315 results about "Ignition control" patented technology

The invention provides an inclined variable-angle aircraft interstage separation ground test device. The inclined variable-angle aircraft interstage separation ground test device comprises an aircraft separation device, an angle adjusting device, a temperature control and acquisition device, a vibration control and impact acquisition device, an ignition control device and a device base. The angle adjusting device comprises a device side plate, an arc groove, an angle ruler, a separation mechanism mounting plate, a supporting hinge, a supporting rod, an adjusting sliding rail, an adjusting base, a locking device, a device base gradienter, a rotating bearing and an auxiliary fixing block. The temperature control device comprises a quartz lamp array heating cage, an outer wall temperature control thermocouple and an inner wall temperature acquisition thermocouple, and can simulate a pneumatic heating environment at a separation moment, so that the thermal deformation matching capability of the separation mechanism in a high-temperature environment and the operation reliability of the separation mechanism are obtained. The vibration control and impact acquisition device is composed of a vibration table, a vibration control sensor and an impact sensor.

The invention relates to a safety air bag ignition control method and device, computer equipment, a storage medium and a computer program product. The method comprises the steps that the running state of the automobile safety air bag control system is configured through the safety control state machine; under the condition that the running state is the normal state, the ignition function of the automobile safety air bag control system is configured to be in a forbidden state through a safety control state machine; in response to the fact that the automobile safety air bag control system is powered on for the first time and / or a watchdog error is detected, the running state is switched to a watchdog error protection state from a normal state through a safety control state machine; and under the condition that the operation result of the sensor data processing unit exceeds a preset threshold value, the operation state is switched from the normal state to the safety air bag ignition enabling state through the safety control state machine, and the ignition function is switched to the starting state. By adopting the method, the low-delay and high-precision response requirements of the chip on the ignition control instruction can be met.

The invention discloses a high-integration intelligent ignition head device and an automobile safety communication power supply system thereof. The device comprises an input unit, a power management module, a communication module, a communication judgment module, an MCU, a voltage sensing module, a current sensing module, an ignition control module, an ignition element and a substrate, and an environment self-adaption unit, a dual-mode wireless energy supply unit and an optical fiber diagnosis channel can be additionally arranged. The system adopts the device, communicates with a central control unit through a redundant optical fiber bus and a double-wire bus, and further comprises the central control unit, a dynamic topology reconstruction unit and a pre-ignition energy distribution unit. Through digital signal control, multi-dimensional sensing module integration and a double-wire bus topological structure, ignition threshold multi-stage protection, state real-time monitoring and feedback, multi-ignition-head parallel independent control and miniaturized function integration are achieved, and the reliability, the intelligent degree and the driving efficiency of an automobile safety system are improved.

The invention relates to the technical field of wall-hanging stoves, and discloses an ignition control method and device of a wall-hanging stove, a controller and the wall-hanging stove.The ignition control method comprises the steps that when ignition of the wall-hanging stove fails, the valve opening current of a gas proportional valve of the wall-hanging stove is detected, and when the valve opening current is smaller than a preset current threshold value, the valve opening current is increased, and the wall-hanging stove is controlled to execute ignition operation again; when the valve opening current is larger than or equal to the preset current threshold value, the fan rotating speed of the wall-hanging stove is detected; and when the rotating speed of the fan is larger than the preset rotating speed threshold value, the rotating speed of the fan is adjusted to the preset rotating speed threshold value, and the wall-hanging stove is controlled to execute re-ignition operation. According to the method, the valve opening current is firstly adjusted when the execution of the ignition operation fails, so that the ignition success rate of the wall-hanging stove is increased by increasing the air inlet pressure, and the rotating speed of the fan is adjusted when the valve opening current is greater than the preset current threshold value, so that the ignition failure caused by flame separation and fire transfer failure is avoided by reducing the air inlet amount of cold air; the ignition success rate of the wall-hanging stove is improved.

