Microsecond initiating explosive device ignition current detection circuit based on single operational amplifier

Abstract

The invention provides a microsecond initiating explosive device ignition current detection circuit based on a single operational amplifier. The microsecond initiating explosive device ignition current detection circuit comprises a transient current sampling trigger circuit, a retention time control circuit and a signal retention release circuit which are connected with one another, wherein an output end of the transient current sampling trigger circuit is connected with an input end of the retention time control circuit and an input end of the signal retention release circuit, an output end of the retention time control circuit is connected with the signal retention release circuit; the transient current sampling trigger circuit comprises a current sensor and a trigger circuit; the retention time control circuit comprises an RC time delay circuit and a hysteresis comparison circuit; and the signal retention release circuit comprises an RC circuit, a switching circuit and an operational amplifier circuit. The current detection circuit is sensitive in current tracking, accurate in detection, few in chip, high in reliability and suitable for current detection of the initiating explosive device initiation device of a spacecraft.

Description

technical field [0001] The invention relates to the technical field of current detection circuits, in particular to a microsecond-level pyrotechnic device ignition current detection circuit based on a single operational amplifier. Background technique [0002] In the field of aerospace, it is necessary to use a large number of detonating devices to unlock the important functions of the spacecraft, mainly the unlocking method of pyrotechnics. The reliability of the ignition process of pyrotechnics is of great significance to the reliability of multi-spacecraft missions. The telemetry of the pyrotechnics detonation process by the spacecraft is mainly state telemetry, which cannot effectively reflect the magnitude of the detonation current of the pyrotechnics. According to the differences in battery voltage, loop impedance, pyrotechnic product characteristics, etc., the explosive current generation time ranges from 200us to 10ms, ranging from microseconds to milliseconds, while...

AI Technical Summary

Problems solved by technology

The spacecraft’s telemetry for the initiation process of pyrotechnics is mainly based on state telemetry, which cannot effectively reflect the magnitude of the initiation current of pyrotechnics

According to the differences in battery voltage, loop impedance, pyrotechnic product characteristics, etc., the explosive current generation time ranges from 200us to 10ms, ranging from microseconds to milliseconds, while the spacecraft telemetry acquisition cycle is second level, so the spacecraft It is impossible to directly collect the instantaneous current signal of the ignition process of pyrotechnics

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