487 results about "Engine knocking" patented technology

The invention discloses a high-horsepower fuel oil dune buggy gas supply assembly, and belongs to the technical field of internal combustion engine gas inlet systems, the high-horsepower fuel oil dune buggy gas supply assembly comprises an outer cover, a sealed space is limited in the outer cover, and the outer cover is provided with a gas inlet head and a gas exhaust head; the inner container is arranged in the sealed space of the outer cover, and the inner container comprises a first inner shell and a second inner shell; and the pumping piece is arranged in the first inner shell and used for pressurizing air and pumping the air to the second inner shell. Through optimization of the overall structure, high-pressure airflow is generated through the pumping piece, air is physically separated into cold air and hot air in the vortex chamber, and cold air far lower than the environment temperature can be actively provided for an engine without any refrigerant and a complex compressor; the problems that the fuel oil dune buggy is low in inflation efficiency and high in detonation risk in a high-temperature environment are solved, strong, stable and continuous power is output, and power attenuation of the high-horsepower fuel oil dune buggy caused by high-temperature protection of an engine is relieved.

The embodiment of the invention provides an engine control method and device, a vehicle and a storage medium, and the method comprises the steps that the running state of the vehicle is monitored, a state monitoring result is obtained, and the state monitoring result is used for representing whether the knocking phenomenon occurs in the current running state of the vehicle or not; in response to the state monitoring result that the knocking phenomenon occurs in the current running state of the vehicle, the fuel quality of fuel currently used by the vehicle, the current running parameters and running state parameters of an engine and a first control parameter are obtained, the fuel quality is used for reflecting the combustion capacity of the fuel in multiple dimensions, and the fuel quality is used for reflecting the combustion capacity of the fuel in multiple dimensions; the running state parameters are used for reflecting running conditions of the engine; adjusting a first control parameter currently used by the engine based on the fuel oil quality and the operation parameter operation state parameter to obtain a target control parameter; and controlling the engine to operate based on the target control parameter. The technical problem that in the related technology, the stability of controlling operation of the engine is poor is solved.

The invention provides a methanol-diesel dual-fuel engine knock control method, relates to the technical field of engine control, and aims to implement multi-cylinder independent control, realize differentiated control of each cylinder, independently collect and filter knock sensor signals of each cylinder, and improve the reliability of the engine knock control. Extracting the detonation characteristic intensity of each cylinder by using a fast Fourier transform and time domain integral analysis method; judging which level of response strategy threshold range the knock characteristic intensity is located in, and executing a response strategy of a matching level; and establishing an adaptive learning mechanism, and optimizing the threshold value of each level of response strategy. The method has the advantages that the knocking detection accuracy is remarkably improved, the optimal control boundary under different methanol mixing proportions is achieved through a self-adaptive learning mechanism, the problem of inconsistency of cylinders under the dual-fuel working condition is solved by adopting a differentiated cylinder control strategy, the engine safety is guaranteed, and the reliability of the engine is improved. Torque output under the full-load working condition is improved, the failure rate of knock-related parts is reduced, the service life of an engine is prolonged, and pollutant emission is reduced.

The invention relates to the technical field of vehicle supercharging control, in particular to a supercharger performance control method and device of a hybrid power system and a vehicle. The method comprises the steps that a plateau ignition angle MAP table and a plateau air inlet VVT angle MAP table of the vehicle in a high altitude mode are obtained; a plateau air inlet VVT angle MAP table is corrected, meanwhile, the knocking thrust angle condition of the hybrid power system is checked, and the maximum performance of a current supercharger is determined so as to correct the exhaust gas recirculation rate; calibration limits are generated based on at least part of detonation, preignition, the highest rotating speed of turbine hardware, the combustion center of gravity, the combustion boundary and the HCU series-parallel economic line, and comprehensive test check is conducted based on the calibration limits so that performance optimization can be conducted on the engine. Therefore, the problems that in the related technology, due to the fact that the performance and the response speed of the supercharger in the plateau area are reduced, the actual torque of an engine cannot meet the requirement of a hybrid power system, and then the series-parallel connection switching and electricity protection capacity of the vehicle is affected are solved.

