1056 results about "Aircraft landing" patented technology

The invention discloses an unmanned aerial vehicle accurate position landing method and system based on image recognition analysis, particularly relates to the technical field of aircraft landing, and aims to solve the problem of influence of jitter interference caused by micro airflow on landing precision. Identifying the jitter signal intensity and judging whether the jitter signal intensity is abnormal or not by detecting the posture change of the unmanned aerial vehicle in the landing process in real time; when the jitter is abnormal, carrying out multi-frame image superposition processing to generate a stable image sequence; detecting fine texture disturbance between adjacent frames based on multi-resolution fractal dimension analysis, and compensating non-linear influence caused by micro airflow; recording a jitter trajectory and calculating the relative displacement of the landing target through reverse trajectory reconstruction; extracting calibrated landing area features in combination with a convolutional neural network, generating an offset compensation value of a landing point, and dynamically correcting a landing path; according to the invention, the landing precision of the unmanned aerial vehicle in a complex environment is improved, and reliable guarantee is provided for automatic landing of the unmanned aerial vehicle.

The invention discloses an aircraft landing method and system and a vertical take-off and landing aircraft, and relates to the technical field of aircraft control, and the aircraft landing system comprises a landing path planning module which is used for responding to a landing instruction, determining a target landing point of the aircraft, and planning a landing path of the aircraft to obtain the landing path of the aircraft; the trajectory prediction module is used for predicting the flight trajectory of the aircraft based on the flight state information of the aircraft to obtain a predicted flight trajectory; the re-flight decision module is used for evaluating the flight state of the aircraft in the tilting transition stage based on the landing path and the predicted flight path; and according to the first evaluation result, carrying out re-flight decision processing on the aircraft, and determining whether to control the aircraft to carry out re-flight so as to guarantee safe landing of the aircraft. According to the scheme, the automatic landing capability of the aircraft can be effectively improved, and meanwhile, the landing safety of the aircraft is ensured through the re-flight decision module.

The invention relates to the technical field of airport ground service vehicle management and control, and discloses a multi-agent simulation airport ground service vehicle scheduling system and method. In view of the fact that the efficient airport ground service is a key factor for improving the flight turnover rate, the method comprehensively considers the ground service requirements in the whole process from aircraft landing to takeoff, and achieves the dispatching and control of ground vehicles based on multi-agent simulation. The method comprises the following steps: designing an intelligent agent and an interaction rule thereof, inputting basic information, constructing an airport ground service vehicle scheduling and management and control model, and visually outputting a result. Compared with the prior art, the airport ground service vehicle scheduling system can truly describe the service characteristics of the airport ground service vehicles, and the system can realize the comparison of various ground service vehicle scheduling and control strategy effects, thereby providing a scientific basis for the optimization of the airport ground service vehicle scheduling.

A ground detection system for an aircraft based on capacitive sensing. The system comprises an electrode mounted to an aircraft landing gear. As the aircraft landing gear approaches the ground, the electrode and the ground together form a variable capacitor having a capacitance that depends on a distance of the electrode from the ground. Signal processing electronics are used to measure the capacitance and, on the basis of the measured capacitance, determine a distance of the aircraft from the ground.

The invention provides an aircraft landing gear dismounting and mounting device, belongs to the technical field of aviation equipment, and solves the problem that in the prior art, landing gear dismounting and mounting equipment is difficult to meet the requirements for efficient, accurate and flexible dismounting and mounting in the modern aviation maintenance field. Comprising a frame, a moving frame is arranged on the inner side of the frame, and the moving frame is driven by a first driving device; a moving plate is arranged on the frame and is driven by a second driving device; an arc-shaped guide rail is arranged on the movable plate, a supporting frame is arranged on the arc-shaped guide rail, a lifting device and a fixing device are arranged on the supporting frame, and a clamp is arranged on the top of the lifting device. According to the undercarriage disassembling and assembling device, through cooperative operation of the first driving device, the second driving device and the lifting device, all-directional flexible adjustment of the tool on the X axis, the Y axis and the Z axis is achieved. Due to the design of the arc-shaped guide rail, the supporting frame can flexibly rotate within a certain angle range, and the adaptability and flexibility of the device are further enhanced.

