, the control surface of the fixed wing and the control surface of the empennage according to the fault motor; acquiring the current flight height of the unmanned aerial vehicle, and performing landing control on the unmanned aerial vehicle according to the current flight height until the unmanned aerial vehicle lands to the ground; and performing fault detection processing on the unmanned aerial vehicle, and generating a fault processing flow record. The fault motor can be accurately identified and positioned in the landing process of the unmanned aerial vehicle, and corresponding emergency measures are taken according to the position relation of the fault motor, so that the unmanned aerial vehicle can maintain stability in the air and stably land on the ground, the phenomenon of explosion of the unmanned aerial vehicle is effectively avoided, and the safety of the unmanned aerial vehicle is improved. And the landing safety and stability of the unmanned aerial vehicle are ensured.

The invention relates to a resource orchestration method and device for a collaborative network, equipment, a storage medium and a program product. Comprising the following steps: constructing an optimization model taking maximization of total satisfaction, minimization of service duration and minimization of energy consumption of an unmanned aerial vehicle as targets; the total satisfaction is the sum of the satisfaction of each target area, the service duration is the sum of the sensing duration, the transmission duration, the calculation time and the flight time corresponding to each target area, and the energy consumption of the unmanned aerial vehicle is the sum of the sensing energy consumption, the transmission energy consumption, the flight energy consumption and the hovering energy consumption corresponding to each target area; solving the optimization model under the constraint of a preset constraint condition to obtain a computing resource allocation strategy and a sensing communication strategy; comprise computing time, sensing duration, service sequences, flight heights and transmission power of various computing resources. By adopting the method, multi-target collaborative optimization is realized, namely, the service duration and the energy consumption of the unmanned aerial vehicle are minimized while the total satisfaction degree of the system is maximized.

The invention belongs to the technical field of aircraft fuel tank inerting, and particularly relates to a method for calculating the shedding rate of a catalyst coating of an ozone converter in single flight. Comprising the following steps: S1, acquiring the mass M of a catalyst coating of the ozone converter; s2, acquiring flight profile data, wherein the flight profile data comprises a relationship H (t) between the flight height H and time t of the aircraft, time h required by one flight cycle of the aircraft, and time t1 and t2 for starting working and closing of an inerting system; s3, the relation m (H) between the mass m of dust contained in unit volume of entrained air in the entrained air of the inerting system and the flight height H is obtained; s4, the air entraining flow Q of the inerting system is obtained; s5, obtaining a guarantee value F and a dust holding capacity M1 of the minimum replacement interval of the filter; and S6, calculating the single flight shedding rate mu of the catalyst coating of the ozone converter.

The invention discloses a take-off and landing guiding method and device for a manned vertical take-off and landing aircraft, and the method comprises the steps: carrying out the automatic division of a flight guiding stage through the entering and exiting logic based on the flight height, the vertical speed and the horizontal speed; automatically activating a first guide mode in a vertical takeoff stage and a vertical landing stage according to a short-distance target point alignment principle, and automatically activating a second guide mode in an acceleration climbing stage, a cruise stage and a deceleration descending stage based on a track deviation and speed guide cooperation principle; respectively configuring special guidance symbols and general flight information of the first guidance mode or the second guidance mode; the guidance available state is combined, a corresponding guidance state notice is generated according to the flight guidance stage, and the guidance available state judgment basis comprises sensor data validity, GPS positioning accuracy not larger than a first preset value and inertial navigation system error smaller than a second preset value; according to the invention, visual and accurate flight guidance information meeting the requirements of different flight stages can be provided for pilots.

The application provides a fixed-wing aircraft airspeed calibration flight test method based on a standard machine. The method comprises the following steps: determining the weight of the fixed-wing aircraft as a first weight, setting the aircraft to a specified take-off configuration, and taking off according to a take-off procedure; the standard machine flies to a specified airspace according to a plan; at an initial specified flight height, a tow cone is released to a specified length, and the tow cone can obtain an accurate static pressure value in the current area without being affected by a spoiler; the flap and slot wing configuration of the fixed-wing aircraft is set to a first flap and slot wing configuration; the aircraft is trimmed at a given speed; the speed in the above step is set to other speeds within the speed envelope of the first flap and slot wing configuration, and the steps are repeated; the standard machine obtains airspeed errors under the first flap and slot wing configuration and different speeds; and the airspeed errors under the first flap and slot wing configuration and different speeds are fitted to obtain an airspeed correction curve under the first weight, the first flap and slot wing configuration. More accurate airspeed errors can be obtained.

