GPS synchronous turbine power generation adjusting method for low-altitude aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to a GPS synchronous turbine power generation adjusting method for a low-altitude aircraft, and the method comprises the following steps: S1, flight parameter collection: obtaining flight parameters of the aircraft in real time; s2, dynamic terrain prediction energy adjustment: analyzing terrain change of an area in front of the aircraft in advance, and automatically adjusting the rotating speed and the output power of a turbine generator; s3, adaptive turbine adjustment in the extreme environment, wherein the most suitable turbine power generation mode is automatically selected; s4, power generation and electric energy distribution optimization: distributing the generated electric energy to each device of the aircraft; and S5, electric energy state feedback and adaptive adjustment: monitoring the electric energy state of the aircraft in real time, and dynamically adjusting the working state of the turbine generator. According to the method, the power generation efficiency is improved, the endurance time of the aircraft is effectively prolonged through the efficient power generation power adjusting mode, and energy waste is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to a GPS synchronous turbine power generation regulation method for low-altitude aircraft. Background Art

[0002] When low-altitude aircraft perform missions in complex environments, the requirements for energy management and flight performance are extremely stringent. As the core energy supply device of the aircraft, the turbine power generation system must be able to adapt to the changing terrain, complex airflows and extreme environmental conditions faced during flight. In order to ensure the smooth execution of flight missions, the aircraft needs to have efficient power generation capabilities and be able to dynamically adjust power generation and power distribution according to mission requirements. As the complexity of flight missions increases, ensuring the stable operation of aircraft in changing environments and improving energy utilization efficiency has become a key challenge in low-altitude aircraft technology.

[0003] Existing aircraft turbine power generation systems have significant deficiencies when dealing with complex terrain and extreme environments. On the one hand, traditional systems lack dynamic terrain prediction and environmental adaptability, resulting in the inability to synchronize power generation with actual environmental changes, which easily leads to energy waste or insufficient power generation. On the other hand, existing technologies lack intelligent adjustment mechanisms in terms of power distribution, making it difficult to reasonably allocate power according to mission priorities, affecting the normal operation of mission-critical equipment. In addition, in the face of extreme environments such as high temperature, low pressure, and strong winds, existing systems are unable to adjust the power generation mode in a timely manner, resulting in equipment performance degradation or failure, affecting the overall stability of the aircraft and the mission completion rate.

[0004] The present invention aims to solve the above problems and proposes a GPS synchronized turbine generator adjustment method for low-altitude aircraft to enhance the environmental adaptability of the aircraft, extend the life of the equipment and improve the reliability and efficiency of the mission. Summary of the invention

[0005] The invention provides a GPS synchronous turbine power generation adjustment method for a low-altitude aircraft to solve the problem of poor environmental adaptability of the aircraft.

[0006] The method for regulating a GPS-synchronized turbine generator for a low-altitude aircraft comprises the following steps:

[0007] S1, flight parameter collection: obtain the flight parameters of the aircraft in real time through the GPS unit on the low-altitude aircraft, including position information, speed information and flight altitude;

[0008] S2, Dynamic Terrain Prediction Energy Regulation: Based on the aircraft's location information and terrain database, the terrain changes in the area ahead of the aircraft are analyzed in advance, and the impact of the terrain on airflow and turbine power generation is predicted. When the complexity of the terrain is predicted to increase (such as mountains, canyons, urban high-rise buildings, etc.), the speed and output power of the turbine generator are automatically adjusted. Specifically, it includes:

[0009] S21, terrain data analysis: obtain the real-time location information of the aircraft through GPS, and analyze the terrain characteristics of the area in front of the aircraft in combination with the terrain data in the terrain database, including the height change of the terrain, the undulation of the terrain and the density of buildings;

[0010] S22, airflow change prediction: based on the analysis results of terrain characteristics, combined with the current flight speed of the aircraft and airflow monitoring data, predict the local airflow changes caused by terrain changes;

[0011] S23, power generation and speed regulation: automatically adjust the speed and output power of the turbine generator according to the predicted results of terrain and airflow changes;

[0012] S3, Adaptive turbine adjustment in extreme environments: The environmental sensors monitor the environmental parameters of the aircraft area in real time, including temperature, air pressure, humidity, and wind speed. Combined with the environmental data, the most suitable turbine power generation mode (such as high wind speed mode, low temperature and low load mode, etc.) is automatically selected;

[0013] S4, power generation and power distribution optimization: Combine the flight mission priority and the real-time energy demand of the aircraft, adjust the turbine power generation according to extreme environmental conditions, and distribute the generated power to various equipment of the aircraft;

[0014] S5, power status feedback and adaptive adjustment: Real-time monitoring of the aircraft's power status, including the remaining battery power and the power consumption of the current equipment. When insufficient power is detected, the working status of the turbine generator is dynamically adjusted to increase or decrease the power generation to maintain the aircraft's power balance.

[0015] Optionally, the flight parameter collection in S1 includes:

[0016] S11, GPS location information acquisition: obtain the location information of the aircraft in real time through the GPS unit on the aircraft, including longitude, latitude and altitude;

[0017] S12, speed information acquisition: obtaining the speed information of the aircraft in real time through the inertial navigation unit (INS) on the aircraft, including horizontal speed and vertical speed;

[0018] S13, flight altitude acquisition: obtain the altitude of the aircraft (relative to sea level) through the GPS unit to provide the absolute altitude information of the aircraft.

[0019] Optionally, the terrain data analysis in S21 includes:

[0020] S211, terrain feature analysis: The location information of the aircraft is obtained through GPS, and combined with the terrain data in the terrain database, the height change, terrain undulation and density of buildings are analyzed, including:

[0021] Altitude change analysis: Get the altitude of the aircraft through GPS , and combined with the terrain data in the terrain database, calculate the change in terrain height in the front area;

[0022] Analysis of terrain undulation: It is a measure of the degree of change in the terrain surface in the area ahead, calculated by analyzing the changes in height within the area;

[0023] Building density analysis: Building density Measure the distribution of buildings in the area;

[0024] S212, Terrain Complexity Analysis: Calculate the terrain complexity based on the analysis results of terrain characteristics ;

[0025] S213, terrain prediction window calculation: according to the speed of the aircraft and the current terrain complexity Calculate terrain prediction window , used to determine the impact of the front area.

[0026] Optionally, the airflow change prediction in S22 includes:

[0027] S221, flight speed and airflow monitoring data combination: real-time monitoring of airflow data around the aircraft through airflow sensors (including wind speed and direction), combined with the current flight speed of the aircraft , terrain characteristics, as input variables for airflow change prediction;

[0028] S222, airflow change prediction: The airflow change prediction is based on the local airflow model, combined with the aircraft speed and terrain characteristics to calculate the local airflow change. .

[0029] Optionally, the power generation and speed regulation in S23 includes:

[0030] S231, automatic adjustment of generator speed and power: Automatically adjust the speed of the turbine generator according to the predicted results of terrain and airflow changes and output power ;

[0031] S232, Adaptive Optimization: When the terrain complexity exceeds the complexity threshold or the airflow fluctuation exceeds the fluctuation threshold, the turbine speed is automatically reduced to reduce the power generation power. When the airflow is stable and the terrain is flat, the speed and power output are increased to improve the power generation efficiency and meet the energy needs of the aircraft.

[0032] Optionally, the extreme environment adaptive turbine regulation in S3 includes:

[0033] S31, Environmental Parameter Monitoring and Analysis: Real-time monitoring of environmental parameters in the area where the aircraft is located, including temperature, air pressure, humidity and wind speed, and comparison of real-time environmental parameters with preset environmental standards to analyze whether the current environment is an extreme condition, including high temperature, low pressure, strong wind or high humidity;

[0034] S32, Adaptive power generation mode selection: Based on the results of environmental parameter monitoring and analysis, automatically select the turbine power generation mode that best suits the current environment.

[0035] Optionally, the environmental parameter monitoring and analysis in S31 includes:

[0036] S311, real-time monitoring of environmental parameters: using environmental sensors on the aircraft to monitor the environmental parameters of the area where the aircraft is located in real time, including temperature, air pressure, humidity and wind speed;

[0037] S312, environmental standard comparison and extreme condition analysis: Compare the real-time monitored environmental parameters with the preset environmental standards to analyze whether the current environment meets the threshold of extreme conditions. The preset extreme conditions include:

[0038] High temperature: When the temperature exceeds the preset high temperature threshold, it is judged as a high temperature environment;

[0039] Low pressure: When the air pressure is lower than the preset low pressure threshold, it is judged as a low pressure environment;

[0040] Strong wind: When the wind speed exceeds the preset strong wind threshold, it is judged as a strong wind environment;

[0041] High humidity: When the humidity exceeds the preset high humidity threshold, it is determined to be a high humidity environment.

[0042] Optionally, the adaptive power generation mode selection in S32 includes:

[0043] S321, high temperature environment power generation mode: when high temperature conditions are detected (the temperature exceeds the preset high temperature threshold), it automatically enters the heat dissipation protection mode. In the heat dissipation protection mode, the turbine generator speed is reduced. To reduce heat accumulation in the equipment;

[0044] S322, low pressure environment boost compensation mode: When the aircraft enters a low pressure environment (air pressure is lower than the preset low pressure threshold), the boost compensation mode is automatically activated. In a low pressure environment, the air density decreases, resulting in a decrease in power generation efficiency. By increasing the speed of the turbine generator To compensate for the effect of thin air on power generation efficiency;

[0045] S323, strong wind environment stable control mode: when the wind speed exceeds the strong wind threshold, it enters the stable control mode, in the strong wind environment, the speed of the turbine generator is reduced, and the impact of strong wind on the turbine blades and generator is resisted by reducing the load pressure;

[0046] S324, high humidity environment protection operation mode: When the humidity exceeds the preset high humidity threshold, the protection operation mode is started to deal with the risks of equipment moisture and electrical short circuits in high humidity environments. At the same time, the protection functions are activated, including increasing insulation protection and moisture-proof measures for turbine blades.

