310 results about "Level flight" patented technology

The invention discloses a decision-making method and decision-making system for low-power autonomous landing based on a vertical take-off and landing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle landing decision-making. Comprising the following steps: acquiring topographic point cloud data, establishing a neural network model, and extracting and predicting topographic feature parameters including obstacle density and maximum height; calculating an obstruction influence index and a vertical energy consumption influence index in combination with cruise area point cloud data and real-time environment parameters including environment temperature, wind speed and the like, and correcting a return electric quantity threshold value; dynamically correcting the return electric quantity threshold value by further combining the health parameters of the battery, including storage time, cycle charging times and environment temperature; and comparing the dynamic homeward voyage electric quantity threshold with the real-time electric quantity, and generating a landing or homeward voyage decision instruction. The horizontal flight and vertical take-off and landing energy consumption of the unmanned aerial vehicle under different topographic conditions is comprehensively considered, and correction is performed in combination with the battery performance, so that the electric quantity management strategy of the unmanned aerial vehicle is more intelligent and precise.

The invention discloses a multi-vertical fixed-wing unmanned aerial vehicle flight path planning and intelligent obstacle avoidance method, and relates to the technical field of unmanned aerial vehicle flight path planning. Comprising the following steps: according to the dynamic characteristics of the multi-vertical fixed-wing unmanned aerial vehicle in a vertical take-off and landing mode and a horizontal flight mode, constructing a unified kinematics model and initializing unmanned aerial vehicle parameters and an environment model; carrying out global pre-flight path planning by adopting an improved particle swarm optimization algorithm, and generating a global flight path of the multi-vertical fixed-wing unmanned aerial vehicle according with flight characteristics; in the actual flight process, in combination with a deep reinforcement learning DDPG and an improved interference fluid power system IIFDS algorithm, flight modes of the unmanned aerial vehicle are intelligently switched, and multiple dynamic obstacles are efficiently and automatically avoided; and after obstacle avoidance is completed, the unmanned aerial vehicle rapidly restores the fixed-wing flight mode and flies along the preset route again. According to the method, the problem of multi-vertical fixed-wing unmanned aerial vehicle cooperative flight path planning in multiple complex scenes can be solved, and the purpose that the cost of task execution of multiple unmanned aerial vehicles is minimum is achieved.

The invention relates to a fighter bottom layer flight control method based on deep reinforcement learning. The method comprises the following steps: S1, designing a target updating mode and a termination condition function of flight control according to a simulation environment; s2, constructing a state space, an action space and a reward function controlled by the fighter according to the simulation environment; s3, building a deep neural network model based on a PPO algorithm; and S4, training a fighter bottom layer flight control model based on a PPO algorithm. According to the control method disclosed by the invention, the intelligent agent only needs to concentrate on advanced task planning when completing high-level task decisions such as battle and tracking, so that the training of basic decisions for bottom-layer aircraft control is reduced, the algorithm is easier to converge, and the learning cost is reduced.

The utility model relates to a cross-medium aircraft convenient for adjusting flight attitude, which comprises a water-drop-shaped centrosymmetric aircraft body with an aircraft head and an aircraft body, and the aircraft head of the aircraft body is positioned on the front side of the aircraft body. The aircraft body is further provided with an underwater power mechanism used for providing underwater flight power and an air power mechanism used for providing air flight power, the side portion of the aircraft body is connected with four or six fixed wings, slip-flow rudders controlled to rotate are arranged on the rear edges of the fixed wings, and the rotating axes of the slip-flow rudders are parallel to the wing faces of the fixed wings and perpendicular to the long axis of the aircraft body. Each fixed wing is provided with a slipstream rudder, so that the cross-medium aircraft can be conveniently controlled to pitch, roll, yaw and other actions, and the cross-medium aircraft can be conveniently switched between a hovering flight attitude and a level flight attitude.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The first wing can be coupled to the boom by a (first) articulated joint. The propulsion assembly can be coupled to the boom by a (second) articulated joint. The articulated joints can provide various adjustments between the wing(s) and the boom (e.g., stowed, deployed, anhedral, dihedral, sweep, angle of attack, collective pitch control, the cyclic pitch control, etc.) and between the propulsion system and the boom (e.g., to move between vertical flight and horizontal flight). A payload can be connected to the boom with one of the articulated joints whereby the articulated joint adjusts a position of the payload during flight to maintain desired flight characteristics and stabilize the payload.

