Rotary detonation engine oil injection strategy control method and device and computer storage medium

Abstract

The invention discloses a rotary detonation engine oil injection strategy control method which comprises the following steps: acquiring a pressure signal and a temperature signal of an annular combustion chamber of a rotary detonation engine, and carrying out working condition division on an engine operation state: under a stable detonation working condition, linearly adjusting the oil injection quantity to an optimal detonation wave working interval; and under the unstable detonation working condition, the fuel injection quantity is adjusted based on the ratio of the detonation wave propagation speed to the detonation wave theoretical propagation speed, an oxidizing agent is injected according to the oxidizing agent flow determined by the optimal fuel injection quantity and oxidizing agent flow ratio till the engine reaches the stable detonation working condition, or the fuel injection quantity and the oxidizing agent flow are linearly adjusted for multiple times. The invention further discloses a corresponding control device and a computer storage medium. It is guaranteed that the engine has stable detonation combustion performance, the unstable oscillation phenomenon of detonation waves is restrained, and the combustion efficiency of the rotary detonation engine is improved.

Description

Technical Field

[0001] This invention relates to a method for controlling the fuel injection strategy of a rotating detonation engine, and more particularly to a method, apparatus, and computer storage medium for controlling the fuel injection strategy of a rotating detonation engine. Background Technology

[0002] Rotating detonation engines are novel propulsion devices based on isochoric combustion theory, possessing significant application potential in aerospace, energy, and other fields. However, the fuel injection control technology of rotating detonation engines has certain shortcomings. Compared to traditional engines, one of the key advantages of rotating detonation engines is the ability to generate detonation waves within the combustion chamber, which can produce greater power. However, current fuel injection techniques struggle to precisely match the propagation speed, pressure, and temperature of the detonation waves within the combustion chamber, making it difficult to maintain stable detonation waves. Furthermore, the uneven fuel distribution within the annular combustion chamber of rotating detonation engines results in poor uniformity of fuel-oxidant mixing, leading to localized fuel richness or lack of fuel, which reduces combustion efficiency. Summary of the Invention

[0003] To address the shortcomings of the prior art, this invention provides a method for controlling the fuel injection strategy of a rotating detonation engine, aiming to improve the uniformity and stability of the detonation wave within the combustion chamber and enhance combustion efficiency. This invention also provides a device for controlling the fuel injection strategy of a rotating detonation engine and a computer storage medium.

[0004] The technical solution of this invention is as follows: A method for controlling the fuel injection strategy of a rotating detonation engine, comprising the following steps:

[0005] The pressure and temperature signals of the annular combustion chamber of the rotating detonation engine are collected. The combustion chamber pressure is obtained based on the pressure signal and the propagation speed of the detonation wave is calculated. The combustion chamber temperature is obtained based on the temperature signal.

[0006] The engine operating conditions are divided into two categories based on combustion chamber pressure, detonation wave propagation speed and combustion chamber temperature: stable detonation condition and unstable detonation condition.

[0007] Under stable detonation conditions, the optimal operating range of the detonation wave is set. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal operating range of the detonation wave, the fuel injection quantity is linearly adjusted several times until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0008] Under unstable detonation conditions, a first proportional threshold is set. When the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold, the fuel injection quantity is adjusted based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed. Oxidizer is injected at the oxidizer flow rate determined based on the optimal fuel injection quantity-oxidizer flow rate ratio until the engine reaches stable detonation conditions. When the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​is greater than the first proportional threshold, the fuel injection quantity and oxidizer flow rate are linearly adjusted several times until the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold.

[0009] Furthermore, the operating conditions include a start-up condition and a shutdown condition. In the start-up condition, fuel and oxidizer are injected at the set initial values ​​of fuel injection quantity and oxidizer flow rate. In the shutdown condition, fuel and oxidizer injection is stopped.

[0010] Furthermore, a second proportional threshold is set. When the deviation ratio of the combustion chamber pressure and the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is less than or equal to the second proportional threshold, it is a stable detonation condition. When the deviation ratio of the combustion chamber pressure or the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is greater than the second proportional threshold, it is an unstable detonation condition. The lower limit of the threshold proportional range is the first threshold.