[0047] Optionally, the power generation and power distribution optimization in S4 includes:

[0048] S41, Flight mission priority and energy demand analysis: According to the priority of flight mission and the real-time energy requirements of each device in the aircraft , calculate the power distribution weight of each device ;

[0049] S42, power regulation in extreme environments: When the aircraft enters an extreme environment (high temperature, low pressure, strong wind or high humidity), it analyzes the current environmental parameters and automatically adjusts the power output of the generator;

[0050] S43, power distribution to devices: according to the distribution weight of each device , the total power generation Assign to each device;

[0051] S44, Power Storage and Management: When the aircraft's power generation exceeds the power demand of the current mission, the excess power is stored in the backup battery.

[0052] Optionally, the power state feedback and adaptive regulation in S5 includes:

[0053] S51, real-time monitoring of power status: real-time monitoring of the aircraft's power status, including the remaining battery power, through sensors and the current power consumption of each device ;

[0054] S52, insufficient power detection: when it is detected that the remaining battery power is lower than the safety threshold or the power demand of the device exceeds the current power supply capacity, it is considered that the power is insufficient;

[0055] S53, Adaptive power generation regulation: Automatically adjust the power output of the turbine generator when insufficient power is detected , in order to maintain the electrical energy balance.

[0056] Beneficial effects of the present invention:

[0057] The present invention realizes the efficient operation of the turbine generator in complex terrain and harsh environment through dynamic terrain prediction energy regulation and extreme environment adaptive turbine regulation. By real-time monitoring of terrain, airflow and environmental parameters, the system can intelligently adjust the power generation according to environmental changes, optimize the utilization rate of airflow, and reduce energy loss. When the terrain is complex or the airflow fluctuates greatly, the system can automatically reduce the power generation to ensure the safety of the equipment. When the environmental conditions are relatively stable, the system increases the power output and improves the power generation efficiency. This efficient power generation regulation method effectively extends the flight time of the aircraft and reduces energy waste.

[0058] The present invention dynamically adjusts the power distribution strategy by combining the priority of the flight mission and the energy demand of the equipment. The system gives priority to powering mission-critical equipment to ensure that these devices always have sufficient power support during the execution of the mission. By reasonably allocating power and storing excess power, the aircraft can ensure the normal operation of other equipment while completing high-priority tasks. This intelligent power distribution method effectively avoids the problem of mission interruption due to improper power distribution, and improves the reliability and efficiency of mission execution.

[0059] The present invention monitors the environmental parameters of the aircraft in real time and automatically selects the most suitable turbine power generation mode to ensure that the system can still operate efficiently in extreme environments. In response to different environmental conditions such as high temperature, low pressure, strong wind and high humidity, the system can quickly adjust the working state of the generator to protect the equipment from environmental influences and prevent performance degradation. Through precise environmental identification and adjustment, the adaptability of the aircraft in complex climatic conditions is greatly improved, the service life of the equipment is extended, and the safety and stability of the flight mission are guaranteed. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only for the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0061] Figure 1 A schematic diagram of a flow chart of an adjustment method according to an embodiment of the present invention;

[0062] Figure 2A schematic diagram of dynamic terrain prediction energy regulation according to an embodiment of the present invention. DETAILED DESCRIPTION

[0063] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. At the same time, it is explained here that in order to make the embodiments more detailed, the following embodiments are the best and preferred embodiments, and those skilled in the art may also adopt other alternatives to implement some known technologies; and the accompanying drawings are only for more specific description of the embodiments, and are not intended to specifically limit the present invention.

[0064] It should be noted that the references to "one embodiment", "embodiment", "exemplary embodiments", "some embodiments" and the like in the specification indicate that the embodiments described may include specific features, structures or characteristics, but not every embodiment may include the specific features, structures or characteristics. In addition, when a specific feature, structure or characteristic is described in conjunction with an embodiment, it should be within the knowledge of a person skilled in the art to implement such feature, structure or characteristic in conjunction with other embodiments (whether or not explicitly described).

[0065] In general, a term can be understood, at least in part, from its use in context. For example, depending, at least in part, on the context, the term "one or more" as used herein can be used to describe any feature, structure, or characteristic in the singular sense, or can be used to describe a combination of features, structures, or characteristics in the plural sense. Additionally, the term "based on" can be understood as not necessarily intended to convey an exclusive set of factors, but can instead, depending, at least in part, on the context, allow for the presence of other factors that are not necessarily explicitly described.

[0066] like Figure 1-Figure 2 As shown, the GPS synchronized turbine power generation regulation method for low-altitude aircraft includes the following steps:

[0067] S1, flight parameter collection: obtain the flight parameters of the aircraft in real time through the GPS unit on the low-altitude aircraft, including position information, speed information and flight altitude;

[0068] S2, Dynamic Terrain Prediction Energy Regulation: Based on the aircraft's location information and terrain database, the terrain changes in the area ahead of the aircraft are analyzed in advance, and the impact of the terrain on airflow and turbine power generation is predicted. When the terrain complexity increases (such as mountains, canyons, urban high-rise buildings, etc.), the speed and output power of the turbine generator are automatically adjusted to optimize airflow utilization and reduce energy loss. Specifically, it includes:

[0069] S21, terrain data analysis: obtain the real-time location information of the aircraft through GPS, and analyze the terrain characteristics of the area in front of the aircraft in combination with the terrain data in the terrain database, including the height change of the terrain, the undulation of the terrain and the density of buildings;

