The combustion of composite solid propellants was studied using ammonium dichromate, chromium carbonate, chromium oxide, basic copper carbonate and cupric oxide as additives. Burning rates were considerably enhanced in each case. Flame temperatures were measured and found to be higher than in cases
Effect of catalyst concentration on burning rate of composite solid propellants
β Scribed by KISHORE, K.; VERNEKER, V. R. P.; SUNITHA, M. R.
- Book ID
- 125847878
- Publisher
- American Institute of Aeronautics and Astronautics
- Year
- 1977
- Tongue
- English
- Weight
- 523 KB
- Volume
- 15
- Category
- Article
- ISSN
- 0001-1452
- DOI
- 10.2514/3.7466
No coin nor oath required. For personal study only.
π SIMILAR VOLUMES
Various theories [1,2] have been proposed for the pressure dependence of burning rate of composite propellants since a knowledge of this pressure dependence is vital for the design of a solid propellant rocket motor. Recently, Girdhar and Arora [3] have measured the burning rate of phenol-formaldehy
It is assumed thai combustion takes place in the turbulent boundary tay,'~ and that the turbuh,tlt ~lante condsts o/ distorted " [letnwl,'ts" but otheru,ts,, vet,tins on a otob'cular scah' the charact~,ristics o/a laminar l~atne. /| /tat-pb~t,' heat-tran,~/rr ~:orv, latton wah a /actor/or truttspira
## Abstract One of the principal parameters associated with a solid propellant is its linear burning rate. Many attempts have been made in the past to determine theoretically the burning rates of solid propellants by the use of appropriate combustion models. The object of the present paper is to pr
Burning rates of phenol-formaldehyde composite propellants based on NH4CI04, KCIO4, NaNOa, and KNO a oxidisers are measured under the pressure of nitrogen at 1-95 atm. The burning rate laws of the type (P[r) = (a + bP) and (P/r) = (a + bP21 a) are tested. It is revealed that the latter gives a super