Air turbine power generation system and method under wide-speed-domain flight working condition

Abstract

According to the air turbine power generation system and method under the wide-speed-range flight working condition, in the system, an air turbine converts air kinetic energy into mechanical energy, and the air turbine comprises an air inlet end located on the front portion and a nozzle end located on the rear portion; the generator is coaxially and directly connected with the air turbine to rotate to generate power based on mechanical energy; the dynamic nozzle area adjusting device is located at the nozzle end, the conical structure can move relative to the nozzle position of the air turbine, and the lead screw is connected with the conical structure to adjust the relative position of the conical structure and the nozzle so as to change the nozzle area and further adjust the exhaust back pressure of the air turbine. The real-time control and feedback module is connected with the generator and the dynamic nozzle area adjusting device, the measuring sensor measures the rotating speed of the generator to obtain a real-time rotating speed signal, and the PID controller is connected with the measuring sensor to calculate the deviation between the current rotating speed state and the target rotating speed state based on the rotating speed signal. And a control signal is output to control the actuating distance of the stepping motor, so that the real-time adjustment of the area of the nozzle is realized.

Description

Technical Field

[0001] This invention relates to the field of ram air turbine power generation technology, and in particular to an air turbine power generation system and method for wide-speed-range flight conditions. Background Technology

[0002] The power output of an air turbine is closely related to its turbine speed, and power control is a crucial element in ensuring the efficient and stable operation of the system. Precisely controlling turbine speed presents certain challenges in power control. On one hand, traditional mechanical control stabilizes power output through variable pitch control. However, due to the large inertia of mechanical systems, they struggle to adapt quickly to sudden changes in wind speed during flight. Frequent adjustments to blade angles increase frictional losses, which accumulate over time and with increased usage frequency, reducing system lifespan and overall power generation efficiency. On the other hand, while electronic speed control systems are relatively precise, they may experience signal interference or response delays under high speeds or extreme conditions. For example, in environments with strong electromagnetic interference, the electronic speed control system may fail to accurately and promptly transmit turbine speed control commands, causing the turbine speed to deviate from the optimal power generation range, thus affecting power generation efficiency. Air temperature and pressure affect air density, thereby altering the force exerted by the air on the turbine. Temperature and pressure vary significantly under different flight conditions. Existing power control technologies often do not adequately consider the impact of these factors on power generation. For example, in high-altitude areas, the air pressure is lower and the air density is lower, which reduces the power generation of the turbine. However, existing control technologies may not be able to automatically adjust the turbine's operating parameters according to changes in air pressure to maintain a stable power output.

[0003] In actual flight, as flight altitude and speed change constantly, airflow is difficult to keep stable. When airflow suddenly increases, the turbine may not be able to quickly adjust to the optimal working state to adapt to the new airflow, resulting in unstable power generation and affecting the stability and reliability of the power system.

[0004] The information disclosed in the background section is only intended to enhance the understanding of the background of the present invention, and therefore may contain information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0005] To address the shortcomings or defects of the existing technology, an air turbine power generation system and method for wide-speed-range flight conditions are provided. This system addresses the stable power supply requirements of air turbine electrical systems under wide-speed-range flight conditions, focusing on issues such as the difficulty in meeting power demands due to the low work capacity of air turbines at high altitudes and low Mach speeds, and the instability of air turbines operating at low altitudes and high Mach speeds. By adjusting the tailpipe opening to indirectly control the airflow through the air turbine channel, a scheme is developed to stabilize the air turbine speed under different operating conditions, ensuring the stable operation of the power generation system. This achieves the goal of stable power supply for air turbine electrical systems under wide-speed-range flight conditions.

[0006] The objective of this invention is achieved through the following technical solutions.

[0007] An air turbine power generation system for wide-speed-range flight conditions includes,

[0008] An air turbine converts the kinetic energy of air into mechanical energy. An air turbine includes an air intake at the front and an air nozzle at the rear.

[0009] A generator, coaxially connected to the air turbine, generates electricity by rotating based on the mechanical energy.

[0010] A dynamic nozzle area adjustment device, located at the nozzle end, includes,

[0011] The conical structure is movable relative to the nozzle position of the air turbine.

[0012] A lead screw, connected to the conical structure, adjusts the relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the exhaust back pressure of the air turbine.

