620 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 present invention relates to the field of engine control technology, and specifically provides an engine electronic main water pump control method, device and storage medium. In the method: S1, obtains a first parameter group and a knock compensation parameter, and determines whether the electronic main water pump can start closed-loop control based on a target water temperature based on the first parameter group and the knock compensation parameter. If the determination is yes, enters S2; S2, determines whether the conditions for starting the knock compensation function are met based on the current engine state; if the determination result is yes, enters S3, and if the determination result is no, enters S5; S3, determines whether knock compensation is performed based on the current electronic main water pump output offset. If the electronic main water pump output offset is greater than a preset value, knock compensation is performed and enters S4; otherwise, enters S5; S4, switches the closed-loop control based on the target water temperature to the open-loop control based on the target water temperature; S5, starts the open-loop control strategy based on the target water temperature; in this way, the purpose of increasing the engine cooling intensity and thermal efficiency is achieved.

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 relates to the technical field of engines, in particular to a piston combustion chamber for a diesel and natural gas engine and the engine, and the piston combustion chamber for the diesel and natural gas engine comprises an omega-shaped pit. The straight opening type omega-shaped pit structure is adopted, compared with a traditional ignition type combustion chamber, the ineffective conical volume in the center of the combustion chamber is removed, the top dead center injection diffusion combustion mode is better met, the air utilization rate is higher, the compression ratio is higher, and higher heat efficiency can be better achieved; compared with a traditional necking omega-shaped diesel engine combustion chamber, a plurality of necking structures are removed, the first annular concave face and the second annular concave face are designed, the characteristic of natural gas injection is better met, the front end space of flames is fully released, the air utilization rate is increased, the heat transfer loss is reduced, and the combustion efficiency and the heat efficiency are improved; due to the design of the large-curvature concave surface, the problems of heat load concentration and particle friction caused by a sharp structure can be avoided, and the problems of out-of-control combustion, knocking and engine damage are reduced.

The invention discloses a pulse detonation attitude control engine system which comprises an ignition detonation straight pipe and at least one S-shaped attitude control pipe. The ignition detonating straight pipe comprises an ignition section and an obstacle detonating section which are sequentially arranged in the axial direction; wherein an explosion promotion barrier is arranged in the barrier explosion initiation section; each S-shaped attitude control tube comprises a branch tube and two bent push tubes; the center of the branch pipe is vertically arranged at the tail end of the obstacle detonating section and is communicated with the obstacle detonating section through a valve; the two bent push pipes are symmetrically arranged relative to the center of the branch pipe to form an S shape; each bent push pipe comprises a bent pipe section and an exhaust nozzle section, and the two ends of each bent pipe section are connected with the corresponding branch pipe and the corresponding exhaust nozzle section respectively. According to the invention, the advantages of high-efficiency combustion and high-precision adjustable pulse thrust of the pulse detonation engine can be played as far as possible while the microminiaturization of the attitude control engine is met, the thermodynamic cycle theory can be improved by more than 20% compared with common chemical propulsion, and the on-orbit life of a spacecraft is effectively prolonged.

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 the technical field of aero-engines, and discloses an efficient thermal protection hybrid thermodynamic cycle combined engine and a control method thereof.The combined engine composed of an external rotary detonation engine and an internal turbine engine is adopted, and modal switching of the combined engine is achieved through an inlet adjusting valve and an adjustable exhaust nozzle; the working upper limit of a turbine engine can be effectively joined, power relay can be completed, so that a thrust gap is spanned, the structural design complexity is relatively low, the system stability is relatively high, and in a stress application rotating detonation mode, the reliability is high. Combustible mixtures sprayed by the rotary detonation engine are guided into the afterburner of the turbine engine through the afterburner diverter valve for detonation combustion, an original cooling device of the afterburner is used for thermal protection, and an outer casing is prevented from being damaged due to high temperature.