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention belongs to the field of aircraft design and control, and particularly relates to a control method of a combined type unmanned aerial vehicle based on passive hinge tilting. The composite unmanned aerial vehicle carries a tilting device and a fixed wing, the tilting of the tilting device is controlled by differential speed of motors at the two ends of the tilting device, and vertical take-off and landing and tilting transition of the unmanned aerial vehicle are controlled by adopting a PID control law. The main control board controls the main power motor and provides main power for the vertical take-off and landing stage and the horizontal cruise stage of the unmanned aerial vehicle. The sub-control board controls tilting motors at the two ends of the tilting device and provides power for enabling the tilting device to tilt. When the unmanned aerial vehicle takes off and lands, the tilting device is in a locked state, and after the unmanned aerial vehicle reaches a cruise height, the unmanned aerial vehicle is controlled to fly horizontally through the tilting device to complete a cruise task; and after the cruise is finished, the unmanned aerial vehicle is controlled to enter a hovering state through the tilting device. According to the invention, decoupling of forward flight and pitch angle attitude is realized, multiple purposes are realized, and flight tasks can be completed in a complex environment.

The invention discloses an airborne low-detectability photoelectric long-distance stable tracking and aiming method based on a time-sensitive opposite target, and belongs to the technical field of airborne photoelectric detection and target tracking. The method comprises the following steps: step 1, target detection and miss distance calculation: in a level flight section of an airplane, imaging a target in a field of view, carrying out target detection by adopting an optical flow method, and detecting a moving target by analyzing a motion vector of pixel points in an image sequence; and resolving the deviation amount of the target image relative to the visual axis in real time, namely the target pixel miss distance. 2, designing a stable tracking loop: designing a two-layer control structure for the stable tracking loop, stably inhibiting high-frequency disturbance by a gyroscope of an inner loop, performing tracking correction on low-frequency deviation by an outer loop based on pixel miss distance, and finally realizing high-precision tracking. On the basis of real-time pixel miss distance feedback, a two-layer control structure is designed, the miss distance fed back by an outer ring tracking loop is converted into an inner ring control instruction, and the tracking precision and stability are improved.

The invention belongs to the technical field of aircraft simulation, and particularly relates to an aircraft maneuvering load simulation method and device considering a downwash effect. The method comprises the following steps: S1, carrying out 1g level flight balancing on the aircraft, and determining a balancing attack angle of the aircraft and a balancing elevator skewness of the aircraft; s2, superposing the aerodynamic coefficient increment brought by the downwash angle of attack to the aerodynamic coefficient of the aircraft body, and determining the aerodynamic force of the aircraft; s3, dynamic response solving is carried out on aerodynamic force of the aircraft, and the aerodynamic attack angle, the flight speed and the pitch angle speed are obtained; s4, calculating elevator skewness at the current moment according to elevator instruction input; and S5, re-determining the aerodynamic force of the aircraft according to the flight speed, the pitch angle speed, the aerodynamic angle of attack and the elevator skewness until the simulation is finished. According to the method, the effect of the downwash influence in the aircraft maneuvering load determination process is reasonably considered, the simulation process is simple, the precision is high, and the engineering practice requirement is met.

The invention relates to the technical field of hybrid aircrafts, and discloses a high-power take-off energy supply system for a hybrid aircraft based on superconducting magnetic energy storage, which is characterized in that a superconducting coil is directly soaked in a hydrogen storage tank of the aircraft, and a large amount of liquid hydrogen carried by the aircraft is used as a cold source of the superconducting coil; the weight of a refrigerating machine and a heat preservation tank which are necessary for original superconducting magnetic energy storage is saved; when the aircraft is in a scene with low power requirements such as level flight or landing, the power generated by the superconducting generator driven by the gas turbine is greater than the power required by the aircraft, and at the moment, the superconducting coil can be charged to realize energy recovery and storage; under the scene of high power demand such as takeoff, the advantages of high power density, high response speed and the like of the superconducting coil are utilized to provide electric power for the propulsion unit so as to meet the high-power demand of the aircraft in the stages such as takeoff and the like, and the high-power maneuvering, electric energy management and transmission capabilities of the hybrid aircraft are greatly improved.