The invention discloses a modular multi-fuel industrial burner plasma igniter with an efficient cooling structure. The modular multi-fuel industrial burner plasma igniter comprises an ignition module, an efficient cooling module, a fuel adaptation module and an intelligent control module. A plasma arc generator is arranged in the ignition module and is used for generating a high-temperature ignition source; the efficient cooling module adopts a multi-layer surrounding type flow channel design, and active heat management of the ignition module is achieved through forced circulation of a cooling medium; the fuel adaptation module supports rapid switching and stable supply of various fuels such as natural gas, fuel oil and biomass gas through standardized interfaces and pipelines; the intelligent control module integrates ignition control, fuel switching and thermal management strategies, monitors the system state in real time and automatically adjusts operation parameters. By means of the modular architecture and the efficient cooling technology, the problems that a traditional plasma igniter is prone to overheating damage, poor in adaptability and difficult to maintain under the high-temperature and multi-fuel working conditions are solved.

A control for a gas fired pool heater is configurable to operate at either a first voltage or a second voltage higher than the first voltage. The control includes an input voltage measurement circuit and an automatic voltage select circuit. The input voltage measurement circuit is configured to be operable for measuring an input line voltage to determine whether the gas fired pool heater unit is connected with the first voltage or the second voltage. The automatic voltage select circuit is configured to be operable for configuring the control for the correct input line voltage as measured by the input voltage measurement circuit.

The invention provides a hybrid power unmanned aerial vehicle system and method based on multistage emergency control, and the system comprises an engine state monitoring and failure detection module which collects the operation parameters of an engine in real time through a vibration sensor, a rotating speed sensor and a temperature sensor; the multi-state machine emergency control module is in communication connection with the engine state monitoring and failure detection module; the intelligent ignition control module is in communication connection with the engine state monitoring and failure detection module and the multi-state machine emergency control module; the VTOL mode conversion control module is in communication connection with the multi-state machine emergency control module; the dynamic energy management unit is in communication connection with the multi-state machine emergency control module; and the navigation and communication interface module integrates a receiver and a multi-mode communication link and is in communication connection with the multi-state machine emergency control module. According to the invention, full-automatic closed-loop processing from engine failure prediction and intelligent restart to multi-mode emergency decision and execution is realized.

The present invention discloses a vehicle and its engine starting control method, device and crankshaft revolution acquisition method. The engine starting control method specifically includes: acquiring the crankshaft position signal of the engine; performing credibility analysis on the crankshaft position signal to obtain a credibility analysis result, the credibility analysis result at least including: the crankshaft signal is credible, the crankshaft signal is uncredible, and the crankshaft signal is converted from credible to uncredible; determining a target recognition strategy according to the credibility analysis result, and determining the number of crankshaft revolutions of the engine according to the target recognition strategy, the target recognition strategy and the credibility analysis result having a one-to-one correspondence; executing starting ignition control according to the number of crankshaft revolutions. The present invention improves the crankshaft position detection accuracy, optimizes the engine ignition and combustion timing, avoids ignition shock caused by improper ignition timing, and improves the starting noise reduction effect by formulating a crankshaft revolution identification strategy under different signal states.

The invention belongs to the technical field of aviation ignition control circuit design, particularly relates to an interactive control circuit for a dual-channel ignition system of an aero-engine, and aims to solve the problems of low reliability, high delay and high reliability caused by dependence on a mechanical relay in the conventional ignition system control circuit. And a traditional electronic scheme is complex in structure and high in cost. The circuit system comprises a first aviation plug, a second aviation plug, a channel I control circuit, a channel II control circuit, an ignition circuit I and an ignition circuit II. The core is that the two aviation plugs receive a power signal and a control signal in a crossed manner, so that an ignition circuit of any channel can be triggered by a corresponding control signal on any aviation plug, and a redundant and mutually-standby interactive control framework is formed.

The invention discloses an ignition control method, device and equipment for a dual-fuel engine and a storage medium. The ignition control method comprises the steps that the engine rotating speed and the engine torque are obtained; determining engine working conditions according to the engine speed or the engine torque; and controlling a spark plug and / or a dual-fuel injector to start according to the engine working condition, the engine rotating speed and the engine torque. According to the technical scheme, the engine rotating speed and the engine torque are obtained, the engine working conditions are determined according to the engine rotating speed or the engine torque, the spark plug and / or the dual-fuel injector are / is controlled to be started according to the different engine working conditions, and different ignition strategies are executed; flexible switching of different ignition modes of spark plug ignition and compression ignition is achieved, and the abnormal combustion problems of CO2 emission, early-burning explosion and the like of the dual-fuel engine are effectively solved.