The invention provides a multi-scale cross-space learning general aviation aircraft landing runway detection method, and relates to the technical field of computer vision. The method comprises the following steps: firstly, collecting a runway image data set when a general aviation aircraft lands, preprocessing the data set, and dividing the data set into a training set and a test set; then, an AES-YOLOv8 network model for detecting a multi-scale runway target is constructed; the model is based on a YOLOv8s network of multi-scale cross-space learning, and a Backbone network comprises a plurality of improved lightweight channel attention convolution modules LA-AKConv; an EMA attention mechanism is introduced after a spatial pyramid pooling module SPPF of the Backbone network; the Neck network comprises a plurality of C2fSCConv modules fused by C2f and a space and channel reconstruction convolution module SCConv; and the AES-YOLOv8 network model is trained based on the preprocessed data set to obtain a multi-scale cross-space learning airport runway detection model, and the runway state of the general aviation aircraft during landing is detected in real time through the multi-scale cross-space learning airport runway detection model.

The invention relates to a micro-settlement control method for an extra-large-span flat-top straight-wall tunnel under the dynamic load action of an aircraft, and relates to the technical field of tunnel construction. The control method comprises the following steps: S10, uniformly spreading the weight of the airplane to each airplane wheel, and calculating to obtain a static load P1 of the airplane; s20, vertical kinetic energy of the aircraft is converted into impact force, dynamic additional force F is obtained and evenly spread to each aircraft wheel, and the dynamic load P2 of the aircraft is obtained through calculation; s30, adding the static load P1 and the dynamic load P2 to obtain an aircraft landing impact load P3; s40, the distance r from the load acting point to the calculation point and the burial depth h of the tunnel are obtained, and settlement S of the tunnel vault is calculated through the aircraft landing impact load; s50, through Moire-Coulomb model simulation analysis, the influence of the aircraft dynamic load on tunnel construction settlement is obtained; and S60, making a corresponding construction scheme according to the influence of the airplane dynamic load on tunnel construction settlement. The construction problem of undercrossing the airport runway by the tunnel can be solved, and settlement of the airport runway is controlled.

The invention provides a manned aircraft landing aid decision-making system and method, and relates to the technical field of aviation. The method specifically comprises the following steps: acquiring current state data of an aircraft in real time, planning a landing trajectory of the aircraft by adopting an index leveling trajectory method, and determining an optimal glide path of the aircraft; based on the current state data of the aircraft and the optimal glide path of the aircraft, calculating an expected attitude angle and an expected thrust variation of the aircraft by adopting an instruction decision algorithm, performing attitude control on the aircraft according to the expected attitude angle of the aircraft, and generating a flight decision suggestion; wherein the attitude control is divided into two parts: one part is used for calculating an expected three-dimensional angle and a three-axis attitude angular velocity by utilizing angle control; according to the other part, the three-axis attitude angular acceleration is calculated through angular velocity control; and the pilot controls the flight path of the aircraft according to the generated flight decision suggestion to ensure that the aircraft lands along the optimal glide path of the aircraft. The invention aims to solve the problem that the landing trajectory is inaccurate when the aircraft lands.

The invention provides an aircraft landing stage short-time abnormal risk early warning and visual simulation adaptive method based on deep learning, and the method comprises the following steps: synchronizing a multi-source sensor signal, separating the multi-source sensor signal into an impact channel, a wind shear channel and a residual channel, and mapping the multi-source sensor signal into aircraft-runway-wind field graph node features; features are extracted through a space-time diagram convolutional network, and a future trajectory is predicted in combination with a dual-channel attention decoder under physical constraints such as an energy attenuation template; high-risk actions are rapidly inhibited on the basis of real-time risks, the risk probability is calculated through weighted submerged space sampling, graded alarms are output, meanwhile, the alarms drive visual simulation to be adaptively updated, and model online safety iteration is achieved through hard sample mining after landing. According to the method, physical driving modeling, space-time fusion perception and probabilistic risk assessment are adopted, the dependence of a traditional method on an empirical threshold value is overcome, and the early warning precision, the confidence coefficient and the landing safety are remarkably improved.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The invention discloses an MBSE-based aircraft undercarriage system model integration method, and belongs to the technical field of system engineering. The method comprises the following steps: constructing an aircraft undercarriage system architecture, a classification mapping of simulation design information and a GOPPRR-E element model, and a meta-model library; constructing an architecture model according to a demand-function-logic-physical process, and generating a Simulink simulation model according to the architecture; a simulation model semantic mapping rule is constructed according to an OSLC specification, and design information is analyzed to establish an integrated data model; and a Simulink simulation tool integration adapter is constructed, and a tool interoperation service based on Web is provided. According to the method, a multidisciplinary model can be accurately constructed, uniform expression of architecture and simulation models and semantic consistency of heterogeneous models are realized, two-way transmission of cross-domain information and interoperation between tools are supported, the problem of interoperation between architecture modeling and simulation modeling tools in aircraft undercarriage system design is effectively solved, and the design efficiency is improved.