[0013] An electric stepper motor, which drives the lead screw;

[0014] A real-time control and feedback module, connected to the generator and the dynamic nozzle area adjustment device, includes,

[0015] The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal.

[0016] The PID controller is connected to the measurement sensor to calculate the deviation between the current speed state and the target speed state based on the speed signal, and outputs a control signal to control the actuation distance of the stepper motor, thereby realizing real-time adjustment of the nozzle area.

[0017] In the aforementioned air turbine power generation system operating under wide speed range flight conditions, the conical structure has a variable geometric cross-section.

[0018] In the wide-speed-range flight condition air turbine power generation system, the maximum cross-sectional area of ​​the conical structure is smaller than the hollow area of ​​the nozzle.

[0019] In the wide-speed-range flight condition air turbine power generation system, the electric stepper motor drives the lead screw to controllably adjust the axial relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the turbine exhaust back pressure.

[0020] In the air turbine power generation system under wide-speed-range flight conditions, the PID controller calculates the deviation signal between the speed signal measured by the sensor and the target speed, the controller output signal drives the stepper motor to control the nozzle area, and real-time monitoring and adjustment form a closed-loop feedback control.

[0021] In the wide-speed-range flight condition air turbine power generation system, the air turbine is a ram air turbine.

[0022] In the aforementioned air turbine power generation system operating under wide speed range flight conditions, the work capacity of the air turbine is expressed by the following formula:

[0023] (1)

[0024] in, Power for air turbines, power: W , where is the air flow rate (kg / s), Cp is the specific heat capacity of air (J / (kg·K), and T01 and T02 are the total air temperatures at the turbine inlet and outlet (K), respectively.

[0025] In the aforementioned air turbine power generation system operating under wide-speed-range flight conditions, the relationship between the nozzle area and the exhaust back pressure is as follows:

[0026] (2)

[0027] in, For exhaust back pressure, Pa, The nozzle flow area is expressed in square meters (m²).

[0028] The adjustment methods for air turbine power generation systems under wide-speed-range flight conditions include:

[0029] An air turbine converts the kinetic energy of air into mechanical energy.

[0030] The generator is coaxially connected to the air turbine to generate electricity by rotating based on the mechanical energy.

[0031] The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal.

[0032] The PID controller is connected to the measurement sensor to calculate the deviation between the current speed state and the target speed state based on the speed signal, and outputs a control signal to control the operating distance of the stepper motor.

[0033] An electric stepper motor drives the lead screw to actuate the conical structure to adjust the relative position of the conical structure and the nozzle, thereby changing the nozzle area and adjusting the air turbine exhaust back pressure, thus realizing real-time adjustment of the nozzle area. The PID controller provides real-time feedback to adjust the nozzle area to keep the air turbine output power and speed consistent with the target power and speed.

[0034] In the method described, the PID controller closed-loop control includes:

[0035] (3)

[0036] in, K represents the deviation between the target speed and the real-time speed. p K i and K d These are the proportional coefficient, integral coefficient, and derivative coefficient of the control parameters, respectively. For the old nozzle flow channel area, This represents the area of ​​the new nozzle flow channel.

[0037] Compared with the prior art, the beneficial effects of this invention are as follows:

[0038] This invention improves the operational stability of ram air turbines under wide speed range operating conditions; stabilizes the air turbine speed under different operating conditions to ensure stable operation of the power generation system; adjusts the nozzle area in real time to control the exhaust back pressure, thereby precisely adjusting the turbine output power and speed; the actuator is simple and lightweight, with rapid and smooth adjustment, fast response speed, and high adjustment accuracy.

[0039] The description provided is merely an overview of the technical solution of this invention. In order to make the technical means of this invention clearer and more understandable, so that those skilled in the art can implement it according to the contents of the specification, and to make the described and other objects, features and advantages of this invention more obvious and understandable, specific embodiments of this invention are described below. Attached Figure Description

[0040] Various other advantages and benefits of the present invention will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. Furthermore, the same reference numerals denote the same parts throughout the drawings.

[0041] In the attached diagram:

[0042] Figure 1 This is a three-dimensional structural diagram of an air turbine structure from the air inlet end, according to an embodiment of the present invention.

[0043] Figure 2 This is a three-dimensional structural diagram of an air turbine structure with the nozzle end facing outwards, according to an embodiment of the present invention.