The invention discloses an arbitrary three-dimensional terrain visual coverage unmanned aerial vehicle energy optimization trajectory generation method, which comprises the following steps of: generating visual coverage air route points: selecting a mountain region, acquiring a rough digital elevation model by utilizing a geographic information system or level flight shooting, calculating the air route points based on photogrammetry constraints, and calculating the visual coverage air route points; traversing the waypoints according to a predetermined sequence to complete a coverage task; modeling the energy consumption of the motor of the unmanned aerial vehicle: taking the brushless direct current motor as an object, carrying out mathematical modeling in combination with torque dynamics and electromagnetic equations of the motor, constructing a physical information neural network model, and training and optimizing flight data; and track optimal prediction control input mapping: designing an optimal prediction control method based on unmanned aerial vehicle dynamics, and calculating a mapping relation between the track and control input. According to the invention, the coverage efficiency can be obviously improved, so that the single flight coverage range of the unmanned aerial vehicle is expanded.

The invention discloses a meta universe task offloading and resource scheduling method based on deep reinforcement learning, and relates to the technical field of wireless communication, and the method comprises the steps: 1, putting an unmanned aerial vehicle cluster in a user dense region, and enabling a fixed edge server to obtain the position coordinates of the fixed edge server, each user and each unmanned aerial vehicle; 2, a user sends a rendering request to the fixed edge server through the unmanned aerial vehicle cluster; step 3, constructing an optimization target, converting the optimization target into a Markov decision process, solving the optimization target through a PPO algorithm, and obtaining a horizontal flight rate, a flight direction and a vertical direction rate of the unmanned aerial vehicle and a computing resource set available for edge equipment; step 4, the fixed edge server issues a decision result to the user and the unmanned aerial vehicle, and the user and the unmanned aerial vehicle execute a decision; and step 5, after the unmanned aerial vehicle completes the rendering task, returning a result to the user. The method has the characteristics of multi-node collaborative optimization, energy consumption optimization and resource utilization rate optimization.

Described are systems and methods for active weathervaning of a hybrid flight aerial vehicle, such as an unmanned aerial vehicle (UAV). Active weathervaning of the hybrid flight aerial vehicle during can be provided during vertical takeoff and landing (VTOL) / hover flight without the assistance of any low-speed wind sensors and during transitions between VTOL / hover flight and fixed-wing, wing-borne, horizontal flight. Additionally, active weathervaning can be provided during propulsion mechanism failure conditions where the aerial vehicle may be experiencing failure conditions associated with one or more propulsion mechanisms.

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle control method and system for paraglider traction and an unmanned aerial vehicle. According to the control method and system and the unmanned aerial vehicle, the unmanned aerial vehicle is controlled to horizontally fly in front of the paraglider; acquiring relative positions of the unmanned aerial vehicle and the paraglider in the air; the height direction offset of the unmanned aerial vehicle and the paraglider is obtained through the relative positions of the unmanned aerial vehicle and the paraglider in the air; setting an offset threshold value, comparing the offset in the height direction with the offset threshold value in real time, and obtaining a comparison result; according to the comparison result, when the offset of the unmanned aerial vehicle and the paraglider in the height direction is larger than the offset threshold value, the unmanned aerial vehicle is controlled to ascend and descend so as to adjust the height. By controlling the relative height of the unmanned aerial vehicle and the paraglider, the paraglider can obtain the maximum horizontal traction force provided by the unmanned aerial vehicle, the traction efficiency of the unmanned aerial vehicle is improved, and the load of the unmanned aerial vehicle is minimum under the condition that the same traction force is provided.