The utility model relates to an igniter control apparatus. The igniter control equipment comprises an activation isolation power supply module, a working isolation power supply module, a CAN circuit, a processor module, an activation control module, a temperature acquisition module and a temperature sensor, the activation control module comprises a one-out-of-multiple matrix circuit; the control end of the activation isolation power supply module is connected with the processor module, the CAN circuit, the activation control module and the temperature acquisition module are all connected with the processor module, and the temperature acquisition module is connected with the temperature sensor; the activation control module is connected with an external igniter; the igniter control equipment is connected with the upper computer through a CAN bus; the activation isolation power supply module is used for supplying power to an external igniter; and the working isolation power supply module is used for supplying power to the processor module, the temperature acquisition module and the CAN circuit. The equipment realizes electrical isolation of an input power supply, a system power supply and an igniter power supply, and also realizes control of more igniters under the condition of saving hardware interface resources.

The utility model discloses a multi-element accurate proportioning low-temperature brimstone furnace control system, which mainly comprises a central controller, and a data acquisition unit, a fan driving unit, a molten sulfur control unit, a metering pump control unit, an atomization control unit, an ignition control unit, a hearth positive and negative pressure protection unit and a brimstone furnace high and low temperature protection unit which are connected with and controlled by the central controller. The sulfur combustion furnace system automatically and accurately distributes air and sulfur according to the squeezing amount or the flow, the stoving intensity and the like, and the problems that due to the fact that an existing sulfur combustion furnace system is inaccurate in air distribution and sulfur distribution, combustion is insufficient, sublimed sulfur is much, and technological indexes are unstable are solved.

The application discloses a boosting ignition circuit and belongs to the technical field of fuzes. The boosting ignition circuit comprises a main controller, a sinusoidal oscillation circuit, a shaping circuit, a boosting circuit and an ignition control circuit. The boosting ignition circuit solves the technical problem of high reliability of fuze ignition. The boosting ignition circuit is stable and reliable, and double gate control guarantees safety. The boosting ignition circuit can be applied in applications with small ignition current demand.

The utility model relates to an ignition control system for an incandescent light of an acid gas combustion furnace. An inlet of a natural gas cut-off electromagnetic valve is connected with a natural gas pipe network, and an outlet of the natural gas cut-off electromagnetic valve is connected with a natural gas flame arrester; the natural gas flame arrester is connected with an inlet of a natural gas steel wire hose; the natural gas steel wire hose is connected with a natural gas pipe orifice of the incandescent light burner; an inlet of the combustion air cut-off electromagnetic valve is connected with an air pipe network, and an outlet is connected with the combustion air steel wire hose; the natural gas steel wire hose is connected with a natural gas pipe opening of the incandescent light burner, and the combustion air steel wire hose is connected with an air inlet pipe opening of the incandescent light burner. By accurately regulating and controlling the flow ratio of the fuel gas to the combustion-supporting air and adopting the electromagnetic valve for remote control and the temperature sensor for real-time monitoring, the ignition efficiency and safety are remarkably improved, and the ignition failure rate is reduced. The system is simple in structure, convenient to operate and suitable for various acid gas combustion furnaces.

The invention discloses a control distribution method for a spacecraft with an eight-thruster structure, and belongs to the technical field of spacecraft control. The problem that after the number of thrusters of an existing spacecraft is reduced, decoupling control requirements of force / torque in all directions cannot be met is solved. Comprising the steps that eight thrusters are arranged on a spacecraft, so that the eight thrusters are distributed in an axial symmetry mode in a structure installation coordinate system, nozzles face an evasion limiting area, and the axes of the nozzles evade the centroid deviation range of a whole-satellite structure center area; for the combined control of the expected single-axis force and the expected three-axis torque, establishing a relational expression by taking the longest total ignition duration of the four thrusters as a target, and calculating the ignition duration of each thruster; and for combined control of the expected triaxial force and the expected triaxial torque, six thrusters are selected from the eight thrusters to establish a relational expression between the ignition duration and the expected triaxial force and the expected triaxial torque, and the ignition duration of the six thrusters is calculated. The method is used for ignition control of the spacecraft.

