Studying the Formulation Effects on Steady-State and Transient Combustion Behavior of Aluminized Propellants
Final rept. 7 Sep 1998-7 Jun 1999
RUSSIAN ACADEMY OF SCIENCES NOVOSIBIRSK INST OF CHEMICAL KINETICS AND COMBUSTION
Pagination or Media Count:
A new approach based on use of special super heterogeneous propellants that generate during combustion the model agglomerates with given reproducible size and structure has been elaborated for study of model agglomerate evolution. The experiments with agglomerates of 395540 micron size and initial aluminum content 42.6 were carried out in pressure range 1-80 atm. The characteristics of condensed combustion products CCP were measured via sampling technique at pressure 46 atm argon or nitrogen for 12 metalized propellant formulations manufactured using well characterized ingredients. All compositions were based on energetic binder 20. They included totally 18 aluminum commercial or ultra fine particles in various proportion and contained AP or AP and HMX as oxidizer. The replacement of commercial aluminum by electrically exploded aluminum Alex lead to increase of burning rate, decrease of agglomerate mass and increase of metal conversion completeness. All propellant formulation exhibited very effective aluminum conversion total unburnt aluminum content in CCP did not exceed 9. The listed trends are mostly expressed in combustion of HMX containing propellants and even small additive of Alex AlexAl 8.391.7 gives sizable effect. For oxide particles in the size range 0.5-100 microns the typical three-peak structure of mass size distribution was found. The replacement of aluminum by Alex and using argon instead of nitrogen affects slightly the CCP size distribution. Thermal decomposition of different types of the binders and mixtures modeling the pocket matter was investigated at low 10 Kmin and fast 450 Kmin heating rate. Data obtained are not sufficient to make clear the cause of difference in agglomeration behavior for propellant formulations based on these types of binders.
- Combustion and Ignition
- Solid Rocket Propellants