The invention provides a conventional and detonation dual-mode spontaneous combustion propellant space engine, and belongs to the technical field of spacecraft propulsion systems. The conventional and detonation dual-mode spontaneous combustion propellant space engine comprises a propellant control valve, an engine head, an engine body and an external excitation device. The propellant control valve, the engine head part and the engine body part are connected in sequence, and the external excitation device is embedded into the outer wall of the engine body part; according to the invention, by adopting an external excitation mode, the space engine in a detonation mode is realized; by means of a selective excitation mode, the space engine capable of selecting a conventional mode and a detonation mode is achieved. The detonation combustion is applied to the spontaneous combustion propellant space engine, the upper limit of the combustion efficiency of the space engine of a constant-pressure thermodynamic cycle is broken through, and the combustion efficiency is further improved on the original basis.

The invention relates to a control method based on low-temperature cold start of a heuristic integrated heavy oil engine, and relates to the field of heuristic integrated heavy oil engines. According to the technical scheme, the preheating plug in the cylinder is combined with the air inlet heating grid, synchronous control is achieved through the same relay, the electric energy requirements of synchronous work and dragging and preheating are met by means of sufficient battery capacity, and the device can be adapted to the ultra-low temperature of-40 DEG C or below and the plateau environment of 4700 m or above; three starting attempts are supported by single-time power-on through intelligent preheating control logic, the pre-preheating and heating-while-dragging processes are executed each time, fault information is automatically uploaded after starting fails, frequent power-off is not needed, and the starting efficiency is improved. And moreover, through an intermittent post-preheating and intake synchronous heating strategy, the combustion stability in the cylinder is effectively improved, the rotating speed fluctuation time is shortened, and mechanical damage caused by flameout and unstable idling after starting is avoided. In addition, the dragging rotating speed control based on the torque can prevent the problem of engine damage caused by accidental detonation after multiple starting failures.

The invention discloses a rotating detonation afterburner based on centrifugal nozzle discrete injection, and belongs to the technical field of detonation propulsion. The combustion chamber comprises a gas collecting cavity, an injection unit, a centrifugal nozzle, an outer ring and an inner column, wherein an annular detonation combustion chamber is formed between the inner wall surface of the outer ring and the outer wall surface of the inner column. The centrifugal nozzles are uniformly arranged at the intersection of the gas collection cavity and the injection unit in the circumferential direction to realize primary atomization of the fuel oil; the air is accelerated by the injection unit from the air collection cavity and then is mixed with the atomized fuel oil, secondary atomization is achieved, the particle size of liquid drops is remarkably reduced, and the fuel activity and mixing uniformity are improved. The injection unit adopts a Laval nozzle profile, air is accelerated to supersonic speed in the injection unit, and pressure of a combustion chamber is prevented from being transmitted forwards. The rotary detonation engine is suitable for the high-temperature low-oxygen environment, supports the annular combustion chamber configuration and the empty cylinder combustion chamber configuration, can achieve stable rotary detonation detonation and propagation of liquid fuel and air, and provides technical support for engineering application of the rotary detonation engine.

A fuel control system for a turbine engine includes a mixer for mixing first and second fuels to obtain a fuel blend, a fuel blend analyzer, a combustor operable with the fuel blend, and a knock sensor coupled to the combustor. The system also includes a controller configured to: receive a measurement indicative of a composition of the fuel blend; compare the fuel blend measurement to an operational model of the combustor; determine, based on the comparison, a predicted combustion condition in the combustor associated with the fuel blend measurement; control, based on the predicted combustion condition, flow of the first fuel or the second fuel; receive a combustion signal indicative of combustion behavior in the combustor; compare the predicted combustion condition to the combustion signal; and update the operational model if the predicted combustion condition does not match the indicated combustion behavior.

