Feasibility Demonstration of a Large Impulse Solid Rocket Attitude Control Motor. Volume 1

摘要

A solid propellant propulsion system was designed consisting of individual tape-mounted solid propellant rocket motors, which are fed from a storage container into firing position by means of a stepping motor-driven sprocketwheel. The rocket motors are fired, on command, at any of three positions by a signal from an external electrical source. The operation of a typical system in an attitude control application, is shown schematically. Rocket motor optimization studies show that a rectangular motor configuration with an L/D ratio of 2:1 using a simple flat end-burning grain was optimum to provide minimum weight, volume, and sprocket wheel inertia. The design of the rocket motor was based on a quartz-phenolic base, a pre-molded rubber grain inhibitor, a silicone expandable (E) dome, CWP-13 propellant, and a pyrofuze wire pyrotechnic overspray ignition system. The weight of the WSR-101 rocket motor is .0246 pounds.