63 results about "Climb" patented technology

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 an unmanned aerial vehicle track decision-making method based on turbulence prediction, and belongs to the technical field of unmanned aerial vehicle navigation and weather prediction. Aiming at the problems of difficulty in monitoring and predicting low-altitude turbulence and high air route planning risk, the defects of data heterogeneity, insufficient numerical weather forecast resolution and the like exist in the prior art; according to the method, a three-dimensional turbulence intensity field is generated through multi-source meteorological observation data fusion to serve as an observation benchmark, a diagnosis model is constructed in combination with numerical weather forecast data, linear calibration is carried out, or short-term prediction is generated by adopting an observation extrapolation model when forecast data is lacked; further, the turbulence field is mapped into a weighted graph, the height, the climbing rate and the airspace constraint are combined, the optimal track is solved by using a path search algorithm, and the accumulated turbulence cost is minimized; the method is clear in structure, full-process optimization from data fusion to decision making is achieved through multi-model complementation, and the method is suitable for the fields of low-altitude logistics, urban air travel and the like.

This invention discloses an aircraft flight status identification method and system based on ADS-B, comprising: acquiring ADS-B data of the aircraft in real time and caching the ADS-B data in a high-speed cache database; extracting the latest ADS-B data points of the aircraft from the high-speed cache database at set time intervals, and storing multiple consecutively extracted latest ADS-B data points into a fixed-length queue of a preset length to form a temporal ADS-B data sequence; calculating estimated parameters for status determination by combining the aircraft's flight dynamic data with preset geospatial information; and identifying the current flight stage of the aircraft through a state machine model based on the temporal ADS-B data sequence and the estimated parameters, wherein the current flight stage includes one of taxiing, takeoff, climb, cruise, descent, approach, and landing. The method and system of this application improve the accuracy, continuity, and real-time performance of flight status identification.

This invention discloses a plug-in independent power supply hybrid power system for aircraft, which can be installed in situ without altering the original aircraft's core structure. The system employs an external independent power battery module, a small-power engine generator, and a small battery module to form a "three-level independent redundant power architecture," with each unit's power supply circuit electrically isolated from the others. The external independent power battery only charges on the ground and discharges unidirectionally during flight, without energy recovery or reverse charging. It only replaces all functions of the flight control system and electronic control system when the engine and small battery fail. The small-power engine does not participate in takeoff and climb, but is dedicated to cruise power supply. The small battery is responsible for powering the flight control system, electronic control system, and engine starter, sharing a high-voltage DC bus with the generator to achieve bus voltage stabilization and short-term power compensation. Ground charging simultaneously performs a full system self-check. When the battery power is insufficient or the test fails, there is no manual bypass, and the electronic control system is forcibly locked, prohibiting engine starting and ensuring absolute flight safety.

The invention discloses an accumulative climbing algorithm and system, electronic equipment and a storage medium, and the method comprises the steps: calculating an air pressure elevation change value at a current moment according to an air pressure value at the current moment and an air pressure value at a previous moment; calculating a gradient elevation change value according to the average gradient and the average speed within the latest set time length; calculating an absolute value of a difference value between the air pressure elevation change value and the gradient elevation change value; judging whether a first condition or a second condition is met; if the first condition is met, the air pressure elevation change value is less than or equal to 0; the air pressure elevation change value is updated to be 0; if the second condition is met, the difference absolute value is greater than or equal to the difference threshold; if yes, correcting the air pressure elevation change value, and updating the air pressure elevation change value into the corrected air pressure elevation change value; if the first condition and the second condition are not met, the air pressure elevation change value is not changed; and accumulating the air pressure elevation change value into the accumulated climbing value. The technical problem of poor accuracy of the air pressure elevation change value in the prior art is solved.