The invention provides a busy waypoint traffic capacity simulation evaluation method based on a release interval. The method comprises the following steps: step 1, preprocessing flight track data of a flight; step 2, extracting waypoint operation characteristic parameters; step 3, waypoint traffic capacity evaluation simulation; according to the method, traffic flow distribution conditions of different height layers at waypoints, passing-point flight release time interval distribution, aircraft model hybrid ratio and other characteristic data are counted based on historical data, a waypoint topological structure is combined, a busy flight height layer of a busy waypoint serves as an experimental scene, and the simulation evaluation method is constructed.

A UAV control method, a device, a UAV, and a storage medium are provided. The method includes: obtaining a UAV's take-off position; obtaining a height map of an area around the take-off position; determining height information of a highest target in the area around the take-off position based on the height map; determining a relative height between the highest target and the take-off position based on the height information of the highest target; determining a restricted flight altitude of the UAV relative to the take-off position based on the relative height, and controlling the UAV based on the restricted flight altitude; where the restricted flight altitude is greater than or equal to the relative height. It thus can ensure flight safety while offering more reasonable and user-friendly flight flexibility and freedom.

The present application relates to a kind of ground effect wing ship longitudinal coefficient estimation method and its aerodynamic characteristic analysis system, belong to the technical field of ground effect wing ship. It covers preliminary design ground effect wing ship scheme, design and manufacture wind tunnel model, obtain data by 3 times variable flight height test, and utilize these data to deduce the mathematical expression of ground effect wing ship longitudinal aerodynamic coefficient, estimate the longitudinal aerodynamic characteristic in any flight height state by the mathematical expression of ground effect wing ship longitudinal aerodynamic coefficient, to simplify test procedure, reduce test number. The present application significantly reduces the workload of model blowing test by combining theoretical analysis with a small amount of test data, shortens the research and development cycle, reduces the consumption of funds. At the same time, the method can accurately obtain the key partial derivative and relative ground effect height in the stability calculation of ground effect wing ship, improve the design efficiency and accuracy, and has important promoting effect on the development and application of ground effect wing ship technology.

The invention discloses a flying robot inspection system and method based on the Internet of Things, and relates to the technical field of big data analysis. Complete flight data of multiple devices of the same type and the same specification are screened, each inspection state characteristic parameter and the corresponding power consumption value are analyzed and separated in a structured mode, and a double power consumption value prediction mechanism is constructed; according to the method, data subsets are split by a flight state characteristic parameter factory, an exclusive service interface is configured, a first inspection power consumption value is output through a neural network model based on historical common data training, and a second inspection power consumption value is obtained through cooperative training by combining real-time parameters and recent historical data intercepted by a height return flight sliding window; the minimum inspection power consumption value needed by return flight is accurately calculated by constructing the return flight height mapping table, the return flight request is generated through comparison of the remaining electric quantity, the risks of contact loss and falling damage caused by insufficient electric quantity of the flying and climbing robot are effectively avoided, the safety and reliability of inspection operation are greatly improved, and stable application of equipment in complex scenes is guaranteed.

The application discloses an enhanced multi-strategy whale migration optimization UAV path planning method and system, and belongs to the technical field of civil path planning. The method comprises the following steps: constructing a three-dimensional path planning model of a mountainous environment; establishing a comprehensive objective function, wherein a highly relevant dynamic threat range model is adopted for threat cost, a flight height is adopted for dynamic adjustment of a threat source influence radius, and a flight stage is adopted for adaptive adjustment of weight coefficients of each cost item; S3 adopts an initialization strategy based on a good point set theory to generate an initial candidate path, and adopts a golden section ratio to generate an initial population with uniform distribution; S4 adopts an enhanced multi-strategy whale migration optimization algorithm for iterative optimization, calculates a population diversity index D(t), and adaptively selects a Lévy flight strategy or a Cauchy distribution disturbance strategy according to comparison between D(t) and a preset threshold value and a current iteration number; and S5 judges a termination condition and outputs an optimal path. The application improves the safety and efficiency of path planning.

