19 results about "Landing performance" patented technology

The present disclosure provides an unknown unmanned system data-driven multi-step kernel prediction control method and system. The method is aimed at the problem of unknown non-parametric unmanned system model. Only the off-line collected system input and output noise data are used. The Hankel matrix is constructed to extract the time sequence characteristics. The kernel matrix is constructed by combining the renewable kernel function. The nonlinear system rule is converted into high-dimensional linear representable data rule. The multi-step kernel prediction optimization problem based on the kernel matrix is solved on-line and rolling. The optimal control input is output to realize closed-loop control. The present invention does not need to construct an accurate mathematical model and does not need the full-dimensional state of the system. The problem of poor adaptability and long scene error accumulation of the traditional method is solved. The robustness and engineering landing performance are strong.

The invention provides an air-drop system intelligent control method and device based on GRPO reinforcement learning, and belongs to the technical field of air-drop system intelligent control. In the method, a reinforcement learning controller optimized by a group relative strategy is introduced, the autonomous decision-making ability, the dynamic environment adaptability and the high-precision landing performance in the air-drop process are remarkably improved, and the reliability of the air-drop system is improved. Manual intervention is not needed, a control strategy can be dynamically adjusted according to environment changes, control precision is high, and safety is good.

The invention provides an aircraft performance parameter input system and method, and the system comprises a data collection module which is disposed on an installation type EFB device, and is used for collecting the aircraft system data of a flight management system of an aircraft and the environment data of a ground server; and the performance calculation module is deployed on the portable EFB equipment and the mounted EFB equipment, and is used for calculating and evaluating whether the take-off, cruise and landing performances of the airplane meet the safe operation standard or not according to the airplane system data and the environment data provided by the data acquisition module. According to the aircraft performance parameter input system and the input method thereof, the automation degree of the aircraft performance calculation module can be improved, and the consistency and the correctness of unit inspection data are helped; by applying the system and the input method, the situation that a unit spends a lot of time for data input and proofreading work can be avoided, the workload of the unit is reduced, and the possibility of human errors is reduced, so that the flight safety is improved.

The invention discloses a power lifting assisting device which is suitable for the technical field of aviation flight equipment such as unmanned aerial vehicles, manned vehicles, hovercars and flying saucers. The technical problems that existing aviation equipment is insufficient in lifting force, high in energy consumption, poor in lifting stability and low in power redundancy are solved. According to the technical scheme, the lifting assisting device comprises a lifting assisting device body shell, a lifting force auxiliary assembly, a flow guide structure, a power input interface, a fixed connecting base and a control interface; the power input interface is used for being externally connected with an airborne power source, and the lift force auxiliary assembly generates auxiliary lift force under cooperation of the flow guide structure and is in modular connection with an unmanned aerial vehicle or a manned vehicle or a hovercar body through the fixed connecting base. The invention has obvious lift force gain, and is characterized in that the lift force comes from the reaction force of fan rotation to air, the low pressure area formed by air flow above and the impact force of the air flow flowing through the turning of the pipeline, so that the take-off and landing performance and the loading capacity of the aircraft can be obviously improved, and the aircraft is widely applicable to various low-altitude flight equipment.

The utility model discloses a manned aircraft safety intelligent identification guiding buffer device which comprises a double-C-opening landing frame fixed to one side of the bottom end of a manned aircraft body in a bolted mode and a supporting plate arranged at the bottom end of the double-C-opening landing frame. The top end of the vertical rod extends into the double-C-opening lifting frame and is provided with a top beam, a first shock absorption spring is installed between the supporting plate and the double-C-opening lifting frame, and inverted-U-shaped frames are fixed to the two sides of the bottom of the double-C-opening lifting frame. By means of the design of the double-C-opening landing frame, the supporting plate, the shock-proof spring and the horizontal double-rod elastic buffering structure, a more comprehensive buffering effect can be provided in the landing process of the aircraft, effective elastic buffering can be provided in the Z-axis direction, buffering can be synchronously carried out in the vertical direction and the horizontal direction, and the safety of the aircraft is improved. Therefore, the landing performance of the aircraft is enhanced, and the safety and stability of the aircraft are guaranteed.

