87 results about "Ignition delay" patented technology

The present invention is a magnetically powered electrically controlled solid propellant combustion performance test system and method. It includes a support frame, an ignition device, a magnetic sheet, an electromagnet, a PD stress control integrated module, a data acquisition subsystem and a PC terminal; a magnetic sheet is connected below the ignition device, and a PD stress control integrated module is arranged below the ignition device, and an electromagnet is arranged thereon. The PD stress control integrated module regulates the current to make the force between the ignition device and the electromagnet constant, thereby pushing the ignition device electrically controlled solid propellant to slide and maintaining dynamic contact between the propellant and the positive and negative electrodes. The present invention is suitable for testing electrically controlled solid propellants of various systems. The parameters of the entire area of ​​the system can be modulated by the PC terminal, and the combustion performance of the electrically controlled solid propellant, such as multi-stage ignition delay time, energy required for ignition, dynamic burning rate, dynamic current, burning rate adjustable ability with electricity, combustion temperature, flame structure morphology and flameout delay time, can be diagnosed simultaneously.

The invention belongs to the technical field of engines, discloses a methanol engine combustion system, a control method and a methanol engine, and realizes more stable combustion during cold start and low-load working condition operation of the methanol engine through a glow plug; alpha is limited to be smaller than beta, and the vortex motion direction in the combustion chamber is the piston circumferential direction from the first reference surface to the second reference surface and passing through the preset plane, so that methanol injected into the combustion chamber through the methanol injection hole corresponding to the first reference surface can be guided by the vortex motion in the combustion chamber, and the methanol can be injected into the combustion chamber. The ignition time of the methanol injected into the combustion chamber from the methanol injection hole corresponding to the first reference surface by the glow plug is shortened, namely, the ignition delay period of the methanol is shortened; and then flame generated by combustion of methanol ignited by the glow plug is utilized to sequentially ignite methanol injected into the combustion chamber from other methanol injection holes, so that controllable combustion of direct injection methanol in the cylinder is realized.

The invention relates to the technical field of aero-engines, and discloses a combustion chamber with an adjustable air entraining structure, the combustion chamber comprises a cartridge receiver structure, the air entraining structure and an adjusting structure, the cartridge receiver structure comprises a first cartridge receiver and a second cartridge receiver, the first cartridge receiver and the second cartridge receiver are connected with each other and jointly define a mounting cavity, and the first cartridge receiver is provided with a first communication part and a second communication part; the air entraining structure is provided with a communicating cavity, the communicating cavity is provided with a first opening, a second opening and a third opening, the first opening communicates with the first communicating part, the second opening communicates with the second communicating part, and the third opening communicates with the engine; the adjusting structure comprises a first adjusting assembly and a second adjusting assembly, the first adjusting assembly covers the first communicating part and is arranged on the first casing, and the second adjusting assembly covers the second communicating part and is arranged on the first casing; ignition delay and flameout of the auxiliary power device in a small state are avoided, low-frequency excitation of the flame tube in a large state is avoided, and performance degradation of the combustion chamber in an intermediate value state is avoided.

The invention provides an embedded multifunctional plasma flame stabilizer, and relates to the technical field of plasma ignition combustion supporting. The embedded multifunctional plasma flame stabilizer comprises an evaporative flame stabilizer and an embedded exciter, wherein the evaporative flame stabilizer is provided with a combustion area defined by apron boards; the embedded exciter is installed on the surface, facing the combustion area, of the apron board. The exciter is directly integrated on the inner side of the skirt board of the flame stabilizer, and the space utilization rate and the system integration degree are improved on the premise that the aerodynamic configuration and the installation mode are not changed. The discharge area of the exciter covers the backflow area, active free radicals can be generated and local heat can be released under complex and changeable conditions, the reaction activity of mixed gas is enhanced, the ignition delay time is shortened, the ignition boundary is expanded, meanwhile, atomization and mixing are improved, the combustion efficiency is improved, and flame quenching is restrained. The device has ignition assistance, continuous excitation and active thermochemical regulation and control capabilities, and is suitable for a compact combustion chamber environment.

The present invention discloses a method for predicting the ignition of a scramjet combustion chamber, belonging to the technical field of ignition prediction. The method comprises the following steps: numerically simulating the combustion chamber using a three-dimensional density-based steady-state injection; determining whether convergence conditions have been met; extracting flow field data of the combustion chamber after convergence; and calculating the residence time t of aviation kerosene microclusters in the ignition region based on the flow field data. z ; Calculate the ignition delay time t of the ignition area based on the flow field data c Calculate Da in the ignition area. Predict ignition conditions based on Da. The scramjet engine combustion chamber ignition prediction method of the present invention calculates Da based on injection field data and predicts ignition success based on the relationship between Da and 1. This helps adjust actual ignition conditions and improve ignition success rates. It can meet the ignition prediction needs of combustion chambers of various configurations.