The invention discloses a take-off method of a combined unmanned aerial vehicle and the combined unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. During takeoff, the head of the mother aircraft is vertical or inclined upwards, and the son aircrafts are symmetrically arranged below the wings; the son aircraft is synchronously started to drive the whole aircraft to vertically / obliquely lift off, and the mother aircraft is started after being lifted off the ground and is shifted to level flight. When climbing to a target airspace, the ejection connecting device instantly releases the son machine through the connecting base, the torsion spring ejection plate, the plug pin and the driving mechanism, reliable separation of the mother machine and the son machine is achieved, and cooperative or independent operation can be achieved. Elastic electrodes are arranged in the ejection device, and electric energy and data are shared in the combination stage; the sub-aircrafts provide additional lift force and wind-resistant compensation, and the sub-aircrafts can be shut down in the middle of the task to prolong The whole process is runway-free, and fast climbing, endurance extension and task flexibility are taken into account.

The application provides a kind of electric vertical take-off and landing aircraft endurance enhancement method, system, electronic equipment and storage medium, adopt full task cycle stage energy optimization strategy, first obtain the division information of five stages of take-off, climb, cruise, descent, landing in flight mission profile, then real-time monitoring each stage power system output power, energy storage unit remaining capacity and the influence of external environment on energy demand;If the output power of power system in any stage cannot meet the demand, energy is supplemented by switching standby energy storage unit or adjusting power distribution strategy, wherein the take-off and climb stage preferentially calls high-power-density energy storage unit and combines airflow condition to optimize thrust distribution, the cruise stage dynamically adjusts the power output ratio according to the remaining capacity of energy storage and task distance, the descent and landing stage converts gravitational potential energy into electrical energy to recharge energy storage unit through mechanical energy-electric energy conversion device;Realize the accurate management of whole cycle energy, ensure stable operation under complex working conditions.

This invention discloses an airport photovoltaic design method and system based on three-dimensional airspace constraints, which relates to the field of airport photovoltaic engineering technology. S1: Collect legal airspace control data of the target airport, site topography data, flight parameters, and regional annual meteorological and solar radiation data. Based on the collected multi-source data, construct a three-dimensional airspace constraint surface model of the airport, fully integrating four types of core airspace constraint boundaries within the airport: horizontal plane, conical surface, approach surface, and takeoff / climb surface, achieving a three-dimensional quantitative definition of the airspace constraint range. This airport photovoltaic design method and system based on three-dimensional airspace constraints is the first to deeply couple the airport's three-dimensional airspace constraint surface with photovoltaic design, abandoning the traditional two-dimensional uniform height restriction model. It constructs a full-space quantitative model based on the four types of core airspace constraint surfaces, representing a novel technical solution not disclosed in existing technologies, with significant design characteristics specific to airport scenarios.

The present invention provides an unmanned aerial vehicle (UAV) testing method, apparatus, and equipment, belonging to the field of UAV technology. These methods address the low efficiency, long testing time, high testing costs, and difficulty in ensuring accuracy of traditional UAV testing. The method comprises: generating a test command and sending it to the UAV; obtaining flight status data from the UAV; processing the flight status data to obtain performance data, including at least one of endurance, climb rate, maximum range, maximum altitude, and maximum flight speed; and inputting the flight status and performance data into a flight status test model for processing to obtain test data. This solution improves the efficiency and accuracy of UAV testing and reduces testing costs.

The present application belongs to the technical field of flight test, and particularly relates to a kind of troposphere manned airship fuel system hot climate test flight method. Including: S1: determining test flight condition;S2: make airship climb to the minimum safe height after stable flight first time, gradually increase the power of transmitter to maximum continuous power;S3: after speed stabilization, climb to maximum use height at maximum continuous power;S4: monitor fuel pressure, fuel flow and engine operation during climbing, monitor whether there is gas lock phenomenon caused by fuel overheating, which leads to unstable engine operation;S5: if there is no gas lock phenomenon caused by fuel overheating, which leads to unstable engine operation, airship climbs to maximum use height, returns and lands;S6: if fuel pressure is within normal range, fuel flow is within normal range, and engine does not work abnormally due to fuel interruption during test, then fuel system hot climate test flight is completed.

