DEVELOPMENT OF A PURE FLUID MISSILE CONTROL SYSTEM.
Abstract
This report summarizes the complete efforts within the Army Inertial Guidance and Control Laboratory on the development of pure fluid missile control systems. Specific objectives of the program, which is a continuation of previous efforts, are to: (1) develop, test, and evaluate a pure fluid directional control system applicable to an artillery rocket system; and (2) develop, test, and evaluate an improved roll control system using fluid components. Computer studies indicate that a spinning missile with proportional attitude control would have minimum crossrange velocity and position at burnout for the directional control system. A two-degree-of-freedom gyro, with pneumatic spin up and pickoffs, is under development. The pickoff has been tested and the results are presented. A rather detailed discussion of the simulation and gyro development is presented. Proportional amplifiers have been staged with little attenuation in gain, and some of the problems of staging standard units are discussed. Pulse duration modulators have been built. A three pound force valve was mounted on a 200 pound thrust nozzle to test the effectiveness of cold gas, exit plane secondary injection. In this case, the combination reaction control/secondary injection mode did not appear to offer any significant advantage over straight reaction control. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 13, 1965
- Accession Number
- AD0478880