The invention discloses an aviation piston engine redundancy ignition system with an electromagnetic shielding function and an ignition method, and particularly relates to the field of engines. Comprising a first control module and a second control module, the two control modules are connected with two ignition coils through high-voltage damping wires respectively, and each ignition coil is connected with a spark plug mechanism through a high-voltage damping wire; the two spark plug mechanisms are arranged on an air cylinder of the engine; a shielding layer is coated outside the high-voltage damping wire; and the spark plug mechanisms are respectively and correspondingly sleeved with shielding shells. Based on the system, redundancy ignition control is adopted, two control modules are used, each control module can control two sets of independent ignition systems at the same time, release electric energy to two ignition coils at the same time, conduct ignition control, and can effectively restrain electromagnetic interference.

The invention discloses an engine ignition control method and a related device, and relates to the technical field of engine control. The engine ignition control method comprises the steps that the actual water content of methanol fuel of a target engine is obtained; adjusting the ignition energy of an ignition coil according to the actual water content so as to perform ignition control on the target engine; wherein the ignition energy of the ignition coil is in positive correlation with the actual water content. The water content of the methanol fuel of the engine can be measured in real time, then the ignition energy of the ignition coil is adjusted according to the water content, the higher the water content of the methanol fuel is, the larger the corresponding ignition energy of the ignition coil is, and therefore the relatively rarefied methanol fuel can be successfully ignited; therefore, stability of combustion in an engine cylinder is guaranteed, and engine power is improved.

To suppress waste of electric power by making energizing time to an ignition coil appropriate.SOLUTION: A reference energization time is determined based on a voltage of a power supply and a rotation speed. On the basis of a condition related to the combustion state of the internal combustion engine, it is determined whether the combustion state of the internal combustion engine is in a relatively stable first operation state or in a relatively unstable second operation state. To judge whether an actual combustion state is good or bad by detecting the actual combustion state of an internal combustion engine. When it is determined that the combustion state is good in the first operation state (time t1), the energization time is largely reduced and corrected from the reference energization time to a predetermined level, and thereafter, when it is determined that the actual combustion state is bad, the energization time is gradually corrected to be longer by a minute amount (time t2, t3). In the second operation state, when it is determined that the combustion state is good, the energization time is corrected to be gradually shortened by a minute amount from the reference energization time.SELECTED DRAWING: Figure 3

The utility model discloses a pilot deflagration ignition device system, which relates to the technical field of petrochemical torch combustion ignition systems, and comprises an incandescent light deflagration ignition pipeline, a pilot deflagration ignition pipeline, a pilot deflagration ignition pipeline and a pilot deflagration ignition pipeline, one end of the deflagration ignition ring pipeline is connected with the deflagration ignition ring pipe; an outlet of the deflagration mixed fuel gas unit is respectively connected with an incandescent light deflagration ignition control valve and an incandescent light deflagration ignition ring control valve, the incandescent light deflagration ignition control valve and the incandescent light deflagration ignition ring control valve are arranged in parallel, the incandescent light deflagration ignition control valve is connected with an incandescent light deflagration ignition pipeline, and the incandescent light deflagration ignition ring control valve is connected with a deflagration ring ignition pipeline; an inlet of the deflagration ignition unit is respectively connected with an air inlet pipe and a fuel gas inlet pipe; the control unit is in control connection with the incandescent light deflagration ignition pipeline, the deflagration ignition ring pipeline, the deflagration mixed fuel gas unit and the deflagration ignition unit; the ignition device system is simple in structure, successful ignition can be completed in a remote automatic or manual mode, and successful ignition can be completed in an on-site automatic or manual mode.