The invention provides an active pneumatic control system based on an electroactive polymer fiber array and a miniature flight detection device, belongs to the technical field of miniature robots and intelligent materials, and aims to solve the problem that a passive wind power aircraft cannot be actively controlled. The control system comprises a fiber array composed of a plurality of independent EAP flexible fibers, and a control module capable of applying accurate electric signals to specified fibers. The electric signals drive the fibers to generate reversible deformation, so that the collective pneumatic form of the fiber array is changed. The detection device mainly comprises a detector main body, a fiber system and an attitude control system. The fiber system is composed of a fiber array and is unfolded in a natural state to form a windward sail face providing pneumatic elasticity. The attitude control system symmetrically or asymmetrically drives the fiber array through a control module, changes the three-dimensional configuration of the sail surface, adjusts the aerodynamic characteristics in real time, and achieves the precise control of the flight height and direction. The passive aircraft is suitable for a deep space exploration environment.

The invention discloses a cooperative control method for an extended-range engine power system of an unmanned aerial vehicle, and relates to the technical field of computer processing, and the method comprises the following steps: obtaining the current flight height, the current flight speed, the current flight attitude angle and the remaining electric quantity of a battery of the real-time unmanned aerial vehicle; determining motor output power and kinetic energy recovery power in combination with a future height change trend in a preset flight plan; determining a first total power demand according to the current flight height, the current flight speed and the current flight attitude angle; and determining a first power distribution proportion of the output power of the motor to the first total power demand through a table look-up or optimization algorithm according to the residual electric quantity of the battery and the future height change trend. According to the method, the evolution direction of the energy demand is anticipated prospectively based on the flight plan, the weight of motor output and kinetic energy recovery is adjusted in advance, and dynamic pre-compensation of power distribution is achieved.

A path planning method and system of multi-low-altitude intelligent agent cooperation, electronic equipment and storage medium, relate to the field of flight management, and alleviate the problems of insufficient utilization of vertical airspace resources and low airspace carrying capacity in the prior art. A path planning method obtains a three-dimensional airspace model for a target low-altitude airspace, and then obtains a low-altitude airspace constraint model; based on the task type information of each low-altitude intelligent agent, a flight height constraint model is obtained; a path search method is used to obtain a phased flight path of each low-altitude intelligent agent, and then obtain spatiotemporal occupancy information; the spatiotemporal occupancy information is subjected to conflict detection to plan the phased flight path; the phased flight path is subjected to smoothing, optimization processing and executability verification; and the phased flight path that passes the verification is used as an executable flight path. The present application is suitable for multi-intelligent agent cooperative path planning under conditions such as complex urban low-altitude environment and low-altitude task density improvement.

The invention discloses a flying height control and trajectory tracking method for an aerocar in a ground-air dual mode, and the method comprises the following steps: 1, building a four-rotor aerocar dynamics model in a flying state; 2, designing a height controller based on adaptive RBF neural network sliding mode control according to the four-rotor aerocar dynamics model established in the step 1, and controlling the flight height by dynamically adjusting the rotating speed of a motor; and step 3, in a ground driving state, establishing a vehicle trajectory tracking model, designing a linear model prediction control algorithm, and outputting a required front wheel turning angle to realize trajectory tracking control. According to the method, air-ground dual-mode control of the hovercar is innovatively provided, and operation and control of the hovercar are well achieved.