The invention belongs to the technical field of aircraft system design, and relates to a motor power determination method and device for an electric fixed-wing unmanned transport plane. The method comprises the following steps: S1, determining a weight coefficient of a battery; s2, calculating the maximum weight and the wing area of the aircraft; and S3, first motor power is calculated according to the lift limit constraint, second motor power is calculated according to the take-off and lift gradient standard of the single-motor failure aircraft, third motor power is calculated according to the take-off ground takeoff distance, and the maximum value of the first motor power, the second motor power and the third motor power is selected as final motor power. According to the method, the motor top-layer parameter calculation time of aircraft system design is shortened, and the top-layer parameter iteration speed is increased.

The invention belongs to the field of aviation safety and flight data processing, particularly relates to a flight data-based aircraft re-flight climbing gradient determination method, and aims to solve the problem that the existing aircraft re-flight climbing gradient is inaccurate. The method comprises the following steps: based on flight data of a target aircraft, identifying a re-flight action starting moment and a re-flight performance reconstruction moment; based on the flight data, non-standard atmospheric environment factors and local geographical environment factors influencing the geometric height of the aircraft are corrected, the corrected geometric height of the target aircraft is obtained, and a corrected flight track is reconstructed in combination with the real-time horizontal position of the target aircraft; and according to the re-flight motion starting moment, the re-flight performance reconstruction moment and the corrected flight path, determining a re-flight net climbing gradient of the target aircraft in a re-flight initial stage formed from the re-flight motion starting moment to the re-flight performance reconstruction moment. According to the method, the re-flight net climbing gradient containing the initial height loss can be quantified, and the actual re-flight performance of the target aircraft is truly restored.

The invention discloses an unmanned aerial vehicle air route climbing angle dynamic planning method in combination with terrain constraints, and relates to the technical field of low-altitude economy and unmanned aerial vehicle traffic management, and the method comprises the steps: carrying out the parameterization construction of a multi-channel parallel skeleton of a strip-shaped infrastructure, obtaining a central line digital vector path of a target strip-shaped infrastructure as a main axis, and carrying out the calculation of the central line digital vector path; a parallel and multi-channel air route skeleton structure is constructed; according to the dynamic planning method for the air route climbing angle of the unmanned aerial vehicle in combination with the terrain constraint, common violent and high-frequency height adjustment in a traditional terrain following method is avoided through the generated smooth vertical section, and the aircraft can execute tasks with more stable and more continuous power output due to smoothness; and extra energy loss caused by frequent acceleration and deceleration is reduced.

This invention relates to an optimization method for the climb conditions of a high-altitude cruise drone, comprising the following steps: using the climb angle and flight speed of the drone at different altitudes as design variables, a population of N individuals is randomly generated within the variable space formed by the upper and lower bounds of the design variables; the climb time and climb energy consumption of the drone are selected as the flight cost of the drone, and a fitness function is constructed based on flight mechanics analysis; the individual position update method for the chasing behavior is a jump-chasing behavior, and the individual position is updated accordingly; for the jump-encirclement behavior, the individual position is updated; if the maximum number of iterations is met, the update is terminated, and the optimal solution is output as the climb condition optimization scheme. This invention can comprehensively consider the climb time and energy consumption of the high-altitude drone, enabling the drone to reach the cruise altitude more quickly and economically.

The utility model relates to a lubricating oil tank oil supply device, an aero-engine and an aircraft, belongs to the technical field of aerospace, and solves the problem that in the prior art, a lubricating oil tank cannot continuously supply oil and ventilate under various postures of the aircraft. The device comprises an oil supply pipe, an oil suction pipe assembly and a breather pipe, the oil supply pipe is arranged in the lubricating oil tank and can rotate around the axis of the lubricating oil tank. The oil suction pipe assembly comprises an oil suction pipe which is vertically arranged on one side of the oil supply pipe. The central axis of the oil suction pipe and the central axis of the oil supply pipe are coplanar. A balance weight ball is arranged at a pipe opening of the oil suction pipe and used for enabling the oil suction pipe to be located below the oil supply pipe. According to the utility model, oil supply and ventilation of the aircraft can be completely and continuously completed in different postures such as diving, climbing and inverted flying.

