5results about How to "Improve ignition reliability" patented technology

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.

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.

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.