The invention discloses an aviation unmanned aerial vehicle control method and system with intelligent endurance and cooperative obstacle avoidance functions, and belongs to the technical field of aviation unmanned aerial vehicles, and the method comprises the steps: building an energy consumption model through an energy consumption prediction algorithm based on the flight speed, the flight height, the load, the air resistance obtained through the calculation of the real-time wind speed and wind direction, and the battery discharge characteristic; predicting energy consumption under different flight parameter combinations; dynamically optimizing the flight path, the flight speed, the flight height and the task execution sequence of the unmanned aerial vehicle by using a dynamic path planning algorithm; carrying out type identification, geometric modeling and motion trail prediction on environmental obstacles; and when a potential collision risk is detected, dynamically calculating a minimum safe avoidance distance based on an obstacle type and a motion state, and generating a coordinated and consistent obstacle avoidance instruction through action collaborative correction, so that each unmanned aerial vehicle smoothly recovers to an original task path after completing obstacle avoidance. And the cruising ability and the safety of the unmanned aerial vehicle are remarkably improved.

The invention discloses a load calculation method for a complex pneumatic profile nozzle, and the calculation method comprises the steps: rapidly obtaining the large-batch load data of the complex pneumatic profile nozzle in a flight envelope through introducing a concept of a load impact factor of the complex pneumatic profile nozzle, so as to meet the requirement of fatigue life evaluation of the complex pneumatic profile nozzle. The method comprises the specific steps that firstly, basic characteristics of load distribution of the complex aerodynamic surface nozzle are obtained based on a CFD numerical calculation method or a nozzle test, and load influence factors of the complex aerodynamic surface nozzle are obtained; and then the nozzle load variable quantity caused by the flight height, the flight Mach number and the engine state change is calculated by utilizing a nozzle load theoretical formula derived by a one-dimensional isentropic internal flow theory.

A task delivery method assisted by an unmanned aerial vehicle belongs to the field of unmanned aerial vehicles, and comprises the following steps: designing a two-stage scheduling and delivery architecture, and carrying out multi-objective optimization of maximizing task satisfaction and minimizing unmanned aerial vehicle energy consumption on the premise of considering soft deadline, flight height multiplexing and channel conflict; according to a multi-target optimization result, the scheduling center allocates tasks to the unmanned aerial vehicles in real time, and the unmanned aerial vehicles dynamically deliver the tasks in a distributed mode; a multi-unmanned aerial vehicle dynamic concurrent delivery scheme is designed, and the scheme comprises a Gal-Shapley-based task allocation algorithm, a Q-Learning-based unmanned aerial vehicle path planning algorithm and a channel conflict avoiding strategy, and is used for jointly optimizing task allocation identifiers and unmanned aerial vehicle paths, dynamically updating flight paths of multiple unmanned aerial vehicles under the condition of flight height multiplexing and change, and realizing multi-unmanned aerial vehicle dynamic concurrent delivery. And collision-free delivery is realized. The method is high in robustness and stability, excellent in expandability, low in calculation complexity and wide in application prospect.

The invention relates to the technical field of optical imaging, in particular to an aerodynamic optical aberration calculation method, which comprises the following steps of: firstly, dividing an external flow field for an aircraft model carrying an optical imaging system, and setting a speed variable condition, a plurality of flight height sampling points and a corresponding state boundary condition of the aircraft model; according to the Reynolds number and the viscosity interference parameter under each state boundary condition, dividing the flight height sampling points into two types of calculation aberration and prediction aberration; for a predicted aberration sampling point, randomly selecting one as a reference point, calculating the pneumatic optical aberration of the predicted aberration sampling point, and predicting the pneumatic optical aberrations of other predicted sampling points based on the pneumatic optical aberration of the reference point; for aberration calculation sampling points, the corresponding pneumatic optical aberration is solved by directly calculating external flow field density distribution and conversion refractive index distribution of the aberration calculation sampling points. According to the invention, through one-time pneumatic optical transmission aberration calculation, different flight heights are expanded, and the demand for large-scale calculation resources and the time required for evaluation are significantly reduced.