The invention discloses a micro gas generator homogeneous mixed medicament for a safety belt and a preparation method of the micro gas generator homogeneous mixed medicament, the micro gas generator homogeneous mixed medicament is prepared from the following components in percentage by mass: 90-97% of green gas generating medicament particles and 3-10% of nitrocellulose medicament particles uniformly dispersed in gaps of the green gas generating medicament particles, and the sum of the mass percentages of the components is 100%. By utilizing the advantages of high combustion speed and low ignition threshold of the nitrocellulose agent, the ignition delay and the combustion period of the mixed agent are shortened, the exposure time of the safety belt elbow in a high-temperature environment is shortened, the structural strength of the safety belt elbow is ensured, the problem of elbow explosion in a bonfire test is finally solved, and meanwhile, the environment-friendly characteristic of a green gas-producing agent is reserved; in addition, through the two-time charging process of the automatic production line, the mixed charging efficiency is high, and the product consistency is good.

The invention discloses an energetic material, a preparation method thereof and application of the energetic material as an initiating explosive, an explosive and a pyrotechnic compound. The chemical formula of the energetic material is MC10H18B2N6; wherein M is selected from at least one of Mn, Fe, Co, Ni, Cu, Zn and Cd; the crystal structure of the energetic material belongs to a monoclinic system, and the space group is P21 / n. The obtained energetic material has excellent stability and safety, and is green and environment-friendly. Through experimental determination, the thermal stability is greater than or equal to 120 DEG C, the impact sensitivity is greater than or equal to 40J, and the friction sensitivity is greater than or equal to 240N. Compared with an existing commercial propellant (unsymmetrical dimethylhydrazine), the ignition delay time of the energetic material is equivalent, the defects that fuel and an oxidizing agent are seriously mixed and the combustion efficiency is low are overcome, and the energetic material has important commercial application value in the field of green high-performance energetic materials.

The invention relates to a method for operating a vehicle engine in order to regenerate a solid particle filter in an idle mode, in which a pre-ignition is delayed in such a way that an actual ignition takes place at the point in time when a piston is in a position after top dead center in the direction of rotation of the crankshaft. Meanwhile, the injection time of fuel into the intake air in the combustion chamber of at least one cylinder is shortened, so that the air-fuel ratio lambda is increased by at least 5% from 1.

The application provides an improved naphthene hydrocarbon fuel and a low-pressure combustion promoting method thereof, in particular, methylcyclohexane is used as a base fuel, and diethylsilane is added to methylcyclohexane to regulate the ignition temperature and ignition delay time of methylcyclohexane at low pressure. The modified naphthene hydrocarbon fuel obtained by the method has the advantages of stable physical form, no stratification, high heat value, good stability when the fuel is in contact with air at normal temperature and the like, the low-pressure combustion characteristics of the naphthene hydrocarbon fuel are regulated through directional regulation of the combustion base element reaction of the naphthene hydrocarbon fuel, the operation is simple, and the practicability is strong. The application solves the problem of low-pressure regulation difficulty of the hydrocarbon fuel, provides a solution for the low-pressure characteristic regulation of the naphthene hydrocarbon fuel, and provides technical reserves for reliable ignition of advanced aero-engine under low-pressure harsh working conditions.

The application provides a vehicle rollover protection method, device, medium and electronic equipment. When the rollover parameter value of the vehicle meets the preset starting protection task condition on the time axis, the ignition delay duration is calculated, and the time axis is obtained based on the rollover parameter value. When any type of monitoring parameter value on the time axis is greater than the preset monitoring threshold value of the corresponding type, the corresponding type of penetration identifier is set. When the plurality of types are set with the penetration identifier of the respective type, when the ignition delay duration is less than or equal to the preset ignition delay duration threshold value, the ignition instruction of the safety airbag associated with the rollover is generated. Through the multiple feature recognition of the rollover parameter value on the time axis, the ignition instruction of the safety airbag associated with the rollover is determined. Thus, the safe and reliable protection is provided for the passengers when the vehicle rolls over, and the survival rate of the passengers is improved.

