Calculation study on burning rate characteristics of AP/RDX/HTPB propellants

Tuijin Jishu/Journal of Propulsion Technology

Volumn 18, Issue 4, 1997, Pages 75-79

  Zhang, Wei ^a   Zhu, Hui ^a   Liu, Wenyuan ^a  

^a NATIONAL UNIVERSITY OF DEFENSE TECHNOLOGY   (China)

Author keywords

Burning rate; Combustion chemical kinetics; Composite propellant; Nitramine propellant

Indexed keywords

CALCULATIONS; COMBUSTION; REACTION KINETICS;

BURNING RATE; COMPOSITE PROPELLANT; NITRAMINE PROPELLANT;

SOLID PROPELLANTS;

EID: 0031200009     PISSN: 10014055     EISSN: None     Source Type: Journal    
DOI: None     Document Type: Article

References (5)

1. Kuwahara T, Kubota N. Combustion of RDX/AP composite propellants at low pressures. J Spacecraft, 1984, 21(5): 502
2. Cohen N S, Strand L D. Nitramine propellant research. AD-A033034, 1976
3. Cohen N S, Price C F. Combustion of nitramine propellants. J Spacecraft, 1975, 12(10): 608
4. Beckstead M W, Derr R L Price C F. A model of composite solid propellant combustionn based on multiple flames. AIAA J, 1970, 8: 2200