The present application relates to the technical field of inspection planning, and particularly relates to a UAV low-altitude inspection planning system and method based on danger analysis, which performs detailed evaluation on the route of the UAV, combines environmental abnormal influence and dangerous area influence, and considers building collision danger, performs multi-dimensional calculation on flight complexity evaluation, flight height danger and building density danger, comprehensively calculates dynamic and static risks, finally, comprehensively obtains global route danger evaluation result by combining building collision danger of each area and risk evaluation result, and selects the route with the minimum danger according to the global route danger evaluation result, so that the whole scheme realizes multi-dimensional and comprehensive risk evaluation, considers various factors such as environment and building, meets relevant standard requirements, and can effectively reduce UAV flight risk.

The present application belongs to the field of aircraft monitoring and detection, and particularly relates to a kind of aircraft abnormal event detection method, system and storage medium for different voyage scenarios.The present application takes flight height as reference, proposes uniform dynamic time warping (UDTW), obtains mapping matrix {I,v',R,Q'} from DTW under full shot and equal length constraint, and synchronously acts on multivariate flight data with the mapping to output uniform length sequence;Then input the equal length sequence into the weak supervision detector based on attention, output event level label Y, differential feature weight Δβ and instance level probability p ins , realize accurate positioning and explainable analysis of cross voyage anomaly.The method is suitable for high-dimensional, non-equal length and mixed variable data, and improves detection accuracy and robustness.

The application discloses a kind of based on AI vision's network unmanned plane ground effect flight method, equipment and medium, the method includes: in the height calibration stage before unmanned plane flies to next target tower pole, first real-time image in flight direction is collected in real time;According to the image width proportion of distribution wire in first real-time image, dynamically adjust the height of unmanned plane, until reach target tower safety height;After unmanned plane flies over target tower pole according to target safety height, second real-time image in flight direction is collected in real time by vision sensor;According to the image width proportion of distribution wire in each second real-time image and the real-time positioning information of unmanned plane, control unmanned plane to target tower as starting point, follow the height fluctuation of distribution wire in flight direction and carry out flight height change, the technical scheme of the embodiment of the application realizes unmanned plane autonomous height adjustment by visual intelligent analysis, greatly reduces equipment cost and operation complexity, significantly improves the efficiency and quality of unmanned plane inspection.

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a short-distance take-off and landing control method thereof.A power unit, a rotor head and a tilting mechanism for controlling the rotor head to tilt are arranged on a vehicle body of the unmanned aerial vehicle; a tilting transition stage is configured before an off-ground climbing stage in the take-off process of the unmanned aerial vehicle, and in the tilting transition stage, a tilting mechanism increases the dip angle sina of a rotor wing head to a first dip angle in multiple stages according to the increase of the current horizontal speed Vx of the unmanned aerial vehicle; and when Fn is larger than or equal to W, the unmanned aerial vehicle enters a ground clearance climbing stage, the attack angle socb of the unmanned aerial vehicle is adjusted, and when the flight height of the unmanned aerial vehicle reaches the first target height, the tilt angle sina of the rotor head is gradually reduced. According to the short-distance take-off and landing control method for the unmanned aerial vehicle, the rotor head is controlled to realize tilting and swinging of the unmanned aerial vehicle in the take-off and landing process, and the runway length required by take-off and landing of the unmanned aerial vehicle can be remarkably shortened.

To provide a flight method for stably flying a rotary wing unmanned aircraft even in a strong wind.SOLUTION: A method for flying a rotary-wing unmanned aerial vehicle, comprising: when a wind speed at a predetermined height is less than or equal to 10m / s, flying at a flight height less than or equal to 0.5 meters to fly at a wind speed less than or equal to 5m / s.SELECTED DRAWING: Figure 5

The invention belongs to the technical field of recycling of reusable rockets, and particularly relates to a starting method for a first-sublevel vertical recycling landing section of a rocket. The method comprises the steps that the maximum allowable thrust of an engine is determined, and an engine starting decision window is determined; the maximum allowable starting height is set, landing section starting judgment is carried out based on the maximum allowable starting height to complete engine starting, and the flight state parameters of the current landing section are obtained in real time; in each start-up judgment period, if the current flight height is lower than the maximum allowable start-up height, calculating to obtain the required thrust of start-up in the current flight state based on a one-dimensional vertical motion model, and determining a preset threshold value of the fixed-height start-up height based on the vertical descent speed; and comparing the required thrust with a preset thrust threshold value in real time so as to finish accurate judgment of the startup time, and meanwhile, increasing a height to allow startup, and taking a fixed-height startup height as a reliable startup measure. According to the method and the device, the accuracy and the reliability of startup judgment are realized.

