14results about How to "Improve ignition reliability" patented technology

The invention relates to a low-pressure ignition device and method for a torch in a thrust chamber of an open circulating liquid rocket engine. The ignition device comprises a cylindrical ignition chamber, an ignition fuel conveying system and an ignition oxidant conveying system, the ignition chamber is used for being arranged in a thrust chamber of the rocket engine, one end of the ignition chamber is open, the other end of the ignition chamber is provided with an igniter, and the outer surface of the ignition chamber is provided with a fuel runner and an oxidant runner in the axial direction. At least one group of fuel spray holes and oxidant spray holes are formed in the inner wall of the other end of the ignition chamber, the ignition fuel conveying system is communicated with one end of the fuel runner, the fuel spray holes are communicated with the other end of the fuel runner, the ignition oxidant conveying system is communicated with one end of the oxidant runner, and the oxidant spray holes are communicated with the other end of the oxidant runner. The method has the advantages that the ignition reliability of the liquid rocket engine is improved, the complexity of an ignition system is simplified, the reliability of the ignition process of the liquid rocket engine is improved, meanwhile, the system composition is simplified, the reliability of the system is improved, and the cost of the system is reduced.

This invention discloses a safe fragmentation grenade with a quasi-spherical integrated detonation and warhead structure, consisting of a fragmentation warhead and a safe delayed-detonation fuse arranged along the warhead's axis. The fragmentation warhead includes a lower body, an upper body, a lower explosive ring, and an upper explosive ring. The safe delayed-detonation fuse is a delayed-detonation fuse with spatial explosion-proof, redundant safety, and explosive handling characteristics, including a detonator base, a flame detonator, a support tube, an impact delay cap, a firing pin, a firing spring, a detonating charge, a sleeve, a pull pin, a pull ring, a safety ball, and a nut. The upper and lower bodies are also the main structural components of the fuse. The integrated detonation and warhead structure is not a simple stacked structure, resulting in a small size and light weight. The nut encloses the pull pin and pull ring, replacing the traditional grip, resulting in a smooth surface and good safety during service and tactical maneuvers. With an outer contour close to a sphere and a center of mass located at the center, its air resistance characteristics are independent of flight attitude, ensuring a stable trajectory, controllable impact point, and long throwing distance.

The application discloses a kind of ammonia catalytic combustion system and combustion control method, its system includes combustion chamber, catalyst chamber, air chamber and feed pipe;Combustion chamber upper end is equipped with flue gas outlet, lower end surface is fixedly connected bearing plate;Catalyst chamber is installed in the inside of combustion chamber, and the inner wall of combustion chamber and the outer wall of catalyst chamber are enclosed to form combustion space;Catalyst bed is arranged in the inside of catalyst chamber, and a plurality of injection holes are formed in side wall;The inside of air chamber is air cavity, and air inlet is formed in lower end;The bearing plate is penetrated and formed with multiple groups of air flow holes;The feed pipe is inserted into air cavity from the bottom center of air chamber, vertically extends to the top of catalyst chamber, and the top outlet of feed pipe and the top cover between the top of catalyst chamber are reserved ventilation gap.The beneficial effects of the present application are that: combustion chamber, catalyst chamber, air chamber coaxial integrated nested structure, without independent external cracking device, external hydrogen supply system, whole machine height integration, reduce hardware investment and operation cost.

The invention belongs to the technical field of electric initiating explosive devices, and particularly relates to an electric ignition part of a redundant ignition structure. Comprising an electrode plug body made of a ceramic material, the electrode plug body is provided with two independent cylindrical charging chambers which are symmetrical about the axis of the electrode plug body, the two charging chambers are separated by ceramics, all medicaments can be wrapped in the ceramics of the electrode plug body through the charging chambers, only the tops of the charging chambers are open, and each charging chamber is provided with a contact pin. Metalized layers are arranged on the bottom surface of the electrode plug main body and are communicated with each group of contact pins, and a thermistor NTC is arranged between the two metalized layers; an electrostatic discharge tip air gap is formed between the metallization layer and the outer circle of the electrode plug body, and the discharge position between an electric ignition part bridge circuit and the metal shell is converted to the bottom face of the electrode plug under the electrostatic high voltage. According to the electrostatic ignition device, the ignition reliability is improved, the problem of electrostatic ignition between independent charging chambers is solved, and the electrostatic ignition device can be adapted to various electric initiating explosive devices with the diameter not smaller than phi 8.7 mm and the height not smaller than 10.7 mm.