The invention relates to the technical field of engines, and discloses a turbine-based combined cycle engine operation method and a turbine-based combined cycle engine, and the turbine-based combined cycle engine operation method comprises the steps that a pulse detonation combustion mode is adopted in a pure turbine mode; a rotary detonation combustion mode is adopted in a pure stamping mode; a pulse detonation combustion mode is adopted in the transition mode, and meanwhile, a rotary detonation combustion mode is adopted. By utilizing the advantages of self-pressurization and high unit thrust of pulse detonation combustion, the high-speed performance is improved, and the working Mach number upper limit of a pure turbine mode is widened; by utilizing the advantages of high combustion speed, high combustion efficiency, simple structure and short length of rotary detonation combustion, the lower limit of the working Mach number of a pure stamping mode is widened. And in the transition mode, the characteristics of a pure turbine mode and a pure stamping mode are achieved at the same time, and enough thrust is provided for the aircraft.

The invention belongs to the technical field of aviation aircrafts, and particularly relates to a hybrid power engine and an aviation aircraft. The invention provides a hybrid power engine which comprises a detonation combustion chamber, a center shaft and a power generation assembly, the power generation assembly comprises a stator, an outer rotor and fourth permanent magnets, the stator is hinged to the center shaft, the outer rotor is of an annular structure, a plurality of first grooves are formed in the annular outer wall of the outer rotor, and the fourth permanent magnets are embedded in the first grooves; the fourth permanent magnet is matched with the stator for power generation; the detonation combustion chamber is arranged in the outer rotor and drives the outer rotor to rotate; the center shaft is provided with an energy storage part, and the power generation assembly is electrically connected with the energy storage part. The invention further provides an aviation aircraft comprising the hybrid power engine. According to the engine, the detonation combustion chamber combusts to drive the outer rotor to rotate to generate electricity, redundant power of the detonation combustion chamber generates electricity through the power generation assembly and then is stored in the energy storage part, waste of redundant energy is avoided, and the energy storage part can also be used for providing driving power.

The invention relates to the technical field of rocket engines, in particular to a rocket support plate and concave cavity combined oblique detonation engine which comprises a mixing section, a combustion chamber and an exhaust nozzle which are sequentially connected, the mixing section is of a hollow structure, a fuel-rocket support plate assembly is arranged in the mixing section, and a detonation slope-concave cavity combined support plate assembly is arranged in the combustion chamber; a middle flow channel for constant-pressure combustion is formed in the middle of the detonation slope-concave cavity combined supporting plate assembly, and an upper flow channel and a lower flow channel for constant-volume combustion are formed by the upper surface and the lower surface of the detonation slope-concave cavity combined supporting plate assembly and the inner wall of the combustion chamber. According to the device, an oblique detonation combustion mode, a rocket mode, a subsonic combustion ramjet mode and a scramjet mode are integrated into the same engine, a split flow channel structure is formed, full-speed domain coverage from low Mach to ultrahigh Mach (more than 8 Mach) is achieved, and combustion organizations in different flight stages are optimized through a mode switching mechanism.

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.

A rotating detonation combustion system includes a detonation channel including an inner wall and an outer wall and extend in a longitudinal direction from an inlet of the detonation channel to an outlet of the detonation channel. A first mixing element and a second mixing element are disposed in the rotating detonation combustion system. The first mixing element forming a ring on the inner wall and the second mixing element forming a ring on the outer wall of the detonation channel adjacent the inlet. Each of the first mixing element and the second mixing element comprise a plurality of protrusions disposed circumferentially along the inner wall and the outer wall and extend into the detonation channel such that the plurality of protrusions affects vectors of at least a portion of the fuel and at least a portion of the fluid passing through recesses between the plurality of protrusions.