[0070] S22, airflow change prediction: Based on the analysis results of terrain features, combined with the current flight speed of the aircraft and airflow monitoring data, the local airflow changes caused by terrain changes are predicted. For example, the rising airflow in the mountain area or the strong wind in the canyon can be predicted. Through this airflow prediction, the system can determine the change trend of the airflow in the next few seconds to minutes in advance;

[0071] S23, power generation and speed regulation: automatically adjust the speed and output power of the turbine generator according to the predicted results of terrain and airflow changes;

[0072] S3, Adaptive turbine adjustment in extreme environments: The environmental sensors monitor the environmental parameters of the aircraft area in real time, including temperature, air pressure, humidity, and wind speed. Combined with the environmental data, the most suitable turbine power generation mode (such as high wind speed mode, low temperature and low load mode, etc.) is automatically selected to ensure the power generation efficiency and stability of the turbine generator in extreme environments.

[0073] S4, power generation and power distribution optimization: Combine the flight mission priority and the real-time energy demand of the aircraft, adjust the turbine power generation according to the extreme environmental conditions, distribute the generated power to various equipment of the aircraft, give priority to powering mission-critical equipment, and store excess power in backup batteries;

[0074] S5, power state feedback and adaptive adjustment: real-time monitoring of the aircraft's power state, including the remaining battery power and the power consumption of the current equipment. When insufficient power is detected, the working state of the turbine generator is dynamically adjusted to increase or decrease the power generation to maintain the aircraft's power balance;

[0075] Through the above content, precise control and optimization of the turbine generator are achieved, and the power generation power can be dynamically adjusted according to the terrain and extreme environment of the aircraft. By reasonably allocating electric energy, the power needs of critical mission equipment are prioritized, thereby improving power generation efficiency, extending the flight time of the aircraft, and maintaining stable operation of the aircraft in complex or harsh environments. Through all-round intelligent adjustment, the flexibility and reliability of energy management are improved.

[0076] Flight parameter collection in S1 includes:

[0077] S11, GPS location information acquisition: obtain the location information of the aircraft in real time through the GPS unit on the aircraft, including longitude, latitude and altitude;

[0078] S12, speed information acquisition: obtaining the speed information of the aircraft in real time through the inertial navigation unit (INS) on the aircraft, including horizontal speed and vertical speed;

[0079] S13, flight altitude acquisition: obtaining the altitude of the aircraft (relative to the sea level) through the GPS unit to provide the absolute altitude information of the aircraft;

[0080] Through the above content, the position information, speed information and flight altitude of the aircraft are obtained in real time, providing the system with comprehensive flight status data. The longitude, latitude and altitude are obtained through GPS to ensure the accurate positioning of the aircraft. The horizontal and vertical speeds are obtained in real time through INS to provide dynamic information for the adjustment of the flight status. At the same time, the flight altitude collection accurately monitors the absolute altitude of the aircraft through the GPS unit, providing accurate basic data for the energy regulation, mission execution and environmental adaptation of the aircraft, thereby improving the system's intelligent regulation capability and mission execution efficiency.

[0081] The terrain data analysis in S21 includes:

[0082] S211, terrain feature analysis: The location information of the aircraft is obtained through GPS, and combined with the terrain data in the terrain database, the height change, terrain undulation and density of buildings are analyzed, including:

[0083] Altitude change analysis: Get the altitude of the aircraft through GPS , and combined with the terrain data in the terrain database, calculate the change in terrain height in the front area, expressed as:

[0084] ;

[0085] in, is the terrain height of the front area in the terrain database, is the current altitude of the aircraft, altitude change Used to assess the terrain undulations ahead of the aircraft;

[0086] Analysis of terrain undulation: It is a measure of the degree of change in the terrain surface in the front area. It is calculated by analyzing the height change in the area and is expressed as:

[0087] ;

[0088] in, It is the first The height of the point, is the average height of the area, is the number of sampling points, Used to assess the complexity of the terrain in the area ahead;

[0089] Building density analysis: Building density Measures the distribution of buildings in the area, expressed as:

[0090] ;

[0091] in, is the total area occupied by the building, is the total area of ​​the region, Used to determine the impact of buildings on aircraft;

[0092] S212, Terrain Complexity Analysis: Calculate the terrain complexity based on the analysis results of terrain characteristics , expressed as:

[0093] ;

[0094] in, is the complexity of the terrain. is the building density complexity, and is the weight;

[0095] ;

[0096] ;

[0097] in, is the preset maximum terrain relief value, used to standardize terrain relief. is the preset maximum building density, used to normalize the building density;

[0098] S213, terrain prediction window calculation: according to the speed of the aircraft and the current terrain complexity Calculate terrain prediction window , used to judge the influence of the front area, expressed as:

[0099] ;

[0100] in, is the speed of the aircraft, is the time window, is the maximum value of terrain complexity;

[0101] Through the above content, it is possible to more accurately predict the complexity of the flight environment and adjust the aircraft's power generation power and flight altitude in a timely manner. It can cope with a variety of complex terrain scenarios, optimize the aircraft's energy utilization, improve flight safety, and effectively reduce energy waste caused by terrain complexity.