The invention discloses a novel non-premixed natural gas ammonia-doped combustor, and aims to realize efficient mixing of fuel gas and air in the natural gas ammonia-doped combustor, reduce the emission intensity of carbon dioxide and nitrogen oxide, and solve the problems of poor ammonia-doped combustion stability of natural gas, large potential safety hazard of the combustor and the like. The device comprises an ammonia gas nozzle, a swirler, a natural gas nozzle, a secondary air nozzle and a nozzle baffle, and the ammonia gas nozzle, the natural gas nozzle and the secondary air nozzle are sequentially arranged from inside to outside and are concentrically arranged in a surrounding mode; the swirler is positioned between the ammonia gas nozzle and the natural gas nozzle; the nozzle baffle is located between the natural gas nozzle and the secondary air nozzle. The fuel mixing efficiency is enhanced through the swirler, the heat load of a combustion high-temperature area is reduced through secondary air, the combustion delay characteristic of ammonia fuel is improved in combination with the flue gas backflow technology, and a novel combustion technology system with the synergistic effect of the swirler and secondary air flue gas backflow is constructed. The invention relates to the technical field of combustion equipment.

The application provides an engine cylinder pressure calculation method and an engine cylinder pressure virtual sensing system. The method comprises the following steps: establishing a hybrid control combustion model of an engine, inputting first parameters for calculation into the hybrid control combustion model, and performing the following calculation in the hybrid control combustion model: calculating in-cylinder temperature and pressure of the engine in a first stage according to the first parameters, calculating instantaneous in-cylinder local turbulent kinetic energy density in a second stage, calculating a burned gas dilution factor according to the first parameters, the burned gas dilution factor reflecting an obstruction effect of inert gas in a combustion chamber of the engine on mixing of active components, calculating a heat release rate after an ignition delay period in a third stage according to the first parameters, a fuel kinetic energy change rate and the burned gas dilution factor, and calculating a curve of engine cylinder pressure changing with a crank angle according to the heat release rate by using a thermodynamic formula.

The invention discloses a method for predicting ignition characteristics of a hydroxylamine nitrate electrically-controlled solid propellant. The method specifically comprises the following steps: step 1, determining redox reaction of a positive electrode and a negative electrode of the propellant according to components of the propellant; step 2, constructing an ignition theoretical model of a propellant based on a free radical reaction; 3, propellant ignition criteria are established, and an equation for solving propellant ignition characteristic parameters is deduced; 4, propellant ignition condition parameters are set; 5, judging whether the propellant generates energy to ignite or not; and 6, after the ignition requirement is met, propellant ignition characteristic parameters are calculated. The method can directly predict the ignition delay time and the energy required by ignition of the nitric acid hydroxylamine electrically-controlled solid propellant, can quantitatively evaluate the ignition characteristics of the propellant, has small error between the prediction result and the actual measurement result, has the advantages of good economical efficiency, high efficiency and the like compared with a test means, and is suitable for popularization and application. And a large amount of test time and trial-and-error cost can be saved.

The invention relates to an experimental device and method for preventing a quadratic type cloud explosive bomb from fire channeling. The device comprises a cloud explosive bomb main body which is a hollow pipe containing central initiating explosive and cloud explosive fuel, an upper end opening is detachable, and a plurality of notch grooves are distributed in the inner side wall of the cloud explosive bomb main body. The central tube is filled with the porous material, the inert explosion suppression dust is uniformly dispersed in pores of the porous material, and explosion flame propagation of the central initiating explosive is inhibited under the combined action of the porous physical structure and the chemical explosion suppressant, so that the fire channeling phenomenon is prevented. The center initiating explosive is tightly connected with the detonator, and the detonator is fixed through a center initiating detonator plug. And the ignition delay system is used for controlling the initiation time sequence of the central primer detonator and the secondary primer detonator. The method can prevent the fire channeling phenomenon of the cloud explosive bomb, so that the damage power of the cloud explosive bomb is improved, and the method has the advantages of being simple in process, easy to operate, low in cost and suitable for batch production.

The present invention discloses an ignition powder and ignition device for a solid rocket engine. The ignition powder comprises an oxidizer (50-70%), a binder (10-30%), a coupling agent (3-10%), and a fuel (10-35%). The ignition powder has a combustion heat of over 6,000 kJ / kg. Furthermore, the ignition powder has lower mechanical sensitivity than commonly used black powder, improving safety during the ignition operation of the solid rocket engine. The ignition device fully covers the combustion end surface of the solid propellant in the solid rocket engine, achieving full-burning surface ignition of the solid propellant and significantly shortening the engine ignition delay time. The thin-layer metal ignition electrode and polymer insulating film used are completely burned out after the ignition powder burns, without negatively impacting the burning surface of the solid propellant.