The invention discloses a cooperative control method for the air-fuel ratio, the injection opportunity and the cooling liquid temperature of a hydrogen fuel engine. The cooperative control method comprises the steps that S1, operation condition parameters and combustion state parameters of the hydrogen fuel engine are monitored; s2, based on the operation condition parameters, adaptively determining a target air-fuel ratio, a fuel injection opportunity and a cooling liquid temperature through a preset control strategy; s3, the combustion state and the engine operation condition are evaluated in real time through a closed-loop feedback control system, and the following cooperative adjustment is executed: the hydrogen supply amount is adjusted to maintain the target air-fuel ratio; the hydrogen injection time is adjusted, and the combustion phase is optimized. According to the cooperative control method for the air-fuel ratio, the injection opportunity and the cooling liquid temperature in the hydrogen fuel engine, the target air-fuel ratio, the hydrogen fuel injection opportunity and the engine cooling liquid temperature are comprehensively adjusted under a closed-loop feedback control framework, optimal control over the combustion process under different working conditions is achieved, and therefore the braking heat efficiency of the engine is improved, and the service life of the engine is prolonged. And pollutant emission is reduced, knocking is restrained, and the application requirement for efficient cleaning of the engine is met.

The invention relates to the technical field of aero-engine combustion chamber design, in particular to a multi-layer mixing section structure of a pulse detonation combustion chamber. The multi-layer mixing structure is characterized in that the multi-layer mixing structure comprises a multi-layer mixing section arranged in a detonation pipe, an oil supply pipe is arranged on the detonation pipe, the multi-layer mixing section comprises an inner mixing ring and an outer mixing ring, and the inner mixing ring and the outer mixing ring form three Venturi type circulation channels through connecting structures; and a fuel nozzle connected with an oil supply pipe is arranged at the axis of the inner mixing ring. By means of the multi-layer mixing section, incoming flow air is divided into multiple jet flows, the mixing efficiency of fuel oil and air is improved, the mixing uniformity of the fuel oil and air is remarkably improved, and the mixing distance is shortened. Meanwhile, according to the regenerative cooling structure, a fuel oil channel is designed in a multi-layer mixing section, recycling of the wall face of the pulse detonation combustion chamber is achieved, meanwhile, the oil injection temperature is increased, the fuel oil and air mixing effect is improved, and the combustion efficiency is improved.

The application discloses a knock detection method, a knock detection device, computer equipment and a computer storage medium, wherein the knock detection method comprises the following steps: acquiring a pressure signal in an engine combustion chamber; acquiring a resonance frequency of engine knock; decomposing the pressure signal into a high-frequency component signal and a low-frequency component signal according to an empirical mode decomposition method; obtaining a center frequency of the high-frequency component signal according to the high-frequency component signal; in response to the center frequency being located in a range of the resonance frequency, calculating a knock factor according to the low-frequency component signal and the high-frequency component signal; comparing the knock factor with a knock threshold value of the engine, and in response to the knock factor being greater than or equal to the knock threshold value, judging that the engine knocks; and in response to the center frequency being located outside the range of the resonance frequency, or in response to the knock factor being less than the knock threshold value, judging that the engine does not knock. The knock detection method can detect whether the engine knocks.

This control system for a divided-chamber type internal combustion engine comprises: a main combustion chamber; a sub-combustion chamber that is disposed to be separated from the main combustion chamber by a partition wall; a fuel injection valve that is disposed in the main combustion chamber and injects fuel toward the sub-combustion chamber; a knocking detection device that detects knocking; and a control device that executes compression stroke injection for causing the fuel injection valve to inject the fuel in a compression stroke. The control device changes the injection timing of the compression stroke injection when knocking is detected.

