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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005353
pages 335-346

ENHANCEMENT OF COMPOSITE PROPELLANT IGNITION CHARACTERISTICS BY SURFACE ABRASION

Jacquie Hewson
Rocket Systems Engineering, Bristol Aerospace Limited, Rockwood Propellant Plant, 660 Berry Street, Winnipeg, MB, Canada R3C 2S
Robert Le Neal
Rocket Systems Engineering, Bristol Aerospace Limited, Rockwood Propellant Plant, 660 Berry Street, Winnipeg, MB, Canada R3C 2S

要約

During curing of composite solid rocket motor propellants, the propellant polymer tends to accumulate as a thin film adjacent to the mandrel used to form the internal bore of the propellant grain. This binder-rich layer coats the ammonium perchlorate crystals on the propellant surface and may inhibit flame propagation during rocket motor ignition. Poor flame propagation during ignition can affect both ignition performance and the reliability characteristics. Abrasion of the solid propellant bore surfaces to remove the binder-rich layer and expose the ammonium perchlorate oxidizer is a common procedure used to enhance rocket motor ignition. Abrasion of the propellant bore was evaluated as a means to enhance the ignition performance and reliability characteristics of Bristol 2.75-in. CRV7 rocket motors. Techniques were developed using wire brushes to scrub the surface of the propellant bore. Automated production processes were developed to provide uniform abrasion of the propellant surface, resulting in consistent enhancement of the rocket motor ignition characteristics. This paper describes the development of the CRV7 propellant bore abrasion process, and describes the results of the testing performed to quantify the effect of propellant abrasion on the rocket motor ignition characteristics.

キーワード: propellant, ignition, rocket

参考

  1. Carr, C. E. and Thomas, M. J. , Factors influencing BKNO3 igniter performance.

  2. Hewson, J. , CRV7 C15 bore scrubbing qualification final report.

  3. Hewson, J. , Evaluation of CRV7 C17 ignition thrust requirements.

  4. Judge, M. , Ignition characterization of Black Brant Mk1 solid propellant.

  5. Mayor, L. , CRV7 C15 Delayed Release Investigation.

  6. Norrie, K., Judge, M. D., Ford, K. P., Curran, P. O., and Atwood, A. I. , Design of a robust high altitude rocket motor igniter.

  7. Ramohalli, K. , Parametric study of igniter design and application to low smoke solid rockets.


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