The invention relates to the technical field of engineering surveying and mapping, and discloses a planning scheme real-time optimization method and system based on engineering surveying and mapping, and the method comprises the steps: obtaining engineering surveying and mapping data and standard surveying and mapping data; performing spatial registration on actual measurement elements in the engineering surveying and mapping data and design elements in standard surveying and mapping data to obtain element pairs of the working condition; extracting a measurement feature point set from the element pairs, and calculating turning angle difference values of the actual measurement elements and the design elements at corresponding feature vertexes; measuring a direction vector and a space distance from the space gravity center of the design element to the space gravity center of the actual measurement element to obtain a point position deviation of the working condition; fusing the point position deviation and the turning angle difference value to obtain a surveying and mapping deviation result of the working condition; generating a surveying and mapping adjustment instruction of the working condition based on the surveying and mapping deviation analysis result; according to the method, the landing performance of quantitative analysis and accurate adjustment operation of terrain and element deviation in the engineering surveying and mapping field can be improved.

This invention discloses a time-series-based method for detecting the landing performance of a standing long jump. The method decomposes the long jump motion and generates scatter plots for each decomposed motion based on the time series. The landing situation is determined based on the scatter plots, and the method identifies the frame containing the landing moment in the long jump image where the jump distance can be accurately calculated. The final long jump distance is then calculated quickly and accurately. The calculation process does not require setting complex image processing thresholds, determining the jump foot posture, or identifying skeletal key points. It can handle more landing situations, has greater versatility, is simple to calculate, has a fast processing speed, and high accuracy. Furthermore, the long jump image is processed before calculation, segmenting the human body and background, minimizing interference from the background during the calculation of the segmented image.

The invention belongs to the technical field of shield launching construction, and particularly relates to a shield negative ring dismantling opportunity dynamic judgment method based on duct piece circular seam strain monitoring. Resistance strain gauges are arranged on the spliced-1 ring segment and the circular seam surface in contact with the 0 ring segment, and the resistance strain gauges are connected with a strain acquisition instrument; measuring reflectors are arranged on the inner arc surfaces of the-1 ring pipe pieces; firstly, whether the negative ring reaction frame is allowed to be dismantled to release supporting stress is judged by judging that the strain value of the resistance strain gauge is stabilized at a target threshold value; judging that the negative ring duct piece is allowed to be dismantled by judging that the daily variation of the horizontal displacement value and the elevation value of the-1 ring duct piece is smaller than a target threshold value; through'stress + deformation 'two-dimensional monitoring and quantitative threshold judgment, the construction safety is improved, the space of a starting well is released 10-15 days in advance, the reuse rate of negative ring segments is improved, the technical feasibility and the landing performance are high, and the method is suitable for various shield construction scenes.

The invention belongs to the technical field of flight performance of aircrafts, and particularly relates to a flight performance calculation method of a high-safety amphibious rotorcraft. The method comprises the steps that the flight performance of the aircraft at least comprises the cruise speed, the flight time range, the practical lift-off, the taxiing takeoff performance and the autorotation landing performance; the method is high in universality, performance calculation can be carried out on the safe amphibious rotor aircraft, and research and development investment of the amphibious rotor aircraft is effectively reduced.

The invention provides a method and a device for acquiring a landing load of a semi-rocker arm type undercarriage. The method comprises the following steps: acquiring basic parameters and an initial motion state of the designed semi-rocker arm type undercarriage; the basic parameters and the initial motion state are input into a preset differential equation set to be solved, and the vertical displacement of the mass center height of the undercarriage and the ground vertical load in the landing process of the undercarriage are obtained through a numerical iteration algorithm; the preset differential equation set is a mass center height change equation, a wheel fork rotation angle equation, a tire course deformation equation and a tire rolling motion equation established based on a Lagrange second-class equation; according to the vertical displacement and the ground vertical load in the landing process of the undercarriage, the energy absorption efficiency and the landing overload are obtained; and evaluating the landing performance according to the energy absorption efficiency and the landing overload. A differential equation set is derived by utilizing a Lagrange second-class equation, and the characteristics of parts such as a buffer and a tire are combined, so that the landing load is calculated, and a data basis is provided for design optimization of an undercarriage.