The invention discloses an ignition angle control method and device of an extended range engine, a vehicle and a storage medium, and the method comprises the steps that for each air cylinder of the extended range engine, the target correction amplitude corresponding to a current knock signal of the air cylinder is obtained, the absolute value of the target correction amplitude is not larger than the ideal correction amplitude, and the target knock signal of the air cylinder is obtained; the ideal correction amplitude is used for correcting an ignition angle and is a preset correction amplitude threshold value corresponding to a target interval to which current working condition parameters of the extended-range engine belong; according to a preset basic ignition angle of the extended-range engine and the target correction amplitude corresponding to the air cylinder, the target ignition angle of the air cylinder is obtained; ignition angle control is achieved through separate cylinders, each cylinder is combined with a current knock signal, a target ignition angle in a better state is obtained under different working condition parameters, oil consumption is reduced, and the performance of an engine is improved.

This can suppress the occurrence of water hammer within the cylinder. [Solution] The control device 90 of the internal combustion engine 1 controls the internal combustion engine 1, which includes a fuel pump 16 that pressurizes fuel and an injector 15 that supplies fuel into the cylinder 4 by injecting the fuel pressurized from the fuel pump 16. The control device 90 is configured to stop the operation of the fuel pump 16 when the degree of discrepancy between the output timing of a signal output from a knocking sensor 48, which is a sensor that detects the vibration state of the internal combustion engine 1, and the output timing of an injection command signal that drives the injector 15, is greater than a predetermined degree.

The application provides a kind of ignition method, device, medium and methanol engine system of methanol engine.The method determines whether early ignition or knock occurs by analyzing the pressure and temperature at the current time, according to the fault judgment result, the ignition mode can be intelligently adjusted, if potential early ignition or knock is detected, the system will adjust from the initial ignition mode to the ignition mode using more spark plugs, such as using the main spark plug and all auxiliary spark plugs at the same time, or only using the main spark plug to ignite, to reduce the instability in the combustion process, to suppress the occurrence of abnormal combustion phenomenon, once the final ignition mode is determined, the system will execute ignition according to the mode, thereby effectively controlling early ignition, knock and other faults without sacrificing engine performance, thereby solving the problem that the existing scheme is difficult to suppress early ignition and knock phenomenon of methanol engine during ignition period.

An accessory power unit assembly includes a combustor assembly that includes a pulse detonation tube that defines a curved passage between an inlet that receives a compressed airflow and a discharge end. The detonation tube operates as a resonant cavity to sustain a standing pressure wave. Fuel injected into the pulse detonation tube is timed to coincide with movement of a standing wave toward a discharge end. The standing wave provides an increase in pressure of an output exhaust gas driving the turbine without a corresponding increase in load.

The application discloses an ammonia-hydrogen internal combustion engine knock suppression system and a knock suppression method, and belongs to the technical field of internal combustion engine combustion control. The suppression system comprises an ammonia gas supply unit, a hydrogen gas supply unit, a cylinder pressure sensor, a pressure sensor and an electronic control unit. The ammonia gas supply unit realizes ammonia gas supply in a cylinder. The hydrogen gas supply unit realizes hydrogen gas supply in the cylinder. The cylinder pressure sensor is used for monitoring the pressure in the cylinder in real time and calculating CA50. The pressure sensor is used for monitoring the knock intensity of the cylinder. The electronic control unit is electrically connected with the ammonia gas supply unit, the hydrogen gas supply unit, the cylinder pressure sensor and the pressure sensor respectively, is used for receiving sensor signals, calculating ammonia energy (AER) and knock intensity (KI), controlling the ignition time and dynamically adjusting the ammonia mixing ratio, realizing the collaborative optimization of knock suppression and thermal efficiency, and achieving the win-win effect of "knock suppression" and "efficiency increase".