To provide a dust removal system and a dust removal method, which can more reliably remove dust from within a combustor.SOLUTION: A dust removal system comprises two shock wave generation devices each configured so as to generate a shock wave for removing dust in a combustor. The two shock wave generation devices each include: a chamber configured so as to be filled with a mixture containing a fuel and an oxidizing agent; an ignition device for igniting the mixture in the chamber; and a launch unit for using a detonation wave produced by the ignition by the ignition device to launch a shock wave into the combustor. The two shock wave generation devices are arranged so that two shock waves respectively launched from the two launch units reinforce one another due to interference. The dust removal system further comprises an ignition control unit configured so as to send, to each of the two ignition devices, an ignition command for starting ignition.SELECTED DRAWING: Figure 1

The utility model relates to a switch control device for an ignition system of engineering machinery and the ignition system comprising the switch control device. The ignition system comprises an ignition switch and a power switch, and the device comprises a pressure detection mechanism used for detecting the pressure value of at least one seat of the engineering machinery; the idle speed detection mechanism is used for detecting whether an engine of the engineering machinery is in an idle speed working condition or not; the first timer is configured to start timing based on detection results of the pressure detection mechanism and the idle speed detection mechanism; the first control loop is configured to turn off the ignition switch when the timing time of the first timer reaches a first duration; and the second control loop is configured to turn off the power switch when the timing time of the first timer reaches a second duration. The ignition control device can effectively prevent the problem of power shortage caused by continuous discharge of the storage battery in an unmanned use state, and avoids the trouble that the machine cannot be started for the second time due to the power shortage of the storage battery.

The invention relates to a high-reliability ignition control system based on a dual-detection dual-drive mechanism, and belongs to the technical field of hardware circuit design. The test system receives a data stream signal sent by the PC monitoring system through a serial port cable and then sends a response data transmission signal to the high-reliability ignition control system through a communication cable; the high-reliability ignition control system carries out power supply identification signal detection and state identification signal detection, if the high-reliability ignition control system supplies power to a battery and is in a release state, an ignition control process is started, and an ignition voltage signal is fed back to the test system through a communication cable; otherwise, ignition control is not carried out; the test system processes the ignition voltage signal to obtain an ignition voltage value, and inputs the ignition voltage value to the PC monitoring system for display; and the ignition control adopts a double-switch control mode of an electromagnetic relay and a solid relay to realize short circuit and disconnection of an ignition circuit so as to ensure accurate control and high reliability of ignition. The device has the advantages of high safety, high reliability, multi-path ignition control, mistaken ignition prevention and the like.

1. The name of the design product: electronic gas ignition switch. 2. The use of the design product: for gas stove, water heater and other equipment that need electronic ignition control. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 2.

The application provides a kind of ignition chip for igniter and its ignition control method, can prevent ignition device from being triggered by stray current and other external interference, greatly improve the safety, including signal input terminal, digital processing unit, digital processing unit is connected with signal input terminal;Security switch unit is arranged between the signal input terminal and firing resistance, the digital processing unit is connected with the security switch unit;Ignition switch unit includes upper bridge switch tube and lower bridge switch tube, upper bridge switch tube and the lower bridge switch tube are connected with the digital processing unit respectively, the signal input terminal is inputed to the signal input terminal by the digital processing unit, and the upper bridge switch tube and the lower bridge switch tube are controlled;The digital processing unit receives the instruction signal inputed by the signal input terminal, while opening the security switch unit and the ignition switch unit, the signal input terminal and the loop of firing resistance are conducted to ignite.

The invention discloses an automatic ignition control system and method capable of saving fuel gas, and relates to the technical field of accident tail gas treatment in polycrystalline silicon production. The method comprises the steps that S1, tail gas channels are arranged in a graded mode, specifically, accident tail gas emptying airflow is guided to a second-stage or above diffusion channel; 2, incandescent light grading linkage control is conducted, specifically, incandescent light systems of two or more grades are arranged, the number of the incandescent light systems is consistent with the number of the grades of the diffusing channels, each grade of diffusing channel corresponds to one incandescent light, and instrument control valves are arranged on fuel gas pipelines of the incandescent lights and interlocked with pressure signals of an air inlet buffer tank; and S3, graded ignition triggering: when the pressure of the gas inlet buffer tank reaches a pressure threshold value of a corresponding grade, opening an instrument control valve of a fuel gas pipeline of an incandescent light of the corresponding grade in an interlocking manner, and simultaneously triggering a corresponding high-energy ignition gun to act, so that the fuel gas is ignited after entering the incandescent light. An automatic ignition system for silane accident tail gas has the problems of consumption of a large amount of ineffective fuel and high operation cost.

