MOS tubular ignition circuit for launch control equipment

Abstract

The invention relates to an MOS tubular ignition circuit for launch control equipment and belongs to the technical field of circuit design of the launch control equipment. The ignition circuit comprises an MOS tube, an audion and a resistor. In a non-ignition state, based on the characteristics of the NPN type audion and the MOS tube, an ignition positive voltage signal and an ignition negative output signal are in a disconnection state, an access cannot be formed between the ignition positive voltage signal and an ignition positive output signal, and the resistor between an ignition positiveoutput signal and the ignition negative output signal can provide short-circuit protection for an electro-explosive component; and in an ignition state, accesses are formed between the ignition positive voltage signal and the ignition negative output signal and between the ignition positive voltage signal and the ignition positive output signal, and therefore ignition excitation can be provided for the electro-explosive component. The MOS tubular ignition circuit can accurately and reliably send out ignition control signals to complete ignition control over the electro-explosive component; andthe safety of the electro-explosive component can be effectively guaranteed in the non-ignition state.

Description

technical field [0001] The invention relates to a MOS tube type ignition circuit, in particular to a MOS tube type ignition circuit for a hair control device, belonging to the technical field of a hair control device circuit design. Background technique [0002] The missile launch control system is referred to as the launch control system, and its task is to control the launch preparation and launch process of the missile to ensure the normal and smooth launch of the missile. The launch control system not only judges and confirms the restrictive conditions of missile launch, but also ensures the reliability and safety of missile launch, that is, it needs to ensure that the specified tasks are completed within the specified time, and it is also necessary to ensure that the missiles can be launched in accordance with the correct Launch procedure proceeds. Reliability and safety are both closely related and have certain contradictions, which must be considered comprehensively ...

AI Technical Summary

Problems solved by technology

[0004] Although the above design methods have been proved to be feasible by type tests, there are the following problems: in the pre-launch preparation stage of the missile, the normally closed contact of the relay is controlled by the release state of the internal ignition circuit of the launch control equipment to the missile. The pyrotechnic device protects against the short circuit state

In this state, if the release state control relay fails to work, that is, the two sets of normally closed contacts of the release state control relay respectively connected to the ignition positive and negative circuits do not operate normally, or the release state control relay itself exists When the fault cannot be closed, the ignition circuit cannot be connected normally, and the missile cannot be ignited and launched normally.

Similarly, if the ignition control relay in the ignition circuit fails to work, the two sets of normally open contacts of the ignition control relay connected to the ignition positive and negative circuits respectively do not operate normally, or when the ignition control relay itself is faulty and cannot be closed , the ignition circuit cannot be connected normally, and the missile cannot be ignited and launched normally.

[0005] In addition, because the values ​​of the ignition current are large, in general, when designing the ignition circuit, the device selection will be carried out according to the derating design principle. Since the volume of the electromagnetic relay has a certain relationship with the current-carrying parameters, the volume of the electromagnetic relay selected for the ignition circuit Both are large and in large number, which will cause the launch control equipment to be large in size and heavy in weight to a certain extent, which is inconvenient to be used in portable launch control systems that require volume and weight

Images