[0102] Airflow change predictions in S22 include:

[0103] S221, flight speed and airflow monitoring data combination: real-time monitoring of airflow data around the aircraft through airflow sensors (including wind speed and direction), combined with the current flight speed of the aircraft , terrain characteristics, as input variables for airflow change prediction;

[0104] S222, airflow change prediction: The airflow change prediction is based on the local airflow model, combined with the aircraft speed and terrain characteristics to calculate the local airflow change. , expressed as:

[0105] ;

[0106] in, is the predicted local airflow change, It is the change in terrain height that affects updrafts or downdrafts. It is the undulating terrain, describing the ruggedness of the terrain, which affects the stability of the airflow. is the density of buildings. The denser the buildings, the greater the interference to the airflow. is the flight speed of the aircraft. At higher speeds, the airflow changes more significantly. is the current air velocity, is an empirical coefficient, determined by experiment or simulation;

[0107] Through the above content, it is possible to identify in advance the airflow changes that may affect flight stability and turbine power generation efficiency, and then adjust the power generation power and flight altitude in real time to ensure that the aircraft can still operate efficiently in complex terrain and airflow environments, thereby improving the energy management efficiency of the aircraft and enhancing flight stability and safety in changeable airflows.

[0108] The power generation and speed regulation in S23 include:

[0109] S231, automatic adjustment of generator speed and power: Automatically adjust the speed of the turbine generator according to the predicted results of terrain and airflow changes and output power , expressed as:

[0110] ;

[0111] ;

[0112] in, is the rated speed of the turbine generator, is the predicted amount of airflow change, is the current air velocity, is the terrain complexity, is the maximum value of terrain complexity, It is an empirical coefficient used to adjust the variation of output power;

[0113] S232, Adaptive Optimization: When the terrain complexity exceeds the complexity threshold or the airflow fluctuation exceeds the fluctuation threshold, the turbine speed is automatically reduced to reduce the power generation. When the airflow is stable and the terrain is flat, the speed and power output are increased to improve the power generation efficiency and meet the energy needs of the aircraft.

[0114] The complexity threshold is used to determine whether the terrain changes exceed the range of stable operation. and terrain adaptability Setting, expressed as:

[0115] ;

[0116] in, is the complexity threshold, is the maximum allowed value of terrain complexity, It is the maximum terrain complexity fluctuation percentage set by the system;

[0117] The fluctuation threshold is used to detect whether the current airflow velocity change exceeds the limit that can stabilize power generation. The threshold is based on real-time airflow monitoring data and the maximum fluctuation value that the system can tolerate. Set it up, expressed as:

[0118] ;

[0119] in, is the average air velocity in the current environment, It is the maximum allowable airflow fluctuation percentage set by the system;

[0120] Through the above content, combined with the real-time prediction results of terrain complexity and airflow changes, the speed and output power of the generator are automatically adjusted to ensure that the system automatically reduces the power generation power when the terrain complexity increases or the airflow fluctuates violently, so as to reduce energy consumption and avoid the loss of power generation efficiency. When the airflow is stable and the terrain is flat, the system can increase the speed and power output, improve the power generation efficiency and meet the energy needs of the aircraft, thereby improving the overall efficiency of the power generation system, enabling the aircraft to operate efficiently and safely in various complex environments, extending the flight time of the aircraft and optimizing energy utilization.

[0121] Extreme environment adaptive turbo tuning in S3 includes:

[0122] S31, Environmental Parameter Monitoring and Analysis: Real-time monitoring of environmental parameters in the area where the aircraft is located, including temperature, air pressure, humidity and wind speed, and comparison of real-time environmental parameters with preset environmental standards to analyze whether the current environment is an extreme condition, including high temperature, low pressure, strong wind or high humidity;

[0123] S32, adaptive power generation mode selection: based on the results of environmental parameter monitoring and analysis, automatically select the turbine power generation mode that best suits the current environment;

[0124] Through the above content, extreme conditions can be accurately identified and the most suitable power generation mode for the current environment can be automatically selected. The working state of the generator can be flexibly adjusted according to environmental changes to ensure high power generation efficiency under harsh conditions and avoid performance degradation due to environmental fluctuations. The environmental adaptability of the aircraft is improved, the service life of the system is extended, and energy management is optimized to ensure that the aircraft can operate stably under various climatic conditions.

[0125] Environmental parameter monitoring and analysis in S31 include:

[0126] S311, real-time monitoring of environmental parameters: using environmental sensors on the aircraft to monitor the environmental parameters of the area where the aircraft is located in real time, including temperature, air pressure, humidity and wind speed;

[0127] S312, environmental standard comparison and extreme condition analysis: Compare the real-time monitored environmental parameters with the preset environmental standards to analyze whether the current environment meets the threshold of extreme conditions. The preset extreme conditions include:

[0128] High temperature: When the temperature exceeds the preset high temperature threshold, it is judged as a high temperature environment;

[0129] Low pressure: When the air pressure is lower than the preset low pressure threshold, it is judged as a low pressure environment;

[0130] Strong wind: When the wind speed exceeds the preset strong wind threshold, it is judged as a strong wind environment;

[0131] High humidity: When the humidity exceeds the preset high humidity threshold, it is judged as a high humidity environment;