The application discloses a flying car cabin oxygen concentration regulation method, device, equipment and program product, comprising: obtaining the cabin environment parameters, the current flight height and the passenger physiological parameters of the flying car; determining the oxygen supply demand level of the flying car according to the cabin environment parameters and the passenger physiological parameters; determining the target oxygen supply strategy according to the current flight height and the oxygen supply demand level, and regulating the oxygen concentration of the target flying car through the air circulation system and / or the oxygen generation and supply system. The application realizes dynamic and accurate adjustment of the oxygen concentration of the flying car, guarantees the breathing safety of the passengers, and can be applied to the technical field of flying cars.

The invention discloses a plane structure-oriented airborne camera homography mapping chain calibration method. The method comprises the steps of selecting a camera, determining a flight height, planning a waypoint distance and layout, and designing a flight route. Performing trial flight in a waypoint area in the middle of a preset route, and using a natural marker for initial calibration; visible light or infrared thermal images are collected, and the collected images are preprocessed; calibrating a frame image as a reference point, and dividing an aerial image sequence into a front acquisition sequence and a rear acquisition sequence; selecting a calibration feature point from the marker; establishing a world coordinate system of the calibration frame image; a projection transformation matrix of the image coordinate system and the world coordinate system is solved, a proportionality coefficient is obtained through calculation, and calibration of the calibration frame image is completed; solving a homography matrix between adjacent frame images of a front sequence and a homography matrix between adjacent frame images of a rear sequence; constructing a homography matrix mapping chain of pixel coordinates of any frame image and the calibration frame image through matrix multiplication; solving the world coordinates of the feature points of any frame of image, and completing the calibration of each frame of image.

The invention discloses an emergency aerial remote sensing method, device and equipment and a storage medium, and belongs to the technical field of aerial remote sensing. The method comprises the steps of searching an emergency target and determining longitude and latitude coordinates of the emergency target; calculating the distance between the vertical point of the aircraft on the ground surface and the emergency target according to the relative flight height of the aircraft and the angle information of the remote sensing equipment on the aircraft; according to the distance between the vertical point of the airplane on the ground surface and the emergency target and the latitude and longitude coordinate values of the emergency target, calculating latitude and longitude variation of two end points of the route relative to the emergency target, and generating the route; and flying according to the generated route, and acquiring multi-source remote sensing data of the emergency target by using different remote sensing devices. Through intelligent route planning, the problems of blind flight and poor data quality in traditional emergency remote sensing are solved, the target searching efficiency and the remote sensing data precision are remarkably improved, and the method is suitable for emergency scenes such as natural disaster monitoring and accident search and rescue.

The application discloses a kind of methods for judging droplet impact on hypersonic wall in high water vapor environment, and relates to the technical field of hypersonic speed, comprising, obtaining the initial physical parameters of droplet and the leading edge flow field parameters of hypersonic vehicle;Based on the initial physical parameters of droplet and the flow field parameters behind shock wave, the breaking displacement of droplet before breaking and vaporizing can be calculated;Based on the leading edge flow field parameters of the vehicle, the maximum geometric distance of droplet from passing through the shock wave to the wall of the vehicle is calculated;Impact criterion formula is constructed, the breaking displacement is compared with the maximum geometric distance, and the impact determination signal of droplet is output according to the comparison result.The application realizes the accurate determination of droplet impact or not, adapts to the sea-skimming flight condition of hypersonic vehicle, and can also determine the impact risk boundary to guide the flight height planning, and overall realizes the efficient and accurate judgment of droplet impact on hypersonic wall in high water vapor environment, to ensure the flight safety of the vehicle.