[0044] Figure 3 This is a schematic diagram of a dynamic nozzle area adjustment device according to an embodiment of the present invention;

[0045] Figure 4 This is a logic block diagram of the real-time control and feedback module of the present invention.

[0046] The present invention will be further explained below with reference to the accompanying drawings and embodiments. Detailed Implementation

[0047] Specific embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While specific embodiments of the invention are shown in the drawings, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the invention and to fully convey the scope of the invention to those skilled in the art.

[0048] It should be noted that certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that different terms may be used to refer to the same component. This specification and claims do not distinguish components based on differences in terminology, but rather on differences in function. The terms "comprising" or "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising but not limited to." The following descriptions are preferred embodiments for carrying out the invention; however, these descriptions are for the purpose of understanding the general principles of the specification and are not intended to limit the scope of the invention. The scope of protection of this invention is determined by the appended claims.

[0049] To facilitate understanding of the embodiments of the present invention, the following will provide further explanation and description with reference to the accompanying drawings and several specific embodiments, and the accompanying drawings do not constitute a limitation on the embodiments of the present invention.

[0050] To better understand, such as Figures 1 to 4 As shown, an air turbine power generation system for wide-speed-range flight conditions includes,

[0051] An air turbine converts the kinetic energy of air into mechanical energy. An air turbine includes an air intake at the front and an air nozzle at the rear.

[0052] A generator, coaxially connected to the air turbine, generates electricity by rotating based on the mechanical energy.

[0053] A dynamic nozzle area adjustment device, located at the nozzle end, includes,

[0054] Conical structure (such as) Figure 2 (As shown) is fastened to the lead screw and nut with screws, and its position relative to the air turbine nozzle is movable.

[0055] A lead screw, connected to the conical structure, adjusts the relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the exhaust back pressure of the air turbine.

[0056] An electric stepper motor, which drives the lead screw;

[0057] A real-time control and feedback module, connected to the generator and the dynamic nozzle area adjustment device, includes,

[0058] The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal.

[0059] A PID controller, connected to the measurement sensor, calculates the deviation between the current rotational speed and the target rotational speed based on the rotational speed signal, and outputs a control signal to control the actuation distance of the stepper motor, thereby achieving real-time adjustment of the nozzle area. Wide-speed-range flight conditions refer to the speed range where the turbine speed is from 0 to over 100,000 rpm.

[0060] In a preferred embodiment of the air turbine power generation system for wide-speed-range flight conditions, the conical structure has a variable geometric cross-section.

[0061] In a preferred embodiment of the air turbine power generation system for wide-speed-range flight conditions, the maximum cross-sectional area of ​​the conical structure is smaller than the hollow area of ​​the nozzle.

[0062] In a preferred embodiment of the air turbine power generation system under wide-speed-range flight conditions, an electric stepper motor drives the lead screw to controllably adjust the axial relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the turbine exhaust back pressure.

[0063] In a preferred embodiment of the air turbine power generation system under wide-speed-range flight conditions, the PID controller calculates the deviation signal between the rotational speed signal measured by the sensor and the target rotational speed, the controller output signal drives the stepper motor to control the nozzle area, and real-time monitoring and adjustment form a closed-loop feedback control.

[0064] In a preferred embodiment of the air turbine power generation system for wide-speed-range flight conditions, the air turbine is a ram air turbine.

[0065] In a preferred embodiment of the air turbine power generation system for wide-speed-range flight conditions, the work capacity of the air turbine is expressed by the following formula:

[0066] (1)

[0067] in, Power for air turbines, power: W Air flow rate (kg / s), Cp (specific heat capacity of air, J / (kg·K)), T 01 and T 02 These are the total air temperatures at the turbine inlet and outlet, respectively, in K.

[0068] In the preferred embodiment of the air turbine power generation system under wide-speed-range flight conditions, the relationship between the nozzle area and the exhaust back pressure is as follows:

[0069] (2)

[0070] in, For exhaust back pressure, Pa, The nozzle flow area is expressed in square meters (m²).

[0071] The adjustment methods for air turbine power generation systems under wide-speed-range flight conditions include:

[0072] An air turbine converts the kinetic energy of air into mechanical energy.

