ASRM propellant and igniter propellant development and process scale-upA program of formulation and process development for ANB-3652 motor propellant was conducted to validate design concepts and screen critical propellant composition and process parameters. Design experiments resulted in the selection of a less active grade of ferric oxide to provide better burning rate control, the establishment of AP fluidization conditions that minimized the adverse effects of particle attrition, and the selection of a higher mix temperature to improve mechanical properties. It is shown that the propellant can be formulated with AP and aluminum powder from various producers. An extended duration pilot plant run demonstrated stable equipment operation and excellent reproducibility of propellant properties. A similar program of formulation and process optimization culminating in large batch scaleup was conducted for ANB-3672 igniter propellant. The results for both ANB-3652 and ANB 37672 confirmed that their processing characteristics are compatible with full-scale production.
Document ID
19930065891
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Landers, L. C. (Aerojet, ASRM Div., Sacramento CA, United States)
Booth, D. W. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Stanley, C. B. (Aerojet, ASRM Div., Iuka MS, United States)
Ricks, D. W. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 93-2055
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit