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国际能源材料和化学驱动期刊
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN 打印: 2150-766X
ISSN 在线: 2150-7678

国际能源材料和化学驱动期刊

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i6.60
pages 541-554

MANUFACTURING AND TESTING OF A DUAL-PROPELLANT NOZZLELESS BOOSTER TECHNOLOGY DEMONSTRATOR

Gideon J. van Zyl
Rheinmetall Denel Munition, Western Cape, P O Box 187, Somerset West, 7129, South Africa
Martin Hubinger
Rheinmetall Denel Munition, Western Cape, P O Box 187, Somerset West, 7129, South Africa

ABSTRACT

The total impulse delivered by a nozzleless booster rocket motor is mainly determined by the burning rate and ballistic properties of its propellant. Propellants with low burning rate pressure exponents (n-values) and high burning rates permit significant increases in performance. It is common knowledge that ferrocene-based burning rate catalysts reduces the burning rate pressure exponent and increases the burning rate significantly. Therefore, ballistic properties produced by the ferrocene-grafted HTPB polymer, Butacene®, are highly effective in nozzleless booster motors. However, high burning rate Butacene-based propellants may produce a high initial pressure peak during the ignition phase of the nozzleless booster motor, which may necessitate the use of a stronger and thus heavier motor casing. One way to reduce this high ignition pressure is to design a dual-propellant grain that consists of two concentric propellant layers. A thin inner layer contains a propellant with a slightly lower burning rate, while the much larger outer layer consists of a higher burning rate Butacene-based propellant. In this case, the inner propellant layer consisted of a Fe2O3-based reduced smoke propellant, while the outer layer consisted of a Butacene-based reduced smoke propellant. Formulations and properties of the two propellants used in the manufacturing of the dual-propellant nozzleless booster motor are reported. A good bonding interface between the Butacene and Fe2O3 propellant layers was ensured by application of an isocyanate-based activation coat between the layers. A displacement casting process was used for the manufacturing of the dual-propellant grain. The results of the static test-firing of this nozzleless booster motor showed that the high ignition pressure was reduced by using the dual-propellant design concept.

REFERENCES

  1. Davenas, A., Solid Rocket Propulsion Technology.

  2. Procinsky, I.M. and McHale, C.A., Nozzleless Booster for Integral-Rocket-Ramjet Missile Systems.

  3. Atwood, A.I., Curran, P.O., Price, C.F., Boggs, T.L., and Booth, D., High Pressure Burning Rate Studies of Ammonium Perchlorate (AP)-Based Propellants.

  4. Lessard, P., Beaupré, F., and Brousseau, P., Burn Rate Studies of Composite Propellants Containing Ultra-Fine Metals.


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