The application discloses an aviation piston engine redundant ignition system with an electromagnetic shielding function and an ignition method, and particularly relates to the field of engines. The system comprises a first control module and a second control module, two control modules are connected with two ignition coils through high-voltage damping lines, each ignition coil is connected with a spark plug mechanism through a high-voltage damping line, two spark plug mechanisms are arranged on a cylinder of the engine, the high-voltage damping line is coated with a shielding layer, and the spark plug mechanism is correspondingly sleeved with a shielding shell. Based on the system, redundant ignition control is adopted, two control modules are used, each control module can control two independent ignition systems at the same time, electric energy is released to two ignition coils at the same time, ignition control is performed, and electromagnetic interference can be effectively inhibited.

The present invention relates to the technical field of energy conversion, and in particular to an ammonia plasma ignition burner and a combustion method, comprising an ammonia plasma igniter, an injection box, an ammonia supply device and a diverter, wherein the diverter comprises an injection module and a heat recovery channel; the injection module is connected to the front side of the injection box and communicated with the inner cavity of the injection box, and the ignition zone can preheat the injection module and ignite the ammonia output by the injection module to the combustion zone; the heat recovery channel communicates the inner cavity of the injection box and a first combustion chamber, so that the ammonia in the inner cavity of the injection box flows back to the first combustion chamber and is ignited, and the beneficial effect is that the ammonia plasma igniter plays an ignition role in the initial stage of combustion, and when the ammonia in the injection box can reach the temperature of autonomous combustion, it still maintains self-sustaining combustion after the ammonia plasma ignition burner is turned off, thereby ensuring the reliability of the ammonia plasma ignition burner.

A multi-start carrier power system, the design includes the power system architecture of the main power module, the auxiliary power module and the supercharged delivery module, the reusable carrier power scheme, the unified propellant type used by the main and auxiliary power systems, the simplified carrier power system, the improved reusable maintenance of the carrier power system, the realization of the multi-start function and the start number not limited by the starting device, with the multi-start, multi-reuse ability, while reducing the difficulty of power architecture design, the internal design optimizes the layout space, which simplifies the ignition system, improves the ignition reliability and stability, and the ignition number is not limited.

The invention relates to the technical field of diesel generators, in particular to an ultra-light diesel generator set and a working method thereof, and the ultra-light diesel generator set comprises an oil tank, an oil pump, an electronic control unit, a starter set, an engine and a generator connected to the output end of the engine; the oil inlet end of the oil pump extends into the bottom of the oil tank inner cavity; the other end of the oil pump is connected with an oil inlet pipe; an oil injector is connected between the oil inlet pipe and the engine; a pulse cracker is connected in the oil sprayer; the starter unit, the generator and the oil pump are all electrically connected to the electronic control unit. And a plasma ignition head is arranged on the engine. When the device is used, the device is high in low-temperature adaptability, high in starting and response speed, high in efficiency, high in reliability and more convenient to carry.

The invention relates to a high-voltage pulse deburring device and a using method thereof, and belongs to the technical field of electric vacuum device manufacturing, the high-voltage pulse deburring device comprises an ignition power supply unit, a pulse modulation and boosting unit, an energy power supply unit, a pulse forming network, a detection power supply unit and an output terminal, high-voltage ignition pulses are modulated by the pulse modulation and boosting unit; the energy power supply unit outputs a second direct-current voltage; and the detection power supply unit outputs a third direct-current high voltage and cooperates with the double-range leakage current detection meter to perform a withstand voltage test. According to the invention, the functions of ignition, ablation and detection are integrated, and the deburring process which is efficient, energy-saving, accurate and controllable in energy, free of damage to electrodes and simplified in process is realized through ignition and ablation separation design, pulse width and hot melting time constant matching, automatic switching of circuit isolation devices and safe interlocking of a control unit.