The invention discloses an aircraft landing gear drop test device and method, and relates to the technical field of aircraft landing test devices.The aircraft landing gear drop test device comprises a platform, and a supporting structure is arranged on the platform; the rack is movably connected with the supporting structure so as to ascend and descend relative to the supporting structure. Moreover, a mounting seat is arranged on the rack so as to be connected with the undercarriage; the connecting seat is arranged on the platform and is arranged below the rack; the test box body is detachably connected to the connecting base, and the test box body is provided with a first cavity with an upward opening so as to contain a pavement material. According to the undercarriage drop test device and the undercarriage drop test method, different pavement materials can be loaded in the first cavity of the test box body, so that different pavement structures are formed, and the undercarriage drop test device can perform simulation experiments on various pavement working conditions.

The invention relates to the technical field of airport lighting equipment, in particular to an airport navigational light control system based on flight information, which comprises an irradiation unit for outputting navigational light by using irradiation parameters to generate navigational light information, an aviation interaction unit for generating and outputting real-time flight information, and a control unit for controlling the airport navigational light according to the real-time flight information. The information receiving unit is used for receiving the real-time flight information output by the aviation interaction unit and positioning the real-time position of the aircraft in the air, and the analysis unit is used for determining whether the flight state of the aircraft meets the standard or not and the reason for the non-conformity and generating a corresponding processing instruction. And the control unit is used for receiving the corresponding processing instruction, determining the irradiation parameters of the irradiation unit and sending a corresponding notice to the aviation interaction unit. The corresponding instruction is sent to the aircraft based on the flight environment or the real-time flight state of the aircraft, the irradiation parameters of the lamplight are adjusted in a targeted mode, it is guaranteed that the aircraft can stably land to the designated site, and meanwhile the navigation aiding efficiency of the system for aircraft landing is effectively improved.

The invention provides a pilot landing operation analysis method and device, electronic equipment and a storage medium. The pilot landing operation analysis method comprises the steps that external environment parameters and aircraft running state parameters formed in the process that a pilot operates an aircraft to land are obtained; calling a neural network model and inputting the external environment parameters and the aircraft operation state parameters into the neural network model to obtain a state transition matrix at each time point; based on the state transition matrix, hidden states corresponding to the state transition matrix are obtained, so that pilot landing operation analysis is completed, the hidden states are used for representing all states of an attention distribution mode of a pilot, and the hidden states comprise the state without attention loss, the state of attention loss of a yaw angle and the state of attention loss of a height; and any one or more of states in which attention to airspeed is missing. The landing operation of the pilot is accurately and objectively analyzed, so that the risk is conveniently managed and controlled in a targeted manner, and the flight safety level of the pilot is improved.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The invention belongs to the technical field of alloy steel, and relates to composite reinforced high-toughness steel and a preparation method thereof. The steel comprises the following chemical components in percentage by weight: 6.0%-9.4% of Ni, 7.6%-8.9% of Co, 0.8%-3.8% of Cr, 1.0%-2.6% of Mo, 0-0.9% of W, 0.05%-0.60% of V, 0-0.10% of Nb and the balance of Fe. C and Al are added to serve as strengthening elements, and the balance is Fe and impurity elements. When 0.14% < = C < 0.20%, 1.2% < = Al < = 1.6%, 1.0% < = Mo + W / 2 < = 2.0%; when 0.20% < = C < = 0.35%, 0.6% < = Al < = 1.3%, and 2.0% < = Mo + W / 2 < = 3.0%. The alloy is subjected to vacuum induction melting or multi-time melting, homogenizing diffusion annealing and forging rolling to form a material, so that the tensile strength of the steel reaches 2200-2350 MPa or above, the yield strength reaches 2000-2150 MPa or above, and the steel has excellent strength, plasticity and toughness matching and can be used for components such as engine shafts, aircraft landing gears, high-performance shells, frame beams and molds.

The aircraft landing gear part supporting device comprises a first supporting structure and a second supporting structure, an aircraft landing gear part comprises a landing gear body and a central wing, the first supporting structure is connected with the central wing, and the second supporting structure is connected with the landing gear body. The first supporting structure and the second supporting structure jointly support the aircraft landing gear part, so that the maintenance space between the landing gear part and the ground is increased, the aircraft landing gear part supporting device can support the aircraft landing gear part of a general-purpose aircraft, the maintenance space between the landing gear part and the ground can be increased, and the service life of the aircraft landing gear part is prolonged. And maintenance training is facilitated.