The invention discloses an ignition prediction method for a scramjet engine combustion chamber, and belongs to the technical field of ignition prediction. The ignition prediction method for the combustion chamber of the scramjet engine comprises the following steps that numerical simulation is conducted on the combustion chamber through three-dimensional density-based steady-state injection; judging whether a convergence condition is met; extracting flow field data of the combustion chamber after convergence; the residence time tz of the aviation kerosene micelles in the ignition area is calculated according to the flow field data; the ignition delay time tc of the ignition area is calculated according to the flow field data; and calculating the Da of the ignition area. And predicting the ignition condition according to the Da. According to the ignition prediction method for the combustion chamber of the scramjet engine, Da is calculated according to injection field data, whether ignition succeeds or not is predicted according to the size relation between Da and 1, the actual ignition working condition can be adjusted, and the ignition success rate is increased; and ignition prediction requirements of combustion chambers of various configurations can be met.

An object of the present invention is to achieve both ensuring combustion stability of an internal combustion engine and reducing particulate matter (PM) during operation in a catalyst warm-up mode with ignition retardation. A control device 150 is a control device for a fuel injector 101 that injects fuel directly into a cylinder cavity 615 of an internal combustion engine 10 operating in a catalyst warm-up mode in which a catalyst is warmed up by ignition retardation, in which an ignition timing is retarded to an expansion stroke.The control device 150 controls the fuel injection device 101 such that a fuel injection immediately before the ignition timing is performed among a plurality of fuel injections performed during one combustion cycle in the expansion stroke during operation in the catalyst warm-up mode, and an injection amount of the fuel injection immediately before the ignition timing decreases as the ignition timing is retarded.

A control system (200), a method (600), and computer software (208) for controlling an engine (102) and an electric machine (106) of a vehicle (1). The method (600) comprises: receiving (606) a first input signal indicative of an engine idle torque requirement (TA) during engine idling; comparing (610) an instantaneous torque requirement (TA or TA+TB) with a reference engine idling torque (TC) associated with use of a base ignition retardation value; and outputting a control signal (612, 616, 618) to control output torque of the engine in dependence on the comparison, wherein if the instantaneous torque requirement (TA or TA+TB) is less than the reference engine idling torque (TC), the control signal requests (612) the reference engine idling torque (TC) with the base ignition retardation value, and the control system is configured to control the electric machine (106) to impose a retarding torque on the engine (102) to generate electrical energy, thereby reducing a net torque.

This application relates to the field of aerospace technology, and particularly to a combustion test device for metal particles under a microscope. The combustion test device for metal particles under a microscope includes an optical microscopy component, a combustion test component, an oxidant pressurization component, and an observation component; the optical microscopy component can ignite metal particles and measure the energy for igniting the metal particles; the combustion test component can provide a combustion condition with pressure for the metal particles; the oxidant pressurization component can supply an oxidant with adjustable pressure to the combustion test component; the observation component can capture the combustion process of the metal particles to obtain the ignition delay time, combustion time, and visible light images during the combustion process of the metal particles. This application can overcome the problem in the prior art that the observation scale cannot be reduced to the level of dozens of micrometers and nanometers; at the same time, it can meet the precise control of the combustion environment components, pressure, and ignition energy.

The application discloses a preparation method of a core-shell structure nickel-aluminum-boron composite fuel, and comprises the following steps: S1, target material treatment: selecting a target material with a proper size, polishing the target material before use, then performing ultrasonic cleaning on the target material with anhydrous ethanol and acetone for 10 minutes, and placing the target material into a sputtering chamber after drying; S2, powder laying: grinding boron powder, and then uniformly laying the boron powder on a glass substrate with a proper size; S3, vacuumizing and pretreating a reaction chamber; S4, sputtering coating; and S5, detecting the modified amorphous boron coated with aluminum. The method is simple, controllable, safe, low in cost and suitable for industrialized scale production. The composite boron powder obtained by the method has an amorphous boron powder as a core and a nickel-aluminum coating layer, has a short ignition delay time, is high in combustion efficiency, and can be directly used as a boron-based energetic material.

