Abstract: A controlled rectifier firing circuit for the warhead of a missile located n a rocket powered test sled traveling along a track in a target vulnerability test range. The firing circuit includes a silicon controlled rectifier which when rendered conductive discharges a capacitor to fire a warhead detonator. A relatively high voltage DC source is coupled to the capacitor prior to sled travel toward the target. A second capacitor is also charged from the high voltage source and discharges through a resistance when an impact type actuator switch is closed at the time of detonation. The voltage developed across the resistor is coupled to the gate electrode of the silicon controlled rectifier which renders it conductive, causing the first capacitor to discharge through the detonator to fire the warhead.

Abstract: The invention involves the design of a miniaturized piezoelectric pressure ransducer used for measuring pressure-time characteristics in gun tubes during the propellant ignition and burning process. The transducer utilizes a Z-cut tourmaline crystal as the piezoelectric pressure sensing element which produces a finite amount of electrical charge (normally expressed in picocoulombs) for a given change in pressure. The tourmaline crystal is incapsulated in a mechanical fixture which provides means for mounting in the gun tube. Electrical terminals are provided for connnecting to signal conditioning and recording instrumentation. Insulators are provided for electrically insulating the pressure sensing element from weapon ground.