The present application belongs to the technical field of shield launching construction, and particularly relates to a dynamic determination method for shield negative ring dismantling opportunity based on segment ring joint strain monitoring; resistance strain gauges are arranged on the joint surface of the -1 ring segment which is in contact with the 0 ring segment after the -1 ring segment is assembled, and the resistance strain gauges are connected with a strain acquisition instrument; reflective sheets are arranged on the inner arc surface of the -1 ring segment; firstly, the strain value of the resistance strain gauge is judged to be stable at a target threshold value to determine that the negative ring reaction frame can be dismantled to release the supporting stress; then, the daily change amount of the horizontal displacement value and the elevation value of the -1 ring segment is judged to be less than a target threshold value to determine that the -1 ring segment can be dismantled; through the "stress + deformation" two-dimensional monitoring and quantitative threshold determination, the construction safety is improved, the launching shaft space is released 10-15 days in advance, the negative ring segment reuse rate is improved, the technical feasibility and landing performance are strong, and the method is suitable for various shield construction scenes.

The invention relates to the technical field of intelligent traffic and artificial intelligence crossing, in particular to a GCN multi-dimensional spatial-temporal feature OD path flow prediction method and device. According to the method, six types of multi-source data are accessed, preprocessing is carried out through a time sequence branch (cleaning, long tail processing, OD identification, flow statistics and data fusion) and a space branch (graph structure construction and matrix conversion), Conv-LSTM and an improved GCN are adopted to extract spatial and temporal features in parallel, and after Transform adaptive fusion, a full connection layer outputs the OD path flow of the next day. The device comprises a data access module, a data processing module, a feature extraction module, a model application module and a hardware support unit. According to the method, through multi-dimensional feature fusion and improved GCN adaptive variable input, the long tail effect and space sparsity problems are solved, the prediction precision is remarkably improved, generalization is high, traffic planning and resource allocation can be supported, and engineering landing performance is good.

Provided is a method for landing an aircraft, etc., in which the landing performance of a directional aircraft is improved by heading in the nose direction in which the lift and drag are in balance, based on wind speed data and wind direction data related to the landing site. In the method for landing an aircraft according to the present invention, the aircraft is configured to generate lift in response to wind from the nose direction of the fuselage, and the nose direction of the fuselage is controlled based on wind speed data and wind direction data related to the landing site, and the descent of the fuselage is started.

The application provides a helicopter field ground landing feasibility evaluation method, which comprises the following steps: determining the diameter of a helicopter landing area based on the overall length of the helicopter; wherein the landing area is a circular area; selecting three measuring points on the boundary of the landing area; measuring the ground bearing capacity at the measuring points based on a ground bearing capacity detection device to obtain test data; inputting the test data into a general ground soil layer model to obtain a landing area ground soil layer model; setting a maximum landing gear allowable settlement amount; performing ground model dynamic loading simulation by using Abaqus finite element simulation software based on tire characteristics and the landing area ground soil layer model, and calculating the ground settlement amount; if the ground settlement amount is equal to the landing gear allowable settlement amount, determining the maximum ground allowable landing load; and determining the landing state by using landing gear landing performance calculation software based on the maximum ground allowable landing load.

This application belongs to the field of unmanned aerial vehicle (UAV) control technology, and provides a method and apparatus for automatic landing control of UAVs. The method includes: collecting operational state parameters and environmental disturbance data of the UAV during the automatic landing phase; determining the dynamic model and landing constraints of the UAV landing process based on the operational state parameters and environmental disturbance data; constructing a multi-objective fitness function for evaluating landing performance based on the landing constraints; globally optimizing the landing control parameters of the UAV using a particle swarm optimization algorithm, with the goal of optimizing the multi-objective fitness function, to determine the target landing control parameters; and controlling the UAV to complete the automatic landing based on the target landing control parameters. This application improves the landing accuracy and attitude stability of UAVs in disturbed environments, and achieves safe, accurate, and efficient autonomous landing of UAVs in complex scenarios such as strong winds and turbulence without relying on precise mathematical models.