The invention discloses an asymmetric runner integrated exhaust manifold of an automobile exhaust system and a cold start ignition control method, and relates to the technical field of automobile exhaust systems. The exhaust manifold and an engine cylinder cover are integrated, and the exhaust manifold comprises a manifold body, an asymmetric branch flow channel set, an integrated thermal coupling structure, a waste gas confluence cavity, a temperature collecting module and a sealing structure. The asymmetric branch runner group is adaptive to the exhaust characteristics of each cylinder, so that airflow interference and heat loss are reduced; the integrated thermal coupling structure conducts heat with cylinder cover waste heat through water jacket flow adjustment, and the waste gas temperature is increased; and the temperature acquisition module acquires temperature data in real time and transmits the temperature data to the ECU to realize closed-loop control. According to the cold start ignition control method, rapid ignition of the aftertreatment device is achieved through working condition recognition, temperature feedback, thermal coupling flow adjustment and air-fuel ratio and ignition advance angle cooperative adjustment. The problems that in the prior art, cold start ignition is delayed, emission exceeds the standard, and fuel economy is poor are solved, ignition time is shortened by 18-25 seconds, cold start emission is greatly reduced, and the method adapts to national sixth B and above emission laws and regulations and has good mass production feasibility and application value.

The present invention discloses a mechanical pull-fire pyrotechnic delay gas generating device, belonging to the technical field of initiators. The gas generating device includes a three-stage mechanical safety mechanism (primary safety, secondary safety, and service safety), a firing mechanism, an ignition component, a delay component, a main charge package actuating component, etc. The gas generator of the present invention meets the requirements of mechanical pull-fire, mechanical safety, pyrotechnic delay, and stable output at low pressure. Compared with traditional electrically fired gas generators, the present invention has high safety in electromagnetic environments and service transportation, and also has the advantages of low cost, high practicability, and stable work ability in low-pressure environments, and has broad application prospects.

The invention belongs to the technical field of high-temperature coke ignition time measurement, and particularly relates to a device and a method for measuring high-temperature coke ignition time delay. The device for measuring the ignition time delay of the high-temperature coke comprises a plane flame burner, an image acquisition unit and a data processing unit, in the plane flame burner, a top preset section of a central powder feeding pipe extends into a hearth; the image acquisition unit is used for acquiring a motion trail diagram that coke particles output by the top preset section are gradually heated to be on fire; and the data processing unit is used for performing brightness data extraction according to the motion trail diagram to obtain ignition time, and taking the time interval from the time when the coke particles are output into the hearth from the top preset section to the ignition time as ignition time delay output of the high-temperature coke. According to the invention, the technical problem that only the ignition delay of normal-temperature pulverized coal can be effectively measured and the high-temperature coke with a certain temperature cannot be accurately measured in the prior art is solved.

The application provides a combustion system for mixed combustion of carbon-free fuel and coal powder, which comprises, from inside to outside, a hydrogen combustion device, a methanol combustion device, a nozzle concentration and dilution separator and a coal powder combustion device which are coaxially sleeved, and an ignition device. High-speed rotational flow hydrogen gas sprayed by a hydrogen gas nozzle of the hydrogen combustion device aerodynamically atomizes methanol sprayed by a methanol nozzle of the methanol combustion device, and a dilute coal powder gas flow separated by concentration and dilution is introduced into a central high-temperature zone by the jet entrainment effect of the nozzle concentration and dilution separator, so that the hydrogen gas-methanol-coal powder is sequentially ignited. The application solves the problems of ignition delay and unstable combustion during mixed combustion of multiple fuels, realizes fuel staging and flue gas recirculation through structural optimization, significantly reduces the generation amount of NOx and carbon dioxide emission, so that the hydrogen gas, methanol and coal powder are efficiently and cooperatively combusted, and low nitrogen emission and high burnout rate are simultaneously achieved. The application further provides a boiler.

The present invention belongs to the technical fields of computational fluid dynamics and numerical combustion, and specifically discloses an efficient global ignition delay time synchronization algorithm for OpenFOAM simulation results, which includes the following steps: First, expand a chemical solver capable of synchronously calculating ignition delay times of multiple grid cells and various thermodynamic states; then, for the intermediate moment results obtained from the zero-dimensional ignition simulation of this solver, develop an extraction solver for the ignition delay time on each grid cell. By adopting the above-mentioned efficient global ignition delay time synchronization algorithm for OpenFOAM simulation results, the present invention can accurately, efficiently, and quickly predict the global ignition delay time, ignition probability, and evolution information of ignition positions of any actual calculation configuration in OpenFOAM numerical simulation; it can analyze the local flow, thermodynamic, and thermochemical states of successful ignition, support the development of higher-order and higher-dimensional ignition theoretical models; and further guide the ignition design of actual combustion devices and improve the ignition success rate.

