Pressure dependence of burning rate of ammonium perchlorate-hydrocarbon binder solid propellants

Friction sensitivity of composite propellants and their ingredients is of significant interest to mitigate the risk associated with the accidental initiation while processing, handling, and transportation. In this work, attempts were made to examine the friction sensitivity of passive binder: Hydroxy Terminated Polybutadiene/Aluminium/Ammonium Perchlorate and active binder: (Polymer + Nitrate Esters)/Ammonium Perchlorate/Aluminium/Nitramine based composite propellants by using BAM Friction Apparatus. As per the recommendation of NATO standard STANAG–4487, the friction sensitivity was assessed by two methods: Limiting Frictional load and Frictional load for 50% probability of initiation (F50). The test results showed that the active binder based formulations were more vulnerable to frictional load as compared to the formulations with passive binders. Examination of a comprehensive set of propellant compositions revealed that the particle size distribution of Ammonium Perchlorate and burn rate catalysts were the most influential factors in dictating the friction sensitivity for HTPB/Al/AP composite propellants. For active binder/AP/Al/Nitramine composite propellants, the formulation with RDX was found more friction sensitive with a sensitivity value of 44 N as compared to its HMX analog (61 N). The correlation studies of friction sensitivity, burning rate, and thermal decomposition characteristics of HTPB/Al/AP composite propellants is described.

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Pressure dependence of burning rate of composite solid propellants

AIAA Journal ◽

10.2514/3.7542 ◽

1979 ◽

Vol 17 (2) ◽

pp. 223-224 ◽

Cited By ~ 1

Author(s):

R. P. Rastogi ◽

H. J. Singh ◽

A. K. Srivastava

Keyword(s):

Burning Rate ◽

Pressure Dependence ◽

Solid Propellants ◽

Composite Solid Propellants ◽

Composite Solid

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Comment on "Pressure Dependence of Burning Rate of Composite Solid Propellants"

AIAA Journal ◽

10.2514/3.61103 ◽

1979 ◽

Vol 17 (2) ◽

pp. 222-223

Author(s):

Carl W. Nelson ◽

George F. Adams ◽

J. Richard Ward

Keyword(s):

Burning Rate ◽

Pressure Dependence ◽

Solid Propellants ◽

Composite Solid Propellants ◽

Composite Solid

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Pressure Dependence of Burning Rate of Composite Solid Propellants

AIAA Journal ◽

10.2514/3.60922 ◽

1978 ◽

Vol 16 (5) ◽

pp. 534-536 ◽

Cited By ~ 5

Author(s):

R.P. Rastogi ◽

H.J. Singh ◽

Desh Deepak ◽

A.K. Srivastava

Keyword(s):

Burning Rate ◽

Pressure Dependence ◽

Solid Propellants ◽

Composite Solid Propellants ◽

Composite Solid

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Combustion stability analysis of composite propellants with octogen

Scientific Technical Review ◽

10.5937/str2002022b ◽

2020 ◽

Vol 70 (2) ◽

pp. 22-28

Author(s):

Marica Bogosavljević ◽

Slavko Mijatov ◽

Aleksandar Milojković ◽

Vesna Rodić

Keyword(s):

Stability Analysis ◽

Burning Rate ◽

Ammonium Perchlorate ◽

Oxide Powder ◽

Combustion Stability ◽

Operating Pressure ◽

Solid Propellants ◽

Rate Laws ◽

Composite Solid Propellants ◽

Composite Solid

Research of operating pressure levels with irregular combustion and the effect on combustion instability of composite solid propellants with different quantity of octogen (HMX) are presented in this paper. The content of HMX increased in relation to the oxidant, ammonium perchlorate (AP). Combustion stability of the propellants was improved by adding titanium (IV) oxide powder and through the optimal projected ratio of two oxidizer fractions. Parameters of burning rate laws were determined and p-t diagrams were observed and compared.

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