The invention provides a method for determining constant surface speed and Mach number climbing performance of a flight management system, and belongs to the technical field of aircraft management systems. Comprises: initializing pneumatic and engine data based on a performance database; inputting various initial parameters based on an aircraft climbing state; the climbing conversion height hpc is calculated based on the fact that the vacuum speed corresponding to the CAS and the vacuum speed corresponding to the Mach of the climbing strategy are equal; comparing the climbing conversion height hpc, the climbing ending height hpf and the step length midpoint height hpseudoi to judge whether to subsequently perform equal CAS climbing calculation or equal Mach climbing calculation; the step number n of the climbing process is calculated, and the midpoint height hpseudoi of the step length of the ith step is calculated; taking the hpseudo as an input parameter, and respectively calling corresponding functions; calculating a new step length hpstep x, taking the new step length hpstep x as a new step length, and respectively calling the corresponding functions again; and outputting a corresponding step length calculation result, and storing the corresponding step length calculation result into an output result matrix Outputm. Performance parameters obtained by the method are higher in precision.

The present invention relates to an iterative learning control method for aircraft track tracking based on Gaussian process regression, belonging to the field of civil aircraft control technology. This method solves the problem in the prior art of requiring a system model, which is difficult to accurately establish, as prior information in order to perform iterative learning control of civil aircraft takeoff. The present invention's iterative learning control method for aircraft track tracking based on Gaussian process regression utilizes known input data, output data, and tracking error data from iterative learning control of the controlled system during its climb phase, and constructs an input-output relationship model of the controlled system through Gaussian process regression. This method can achieve the goal of tracking the aircraft track against the target trajectory even when the aircraft dynamics model information is completely unknown.

The wide-range intelligent variable aircraft design method based on the curved shock wave theory comprises the following steps: 1) according to a flight envelope, the aerodynamic design of the wide-range intelligent variable aircraft is divided into a minimum resistance state, an optimal lift-drag ratio state and a maximum lift state, wherein the minimum resistance state corresponds to a boost climb section and a free flight section, the optimal lift-drag ratio state corresponds to a re-entry glide section, and the maximum lift state corresponds to a terminal down pressure section; 2) the aerodynamic design of the minimum resistance state is as follows: the aerodynamic profile of the wide-range intelligent variable aircraft is inversely designed based on a full three-dimensional curved shock wave surface; 3) the aerodynamic design of the optimal lift-drag ratio state is as follows: the aerodynamic profile of the wide-range intelligent variable aircraft is designed based on a full three-dimensional curved shock wave surface and a wall surface pressure distribution simultaneously controllable inverse method; 4) the aerodynamic design of the maximum lift state is as follows: the aerodynamic profile of the wide-range intelligent variable aircraft is inversely designed based on a three-dimensional wall surface pressure distribution.

The invention relates to the field of commercial aircraft control, in particular to a robust longitudinal tracking control method for a commercial aircraft in a climbing stage based on an event trigger mechanism, which comprises the following steps: step 1, on the basis of a hypothesis of a small attack angle, considering system uncertainty including unmodeled dynamics and exogenous disturbance, and determining a minimum attack angle; establishing a commercial aircraft state space model; 2, designing an integral sliding mode surface and a controller based on a disturbance term of the commercial aircraft state space model, and carrying out disturbance adaptive estimation; 3, designing a sliding mode controller based on a backstepping method based on the disturbance term estimation value, and ensuring that the tracking error of the flight path angle of the aircraft can be converged to 0; 4, designing a dynamic switching event triggering mechanism based on the stable system to ensure that the system can be asymptotically stable; 5, applying to a longitudinal tracking control strategy of the commercial aircraft; accurate longitudinal attitude tracking control of the commercial aircraft can be realized under an event triggering framework.

A climb assist system dynamically adjusts a rate and a level of load assist that the system provides to a climber during traverse of a structure. The system includes a load sensor system configured to detect the state of the climber, such as the load applied by the climber to an assist rope, to provide an upward support force on the climber to compensate the climber's weight. Additionally, the system includes a sender configured to transmit data to a receiver of the system. The system includes a controller configured to interpret the received data and thereafter provide control through a controlled motor and drive system to provide load assist to the climber. A safety function of the system is configured to receive data indicative of a rate of descent of the climber, and slow or stop the descent if one or more conditions are met.