The invention discloses an ignition chamber structure for a liquid rocket engine, which is characterized in that a middle rotational flow ring body and a combustion chamber are sequentially arranged in an outer barrel, a heat dissipation cavity and a liquid collection cavity are formed among the middle rotational flow ring body, the combustion chamber and the outer barrel, the middle rotational flow ring body is provided with a gas nozzle, and the combustion chamber is provided with an ignition nozzle. The combustor has the remarkable advantages that the tangential gas nozzle forms a strong swirling flow field, so that fuel and an ignition agent are fully mixed, and the ignition delay time is shortened by more than 30%; the heat dissipation cavity is combined with the heat dissipation fins of the outer cylinder body for dual heat dissipation, and the temperature of key parts is reduced by 20-30 DEG C; the ceramic coating and transition layer composite structure on the inner wall of the combustion chamber improves the corrosion resistance by more than 50%; and the plug-in I-shaped connecting part realizes modular design, so that the assembly efficiency is improved by 40%, and the use cost is reduced. The ignition chamber structure effectively improves the performance and reliability of the rocket engine and has good application prospects.

The present invention discloses a pulverized coal graded flameless combustion device coupled with dense-lean separation, comprising: a primary air nozzle for conveying pulverized coal and primary air into a combustion chamber; a secondary air nozzle and a tertiary air nozzle for conveying secondary air and tertiary air into the combustion chamber, respectively, wherein the secondary air and the tertiary air are high-speed oxidant airflow and high-temperature oxidant airflow, respectively; the secondary air nozzle is coaxially arranged inside the tertiary air nozzle, the primary air nozzle is evenly distributed around the tertiary air nozzle, and a separation mechanism is provided inside the primary air nozzle for separating the pulverized coal airflow into a dense pulverized coal airflow and a lean pulverized coal airflow, wherein the dense pulverized coal airflow is closer to the oxidant airflow. On the one hand, the present invention reduces the energy consumption and cost of the flameless combustion technology through an oxidant injection method that cooperates with external preheating and internal speed increase, and on the other hand, promotes pulverized coal ignition by dense-lean separation of the pulverized coal airflow, shortening the ignition delay and the flame floating distance.

The invention provides a method for catalyzing rapid spontaneous combustion of an N (CN) 2-IL-H2O2 system by twin-crystal Cu NPs, belongs to the field of rocket propellants, and aims to solve the problem that the N (CN) 2-IL-H2O2 system does not spontaneously ignite. The twin crystal Cu NPs and N (CN) 2-IL ionic liquid are mixed, the obtained mixed fuel is dropped into a cylindrical open glass bottle oxidant pool containing H2O2, and the ignition delay time is tested. The ignition process is recorded by a high-speed camera, and obtained data is an average value of three times of ignition tests. The spontaneous combustion performance of the N (CN) 2-IL-H2O2 system is reduced by utilizing the twin boundary defect of Cu NPs, and the ignition delay time is as low as 25 ms. The method is simple in operation and rapid in reaction, relatively low ignition delay time can be obtained, and accurate synthesis of the twin crystal Cu NPs is beneficial to industrial application of an N (CN) 2-IL-H2O2 propulsion system and rapid development of the aerospace industry in China.

The battery pack having a fire delay structure according to the present invention is characterized by comprising: at least one battery module; a housing for accommodating the battery module; a cooling unit for cooling the battery module while the cooling water moves; and an injection unit for injecting cooling water to the battery module.

The invention discloses an ignition and flameout modeling combustion chamber testing device and system and a flame characteristic research method, and belongs to the technical field of gas turbine combustion chamber testing. The test device comprises a combustion chamber, a swirler assembly, a fuel nozzle and a plurality of igniter mounting ports respectively corresponding to key flow field positions such as an inner backflow area, a main backflow area and an outer backflow area. A tower-type cyclone or a rotary sliding arc exciter can be selected as the cyclone assembly, and a gas supply system, an oil supply system, an ignition system and an optical test system are integrated in the test system. The method comprises the following steps of: igniting by using different igniters or at different positions, capturing a flame development process by utilizing high-speed imaging, and performing flame mode diagnosis by combining image processing, flame mode diagnosis based on a non-dimensional number, POD, DMD and other methods. Influences of different ignition modes and ignition positions on a flame propagation path, an ignition success rate, ignition delay, flame stability and lean-burn ignition limit and internal physical mechanisms thereof are systematically analyzed.