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Erschienen in:
Study of a Concept of Energetic Materials Consisting of a Solid Fuel Matrix Containing Liquid Oxidizer Kapitel lesen Erstes Kapitel lesen

2020 | OriginalPaper | Buchkapitel

11. Survey of Low-Burn-Rate Solid Rocket Propellants

verfasst von : Adam Okniński, Paweł Nowakowski, Anna Kasztankiewicz

Erschienen in: Innovative Energetic Materials: Properties, Combustion Performance and Application

Verlag: Springer Singapore

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Abstract

This chapter presents the topic of low-burn-rate composite solid rocket propellants. While the majority of presently developed systems require high burn rates, several applications benefit from propellants with decreased regression rates. This includes solid rocket motors as well as gas generators. Background descriptions of the general aspects that impact on the burn rate of composite propellants are provided. Focus is given to means that enable obtaining low regression rates. While operational chamber pressure and grain temperature enable burn rate adjustment, they are in a relatively narrow range for most applications. Temperature cannot be arbitrarily set because it is defined by the firing conditions for a given composition. As for pressure, its decrease leads to loss of performance and has a strong impact on the overall motor design, and may have to be avoided. Internal flow field optimization and inhibiting heat transfer into the propellant grain is also significant. However, for the most demanding applications, limiting or preventing propellant erosion is not a sufficient solution. Most importantly, burn rate moderation can be done via the use of coolants, which serve as the most popular burn rate suppressants. Over 100 additives, which were investigated worldwide are listed. Methods enabling burning moderation include influencing the kinetics of decomposition of the oxidizer and binder regression. Moreover, oxidizer particle size and packing are significant. Bimodal and trimodal oxidizer distributions are typically used. Particle dimensions, but also shape, impact on combustion. Also fuel particle size, shape, surface area and surface finishing are important for the regression rate. Furthermore, the use of alternative oxidizers to ammonium perchlorate may be considered. Challenges in development of low-burn-rate propellants are discussed. This includes obtaining necessary properties, performance and meeting system-level requirements for various applications. A review of historical developments of low-burn-rate propellants is given with information on the most recent advances. Compositions, their burn rate and performance, are discussed. Moreover, the impact of several low regression rate propellants on solid rocket motor design is provided. This includes material oxidation, nozzle erosion and expected heat loads. Finally, an outlook on further low-burn-rate propellant development and utilisation is given.

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Vorheriges Kapitel Recent Achievements and Future Challenges on the Modeling Study of AP-Based Propellants
Nächstes Kapitel Burning Rate of PVC—Plastisol Composite Propellants and Correlation Between Closed Vessel and Strand Burner Tests Data
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Metadaten
Titel
Survey of Low-Burn-Rate Solid Rocket Propellants
verfasst von
Adam Okniński
Paweł Nowakowski
Anna Kasztankiewicz
Copyright-Jahr
2020
Verlag
Springer Singapore
Buch
Innovative Energetic Materials: Properties, Combustion Performance and Application

Print ISBN: 978-981-15-4830-7

Electronic ISBN: 978-981-15-4831-4

Copyright-Jahr: 2020

DOI
https://doi.org/10.1007/978-981-15-4831-4_11