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 present invention discloses a control method, device, equipment and medium for a natural gas engine. The method comprises: obtaining operating parameters of the engine, and determining an optimal range of an intercooler temperature of the engine according to the operating conditions corresponding to the operating parameters; adjusting the intercooler temperature of the engine to an intercooler temperature lower limit value corresponding to the optimal range of the intercooler temperature by controlling the rotation speed of a fan when no detonation occurs in the engine; adjusting the ignition angle and the EGR rate of the engine to a first ignition angle and a first EGR rate, respectively, based on a first preset curve and the lower limit value of the intercooler temperature, and controlling the engine to operate at the first ignition angle and the first EGR rate so that the engine operates with minimum gas consumption, and returning to the step of obtaining the operating parameters of the engine; in such operation, the combustion efficiency of the engine can be improved, and the economy is good.

The present application belongs to the field of detonation turbine engine design, and is a device for separating detonation and afterburner airflow exhaust, comprising an inner nozzle, an outer nozzle, an inner regulating device, and an outer regulating device; when the detonation turbine engine is working, the high-temperature combustion gas in the afterburner combustion chamber enters the inner nozzle, the high-temperature combustion gas in the detonation combustion chamber enters the high-temperature combustion gas channel, and the outer cooling gas is divided into two streams and enters the first cooling channel and the second cooling channel respectively, cooling the wall surfaces of the outer nozzle and the inner nozzle. At the same time, the outer cooling gas in the first cooling channel and the second cooling channel enters the heat shield, so that the inner regulating device will not come into contact with the high-temperature combustion gas generated by the detonation combustion chamber, and at the same time, it is continuously cooled by the outer cooling gas, thereby minimizing the ambient temperature of the inner regulating device located in the outer high-temperature area, and effectively reducing the risk of ablation of the cylinder wall and the inner regulating device caused by the outer high-temperature area.

The present invention discloses a solid caseless rotary detonation engine, comprising a charge supply assembly, a charge pushing assembly, and a charge combustion assembly. The present invention has the following beneficial effects: by providing a charge rotating supply trough, multiple caseless solid charges can be impacted simultaneously, thereby generating an explosion; the gas detonation waves generated by the explosion of the multiple caseless solid charges are discharged through the combustion chamber, generating a large thrust, which can propel a large-volume and heavy rocket engine; in addition, the present application further connects a push plate with impact pins having perforations corresponding to the slots provided by the charge rotating supply trough; when the push plate is pushed forward, each impact pin can pass through the perforations and impact the caseless solid charge, thereby generating an explosion.

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.

The present application provides a knock sensor tamper detection method, device, electronic device, and storage medium. The method comprises: defining a vehicle characteristic signal based on a first engine crankshaft angle window; obtaining a current vehicle operating condition; obtaining a current vehicle characteristic signal based on the current vehicle operating condition; determining a signal deviation between the current characteristic signal and a reference characteristic signal; determining whether the signal deviation is below a preset minimum limit; if so, obtaining a duration for which the signal deviation is below the preset minimum limit; and if the duration for which the signal deviation is below the preset minimum limit reaches a preset duration, determining that the knock sensor has been tampered with. This method solves the technical problem that existing technologies can only detect situations where the knock sensor has been completely removed or has no installation torque, but cannot detect tampering such as installing and then tightening a rubber pad, which may result in a failure to protect the engine when knock actually occurs.

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 present invention discloses a control method for a vehicle radiator fan, which belongs to the technical field of engine control. The present invention considers the following aspects: the reason for fan control based on water temperature is that the fan needs to be turned on when the water temperature is too high to avoid poor vehicle power, economy and emissions, and to avoid the occurrence of knock; the reason for fan control based on intake air temperature and vehicle speed is that when the intake air temperature is too high and the vehicle speed is too low, the risk of engine knock will increase; the purpose of dynamic control and intelligent control optimization based on the real-time performance of the cooling system is to perform dynamic control optimization in real time because the engine operating conditions are transient and complex, and to improve control optimization for cooling system aging to provide control accuracy.