The invention discloses an aircraft landing gear shimmy test bed and a test method, the aircraft landing gear shimmy test bed comprises a main body rack, a hanging basket system, a large flywheel, a flywheel driving system, an excitation device and a follow-up displacement measurement system.The aircraft landing gear shimmy test bed can simulate the shimmy of an aircraft after undercarriages of different design configurations are subjected to interference excitation force or interference torque in the process of takeoff, taxiing, landing and the like of the aircraft; the control effect of the shimmy damping system on the stability of the undercarriage has short excitation time so as to simulate real working conditions, the shimmy stability performance of the undercarriage can be accurately detected, excitation is continuously carried out under the condition that the test state is continuously changed, and the working efficiency is greatly improved. The follow-up displacement measuring system designed by the invention can enable the exciting force and the center of the axle to be always kept on the same horizontal plane, can apply torque control and torque excitation control, is suitable for undercarriage shimmy tests with different axle heights, different tire diameters and different excitation modes, and has certain universality.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The invention discloses an aircraft landing control method and system and a vertical take-off and landing aircraft, and relates to the technical field of aircrafts, and the method comprises the steps: determining the current flight stage of the aircraft; generating a planned flight path based on the current flight stage of the aircraft and a pre-selected landing area; generating a suggested control instruction for switching the aircraft from the original planned flight path to the planned flight path; and acquiring a control instruction based on the suggested manipulation instruction, and controlling the aircraft to fly according to the planned flight path based on the control instruction. According to the scheme, the landing safety and accuracy of the aircraft in the urban low-altitude complex environment can be improved. And specific landing strategies are provided for different flight stages, so that the flight safety is ensured.

The invention discloses a control method and system based on a self-positioning helicopter field navigation aid lamp and a medium, and relates to the technical field of aircraft landing auxiliary devices.The method comprises the steps that environment information, unmanned aerial vehicle state information and navigation aid lamp layout information are obtained, and initial guiding parameters are determined; calculating a visual guidance signal parameter based on the position condition of the unmanned aerial vehicle relative to each navigation aid lamp and the initial guidance parameter; determining a navigation aid lamp control scheme according to the visual guidance signal parameters and the initial guidance parameters, and sending a lighting starting instruction to a plurality of corresponding navigation aid lamps; acquiring environment feedback information from each navigation aid lamp area, and calculating an environment difference value; if the environment difference value exceeds a preset environment change threshold range, triggering an environment adaptability adjustment instruction; and calculating corresponding navigation-aid lamp adjusting parameters and sending an illumination adjusting instruction to the corresponding navigation-aid lamp area. According to the invention, the safety and reliability of the unmanned aerial vehicle under a complex or emergency landing condition are improved.

A locking system for doors of a deployable aircraft landing gear system includes a spring-biased swing arm configured to be pivotally attached to a body of an aircraft and including a roller at a distal end of the swing arm. The swing arm is configured to engage with a portion of a first landing gear bay door to prevent the first landing gear bay door from opening.

A method for determining and adjusting the landing safety area of ​​an aircraft based on laser radar. It includes the following steps: setting a landing safety area; calculating whether there are points in the landing safety area that are more than 1 / 2H in height; moving the landing point A outward; calculating the height difference between the highest point and the lowest point in the landing surface, if the height difference is ≤10cm, it is considered to be relatively flat; otherwise, moving the landing point A outward. Beneficial effects of the present invention: 1. It can accurately determine the landing safety area, thereby greatly improving the safety of the aircraft during landing, which is of great significance; 2. It can automatically adjust the landing safety area without the need to pre-equip the landing point, thus saving energy consumed by the transfer, which has very important economic benefits; 3. As the price of laser radar becomes lower and lower, it has a higher cost-effectiveness than equipment such as millimeter-wave radar, image recognition and other equipment and technologies, so it has a wider application prospect.

The invention relates to the field of aviation noise control, and provides an aircraft landing gear noise reduction device and method based on micro metal wire spiral winding. The device part comprises a metal wire and a metal wire fixing buckle, the metal wire is fixed through the metal wire fixing buckle, and meanwhile the size and material parameters of the metal wire are designed in a targeted mode. In the method part, the designed metal wire is wound on a cylindrical bluff body part, possibly generating vortex shedding and vortex-fixing interference, on the nose gear in a spiral winding manner, and the two ends and the axial interval position of the metal wire are fixed through the metal wire fixing buckles, so that the metal wire is ensured to be fastened. Therefore, through the wound metal wires, single-frequency noise in the over-top direction caused by falling of a towing rod vortex can be effectively eliminated, broadband noise is reduced, and the noise control capability of an airplane is improved. The method is suitable for various civil aircraft types, and has the advantages of being simple in structure, remarkable in noise reduction effect, high in practicability, high in adaptability and the like.