The application discloses a controllable energy-absorbing CH-type corrugated stand column and an aircraft fuselage structure, and belongs to the technical field of aircraft structures. A H-type corrugated section is arranged in the middle section of the CH-type corrugated stand column, and upper and lower ends are C-type connecting sections, which are connected with a floor beam and a fuselage frame through corner pieces, respectively. The aircraft fuselage structure comprises the CH-type corrugated stand column and the fuselage frame, and a plurality of induction openings are arranged at the upper edge strips of the fuselage frame. Through the combined action of the CH-type corrugated stand column and the fuselage frame, a plurality of plastic hinges are generated at the induction openings, so that stable progressive failure of the CH-type corrugated stand column under pressure is ensured, controllable failure and energy absorption stability of the aircraft fuselage frame section are realized, the energy absorption efficiency of the structure and the landing performance are greatly improved, and the problems of uncontrollable deformation of the thin-walled structure of the aircraft fuselage lower opening section and low energy absorption efficiency are solved.

The application discloses a mountainous environment-oriented unmanned aerial vehicle joint resource allocation and trajectory design method and belongs to the technical field of unmanned aerial vehicle communication and energy efficiency optimization. The application firstly models a complex mountainous area as a prism and establishes a non-convex shielding constraint, then constructs an optimization problem with a total communication rate / total consumed energy as a target, and incorporates communication quality, power / bandwidth allocation, flight safety and other constraints; the non-convex constraint is transformed through a Big-M method and a Lagrange relaxation technique, the fractional target function is transformed by using a Dinkelbach algorithm, the resource allocation and trajectory design sub-problems are alternately optimized in combination with a block coordinate descent framework, and solving is performed with the aid of a CVX toolbox. The application is suitable for a mountainous area and other multi-obstacle scenes, the communication reliability and energy efficiency are significantly improved, the algorithm converges fast, has strong engineering landing performance, and can be widely applied to the fields of emergency communication, mountainous area survey and the like.

The present application belongs to the field of virtual space operation, and relates to an emergency positioning and guiding method based on a virtual multi-terminal co-creation ecology, comprising: building a global virtual space name system and a core database; performing three-dimensional grid division on global sky space to establish virtual space units; generating global unique and traceable virtual space names for each virtual space unit based on a surname naming rule; establishing a precise mapping relationship between virtual space names and real geographical coordinates to build a virtual landmark identification core database; building a cloud virtual landmark identification system; visually presenting sky surname regions; performing airplane emergency alternate virtual guidance; implementing full-scene emergency help and search and rescue, and performing normal commercial operation and emergency priority switching. The method can be supported by cloud computing power, reduce terminal performance short boards, cover all scenes and all weather, standardize virtual space names, globally unify traceability, through emergency commercial combination, has high landing performance, and is fully compatible with multiple terminals and has high popularization degree.

The application provides a prefabricated plate foundation splitting design method based on optimal economic size of prefabricated components, relates to the technical field of power transmission line tower plate foundations, and specifically comprises the following steps: under a set constraint condition, a plurality of splicing combinations of a predetermined plate foundation are randomly generated, a performance simulation test is performed and a cost is calculated by using a finite element analysis model, a comprehensive performance index and a comprehensive cost are generated through data processing, a cost-performance coupling coefficient is calculated, double-optimal parameter combinations are screened, a prediction model is constructed and trained, and the optimal combination of the splicing combination is obtained through iterative optimization combined with a genetic algorithm, so as to serve as the optimal economic size of the splicing combination. The application realizes multidimensional collaborative optimization, breaks through the limitation of traditional design, accurately balances performance and cost through intelligent optimization, fully considers engineering practice, enhances design landing performance, effectively improves construction efficiency, reduces cost, and guarantees foundation safety.