The invention relates to the technical field of hovercars, and discloses a vertical-lifting flat-flying car which comprises a power system used for providing power, a wing-shaped car body, a multifunctional rotor wing, a tilting ducted fan engine and an empennage assembly, the wing-shaped car body comprises a car body front edge part and a car body rear edge part, and the tilting ducted fan engine provides power for lifting and cruising. The tilting ducted fan engine is arranged on the rear edge portion of the vehicle body and integrated with the empennage assembly, the empennage assembly is arranged on the rear edge portion of the vehicle body and works in cooperation with the tilting ducted fan engine, and aircraft yawing is corrected through thrust vectors of the two fan engines. According to the multifunctional rotor wing, the aircraft can stably take off and land vertically or hover, when the aircraft flies horizontally, the rotating rotor wing can be converted into a fixed wing, meanwhile, the thrust vector of the tilting ducted fan engine is rotated to the horizontal direction, the whole aircraft is changed into a fixed wing structure, and the cruising performance of the aircraft is improved.

The invention discloses a flight trainee attention and error behavior detection method based on a multi-modal physiological signal, and the method comprises the steps: obtaining the electrocardiogram data, eye movement data and electroencephalogram data of a flight trainee in a flight training process, and subjective evaluation data; based on subjective evaluation data, dividing flight student attention distribution conditions into a high grade, a middle grade and a low grade by adopting a clustering algorithm; performing feature optimization processing on the physiological data, and constructing a physiological feature attention level flight behavior associated data set; constructing an attention distribution level judgment model and a flight error behavior detection and early warning model; and outputting an attention level judgment result and a flight error behavior detection and early warning result. According to the method, association mapping of the multi-modal physiological signals and flight performance is realized, an attention grading standard for a flight training specific scene is established, and conversion from passive response to active early warning is realized.

The invention belongs to the technical field of flight test, and discloses a cockpit vision field evaluation test flight method suitable for a troposphere manned airship, which comprises the following steps: selecting an airship test condition; the airship climbs to a preset field height and keeps level flight; a preset flight test action is completed; and commenting by a flight tester, and filling in a cockpit vision field commenting card. According to the method, the blank of the flight test method for evaluating the visual field of the cockpit of the troposphere manned airship with the vector propulsion system is filled, and the flight test efficiency and the flight test quality of the manned airship are improved.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. Some of the rotors are forward canted, while some of the rotors are forward facing. The forward canted rotors are tilted forward slightly from vertical and provide some forward propulsion during horizontal flight. The forward facing rotors may be fixed in a forward facing configuration. Forward swept wings allow for rotor placement which brings efficiency during hover operations.

The invention belongs to the technical field of aircraft simulation, and particularly relates to a flight simulation method and device under gust load. The method comprises the following steps: S1, carrying out 1g level flight balancing on the aircraft, and determining a balancing attack angle of the aircraft and a balancing elevator skewness of the aircraft; s2, determining the aerodynamic force of the aircraft; s3, dynamic response solving is conducted on aerodynamic force of the aircraft, the aerodynamic attack angle, the flight speed and the pitch angle speed are obtained, and normal overload of the aircraft is determined after the flight speed is superposed with the wind speed of the vertical gust field; s4, acquiring the elevator skewness calculated by the stability augmentation system, and superposing the elevator skewness at the previous simulation moment to obtain the actually required elevator skewness; and S5, re-determining the aerodynamic force of the aircraft according to the flight speed, the pitch angle speed, the aerodynamic angle of attack and the actually required elevator skewness until the simulation is finished. The effect of the stability augmentation system in the determination process of the gust load of the aircraft is considered, the simulation process is simple, and the precision is high.

The invention belongs to the field of flight tests of unmanned aerial vehicles, and particularly relates to a calibration method for an airspeed system of a round-trip flight unmanned aerial vehicle with a fixed course angle. Comprising the following steps: step 1, selecting a test point in an aircraft flight envelope; step 2, the aircraft flies back and forth under the condition corresponding to the test point, and flight data of the going path and the returning path in the stable level flight stage are obtained; step 3, respectively selecting a plurality of flight data points of a going path and a returning path from the flight data, acquiring a course angle and a track angle of each flight data point, and according to the course angle and the track angle, judging whether the non-uniformity of the wind field in the flight process meets the requirement; if so, entering step 4; if not, returning to the step 2, and re-executing the test point; 4, acquiring the ground speed of each flight data point, and calculating the wind speed according to the ground speed; 5, calculating the vacuum speed in the flight process according to the wind speed and the ground speed; and 6, calibrating the air speed of the test point according to the vacuum speed.

