Total Impulse Measuring System for Solid-Propellant Rocket Engine

摘要

The culmination of all efforts in the program was the operational emplacement of a solid propellant total impulse measurement system with a total error less than 0.1% in the thrust range 1500 - 10,000 pounds and propellant burning time range 2 - 10 seconds. The achievement of this objective not only supplied the apparatus needed to obtain significant advances in the field of solid propellant performance deter minations, but also clearly demonstrated that a considerable improvement is realizable in general test stand design, where accuracy of measurements is the primary concern. (Author)