[0132] High temperature threshold Used to determine whether the aircraft is in a high temperature environment. It is set according to the aircraft's operating standards and the equipment's tolerance temperature, expressed as:

[0133] ;

[0134] in, The upper temperature limit for normal operation of the aircraft (usually or ), is the high temperature safety margin, which indicates the additional temperature that the equipment can withstand;

[0135] Low voltage threshold Used to determine whether the aircraft is in a low-pressure environment. It is set according to the pressure changes of the aircraft at different altitudes, expressed as:

[0136] ;

[0137] in, is the standard sea level pressure (usually 1013hPa), is the current altitude difference of the aircraft (relative to sea level), is the maximum height that can be set;

[0138] High wind threshold Used to determine whether the aircraft is in a strong wind environment, expressed as:

[0139] ;

[0140] in, is the upper limit of wind speed for safe operation of the aircraft. is the additional wind speed the aircraft can withstand;

[0141] High humidity threshold Used to determine whether the aircraft is in a high humidity environment. It is set according to the humidity tolerance of the aircraft's internal equipment and is expressed as:

[0142] ;

[0143] in, It is the upper limit of normal humidity that the equipment can withstand. is a safety margin for high humidity;

[0144] Through the above content, the environmental conditions of the aircraft can be accurately identified, and the environment can be analyzed according to the preset high temperature, low pressure, strong wind and high humidity thresholds. It can automatically determine whether it is under extreme conditions, and can promptly and accurately feedback environmental changes to ensure that the system can still operate efficiently and safely in complex and harsh environments. It improves the environmental adaptability of the aircraft, enhances the stability of the power generation system, and ensures that the flight mission can be successfully completed under various climatic conditions.

[0145] Adaptive generation mode selection in S32 includes:

[0146] S321, high temperature environment power generation mode: when high temperature conditions are detected (the temperature exceeds the preset high temperature threshold), it automatically enters the heat dissipation protection mode. In the heat dissipation protection mode, the turbine generator speed is reduced. To reduce heat accumulation in equipment and prevent overheating;

[0147] S322, low pressure environment boost compensation mode: When the aircraft enters a low pressure environment (air pressure is lower than the preset low pressure threshold), the boost compensation mode is automatically activated. In a low pressure environment, the air density decreases, resulting in a decrease in power generation efficiency. By increasing the speed of the turbine generator To compensate for the effect of thin air on power generation efficiency;

[0148] S323, strong wind environment stable control mode: When the wind speed exceeds the strong wind threshold, it enters the stable control mode. In a strong wind environment, in order to avoid excessive speed and excessive vibration, the speed of the turbine generator is reduced to ensure the stable operation of the equipment under wind interference. At the same time, the impact of strong wind on the turbine blades and generator is resisted by reducing the load pressure to maintain safe power output;

[0149] S324, high humidity environment protection operation mode: When the humidity exceeds the preset high humidity threshold, the protection operation mode is activated to deal with the risk of equipment moisture and electrical short circuit in high humidity environments. In the protection operation mode, the power output of the generator is reduced to reduce the erosion of moisture on the equipment. At the same time, the protection function is activated, including adding insulation protection and moisture-proof measures for turbine blades to ensure that the power generation equipment can still operate safely before the humidity drops to a safe level;

[0150] Through the above content, the operating status of the turbine generator can be automatically adjusted according to the real-time environmental conditions, which can effectively protect the equipment in harsh environments, prevent overheating, insufficient air pressure, strong wind vibration and moisture erosion, extend the life of the equipment, and ensure safe and stable operation in extreme environments. It improves the environmental adaptability and energy utilization of the aircraft, thereby improving the reliability of mission completion.

[0151] Generation and energy distribution optimization in S4 includes:

[0152] S41, Flight mission priority and energy demand analysis: According to the priority of flight mission and the real-time energy requirements of each device in the aircraft , calculate the power distribution weight of each device , expressed as:

[0153] ;

[0154] in, is the power allocation weight, Indicates the priority of the task, higher priority tasks get higher weights, is the energy requirement of the device, and is the weight coefficient;

[0155] S42, power regulation in extreme environments: When the aircraft enters an extreme environment (high temperature, low pressure, strong wind or high humidity), the current environmental parameters are analyzed and the power output of the generator is automatically adjusted, expressed as:

[0156] ;

[0157] in, is the power output after environmental adjustment. It is the difference between the deviation of environmental parameters (such as temperature, air pressure, etc.) and the standard value. It is the maximum environmental deviation that can be tolerated. When the environmental conditions are bad, the power generation will be reduced to avoid damage to the equipment;

[0158] S43, power distribution to devices: according to the distribution weight of each device , the total power generation The amount of power allocated to each device It is expressed as:

[0159] ;

[0160] in, It is the electrical energy allocated to a device. is the sum of the power weights of all devices, is the total output power of the generator;

[0161] S44, Power Storage and Management: When the aircraft's power generation exceeds the power demand of the current mission, the excess power is stored in the backup battery. The battery charging power It is expressed as:

[0162] ;

[0163] in, It is the electrical energy stored in the backup battery. is the total power output of the generator, It is the total power consumed by all devices in the current task;

[0164] Through the above content, it is ensured that electric energy can be reasonably distributed to various key equipment, and that mission-critical equipment has priority in obtaining electric energy supply to avoid mission interruption due to energy shortage. At the same time, in extreme environments, by intelligently adjusting the power generation capacity and optimizing energy utilization efficiency, it can respond to environmental changes and mission requirements in real time, improve the endurance of the aircraft and the flexibility of energy management, and ensure the continuity and reliability of the flight mission.