The invention relates to the technical field of unmanned aerial vehicle path planning, and particularly provides a fixed-wing unmanned aerial vehicle path planning method considering flight performance constraints, which comprises the following steps of: dynamically adjusting an initial coordinate of a target task point according to target topographic data and flight performance constraint parameters of a target unmanned aerial vehicle; obtaining constraint coordinates conforming to the flight performance constraint parameters; the flight performance constraint parameters comprise the maximum climbing angle, the maximum lift limit and the safety height of the target unmanned aerial vehicle; processing the constraint coordinates according to an improved fast exploration random tree algorithm to obtain constraint paths of at least part of the target point pairs; the target point pairs are two adjacent target task points; the constraint path comprises at least one constraint point obtained according to an improved fast exploration random tree algorithm, and the inter-point turning radius between the constraint point and an adjacent point is not smaller than the minimum turning radius of the target unmanned aerial vehicle; and determining a path planning result of the target unmanned aerial vehicle according to the constraint path. According to the invention, the path planning quality is effectively improved.

The invention provides an electric vertical take-off and landing aircraft endurance enhancement method and system, electronic equipment and a storage medium, and the method comprises the steps: employing a full-task-cycle staged energy optimization strategy, firstly obtaining the division information of five stages of take-off, climbing, cruising, descending and landing in a flight task profile; monitoring the output power of the power system at each stage, the residual capacity of the energy storage unit and the influence of the external environment on the energy demand in real time; if the output power of the power system cannot meet the requirement at any stage, energy is supplemented by switching a standby energy storage unit or adjusting a power distribution strategy, and the high-power-density energy storage unit is preferentially called in the take-off and climbing stages, and thrust distribution is optimized in combination with airflow conditions; the power output proportion is dynamically adjusted according to the energy storage residual capacity and the task distance in the cruising stage, and gravitational potential energy is converted into electric energy to charge the energy storage unit through a mechanical energy-electric energy conversion device in the descending and landing stages; and full-period energy accurate management is realized, and stable operation under complex working conditions is ensured.

This application discloses a method, system, device, and medium for correcting the maximum continuous power of a piston engine for unmanned aerial vehicles (UAVs). The method includes: conducting a climb test flight of the UAV under the maximum continuous power of the engine, and collecting data during the climb process. N This application establishes relevant parameters at different air pressure altitudes; establishes a mapping relationship between the intercooler outlet gas temperature and the atmospheric static temperature; and obtains coefficients at different air pressure altitudes based on this mapping relationship. When simulating the climb performance and full-load cruise performance of the UAV, the mapping relationship between the intercooler outlet gas temperature and the atmospheric static temperature is integrated into the performance simulation system to correct the engine's maximum continuous power. This application enables high-precision correction of the maximum continuous power of a piston engine.

The invention provides a high-speed aircraft performance evaluation method, and belongs to the technical field of high-speed aircrafts, and the method comprises the steps: obtaining the latest flight data of an aircraft, and analyzing the latest flight data of the aircraft to obtain an aircraft rising evaluation coefficient, an aircraft cruising evaluation coefficient and an aircraft landing evaluation coefficient; analyzing the aircraft rising evaluation coefficient, the aircraft cruising evaluation coefficient and the aircraft landing evaluation coefficient to generate a flight state evaluation coefficient; enabling the aircraft to respectively cruise at a limit load and a limit speed, recording corresponding limit load flight data and limit speed flight data, and analyzing the limit load flight data to obtain limit load stability and limit speed stability; generating a limit stability coefficient according to the limit load stability and the limit speed stability; and generating a flight efficiency evaluation coefficient according to the flight state evaluation coefficient and the limit stability coefficient, and completing the evaluation of the efficiency of the aircraft through the flight efficiency evaluation coefficient.