[0011] Furthermore, the first ratio threshold is 15%, and the second ratio threshold is 10%.

[0012] Furthermore, the linear adjustment of the fuel injection quantity until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave includes:

[0013] When the propagation speed of the detonation wave or the combustion chamber pressure is lower than the lower limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly increased until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0014] When the propagation speed of the detonation wave or the combustion chamber pressure is higher than the upper limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly reduced until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0015] Furthermore, the adjustment of the fuel injection quantity based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed is performed according to the following formula:

[0016] ,

[0017] In the formula, This indicates the adjusted fuel injection quantity. This indicates the current fuel injection quantity. This represents the correction factor. This indicates the current propagation speed of the detonation wave. This represents the theoretical propagation speed of the detonation wave.

[0018] Furthermore, the optimal fuel injection quantity to oxidizer flow rate ratio is the ratio of fuel injection quantity to oxidizer flow rate that can generate detonation wave and obtain maximum thrust.

[0019] Furthermore, the linear adjustment of the fuel injection quantity varies by a range of 1% to 2%, and the linear adjustment of the oxidant flow rate varies by a range of 1% to 2%.

[0020] The present invention also provides a rotary detonation engine fuel injection strategy control device, comprising:

[0021] The data acquisition module is used to collect pressure and temperature signals from the annular combustion chamber of the rotating detonation engine, obtain the combustion chamber pressure based on the pressure signal and calculate the propagation speed of the detonation wave, and obtain the combustion chamber temperature based on the temperature signal.

[0022] The operating condition discrimination module is used to classify the engine operating state into operating conditions based on combustion chamber pressure, detonation wave propagation speed and combustion chamber temperature. The operating conditions include: stable detonation operating conditions and unstable detonation operating conditions.

[0023] The first adjustment module is used to set the optimal working range of the detonation wave under stable detonation conditions. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal working range of the detonation wave, the injection quantity is linearly adjusted several times until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal working range of the detonation wave.

[0024] And, a second adjustment module, used to, under unstable detonation conditions, set a first proportional threshold, and when the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold, adjust the fuel injection quantity based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed, and inject oxidizer at the oxidizer flow rate determined based on the optimal fuel injection quantity-oxidizer flow rate ratio until the engine reaches stable detonation conditions; when the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is greater than the first proportional threshold, perform several linear adjustments to the fuel injection quantity and oxidizer flow rate until the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold.

[0025] The present invention also provides a computer storage medium storing a computer program thereon, wherein when the computer program is executed by a processor, the above-described rotary detonation engine fuel injection strategy control method is implemented.

[0026] The advantages of the technical solution provided by this invention are as follows:

[0027] This invention decomposes the engine operation process into multiple different operating conditions. Under different operating conditions, it focuses on improving the detonation wave quality in the combustion chamber of a rotating detonation engine by rationally adjusting the injection method. During the start-up phase, a zoned injection method is used to quickly achieve uniform detonation wave oscillation conditions. In stable detonation conditions, a fine-tuning method ensures that the detonation wave in the combustion chamber is always in an optimal operating state. In unstable detonation conditions, a dynamic fuel injection adjustment mechanism is employed. The ECU stores the optimal equivalence ratio parameters and corresponding detonation wave characteristics (temperature, pressure, and propagation velocity). Intelligent optimization simulation results guide the fuel injection quantity and oxidizer content to quickly return the combustion chamber to stable detonation conditions. When large-amplitude unstable oscillations occur, small-amplitude, multiple linear adjustments to the fuel injection quantity and oxidizer flow rate are made so that the deviation ratio of the detonation wave propagation velocity and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​is less than or equal to 15%, returning to step A of the unstable detonation condition. The adjustment in step A is then used to return to stable detonation conditions. Through multiple and comprehensive control measures, the detonation wave in the combustion chamber can be continuously and stably propagated, ensuring stable detonation combustion performance of the engine, suppressing unstable oscillations of the detonation wave, reducing local heat load in the combustion chamber, and improving the combustion efficiency of the rotating detonation engine. Attached Figure Description

[0028] Figure 1 This is a flowchart illustrating the rotary detonation engine fuel injection strategy control method according to an embodiment of the present invention.

