HOT GAS SERVO CONTROL SYSTEM FOR MISSILES. SUPPLEMENT I.
Abstract
This report culminated activities on the Hot Gas Servo Control System for Missiles. The initial development program provided a system and or components suitable for a high performance rotary or linear fin actuator system or ginballed nozzle actuators. The follow on program expounded upon the reliability of the heart of the system; namely the vane motor and servo valve, discussed material selection and dwells at long length on system dynamic capabilities and system weight for a wide rane of gaseous systems. The reliability testing has demonstrated that this pneumatic system has successfully overcome the previously so called pneumatic lubrication limitations. By the use of dry film lubrication the complete servo has run continuously for 600 minutes at 25% max load and 90% max speed. Life capabilities far in excess of envisioned 1 min. to 10 minute glights have now been demonstrated. The reliability of the servo valve was demonstrated by operating the unit in excess of 500,000 cycles. Thus, the servo has demonstrated maintenance free reliable operation. The alternate materials evaluation study, shows how through the use of thermal insulation and isolation, the initial exotic materials (example Haynes Alloy 25) may be substituted with conventional materials (CRES 416). The weight and energy study shows quantitative data on complete pneumatic fin actuator control systems for a wide range of envisioned applications. The study shows system weight cross-over points for cold gas and hot gas systems.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1966
- Accession Number
- AD0486770
Entities
People
- C. Cole
- E. Cohens
- P. Ochs
- R. Bosworth