1. The name of the design product: electronic device with climbing eVTOL performance calculation graphical user interface. 2. The use of the design product: for an electronic device. 3. The design points of the design product: in the graphical user interface. 4. The picture or photo that best shows the design points: design 1 interface change state diagram 2. 5. Omit the view: the electronic device is a common design, omit other views. 6. Design 1 is designated as the basic design. 7. The use of the graphical user interface: for simulating and analyzing the performance and behavior of eVTOL aircraft (electric vertical take-off and landing aircraft) in the climbing phase. 8. The human-computer interaction mode of the graphical user interface: click the right arrow of "climb" in the main view of design 1 to enter design 1 interface change state diagram 1; in design 1 interface change state diagram 1, click the "constant speed climb" button to enter design 1 interface change state diagram 2. Click the right arrow of "climb" in the main view of design 2 to enter design 2 interface change state diagram 1; in design 2 interface change state diagram 1, click the "constant path climb" button to enter design 2 interface change state diagram 2. 9. Other circumstances that need to be explained: "X" in the interface represents replaceable text, numbers, letters or symbols.

The application discloses a kind of limit warning curve calculation methods based on aircraft climbing performance, this method first generates aircraft motion trajectory model;By estimating flight intent, predict the future flight trajectory of aircraft, use collision detection model to determine whether the future flight trajectory of aircraft intersects with terrain;Calculate the terrain inclination angle, whether the minimum distance between the aircraft pull-up trajectory and terrain is greater than minimum safety distance as the judging condition for finding limit warning point, calculate limit warning curve;Finally, the limit warning curve is optimized, and the best warning curve is obtained.The method can enable the pilot to fly safely when performing combat tasks in low altitude according to the limit warning curve and to pull up to avoid obstacles at the last moment of safe flight.

This application provides a method for total static pressure compensation correction based on helicopter flight status, belonging to the field of helicopter control technology. Specifically, it includes: comparing and analyzing actual flight data with collected data to obtain a table of total static pressure correction values ​​for different airspeed descent rates; collecting the indicated total pressure and indicated static pressure of the current product and calculating the indicated airspeed; calculating the total pressure correction and static pressure correction values ​​for the current cycle based on the indicated airspeed calculated in the current cycle and the climb / deceleration calculated in the previous cycle, referring to the table; obtaining the true static pressure and true total pressure based on the correction values; calculating the true indicated airspeed based on the true static pressure and true total pressure; and obtaining the climb / deceleration for the current cycle based on the climb / deceleration calculation formula using the true static pressure. This application's solution can obtain accurate data sources, avoid erroneous airspeed corrections, more closely approximate true airspeed, benefit flight control, and improve flight quality.

The invention belongs to the technical field of traffic control, particularly relates to a terminal area departure flight program design method capable of cooperatively considering noise reduction and emission reduction, and aims to solve the problem that environmental protection factors are insufficiently considered in current flight program design. The method comprises the steps that the tail end of a runway in the departure direction of a target airport terminal area serves as a starting point, a limited flight area and a noise sensitive area serve as fly-around areas, and an initial departure flight program of a target aircraft is generated; reading a matched target decision in a decision knowledge base based on the initial departure flight program; and based on the noise value and the fuel consumption of each point location of the terminal area and the height of the obstacle area, in combination with the target decision, sequentially generating multiple sections of departure flight programs until the air route connection is completed. According to the method, the climbing path of the aircraft can be adjusted in time, a noise sensitive area is avoided, the pollutant discharge amount is reduced as much as possible, and the purpose of multi-target collaborative design of environmental protection factors and safety factors is achieved.

The application discloses a kind of aircraft energy and heat comprehensive management system, belong to control, adjusting technical field.The system integrates turbine-based combined cycle engine subsystem, fuel heat management subsystem, environmental control subsystem, aircraft accessory subsystem, through from TBCC engine subsystem carry out air bleeding and energy extraction, coordinate the joint work between each subsystem, realize whole machine energy distribution and heat management regulation and control, to respond different engine working state and energy efficiency demand, system has stage regulation and mode switching capability, can be according to the multiple flight conditions in flight envelope including take-off, climb, ram cruise, return carry out power distribution and heat management regulation and control, greatly enrich the selection of effective heat sink and improve heat sink utilization efficiency, realize the temperature of optimal regulation and control different position heat source, effectively reduce weight compensation, improve the maneuverability and long endurance capability of aircraft and reduce flight cost.