The present application belongs to the field of gas stoves, and discloses an igniter discharge method and device. The method comprises: obtaining the current power supply voltage of the DC power supply in the current ignition cycle; determining the initial duty cycle and target duty cycle step of the pulse width modulation PWM signal output to the boost energy storage circuit according to the current power supply voltage; starting from the first PWM cycle, determining the target duty cycle corresponding to the current PWM cycle according to the initial duty cycle, the target duty cycle step and the cycle sequence number of the current PWM cycle, and outputting the PWM signal of the target duty cycle to the boost energy storage circuit to detect the energy storage voltage; if the detected energy storage voltage is greater than or equal to the energy storage voltage threshold or the target duty cycle reaches the preset duty cycle threshold, then in each subsequent PWM cycle, outputting the PWM signal of the target duty cycle to the boost energy storage circuit until the detected energy storage voltage reaches the discharge voltage. The present application can control the ignition frequency of the gas stove within a suitable range.

The invention discloses a rotary detonation engine test system which is composed of a methane gas cylinder (1), a methane pipeline A (2), an electromagnetic valve A (3), a methane pipeline B (4), an electromagnetic valve B (5), a methane pipeline C (6), an oxygen gas cylinder (7), an oxygen pipeline A (8), an electromagnetic valve C (9), an oxygen pipeline B (10), an electromagnetic valve D (11), an oxygen pipeline C (12), an igniter (13), a pressure sensor (14) and a rotary detonation engine (15). The igniter (13) is a plasma igniter, is installed on the rotary detonation engine (15) and is used for igniting mixed gas of methane and oxygen entering the rotary detonation engine (15). The pressure sensor (14) is a water-cooled high-frequency pressure sensor and is used for measuring explosive wave pressure in the rotary detonation engine (15).

The invention discloses an engine control method and an engine. The engine control method comprises the steps that according to the residual amount of waste gas in a pre-combustion chamber this time, whether the set starting scavenging crank angle during next scavenging and the set scavenging crank angle variable amount during next scavenging are adjusted or not is determined; starting a scavenging crankshaft rotation angle according to the set scavenging crankshaft rotation angle and the set scavenging crankshaft rotation angle variation during the scavenging; the set limit start scavenging crank angle range and the set limit scavenging crank angle variation range adjust the set start scavenging crank angle during next scavenging and the set scavenging crank angle variation during next scavenging. By adjusting the set starting scavenging crank angle during next scavenging and the set scavenging crank angle variation during next scavenging, the pre-combustion chamber can be accurately and efficiently scavenged subsequently, so that the scavenging quality is effectively improved, and the ignition efficiency and the ignition reliability of igniting fuel gas in the pre-combustion chamber can be effectively improved.

The invention belongs to the technical field of engine control, and particularly relates to an ignition oil supply method and device based on oil-gas ratio control, and the method comprises the following steps: S1, calculating an initially set oil supply flow according to a given equivalent oil-gas ratio and inlet pressure of a combustion chamber, and supplying oil to the combustion chamber as an oil supply given value; s2, the actual equivalent oil-gas ratio is calculated according to the actual oil supply flow of the current period and the inlet pressure of the combustion chamber; s3, when the actual equivalent oil-gas ratio is larger than the given equivalent oil-gas ratio, the oil supply given value is reduced according to the set oil supply change rate, and otherwise, the oil supply given value is increased according to the set oil supply change rate; and S4, in the process of increasing the oil supply given value, when the actual equivalent oil-gas ratio of the current period is smaller than the given equivalent oil-gas ratio and the actual equivalent oil-gas ratio of the current period is larger than or equal to the given equivalent oil-gas ratio, the engine is ignited. The ignition reliability of the engine is improved.

This invention relates to the field of rocket engine testing technology and discloses a method for handling hazardous media, comprising: setting a first and a second field torch above the thrust chamber of the rocket engine, and setting a third field torch below the thrust chamber; the first, second, and third field torches are adapted to ignite the hydrogen-oxygen mixture discharged before the pre-combustion chamber ignites; a fourth and a fifth field torch are respectively arranged to the left and right of the thrust chamber of the rocket engine; the fourth and fifth field torches are adapted to ignite the hydrogen-rich gas discharged after the pre-combustion chamber ignites; both the hydrogen-oxygen mixture and the hydrogen-rich gas are hazardous media. This application, by setting five field torches and using field ignition, can promptly ignite the hazardous media discharged from the thrust chamber outlet of the rocket engine, safely handle the hydrogen-oxygen mixture and hydrogen-rich gas, and meet the safety testing requirements of rocket engines.