Abstract: A recess or cavity is formed on the exterior of a fuze ogive. A piezo-eleic tape is positioned within the cavity or recess. Fluctuations in the pressure within the recess, caused by air flow over the exterior of the fuze, will cause the piezo-electric tape to produce an electrical signal or current.

Abstract: A null adjustable vortex rate sensor which enables the precise control and elocation of the stagnation point of the fluid stream with respect to the null line of the pickoff located within said chamber. The null adjustable vortex rate sensor is a vortex rate sensor with a fixed position pickoff and a fixed position drain, a rod being concentrically located in the drain and extended from the drain into the chamber. The horizontal adjustability of this rod inside the drain controls the location of the stagnation point at the pickoff within the chamber very precisely thus enabling one to approximately choose the location of the pickoff member and by means of the rod mechanism located in the drain move and adjust the stagnation point to obtain a null output at the fixed position of the pickoff. The pickoff provides a differential pressure signal which is a function of the angular rate of rotation of the chamber in inertial space.

Abstract: In an electronic version of the present invention, the potentiometer is cected to an aircraft control stick for sensing the position thereof. The output is coupled to logic circuits that detect the position of the control stick, associated with a severe maneuver about the pitch axis. Such detection actuates a valve for preinflation of a G-suit. Additional logic circuits are provided for detecting when the rate of control stick movement exceeds a preselected threshold. This, also corresponds with a severe maneuver about the pitch axis of the aircraft and also serves to actuate the G-suit valve. Analogous fluidic components may be utilized to effectuate equivalent operation of the G-suit.