The invention belongs to the technical field of fire extinguishing test systems, and discloses a rapid fire extinguishing test system for explosive fire and a test method thereof.The rapid fire extinguishing test system comprises a storage box, an electromagnetic valve is arranged above the storage box and fixedly communicated with a spray head, and a control mechanism, an ignition mechanism and a water supply mechanism are arranged on one side of the storage box; the control mechanism is used for controlling the electromagnetic valve, the ignition mechanism and the water supply mechanism and detecting whether the gunpowder is burnt or not, and the ignition mechanism is used for igniting the gunpowder; the controller is arranged on one side of the storage box and is in circuit connection with the electromagnetic valve, the ignition mechanism and the water supply mechanism, and the high-speed detector is arranged on one side of the storage box and is in circuit connection with the control mechanism. According to the method and the device, through improvement of the prior art, the optimal fire extinguishing response time can be judged according to different response time, different fire extinguishing water pressures and the residual weight of the gunpowder under different conditions, so that the optimal fire extinguishing scheme is selected, and the fire extinguishing effect is favorably improved.

The utility model relates to the technical field of outdoor stove equipment, in particular to an ignition control device pipeline for an outdoor stove and the outdoor stove, and the ignition control device pipeline comprises a first pipeline and a second pipeline, the first pipeline is specially used for conveying gas, and the second pipeline is provided with a wire passing cavity and specially used for arranging an ignition wire. The independent double-pipeline structural design is adopted and used for gas conveying and ignition wire arrangement, the ignition wire and the gas pipeline are separated, mutual interference of the ignition wire and the gas pipeline can be effectively avoided, the safety and stability of the device are improved, the ignition wire can smoothly penetrate through the design of the wire passing cavity, reasonable wiring is conducted, and the service life of the device is prolonged. By means of the design of the double-pipeline structure, the problems that in traditional integrated design, the size is large and the appearance is not attractive are solved, meanwhile, the portability of the pipelines is improved, the pipelines can be flexibly arranged and fixed according to actual needs, the occupied space of the whole device is reduced, and a user can carry and store the device conveniently.

The utility model relates to the technical field of toy rockets, in particular to a hand-operated power generation type rocket toy which comprises a base, a feeding pipe fitting is arranged on the base, an inner layer structure and an outer layer structure are arranged in the feeding pipe fitting, and a vertically-arranged rocket flying body is installed on the feeding pipe fitting in a sliding mode. The water storage rocket body is communicated with the outer layer structure; the fuel generation structure is communicated with the outer layer structure, and the fuel generation structure is used for forming combustible gas and conveying the combustible gas to the outer layer structure; and the ignition control structure is connected with the inner layer structure and used for igniting combustible gas in the feeding pipe fitting, so that in the rocket flying body launching process, timely and effective pressure relief is conducted on the feeding pipe fitting, and structural materials of the feeding pipe fitting are prevented from being broken under the action of pressure intensity.

To appropriately burn an air-fuel mixture.SOLUTION: A control system S includes: a sensor 4 that is provided in an engine 2 using an air-fuel mixture of natural gas obtained through vaporization of liquefied natural gas containing methane and intake air, and detects a feature amount indicating a combustion state in a combustion chamber of the engine 2 at predetermined intervals; an acquisition section 721 that acquires the feature amount detected by the sensor 4 and a phase in a combustion cycle of the engine 2 corresponding to the feature amount while associating them with each other; a specification section 722 that specifies a maximum phase corresponding to a maximum value of an increase rate of the feature amount on the basis of the plurality of feature amounts detected in one combustion cycle and a phase associated with each of the feature amounts; and an ignition control section 723 that changes ignition timing to the air-fuel mixture so that the maximum phase falls within a predetermined range when the maximum phase is outside the predetermined range set as timing of causing the combustion in the combustion chamber.SELECTED DRAWING: Figure 1