[0029] Figure 2 This describes a change in operating condition of a rotating detonation engine controlled by the fuel injection strategy control method of the rotating detonation engine according to an embodiment of the present invention. Detailed Implementation

[0030] The present invention will be further described below with reference to embodiments. It should be understood that these embodiments are only for illustrating the present invention and are not intended to limit the scope of the present invention. After reading this description, any modifications of this description in various equivalent forms by those skilled in the art will fall within the scope defined by the appended claims.

[0031] The rotary detonation engine fuel injection strategy control device in this embodiment includes:

[0032] The data acquisition module includes a sensor section, with pressure and temperature sensors arranged on the wall of the annular combustion chamber of the rotating detonation engine. The pressure sensors collect pressure signals from the annular combustion chamber, capturing the peak pressure of the detonation wave. The temperature sensors collect temperature signals from the temperature distribution within the combustion chamber. Based on the pressure signals, the combustion chamber pressure is obtained, and the propagation speed of the detonation wave is calculated. The propagation speed of the detonation wave can be obtained by dividing the distance from the pressure peak measured by the pressure sensor by the propagation time. The combustion chamber temperature is then calculated based on the temperature signals.

[0033] The operating condition discrimination module is used to classify the engine operating state into operating conditions based on combustion chamber pressure, detonation wave propagation speed, and combustion chamber temperature. The operating conditions include: stable detonation operating conditions and unstable detonation operating conditions. In this embodiment, it also includes start-up operating conditions and shutdown operating conditions. In a specific embodiment, the module sets a second proportional threshold and determines whether the operating condition belongs to stable detonation operating conditions or unstable detonation operating conditions based on the relationship between the ratio of the deviation of combustion chamber pressure and detonation wave propagation speed from the theoretical Chapman-Jouguet condition value and the second proportional threshold.

[0034] The first adjustment module is used to set the optimal operating range of the detonation wave under stable detonation conditions. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal operating range of the detonation wave, the injection quantity is linearly adjusted until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0035] And, the second adjustment module is used to set a first proportional threshold under unstable detonation conditions. When the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold, the fuel injection quantity is adjusted based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed. Oxidizer is injected based on the oxidizer flow rate determined by the ratio of the optimal fuel injection quantity to the oxidizer flow rate until the engine reaches a stable detonation condition. When the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​is greater than the first proportional threshold, the fuel injection quantity and oxidizer flow rate are linearly adjusted several times until the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold.

[0036] Please combine Figure 1 and Figure 2 As shown, the method for controlling the injection strategy of a rotating detonation engine based on the above-mentioned rotating detonation engine injection strategy control device includes the following steps:

[0037] (1) Collect pressure and temperature signals of the annular combustion chamber of the rotating detonation engine, obtain the combustion chamber pressure based on the pressure signal and calculate the propagation speed of the detonation wave, and obtain the combustion chamber temperature based on the temperature signal.

[0038] (2) The engine operating conditions are divided into working conditions based on combustion chamber pressure, detonation wave propagation speed and combustion chamber temperature. The working conditions include: start-up working condition, stable detonation working condition, unstable detonation working condition and shutdown working condition.

[0039] When the combustion chamber temperature gradually increases from the ambient temperature, it is determined to be a start-up condition, and step (3) is performed.

[0040] When the deviation ratio of the combustion chamber pressure and the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is less than or equal to the second proportional threshold, it is considered a stable detonation condition. This second proportional threshold is set to 10%. At this time, the fluctuation frequency of the pressure and the propagation velocity of the detonation wave in the combustion chamber is stable and within the detonation characteristic frequency range, and step (4) is performed.

[0041] When the deviation ratio of the combustion chamber pressure and the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is greater than the second proportional threshold (10%), it indicates that the pressure or the propagation velocity of the detonation wave in the combustion chamber fluctuates significantly, which is an unstable detonation condition, and step (5) is performed.

[0042] It should be noted that the combustion chamber pressure and the propagation speed of the detonation wave may be greater than or less than the theoretical Chapman-Jouguet condition values. Therefore, the aforementioned deviation refers to the absolute value of the difference between the combustion chamber pressure and the propagation speed of the detonation wave and the theoretical Chapman-Jouguet condition values, and the deviation ratio refers to the ratio of this deviation to the theoretical Chapman-Jouguet condition value.

[0043] When the average pressure in the combustion chamber drops to the level of the exhaust pressure, it is determined to be a flameout condition, and step (6) is performed.

[0044] (3) Under startup conditions, fuel and oxidizer are injected at the set initial values ​​of fuel injection quantity and oxidizer flow rate. That is, a zoned injection strategy is adopted. The annular combustion chamber is divided into multiple independent injection zones, and fuel and oxidizer are injected in a uniform injection manner to quickly ignite the fuel mixture in the combustion chamber and form an initial detonation wave. When the pressure and velocity in the combustion chamber meet the conditions for uniform detonation wave initiation, the detonation wave begins to propagate in the combustion chamber. The nozzle continuously injects a mixture of fuel and oxidizer. This mixture is continuously ignited by the propagating detonation wave, so that the detonation wave can propagate continuously and stably in the annular combustion chamber. The operating conditions of the combustion chamber are continuously monitored and judged. When it is judged to be a stable detonation condition, step (4) is executed; when it is judged to be an unstable detonation condition, step (5) is executed.

[0045] (4) Under stable detonation conditions, this stage is the fine-tuning and optimization stage. After the detonation wave starts to vibrate uniformly, it propagates continuously in the combustion chamber with a uniform wave speed and a stable wave surface. The engine enters the stable detonation condition, and the detonation wave fills the entire combustion chamber. It is necessary to continuously adjust the fuel injection quantity to keep the detonation wave in the optimal operating range. Specifically, the optimal operating range of the detonation wave is set. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal operating range of the detonation wave, the fuel injection quantity is linearly adjusted until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0046] It includes two layers of adjustment. When the propagation speed of the detonation wave or the combustion chamber pressure is lower than the lower limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly increased until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0047] When the propagation speed of the detonation wave or the combustion chamber pressure is higher than the upper limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly reduced until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

[0048] This explanation uses a simulation model as an example; the values ​​may vary for different engines. When the detonation wave propagation velocity or combustion chamber pressure deviates from the theoretical Chapman-Jouguet condition value by -10% to -6% (in the low concentration range), it indicates weak detonation. With the oxidizer flow rate remaining constant, the fuel injection quantity is linearly increased by 1% to 2% to increase the mixture concentration. When the detonation wave propagation velocity or combustion chamber pressure deviates from the theoretical Chapman-Jouguet condition value by 6% to 10% (in the high concentration range), with the oxidizer flow rate remaining constant, the fuel injection quantity is linearly decreased by 1% to 2% to decrease the mixture concentration. Then, sensors monitor the pressure and propagation velocity to confirm whether the wave state has returned to the optimal operating range for detonation. The optimal operating range for detonation is when the deviation of the detonation wave propagation velocity and combustion chamber pressure from the theoretical Chapman-Jouguet condition value is between -6% and 6%. If it returns to the optimal operating range, the fuel injection quantity and oxidizer flow rate remain at their current adjusted state; otherwise, multiple fine adjustments are made by linearly increasing or decreasing the quantity.

[0049] (5) Under unstable detonation conditions, start the unstable detonation condition fuel injection mechanism.

[0050] Specifically, a first proportional threshold is set to represent the deviation of the combustion chamber pressure and the propagation speed of the detonation wave from the theoretical Chapman-Jouguet condition values. In one specific embodiment, this first proportional threshold is 15%, and it is controlled according to two cases, A and B.

[0051] A. When the deviation of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is less than or equal to the first proportional threshold (15%), the decision to increase or decrease the fuel injection quantity is made based on the detonation wave propagation speed and combustion chamber pressure. Specifically, when the deviation of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is between -15% and -10% (less than the lower limit of the low concentration range), the fuel supply is significantly insufficient or the fuel and air mixture is uneven. At this time, the detonation wave propagation is hindered, and the engine performance is significantly reduced. The fuel injection quantity is increased based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed to improve the detonation wave quality. When the deviation of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is between 10% and 15% (greater than the upper limit of the high concentration range), the fuel injection is too rich, resulting in an excessively strong detonation wave. The fuel injection quantity is reduced based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed to improve the detonation wave quality.