The invention discloses a multi-wave rotary detonation engine isolation section analog calculation method based on a rotary heat source, which comprises the following steps: step 1, carrying out three-dimensional modeling on an isolation section to obtain an isolation section digital model; the isolation section digital model is at least provided with two heat sources, and the heat sources are used for simulating detonation waves rotating in the same direction or opposite directions; step 2, performing grid division on the isolation section digital model by using grid drawing software, and inputting the isolation section digital model after grid division into fluid simulation software; 3, giving a flow field control equation; and 4, giving boundary conditions, initial conditions, heat source motion conditions and heat source heat release conditions, and performing calculation simulation on the isolation section of the rotary detonation engine to obtain a simulation calculation result. Motion shock wave development and evolution structures in an isolation section under various combustion conditions of the multi-wave rotary detonation engine can be simulated, the applicable working conditions are rich, the simulation calculation method is simple in condition setting, the calculation stability is high, and high-precision calculation is adapted.

A method of fuel injector management based on cylinder knock detection includes: receiving an individual cylinder knock count from a first cylinder; determining whether a knock metric is initialized for the first cylinder, whether the knock metric deviates from an established baseline knock metric after multiple cycles when the knock metric is initialized for the first cylinder, whether the knock metric is decreasing with respect to the established baseline knock metric when the knock metric deviates from the established baseline knock metric, whether a fuel system memory indicates rich, lean or healthy when that the knock metric is decreasing with respect to the established baseline knock metric, whether a knock adaptation control indicates a reduction of knock for the first cylinder, and updating a health status of a fuel injector based on the indication of rich, lean, or healthy.

The utility model relates to a multi-sparking plug ignition system, combustion chamber and gas engine, multi-sparking plug ignition system includes precombustion chamber and second sparking plug, precombustion chamber is provided in dome structure center, precombustion chamber is provided with first sparking plug, precombustion chamber is provided with a plurality of jet orifice at interval along the circumference, second sparking plug is provided with second sparking plug. At least one spray hole points to a high-frequency detonation area near an exhaust throat of an exhaust passage in the combustion chamber, the second spark plug and the pre-combustion chamber are arranged between the air inlet passage and the exhaust passage in a spaced mode, and the second spark plug is close to the edge of the dome structure. The high-speed jet jetted by the pre-combustion chamber in the multi-spark-plug ignition system enables flame to reach the edge of the combustion chamber as soon as possible, and the second spark plug can accelerate combustion in the nearby space, so that the multi-spark-plug ignition system can effectively improve the flame propagation speed, shorten the time for the flame to propagate to the edge of the combustion chamber and improve the combustion efficiency. Flame can reach the edge of a combustion chamber of an engine as soon as possible, and the aim of reducing the knocking tendency is achieved.

This application provides an engine combustion control method and apparatus, relating to the field of automotive engine technology. The method includes: responding to an engine start command issued by a hybrid vehicle, setting the engine control mode to a high-efficiency combustion control mode; calculating the intake air volume in the engine cylinders based on the vehicle's required torque; calculating the final boost pressure based on the intake air volume; controlling the speed of the electric supercharger based on the final boost pressure; determining the optimal injection frequency and fuel injection parameters for each engine operating condition based on the engine's full-map operating conditions and the intake air volume; and performing fuel injection and engine knock linkage control based on the optimal injection frequency and fuel injection parameters for each operating condition. The engine combustion control method and apparatus provided in this application can achieve efficient combustion of the hybrid engine in the vehicle, achieve optimal thermal efficiency, and enable smooth charging and driving of the vehicle.

The invention discloses a low-combustion-temperature oxygen-deficient high-pressure-index rich-combustion fuel gas generating agent which comprises the following components in percentage by mass: 50-70% of an oxidizing agent; 12%-30% of hydrocarbon solid fuel; 0-2.5% of a combustion rate regulator; 9%-17% of an adhesive; 0-3.5% of a plasticizer; and 0.7-1.3% of a curing agent. The invention also discloses a preparation method of the fuel gas generating agent. According to the low-combustion-temperature oxygen-poor type high-pressure-index rich-combustion gas generating agent, the gas temperature ranges from 1100 K to 1600 K, the pressure index ranges from 0.5 to 0.8, the oxygen coefficient ranges from 0.3 to 0.45, the total molar ratio of rich-combustion gas ranges from 60% to 84.8%, rich-combustion gas is provided for a rotary detonation engine, and a power source is provided for a solid attitude and orbit control engine.