[0073] The generator is coaxially connected to the air turbine to generate electricity by rotating based on the mechanical energy.

[0074] The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal.

[0075] The PID controller is connected to the measurement sensor to calculate the deviation between the current speed state and the target speed state based on the speed signal, and outputs a control signal to control the operating distance of the stepper motor.

[0076] An electric stepper motor drives the lead screw to actuate the conical structure to adjust the relative position of the conical structure and the nozzle, thereby changing the nozzle area and adjusting the air turbine exhaust back pressure, thus realizing real-time adjustment of the nozzle area. The PID controller provides real-time feedback to adjust the nozzle area to keep the air turbine output power and speed consistent with the target power and speed.

[0077] In a preferred embodiment of the method, the PID controller closed-loop control includes:

[0078] (3)

[0079] in, K represents the deviation between the target speed and the real-time speed. p K i and K d These are the proportional coefficient, integral coefficient, and derivative coefficient of the control parameters, respectively. For the old nozzle flow channel area, This represents the area of ​​the new nozzle flow channel.

[0080] In one embodiment, the overall structure of the compact and precisely controlled air turbine power generation system includes four key parts: an air turbine, a generator, a dynamic nozzle area adjustment device, and a real-time control and feedback module.

[0081] The air turbine and generator are arranged in a coaxial direct-drive configuration to efficiently convert high-speed rotating mechanical energy into electrical energy. The air turbine, located at the front of the system, utilizes the total pressure and temperature of the incoming airflow to convert air kinetic energy into mechanical power, driving the generator to generate electricity. The corresponding wide-speed-range self-matching ramjet air turbine structure is shown below. Figures 1 to 2 As shown, the generator is mounted close to the turbine, with a compact and reliable structure, and features miniaturization, light weight and high efficiency, making it particularly suitable for aerospace applications.

[0082] The dynamic nozzle area adjustment device is located at the turbine exhaust end and employs a variable geometry design. The mechanism is controlled by a lead screw controlled by an electric stepper motor, thereby adjusting the nozzle exit area in real time. The device has a conical structure; by changing the axial relative position of the conical structure and the nozzle, the nozzle area is altered, thus adjusting the turbine exhaust back pressure and dynamically controlling the turbine's work capacity. The specific structure is as follows: Figure 3 As shown, by adjusting the control module, such as Figure 2 The rear end of the stepper motor shaft is a lead screw, and the nozzle tail cone is fastened to the lead screw nut. It can move back and forth along the axis as the stepper motor rotates, thereby adjusting the nozzle area. The nozzle area is controlled relative to the lateral position of the nozzle, which in turn controls the airflow through the nozzle, thereby changing the turbine exhaust back pressure. This structure ensures rapid and smooth nozzle area adjustment, fast response speed, and high adjustment accuracy.

[0083] The real-time control and feedback module mainly consists of measurement sensors, a PID controller, and actuators. The actuators further include a stepper motor, a lead screw, and a slider. The real-time output speed sensor signal during motor operation is used as the core input parameter. This core input, combined with the PID controller, reduces the deviation between the measured speed and the target speed. Figure 4 The mechanism shown implements control. Specifically, in this implementation, a PID control embodiment based on the PID algorithm is used.

[0084] Suppose we need to control the generator's output power to stabilize it at the target power output speed of Vset = 30000 rpm. The current speed is V(t), and the nozzle flow area is adjusted by a PID controller.

[0085] PID control formula

[0086] PID controller output Calculated using the following formula:

[0087]

[0088] in:

[0089] ·e(t)=Vset-V(t): Deviation between target speed and real-time speed.

[0090] · : Proportional gain, used for fast error response.

[0091] · Integral gain, used to eliminate steady-state error.

[0092] · Differential gain is used to suppress system oscillations.

[0093] Implementation steps

[0094] 1. Initialize parameters

[0095] Set the target speed Vset=10000rpm.

[0096] o Initialize PID parameters: =2.0, =0.5, =1.0.

[0097] o Initialize the error integral (integral=0) and the previous error (prev_error=0).

[0098] 2. Control loop

[0099] o Within each time step Δt:

[0100] Read the current rotational speed V(t).

[0101] Calculate the current error: e(t) = Vset - V(t).

[0102] Calculate the error integral: integral = integral + e(t)·Δt.