[0165] The power state feedback and adaptive regulation in S5 include:

[0166] S51, real-time monitoring of power status: real-time monitoring of the aircraft's power status, including the remaining battery power, through sensors and the current power consumption of each device ;

[0167] S52, insufficient power detection: when it is detected that the remaining battery power is lower than the safety threshold or the power demand of the device exceeds the current power supply capacity, it is considered that the power is insufficient;

[0168] Safety threshold It is dynamically set based on the priority of the flight mission, the energy requirements of the equipment and the actual energy consumption of the aircraft, and is expressed as:

[0169] ;

[0170] in, is the set power safety threshold, is the total energy demand of the current device, is the task priority coefficient (usually between 0 and 1). The higher the priority, the larger the coefficient. is the power redundancy factor, which is used to ensure additional power reserves, usually to between, is the battery attenuation coefficient (usually less than 1, indicating the percentage of remaining capacity of the battery);

[0171] S53, Adaptive power generation regulation: Automatically adjust the power output of the turbine generator when insufficient power is detected , to maintain the power balance, expressed as:

[0172] ;

[0173] in, is the adjusted generator power output, is the rated power of the generator, is the current total energy demand of the device, is the remaining battery power, is the power demand of the equipment, is the current power supply capacity of the generator, and is the adjustment factor;

[0174] Through the above content, the power output of the turbine generator can be quickly adjusted to avoid mission interruption due to insufficient power. Combined with mission priorities and equipment requirements, dynamic and precise power generation regulation is achieved, ensuring the power supply of key equipment, extending the flight time of the aircraft, and improving the reliability and efficiency of the flight mission.

[0175] The present invention covers any substitution, modification, equivalent method and scheme made on the essence and scope of the present invention. In order to make the public have a thorough understanding of the present invention, specific details are described in detail in the following preferred embodiments of the present invention, but those skilled in the art can fully understand the present invention without the description of these details. In addition, in order to avoid unnecessary confusion about the essence of the present invention, well-known methods, processes, procedures, components and circuits are not described in detail.

[0176] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A GPS synchronized turbine power generation regulation method for low altitude aircraft, characterized in that: The following steps are involved: S1, flight parameter collection: obtain the flight parameters of the aircraft in real time through the GPS unit on the low-altitude aircraft, including position information, speed information and flight altitude; S2, Dynamic Terrain Prediction Energy Regulation: Based on the aircraft's location information and terrain database, the terrain changes in the area ahead of the aircraft are analyzed in advance, and the impact of the terrain on airflow and turbine power generation is predicted. When the terrain complexity is predicted to increase, the speed and output power of the turbine generator are automatically adjusted. Specifically, it includes: S21, terrain data analysis: obtain the real-time location information of the aircraft through GPS, and analyze the terrain characteristics of the area in front of the aircraft in combination with the terrain data in the terrain database, including the height change of the terrain, the undulation of the terrain and the density of buildings; S22, airflow change prediction: based on the analysis results of terrain characteristics, combined with the current flight speed of the aircraft and airflow monitoring data, predict the local airflow changes caused by terrain changes; S23, power generation and speed regulation: automatically adjust the speed and output power of the turbine generator according to the predicted results of terrain and airflow changes; S3, Adaptive turbine adjustment in extreme environments: The environmental sensors monitor the environmental parameters of the aircraft area in real time, including temperature, air pressure, humidity, and wind speed. Combined with the environmental data, the most suitable turbine power generation mode is automatically selected; S4, power generation and power distribution optimization: Combine the flight mission priority and the real-time energy demand of the aircraft, adjust the turbine power generation according to extreme environmental conditions, and distribute the generated power to various equipment of the aircraft; S5, power status feedback and adaptive adjustment: Real-time monitoring of the aircraft's power status, including the remaining battery power and the power consumption of the current equipment. When insufficient power is detected, the working status of the turbine generator is dynamically adjusted to increase or decrease the power generation to maintain the aircraft's power balance.

2. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 1, characterized in that: The flight parameter collection in S1 includes: S11, GPS location information acquisition: obtain the location information of the aircraft in real time through the GPS unit on the aircraft, including longitude, latitude and altitude; S12, speed information acquisition: obtaining the speed information of the aircraft in real time through the inertial navigation unit on the aircraft, including horizontal speed and vertical speed; S13, flight altitude acquisition: obtaining the altitude of the aircraft through the GPS unit to provide the absolute altitude information of the aircraft.

3. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 1, characterized in that: The terrain data analysis in S21 includes: S211, terrain feature analysis: The location information of the aircraft is obtained through GPS, and combined with the terrain data in the terrain database, the height change, terrain undulation and density of buildings are analyzed, including: Altitude change analysis: Get the altitude of the aircraft through GPS , and combined with the terrain data in the terrain database, calculate the change in terrain height in the front area; Analysis of terrain undulation: It is a measure of the degree of change in the terrain surface in the area ahead, calculated by analyzing the changes in height within the area; Building density analysis: Building density measure the distribution of buildings in the area; S212, Terrain Complexity Analysis: Calculate the terrain complexity based on the analysis results of terrain characteristics ; S213, terrain prediction window calculation: according to the speed of the aircraft and the current terrain complexity Calculate terrain prediction window , used to determine the impact of the front area.

4. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 3, characterized in that: The airflow change prediction in S22 includes: S221, flight speed and airflow monitoring data combination: real-time monitoring of airflow data around the aircraft through airflow sensors , combined with the current flight speed of the aircraft , terrain characteristics, as input variables for airflow change prediction; S222, airflow change prediction: The airflow change prediction is based on the local airflow model, combined with the aircraft speed and terrain characteristics to calculate the local airflow change. .

5. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 4, characterized in that: The power generation and speed regulation in S23 includes: S231, automatic adjustment of generator speed and power: Automatically adjust the speed of the turbine generator according to the predicted results of terrain and airflow changes and output power ; S232, Adaptive Optimization: When the terrain complexity exceeds the complexity threshold or the airflow fluctuation exceeds the fluctuation threshold, the turbine speed is automatically reduced to reduce the power generation power. When the airflow is stable and the terrain is flat, the speed and power output are increased to improve the power generation efficiency and meet the energy needs of the aircraft.

6. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 5, characterized in that: The extreme environment adaptive turbo tuning in the S3 includes: S31, Environmental Parameter Monitoring and Analysis: Real-time monitoring of environmental parameters in the area where the aircraft is located, including temperature, air pressure, humidity and wind speed, and comparison of real-time environmental parameters with preset environmental standards to analyze whether the current environment is an extreme condition, including high temperature, low pressure, strong wind or high humidity; S32, Adaptive power generation mode selection: Based on the results of environmental parameter monitoring and analysis, automatically select the turbine power generation mode that best suits the current environment.

7. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 6, characterized in that: The environmental parameter monitoring and analysis in S31 includes: S311, real-time monitoring of environmental parameters: using environmental sensors on the aircraft to monitor the environmental parameters of the area where the aircraft is located in real time, including temperature, air pressure, humidity and wind speed; S312, environmental standard comparison and extreme condition analysis: Compare the real-time monitored environmental parameters with the preset environmental standards to analyze whether the current environment meets the threshold of extreme conditions. The preset extreme conditions include: High temperature: When the temperature exceeds the preset high temperature threshold, it is judged as a high temperature environment; Low pressure: When the air pressure is lower than the preset low pressure threshold, it is judged as a low pressure environment; Strong wind: When the wind speed exceeds the preset strong wind threshold, it is judged as a strong wind environment; High humidity: When the humidity exceeds the preset high humidity threshold, it is determined to be a high humidity environment.

8. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 7, characterized in that: The adaptive power generation mode selection in S32 includes: S321, high temperature environment power generation mode: when high temperature conditions are detected, it automatically enters the heat dissipation protection mode. In the heat dissipation protection mode, the speed of the turbine generator is reduced. To reduce heat accumulation in the equipment; S322, low pressure environment boost compensation mode: When the aircraft enters a low pressure environment, the boost compensation mode is automatically activated. In a low pressure environment, the air density decreases, resulting in a decrease in power generation efficiency. By increasing the speed of the turbine generator To compensate for the effect of thin air on power generation efficiency; S323, strong wind environment stable control mode: when the wind speed exceeds the strong wind threshold, it enters the stable control mode, in the strong wind environment, the speed of the turbine generator is reduced, and the impact of strong wind on the turbine blades and generator is resisted by reducing the load pressure; S324, high humidity environment protection operation mode: When the humidity exceeds the preset high humidity threshold, the protection operation mode is started to deal with the risks of equipment moisture and electrical short circuits in high humidity environments. At the same time, the protection functions are activated, including increasing insulation protection and moisture-proof measures for turbine blades.

9. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 8, characterized in that: The power generation and power distribution optimization in S4 includes: S41, Flight mission priority and energy demand analysis: According to the priority of flight mission and the real-time energy requirements of each device in the aircraft , calculate the power distribution weight of each device ; S42, power regulation in extreme environments: when the aircraft enters an extreme environment, it analyzes the current environmental parameters and automatically adjusts the power output of the generator; S43, power distribution to devices: according to the distribution weight of each device , the total power generation Assign to each device; S44, Power Storage and Management: When the aircraft's power generation exceeds the power demand of the current mission, the excess power is stored in the backup battery.

10. The GPS synchronized turbine power generation regulation method for low altitude aircraft according to claim 9, characterized in that: The power state feedback and adaptive regulation in S5 include: S51, real-time monitoring of power status: real-time monitoring of the aircraft's power status, including the remaining battery power, through sensors and the current power consumption of each device ; S52, insufficient power detection: when it is detected that the remaining battery power is lower than the safety threshold or the power demand of the device exceeds the current power supply capacity, it is considered that the power is insufficient; S53, Adaptive power generation regulation: Automatically adjust the power output of the turbine generator when insufficient power is detected , in order to maintain the electrical energy balance.

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