The invention relates to the technical field of knock control, and discloses an intelligent control system and method for engine knock and preignition, and the method comprises the following steps: collecting engine knock signal data and preignition signal data, and carrying out the signal processing of the knock signal data and the preignition signal data, the method comprises the following steps: generating knock intensity data and preignition intensity data, and during engine knock and preignition identification, setting multi-stage identification thresholds including a basic threshold, a dynamic self-learning threshold and a temperature compensation threshold, and updating the thresholds in real time by utilizing a self-learning algorithm, so that the engine knock and preignition identification accuracy is improved. The method can effectively adapt to sensor signal characteristic change caused by engine wear, fuel quality difference and environment change, solves the problems of misjudgment and missed judgment caused by a fixed recognition threshold value, ensures the accuracy and reliability of knock and preignition recognition, reduces control errors, and improves the reliability of knock and preignition recognition. And the dynamic property, the economical efficiency and the driving smoothness of the engine are effectively improved.

The invention discloses a spark ignition type engine control method, relates to an internal combustion engine, and solves the technical problems of combustion efficiency reduction and single-cylinder misfire easily caused by non-uniform distribution of water in each cylinder in the case of an existing backward temperature compensation technology and a high EGR (Exhaust Gas Recirculation) rate. The method comprises the following steps: acquiring a first humidity value of an intake manifold in an engine, a second humidity value of each cylinder and a reference EGR opening value, calculating a correction coefficient according to the first humidity value, and calculating an EGR target opening value according to the reference EGR opening value and the correction coefficient; and a basic ignition angle is obtained, the humidity offset is calculated according to the second humidity value, the ignition angle compensation amount is calculated according to the humidity offset, and the basic ignition angle is compensated through the ignition angle compensation amount. The invention further discloses a spark-ignition engine control device. It is guaranteed that the engine operates at the knocking boundary for a long time, and efficient combustion is guaranteed.

The application relates to the field of aeroengines, in particular to a rotating detonation combustion chamber with a pressure regulating structure and an injection channel, comprising a duct shell, a combustion chamber body arranged in the duct shell and a Tesla valve arranged at the inlet of the combustion chamber body, the combustion chamber body being provided with an annular channel, the Tesla valve comprising a shell and a flow channel, one end of the shell being fixedly connected with one end of the duct shell, the other end of the shell being coaxially connected with the combustion chamber body, the flow channel being coaxially arranged in the shell, the inlet end of the flow channel being used for air inlet, and the outlet end of the flow channel being communicated with the annular channel in the combustion chamber body; the injection channel is formed between the duct shell, the shell and the combustion chamber body, the inlet end and the outlet end of the flow channel are both provided with a pressure regulating structure, the pressure regulating structure comprises a gas collection cavity and an air inlet hole used for connecting the gas collection cavity with the flow channel, and the injection channel is communicated with the gas collection cavity. The application has the effect of improving the problem that the pressure backflow causes the total pressure loss of the combustion chamber to be large.

Title: Control Unit and Method for Determining Backfire in the Intake Manifold of a Hydrogen Engine. The control unit 118 determines backfire in the intake manifold 110 of the vehicle's hydrogen engine. The intake manifold includes the hydrogen injector 112 and a pressure sensor 114. The hydrogen engine includes the knock sensor 106. Gaseous hydrogen is injected through the hydrogen injector 112 and sent to the engine cylinder. The control unit 118 is configured to detect the first signal indicating a hydrogen flame in the intake manifold 110 via the flame sensor 116. The control unit 118 measures the second and third signals via the pressure sensor 114 and the knock sensor 106, respectively.Control unit 118 validates and determines the presence of backfire based on the correlation of the first signal with the second and third signals. After determining backfire, control unit 118 takes control measures that reduce its occurrence. Figure 1 for the summary.