The invention discloses an unmanned aerial vehicle route planning method, device and equipment and a medium, and the method comprises the steps: obtaining the real-time transient wind field data of an unmanned aerial vehicle, and generating the flow field information of time-space correlation according to the real-time transient wind field data; a flight energy consumption model is established based on the flow field information, the flight energy consumption model is adopted to calculate energy consumption in different stages, node energy consumption attribute values are obtained, and the different stages comprise a level flight stage, a climbing stage and a descending stage; and the node energy consumption attribute value is input into the heuristic search algorithm model to obtain the current path planning with the lowest energy consumption, so that the accuracy of the route planning is improved, and the route energy consumption is saved.

The invention relates to a variable-pitch lift wing for a vertical take-off and landing level flight cruise aircraft, and belongs to the technical field of vertical take-off and landing aircraft wings, the variable-pitch lift wing comprises an aircraft body, a left wing and a right wing are symmetrically arranged on the left side and the right side of the middle of the aircraft body, and the left wing and the right wing are designed according to the shape of a conventional lift wing; the left wing and the right wing are connected in the mode that a variable-pitch shaft penetrates through the aircraft body, a left positioning bearing and a right positioning bearing are fixedly arranged on the two sides, in the aircraft body, of the variable-pitch shaft respectively, a sector gear is arranged in the middle of the variable-pitch shaft, a worm is arranged at the tooth end of the sector gear, and a worm gear is arranged at the tooth end of the worm. A positive and negative rotation servo motor is arranged at one end of the worm to provide power, the servo motor is fixed in the machine body, the worm is used for driving the sector gear to rotate, and the sector gear rotates to drive the left wing and the right wing to rotate synchronously through the variable pitch shaft. The incidence angle of the wing can be changed through forward and reverse rotation of the servo motor.

An aeronautical vehicle performs horizontal flight and / or vertical flight, and has a fuselage, a wing assembly having a first wing part and a second wing part rigidly coupled to one another, a rotor assembly, a horizontal thruster, and an attitude control system. The wing assembly is arranged rotatably with respect to the fuselage to rotate about a vertical pivot axis between a stow position and an active position. The rotor assembly includes two vertical thrust rotors arranged on a rotor support rotatably with respect to the fuselage to rotate the rotor assembly between a stow position and an active position. In a horizontal flight mode the wing assembly is in the active position and the rotor assembly is in the stow position, and in a vertical flight mode the wing assembly is in the stow position and the rotor assembly is in the active position.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle which can float and park on the water surface, can vertically take off to leave the water and is switched into a fixed-wing mode for cruising and level flight. The unmanned aerial vehicle comprises a four-rotor support buoy and a wing body fusion body fixed to the upper portion of the four-rotor support buoy, small wing type buoys are arranged on wing tips of the two sides of the wing body fusion body respectively, and lifting ailerons capable of deflecting up and down are arranged on the rear edges of wings on the two sides of the wing body fusion body respectively. And four motor rotor propeller propelling devices are uniformly arranged at the tip part of the four-rotor bracket buoy.

The invention discloses a vertical take-off and landing control method for a distributed power tandem wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle flight control. An inner ring power unit and an outer ring power unit of the unmanned aerial vehicle are arranged at the front edges of the front wing and the rear wing of the tandem wing unmanned aerial vehicle; lifting ailerons are symmetrically hinged to the rear edges of the two ends of the rear wing; the front wing and the rear wing are connected into a tandem wing with a space height difference through a connecting assembly; the control method comprises the steps of controlling jumping take-off, transition flight, cruise flight and vertical landing, and performing accelerator quantity distribution on the inner ring power unit and the outer ring power unit for jumping take-off, cruise flight and vertical landing; a continuous climbing transition mode is adopted in the transition flight stage, and the flight state is controlled to be converted into a cruise level flight state after transition is completed. According to the unmanned aerial vehicle, the functions of large-angle jump take-off and 90-degree autonomous vertical landing of the tandem wing unmanned aerial vehicle are achieved, distributed power of the unmanned aerial vehicle is controlled and distributed, the energy utilization rate is increased, and the endurance time is prolonged.

