87 results about "Climb" patented technology

The invention relates to the technical field of flight simulation, and particularly discloses an airplane departure flight path simulation method and system based on a BADA model, and the method comprises the steps: obtaining airplane type data in a BADA database, the starting position coordinates of an airplane and airplane departure control parameters, and constructing a flight dynamics model of the airplane in a climbing stage; calculating an external atmospheric parameter of the current height of the aircraft, thrust and resistance of the aircraft, a target indicated airspeed corresponding to a flight stage, and a climbing parameter, a turning parameter and a fuel flow of the aircraft; and calculating a course angle, a vacuum velocity position coordinate and the like of the aircraft at the next moment, carrying out iterative calculation, and drawing a simulated flight path of the aircraft by utilizing the position coordinate. According to the invention, the performance change of the aircraft in each flight stage is dynamically simulated, and the flight mode and parameters are adjusted in real time according to the flight state, so that the behavior of the aircraft in a complex flight environment can be simulated more accurately, and the simulation precision and adaptability are improved.

The invention discloses an aircraft simulation data generation and situation deduction method based on a flight plan, and the method comprises the steps: firstly constructing an analysis model which is used for receiving a flight plan generated by a front end and carrying out the preprocessing, and then carrying out the aircraft situation deduction based on the information of each flight segment. The method comprises the following steps: generating an independent aircraft class, attaching different state attributes to the aircraft class, establishing an aircraft climbing and descending model, and continuously updating the state attributes of the aircraft class according to real-time deduction data. And finally, designing cyclic output of the aircraft simulation situation data once every 4 seconds. The method aims at providing assistance for work of a controller and improving situation awareness and real-time state monitoring of the aircraft in the operation stage. Meanwhile, an aircraft driver is assisted to make a decision autonomously, and control over the aircraft by the driver and information interaction between the driver and a controller are enhanced; and enough reaction time can be reserved for a driver and a controller at the emergency moment.

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.

The invention belongs to the technical field of aircraft design, and particularly relates to a temperature linear change equal-Mach-number climbing aircraft final-initial-state weight ratio calculation method which comprises the steps that 1, the oil consumption rate SFC of an aircraft propulsion system in an equal-Mach-number climbing stage is determined, and the Mach number M and the lift-drag ratio # imgabs0 # climbing angle gamma of an aircraft are determined; step 2, determining a coefficient lambda of temperature change along with height in an equal Mach number climbing stage; 3, determining an initial state height h1 and a final state height h2 of the aircraft in an equal Mach number climbing stage, and calculating an initial climbing state position sound velocity a (h1) and a final climbing state position sound velocity a (h2) of the aircraft; step 4, according to the oil consumption rate SFC of the aircraft propulsion system in the equal Mach number climbing stage, the Mach number M of the aircraft, the climbing angle gamma of the lift-drag ratio # imgabs1 #, the coefficient lambda of the temperature changing along with the height, the sound velocity a (h1) of the climbing initial state position and the sound velocity a (h2) of the climbing final state position, calculating to obtain the final initial state weight ratio # imgabs2 #

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 invention discloses a flight climbing stage calibration airspeed stability discrimination method. The method comprises the following steps: extracting an original height component and an original calibration airspeed component of a flight path point; obtaining an interpolated height component and an interpolated calibration airspeed component; calculating to obtain a height component and a calibration airspeed component in a climbing stage; setting a stability mark FLAG as a stability calibration airspeed discrimination mark; setting a variable height variable; judging whether the variable height variable is smaller than the maximum climbing height or not; obtaining track point time and calibration airspeed corresponding to the climbing height value; and the stability mark FLAG is obtained by continuously counting the difference before and after the time value of the time sequence and the number. According to the method, airspeed stability evaluation closer to an actual flight scene is realized through multi-dimensional parameter fusion and a dynamic threshold value, and risks in the flight operation process can be found in time while the prediction accuracy is improved.

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 present application relates to a flight plan generation method, apparatus, computer device, storage medium, and computer program product. The method includes: obtaining landing data and route data; based on the landing data, selecting the altitude of the descent vertex from the alternative altitudes of the route data; determining the position of the descent vertex according to the altitude of the descent vertex and the route data; screening the altitudes of each waypoint from the alternative altitudes according to the landing data and the altitude of the descent vertex; determining the position of the waypoint according to the altitude of the waypoint and the route data; and determining the position of the climb vertex according to the position of the waypoint and the departure airport data. By using this method, the complete flight plan can be screened according to the resources consumed in each of the three parts, namely the landing phase, the navigation phase, and the climb phase, so as to control the resource consumption in each phase, thereby reducing the resource consumption and saving fuel resources.

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 relates to an aircraft (10) equipped with a hybrid air propulsion system that uses propellers (40) configured to be decelerated, halted, and stowed at the end of a first flight phase, when a second phase of jet thrust propulsion during cruise flight starts. The propellers (40) are supported by nacelles (44) rotatably mounted on supports (45) integrally formed with lateral nose (12) and wing (16) surfaces and lateral tail surfaces (15) and are driven or halted by drive shafts (33) engaged with output shafts (31), respectively, powered by rotational energy sources or braked by propeller brake units, which may be housed in the nose (11), belly (13) and tail (14) of the aircraft (10). Collective pitch control mechanisms (50) and blade folding and unfolding mechanisms (60) are provided in the nacelles (44), which may comprise lateral steering mechanisms (70) configured to laterally direct the reverse thrust of the propellers (40) in order to maintain the alignment of the aircraft (10) on the runway during landings.

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 invention relates to the use of a device for assisting the take-off and climb of an airplane, the device comprising a traction cable, a first end of which is provided with fixing means for fixing it detachably to an airplane, and which can be driven by a drive device, for taking off and climbing a towed airplane, the towed airplane being a transport airplane and / or a cargo airplane, the fixing means being detached from the towed airplane when the towed airplane has reached an altitude greater than 1,000 m.

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.

- Device and method for optimizing a climb phase of an aircraft, in particular in terms of fuel consumption.- The method (P) for optimizing a climb phase of an aircraft, implemented repetitively during said climb phase, comprises an acquisition step (E1) for acquiring current values ​​of input parameters, a determination step (E2) for determining a current optimized DTflex value from the current values ​​of the input parameters and optimized DTflex values ​​recorded in a database (3) and a transmission step (E3) for transmitting the determined current optimized DTflex value to a user system for controlling the thrust of the aircraft, said method (P) making it possible to continuously adapt, during the climb phase, the optimized DTflex value so that it corresponds to the current conditions of the aircraft so as to maximize its performance, in particular in terms of fuel consumption. Figure for abstract: Figure 2.

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.