[0103] Calculate the differential error: derivative = (e(t) - prev_error) / Δt.

[0104] Calculate the PID output:

[0105] + ·integral+ ·derivative

[0106] Adjust the nozzle flow channel area: S= .

[0107] Update the previous error: prev_error=e(t).

[0108] 3. Termination Conditions

[0109] When the rotational speed stabilizes near the target speed (e.g., |e(t)| < 100 rpm), control is stopped.

[0110] The real-time controller receives rotational speed data from the sensor, calculates the deviation between the current rotational speed and the target rotational speed, and outputs a control signal to the actuator of the nozzle adjustment device. This precisely controls the stepper motor's actuation distance, thereby achieving real-time adjustment of the nozzle area. The goal is to minimize the deviation between the measured rotational speed and the target rotational speed, meeting the control objective requirements. See the implementation scheme for details. Figure 3 The content shown is as follows. The specific implementation process is as follows: real-time measurement of turbine speed, PID control algorithm calculates the deviation signal between the measured speed and the target speed, controller output signal drives stepper motor to control nozzle area, system monitors adjustment effect in real time, forming closed-loop feedback control.

[0111] In one embodiment, this embodiment provides a control scheme for managing turbine speed and nozzle area under wide-speed-range flight conditions. The dynamic nozzle area adjustment device is located at the turbine exhaust end and employs a variable geometry design. Mechanism control is achieved through an electric stepper motor controlling a lead screw. By changing the axial relative position of the conical structure and the nozzle, the nozzle area is altered, thereby adjusting the turbine exhaust back pressure, and thus dynamically controlling the turbine's work capacity. The specific structure is as follows: Figure 1 As shown, the nozzle area is controlled by adjusting the lateral position of the control module relative to the nozzle, thereby controlling the airflow through the nozzle and thus changing the turbine exhaust back pressure. This structure ensures rapid and smooth nozzle area adjustment, fast response, and high adjustment accuracy.

[0112] The working principle of this invention is as follows:

[0113] The turbine output work capacity is precisely controlled by adjusting the nozzle area of ​​the turbine. The turbine speed is measured in real time, the PID control algorithm calculates the deviation signal between the measured speed and the target speed, and the controller output signal drives the stepper motor to control the nozzle area. The system monitors the adjustment effect in real time and forms a closed-loop feedback control.

[0114] In the principle of nozzle area control, such as Figures 1 to 2 The work capacity of the air turbine shown can be expressed by the following formula:

[0115] (1)

[0116] in, Power output of the turbine (power: W) Let Cp be the airflow rate (kg / s), Cp be the specific heat capacity of air (J / (kg·K)), and T01 and T02 be the total air temperatures at the turbine inlet and outlet (K), respectively. Based on the aforementioned scheme, the exhaust back pressure in this project is achieved by adjusting the nozzle area, and the relationship between the nozzle area and the exhaust back pressure can be written as:

[0117] (2)

[0118] in, Let be the nozzle flow area. As shown in the formula, the nozzle area is adjusted in real time by the PID controller to keep the turbine output power and speed consistent with the target power and speed.

[0119] Methods for controlling nozzle area

[0120] To achieve the control objective shown in the equation, this project employs a typical PID control algorithm. By measuring the deviation between the real-time rotational speed and the target rotational speed, the increment of the nozzle area is calculated, thereby obtaining the control quantity for the actuation distance of the lead screw motor. This achieves closed-loop control of the nozzle area. The logic block diagram for its implementation can be found in [reference needed]. Figure 4 As shown. The closed-loop control algorithm formula for the nozzle area can be described as follows:

[0121] (3)

[0122] in, K represents the deviation between the target speed and the real-time speed. p K i and K d These are the proportional coefficient, integral coefficient, and derivative coefficient of the control parameters. After obtaining these parameters through experiments, the system response is ensured to be fast and stable. Substituting the results of the equation into the equation allows for the control of the air turbine's work capacity, thereby achieving rapid and precise control of turbine speed and power.