A rotorcraft consisting of a fuselage, a plurality of arms on which electric motors driving propellers are mounted, one or a plurality of pivoting rotor supports on which thrust generating rotors with one or a plurality of blades attach. The rotor supports are substantially vertical when the aircraft is flying vertically, hovering, or on the ground, and tilted with respect to the aircraft when the aircraft has a forward motion component. The rotors can be powered on the ground, in hover, or in vertical flight, and spin in autorotation in horizontal flight.

The invention relates to the field of bridge line shape detection in civil engineering, in particular to a large-span suspension bridge main cable line shape automatic calculation method based on airborne laser scanning. The method comprises the following steps: fusing high-precision inertial navigation, a differential GNSS (Global Navigation Satellite System), airborne laser scanning equipment and an RTK (Real-Time Kinematic) technology, and acquiring a large-scale fine point cloud model by utilizing a two-level route planning method: on the basis of an SCF-Net network, providing an SCF-Bridge-Net based on a sling attention mechanism in combination with the structural characteristics of a suspension bridge; inclination angle, elevation and mileage information of all cable clamps are realized through a geometric information calculation method, and linear measurement of a bridge is realized. According to the method for automatically calculating the line shape of the main cable of the large-span suspension bridge based on airborne laser scanning, aiming at obtaining point cloud of a large suspension bridge structure in the construction process, a high-precision inertial navigation system and a differential GPS fusion method are combined with airborne laser scanning equipment, and a route planning method with a cable clamp as a core path is established through a coarse scanning model; and fine scanning of the large-span suspension bridge is realized.

The invention provides an air-ground amphibious robot which comprises a main machine frame. The flight assembly is arranged above the main rack, comprises a plurality of rotor wing assemblies and is used for enabling the air-ground amphibious robot to be in a vertical flight state or a horizontal flight state; the land walking assembly is arranged below the main machine frame and comprises a pair of driving assemblies, and each driving assembly comprises a land walking device used for enabling the land-air amphibious robot to advance on the ground and a connecting rod assembly used for adjusting the position of the land walking device; the air-ground amphibious robot comprises a first mass center, the land walking device comprises second mass centers, the first mass center and the pair of second mass centers define a virtual plane, and when the air-ground amphibious robot is in a vertical flight state or a horizontal flight state, the connecting rod assembly adjusts the position of the land walking device so that the virtual plane can be roughly in a vertical state. Through the arrangement, the air-ground amphibious robot can be kept stable in different postures or in posture changes, and meanwhile energy consumption can be reduced.

A flight mode transitioning device, method and system configured to facilitate transitioning between vertical flight mode and horizontal flight mode in a vertical take-off and landing (VTOL) aircraft, the device comprising at least one actuator mediated member capable of limiting the movement the aircraft wing so as to enable both forward fight and vertical flight.

The invention discloses a carrier rocket first-level flight section aerodynamic parameter identification method and related equipment, and relates to the field of carrier rockets, and the method comprises the steps: calculating an attack angle and a sideslip angle of a rocket first-level flight section according to actually measured wind field data and flight telemetry data of the launching day; obtaining angular acceleration information according to angular velocity information in the flight telemetry data; calculating the resultant moment information of the rocket body according to the angular acceleration information and the rotational inertia of the rocket body; according to the rocket body resultant moment information, the dynamic pressure information and the rocket body size information, rocket body moment coefficient information is calculated, and the rocket body size information comprises rocket body reference area information and rocket body length information; reverse interpolation operation is carried out according to known aerodynamic parameters and the aerodynamic torque coefficient to obtain rudder deflection control quantities, the known aerodynamic parameters comprise the attack angle, the sideslip angle and the Mach number, and the rudder deflection control quantities comprise the pitching rudder deflection control quantity, the yawing rudder deflection control quantity and the rolling rudder deflection control quantity; and comparing the rudder deviation control quantity with the rudder deviation during actual flight to judge aerodynamic parameters.