Disclosed here is a landing gear support fixture for an aircraft under test having a landing gear. The disclosed landing gear support fixture includes: an axle attachment assembly that is compatibly shaped, sized, and configured to mate with and attach to at least one axle of the landing gear of the aircraft under test; a support platform to support the axle attachment assembly, wherein the support platform is in a fixed position relative to a stationary reference foundation; and a force sensor couplable between the axle attachment assembly and the support platform to provide sensor output associated with load imparted by the landing gear of the aircraft under test.

The invention discloses a method for aircraft thrust imbalance warning and protection. The method comprises the following steps: acquiring thrust rod position angle signals and wheel load state signals of a plurality of engines after an aircraft lands and is grounded; determining whether the thrust states of the plurality of engines are consistent or not based on the thrust rod position angle signal and the wheel load state signal, wherein the thrust states of the plurality of engines comprise a positive thrust state and a negative thrust state; in response to the fact that one or more of the multiple engines are inconsistent with the remaining engine thrust state of the multiple engines, a warning instruction is sent out; and the reverse thrust cover corresponding to the engine in the negative thrust state is locked. The invention further provides a system for aircraft thrust imbalance warning and protection. By means of the method and device, the unbalanced thrust state of the aircraft can be prevented after the aircraft lands, an alarm is given to operation of a pilot, protection is provided, and the safety of the aircraft is guaranteed.

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

The invention provides an unmanned aerial vehicle for intelligent identification of a polar ice rink. The unmanned aerial vehicle comprises an aerial vehicle main body, a solar battery pack, rudder wings, a spiral propeller and an observation cabin, the aircraft is powered by solar energy, so that long endurance time can be achieved; the rudder wings are symmetrically installed on the two sides of the aircraft body to achieve lifting and steering of the aircraft body. The spiral propeller provides propulsive force and cooperates with the rudder wings to complete lifting steering motion. A plurality of functional modules are arranged in the observation cabin, and the functions of ice rink recognition, aircraft and transport ship positioning, data transmission, state monitoring and the like can be achieved. Illumination warning lamps are arranged on the front edges of the two wings of the aircraft, so that ice rink identification and aircraft landing under the extremely night condition are facilitated. The invention also provides a polar ice rink intelligent identification method of the unmanned aerial vehicle. The sea ice morphology around the navigation channel can be observed in detail and accurately, accurate sea ice data can be obtained, the polar transport ship is helped to sail, a captain is assisted to make a decision, and the risk of distress is reduced.

A dual agent reinforcement learning autonomous system (DARLAS) for the autonomous operation of aircraft and / or provide pilot assistance. DARLAS includes an artificial neural network, safe agent, and cost agent. The safe agent is configured to calculate safe reward Q values associated with landing the aircraft at a predetermined destination or calculated emergency destination. The cost agent is configured to calculate cost reward Q values associated with maximum fuel efficiency and aircraft performance. The safe and cost reward Q values are based on state-action vectors associated with an aircraft, which may include state data and action data. The system may include a user output device that provides an indication of an action to a user. The action corresponds to an agent action having the highest safe reward Q value and the highest cost require Q value. DARLAS prioritizes the highest safe reward Q value in the event of conflict.

The invention provides an automatic aircraft landing method based on multi-modal image recognition, and relates to the technical field of aviation navigation and automatic control, and the method comprises the steps: fusing optical, infrared and millimeter wave radar data through a multi-modal sensor, and carrying out the preprocessing to generate a fused image sequence; detecting a runway, an obstacle and a meteorological entity based on an improved YOLOv8 model, and extracting an environment dynamic adaptation factor (EDAF) and a multi-modal fusion confidence coefficient (MFC); predicting and controlling an MPC path planning weight by combining a flight state data dynamic optimization model, and generating a landing instruction; the flight attitude is adjusted in real time by using a redundant PID controller, and control parameters are dynamically corrected through an EDAF; continuously monitoring the system state, and triggering emergency operation based on the decision tree model. Through multi-modal sensing fusion, dynamic parameter optimization and an intelligent emergency mechanism, the problems of low reliability, control parameter staticization and emergency delay of a single sensor are solved, and the landing precision, stability and safety in a complex environment are remarkably improved.