A method of operating a rotating detonation combustor includes providing a flow of air through an air inlet to flow into a detonation chamber, providing a flow of fuel from at least one fuel injector into the detonation chamber, mixing the flow of the fuel and the flow of the air in the detonation chamber to generate a fuel-air mixture, detonating the fuel-air mixture in the detonation chamber to generate rotating detonation waves within the detonation chamber, and controlling, during operation of the rotating detonation combustor from a first power operating state to a second power operating state, different from the first power operating state, the air inlet wall to control the flow of the air through the air inlet into the detonation chamber to control a discharge coefficient and an operating mode within the detonation chamber.

The application relates to the technical field of aero-engines, and provides a rotating detonation combustion chamber detonation wave propagation direction induced air intake pre-rotation structure which comprises an air intake shell, an air intake flow channel is arranged in the air intake shell, the air intake flow channel comprises an air intake passage, a connecting passage, an expansion passage and a backflow passage, one end of the air intake passage is used for introducing air and fuel, the other end is communicated with the connecting passage, the small end of the expansion passage is communicated with one end of the connecting passage away from the air intake passage, and the large end of the expansion passage is communicated with a combustion chamber; the inlet end of the backflow passage is communicated with one end of the connecting passage away from the expansion passage, and the outlet end of the backflow passage is communicated with the air intake passage; a plurality of guide vanes are arranged in the expansion passage and are arranged in a circumferential interval, and a pre-rotation passage for pre-rotating gas is formed between two adjacent guide vanes. The rotating detonation combustion chamber detonation wave propagation direction induced air intake pre-rotation structure can improve the control accuracy of the detonation wave mode in the combustion chamber.

The utility model belongs to the technical field of engines, and provides an anti-explosion structure of a turbocharged engine, which comprises a controller, a knock sensor and an air inlet control electromagnetic valve, the knock sensor is mounted on an engine main body and is positioned in the middle of a cylinder body of the engine, and the air inlet control electromagnetic valve is mounted on the controller. The air inlet control electromagnetic valve is arranged on an air inlet of an exhaust gas turbocharger of the engine body, the signal input end of the controller is connected with the signal output end of the anti-explosion shock sensor, and the signal output end of the controller is connected with the air inlet control electromagnetic valve. The knock sensor can detect the vibration condition of the engine in real time, when knock is detected, the controller receives a knock signal and controls the opening degree of the air inlet control electromagnetic valve, then the compression ratio of the engine is controlled, and therefore knock can be restrained. Not only can the power of the engine be fully released, but also knocking can be inhibited.

The invention discloses an air film cooling structure and a rotary detonation engine, and relates to the technical field of rotary detonation engine thermal protection, the air film cooling structure comprises a cold air cavity and a Tesla valve type air film pipe, the Tesla valve type air film pipe comprises a main flow pipe, a flow dividing pipe and a collecting pipe, and an inlet of the flow dividing pipe is connected and communicated with the side portion of the main flow pipe; an outlet of the flow dividing pipe is connected and communicated with an inlet of the collecting pipe, an outlet of the main flow pipe is connected and communicated with the side portion of the collecting pipe, the main flow pipe and the collecting pipe are linear, the flow dividing pipe is an arc-shaped pipe and protrudes upwards relative to the collecting pipe, and an inlet of the main flow pipe is connected and communicated with the cold air cavity. And an outlet of the collecting pipe is connected and communicated with a combustion chamber of the rotary detonation engine. The rotary detonation engine comprises a combustion chamber and the air film cooling structure, and the combustion chamber is provided with a combustion inlet and a combustion outlet. According to the invention, high-temperature fuel gas anti-invasion can be inhibited when detonation waves pass through, the influence of high-temperature fuel gas on the cold air cavity is reduced, and the cooling efficiency is improved.