[0123] This invention directly converts kinetic energy into mechanical energy using an air turbine, which then drives a generator via a coaxial connection. This reduces energy conversion losses and improves overall system efficiency. Furthermore, its compact design saves space, making it particularly suitable for aerospace applications. Employing a conical structure and a lead screw mechanism, the position of the conical structure is controlled by an electric stepper motor to change the nozzle area, thereby adjusting the exhaust back pressure of the air turbine. This device allows for real-time adjustment of the nozzle area to optimize the air turbine's performance at different speeds. Precise control of the exhaust back pressure enables effective management of the turbine's output power, ensuring efficient system operation across a wide range of flight speeds. A measurement sensor acquires the generator's speed signal; a PID controller calculates the deviation based on this signal and outputs a control signal to the stepper motor, adjusting the nozzle area accordingly. The PID controller responds quickly to speed changes, precisely controlling the nozzle area through a closed-loop feedback mechanism to maintain the target speed and power output, improving system stability and response speed. This optimizes performance under different flight conditions, enabling the air turbine power generation system to maintain a high-efficiency and stable power supply in a wide-speed-range flight environment.

[0124] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this application to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. An air turbine power generation system for wide-speed-range flight conditions, characterized in that, It includes, An air turbine converts the kinetic energy of air into mechanical energy. An air turbine includes an air intake at the front and an air nozzle at the rear. A generator, coaxially connected to the air turbine, generates electricity by rotating based on the mechanical energy. A dynamic nozzle area adjustment device, located at the nozzle end, includes, The conical structure is movable relative to the nozzle position of the air turbine. A lead screw, connected to the conical structure, adjusts the relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the exhaust back pressure of the air turbine. An electric stepper motor, which drives the lead screw; A real-time control and feedback module, connected to the generator and the dynamic nozzle area adjustment device, includes, The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal. The PID controller is connected to the measurement sensor to calculate the deviation between the current speed state and the target speed state based on the speed signal, and outputs a control signal to control the actuation distance of the stepper motor, thereby realizing real-time adjustment of the nozzle area.

2. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, Preferably, the tapered structure has a variable geometric cross-section.

3. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, The maximum cross-sectional area of ​​the conical structure is smaller than the hollow area of ​​the nozzle.

4. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, An electric stepper motor drives the lead screw to controllably adjust the axial relative position of the conical structure and the nozzle to change the nozzle area and thus adjust the turbine exhaust back pressure.

5. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, The PID controller calculates the deviation between the rotational speed signal measured by the sensor and the target rotational speed, and the controller output signal drives the stepper motor to control the nozzle area, forming a closed-loop feedback control through real-time monitoring and adjustment.

6. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, The air turbine is a ram air turbine.

7. The air turbine power generation system under wide-speed-range flight conditions as described in claim 1, characterized in that, The work capacity of the air turbine is expressed by the following formula: （1） in, Power for air turbines, power: W Air flow rate (kg / s), Cp (specific heat capacity of air, J / (kg·K)), T 01 and T 02 These are the total air temperatures at the turbine inlet and outlet, respectively, in K.

8. The air turbine power generation system under wide-speed-range flight conditions as described in claim 7, characterized in that, The relationship between nozzle area and exhaust back pressure is as follows: （2） in, For exhaust back pressure, Pa, The nozzle flow area is expressed in square meters (m²).

9. The adjustment method for an air turbine power generation system under wide-speed-range flight conditions as described in any one of claims 1-8, characterized in that, It includes, An air turbine converts the kinetic energy of air into mechanical energy. The generator is coaxially connected to the air turbine to generate electricity by rotating based on the mechanical energy. The measuring sensor measures the generator's rotational speed to obtain a real-time speed signal. The PID controller is connected to the measurement sensor to calculate the deviation between the current speed state and the target speed state based on the speed signal, and outputs a control signal to control the operating distance of the stepper motor. An electric stepper motor drives the lead screw to actuate the conical structure to adjust the relative position of the conical structure and the nozzle, thereby changing the nozzle area and adjusting the air turbine exhaust back pressure, thus realizing real-time adjustment of the nozzle area. The PID controller provides real-time feedback to adjust the nozzle area to keep the air turbine output power and speed consistent with the target power and speed.

10. The method as described in claim 9, characterized in that, PID controller closed-loop control includes: （3） in, K represents the deviation between the target speed and the real-time speed. p , K i and K d These are the proportional coefficient, integral coefficient, and derivative coefficient of the control parameters, respectively. For the old nozzle flow channel area, This represents the area of ​​the new nozzle flow channel.

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