[0052] The formula for calculating the increase or decrease in fuel injection quantity based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed is as follows:

[0053] ,

[0054] In the formula, This indicates the adjusted fuel injection quantity. This indicates the current fuel injection quantity. This represents the correction factor. This indicates the current propagation speed of the detonation wave. This represents the theoretical propagation speed of the detonation wave.

[0055] While adjusting the fuel injection quantity, oxidizer is injected at a flow rate determined based on the optimal fuel injection quantity-oxidizer flow rate ratio until the engine reaches stable detonation conditions. This process allows the combustion chamber to quickly restore stable combustion, reducing engine damage and the occurrence of knocking.

[0056] The optimal fuel injection quantity-oxidizer flow rate ratio is defined as the optimal equivalence ratio, which can be obtained through numerical calculation. As a preferred embodiment, this embodiment uses an optimization model for calculation. Specifically, in the CFD simulation model, given the corresponding fuel injection quantity and oxidizer content (i.e., the equivalence ratio), the CE / SE method is used to calculate the temperature, pressure, and detonation wave propagation velocity within the combustion chamber. The detonation wave situation within the combustion chamber is observed; cases that can generate detonation waves are set to 0, and cases that cannot generate detonation waves are set to 1. Then, a particle swarm optimization algorithm is used, with the fuel injection quantity and oxidizer content as variable optimization parameters. Whether detonation waves can be generated and the corresponding thrust are used as dual optimization objectives. Through optimization calculation, the equivalence ratio with the largest thrust among the combinations that can generate detonation waves is found as the optimal solution. This optimal solution is the optimal fuel injection quantity-oxidizer flow rate ratio.

[0057] B. When the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is greater than the first proportional threshold, i.e., greater than 15%, the detonation wave propagation speed or pressure will oscillate violently and significantly. Linearly adjust the fuel injection quantity and oxidizer flow rate.

[0058] Specifically, first increase the fuel injection quantity and oxidizer by 1%–2%. Then, monitor the pressure and propagation speed using sensors to confirm whether the detonation wave state has returned to condition A. If the detonation wave is below its optimal operating range (i.e., the deviation of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is less than -15%), increase the fuel injection quantity and oxidizer by 1%–2%. If the detonation wave is above its optimal operating range (i.e., the deviation of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is greater than 15%), decrease the fuel injection quantity and oxidizer by 1%–2%. Repeat these small adjustments until the deviation ratio of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition value is less than or equal to the first proportional threshold, then return to condition A for control.

[0059] (6) When the engine is confirmed to be in a shutdown condition, the high-speed solenoid valve is controlled in time to cut off the supply of fuel and oxidizer, stop the injection of fuel and oxidizer, and the engine stops working.

[0060] It should be noted that the specific methods of the above embodiments can form a computer program product. Therefore, the computer program product implemented in this application can be stored on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.). In addition, this application can be implemented in hardware, software, or a combination of hardware and software, or it can be configured as a computer device including at least one processor and a memory, wherein the memory stores the computer program that implements the above process steps, and the processor is used to execute the computer program on the memory to perform the method steps of the above embodiments.

Claims

1. A method for controlling the fuel injection strategy of a rotating detonation engine, characterized in that, Includes the following steps: Includes the following steps: The pressure and temperature signals of the annular combustion chamber of the rotating detonation engine are collected. The combustion chamber pressure is obtained based on the pressure signal and the propagation speed of the detonation wave is calculated. The combustion chamber temperature is obtained based on the temperature signal. The engine operating conditions are divided into two categories based on combustion chamber pressure, detonation wave propagation speed and combustion chamber temperature: stable detonation condition and unstable detonation condition. Under stable detonation conditions, the optimal operating range of the detonation wave is set. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal operating range of the detonation wave, the fuel injection quantity is linearly adjusted several times until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave. Under unstable detonation conditions, a first proportional threshold is set. When the deviation ratio of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition value is less than or equal to the first proportional threshold, the fuel injection quantity is adjusted based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed. Oxidizer is injected at the oxidizer flow rate determined based on the optimal fuel injection quantity-oxidizer flow rate ratio until the engine reaches stable detonation conditions. When the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is greater than the first proportional threshold, the fuel injection quantity and oxidizer flow rate are linearly adjusted several times until the deviation ratio of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition value is less than or equal to the first proportional threshold.

2. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, The operating conditions include a start-up condition and a shutdown condition. In the start-up condition, fuel and oxidizer are injected at the set initial values ​​of fuel injection quantity and oxidizer flow rate. In the shutdown condition, fuel and oxidizer injection is stopped.

3. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, A second proportional threshold is set. When the deviation ratio of the combustion chamber pressure and the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is less than or equal to the second proportional threshold, it is a stable detonation condition. When the deviation ratio of the combustion chamber pressure or the propagation velocity of the detonation wave from the theoretical Chapman-Jouguet condition value is greater than the second proportional threshold, it is an unstable detonation condition. The lower limit of the threshold proportional range is the first threshold.

4. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 3, characterized in that, The first ratio threshold is 15%, and the second ratio threshold is 10%.

5. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, The linear adjustment of the fuel injection quantity until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave includes: When the propagation speed of the detonation wave or the combustion chamber pressure is lower than the lower limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly increased until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave. When the propagation speed of the detonation wave or the combustion chamber pressure is higher than the upper limit of the optimal operating range of the detonation wave, the fuel injection quantity is linearly reduced until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal operating range of the detonation wave.

6. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, The adjustment of the fuel injection quantity based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed is performed according to the following formula: ， In the formula, This indicates the adjusted fuel injection quantity. This indicates the current fuel injection quantity. This represents the correction factor. This indicates the current propagation speed of the detonation wave. This represents the theoretical propagation speed of the detonation wave.

7. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, The optimal fuel injection quantity to oxidizer flow rate ratio is the ratio of fuel injection quantity to oxidizer flow rate that generates detonation wave and obtains maximum thrust.

8. The method for controlling the fuel injection strategy of a rotating detonation engine according to claim 1, characterized in that, The linear adjustment of the fuel injection quantity varies by a range of 1% to 2%, and the linear adjustment of the oxidant flow rate varies by a range of 1% to 2%.

9. A fuel injection strategy control device for a rotating detonation engine, characterized in that, include: The data acquisition module is used to collect pressure and temperature signals from the annular combustion chamber of the rotating detonation engine, obtain the combustion chamber pressure based on the pressure signal and calculate the propagation speed of the detonation wave, and obtain the combustion chamber temperature based on the temperature signal. The operating condition discrimination module is used to classify the engine operating state into operating conditions based on combustion chamber pressure, detonation wave propagation speed and combustion chamber temperature. The operating conditions include: stable detonation operating conditions and unstable detonation operating conditions. The first adjustment module is used to set the optimal working range of the detonation wave under stable detonation conditions. When the propagation speed of the detonation wave or the combustion chamber pressure exceeds the optimal working range of the detonation wave, the injection quantity is linearly adjusted several times until the propagation speed of the detonation wave and the combustion chamber pressure reach the optimal working range of the detonation wave. And, a second adjustment module, used to, under unstable detonation conditions, set a first proportional threshold, and when the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold, adjust the fuel injection quantity based on the ratio of the detonation wave propagation speed to the theoretical detonation wave propagation speed, and inject oxidizer at an oxidizer flow rate determined based on the optimal fuel injection quantity-oxidizer flow rate ratio until the engine reaches stable detonation conditions; when the deviation ratio of the detonation wave propagation speed or combustion chamber pressure from the theoretical Chapman-Jouguet condition value is greater than the first proportional threshold, perform several linear adjustments to the fuel injection quantity and oxidizer flow rate until the deviation ratios of the detonation wave propagation speed and combustion chamber pressure from the theoretical Chapman-Jouguet condition values ​​are both less than or equal to the first proportional threshold.

10. A computer storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the rotary detonation engine fuel injection strategy control method according to any one of claims 1 to 8.

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