Depressurization Extinguishment of Composite Solid Propellants: Flame Structure, Surface Characteristics, and Restart Capability

Steinz, J. A.; Selzer, H.

doi:10.1080/00102207108952268

Cited by 25 publications

(3 citation statements)

References 10 publications

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“…[70][71][72]. They showed that, regardless of the depressurization rate, the flame intensity (as seen by spectral emissions from OH, NH, CN, Na lines and carbon continuum) falls to zero soon after the impact of the first rarefaction wave on the burning surface.…”

Section: 12-experimental Results On Dynamic Extinction By Fast Depmentioning

confidence: 99%

Nonlinear Burning Stability of Solid Propellants.

Luca¹,

Riva²,

Zanotti³

1983

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Section: 12-experimental Results On Dynamic Extinction By Fast Depmentioning

confidence: 99%

Nonlinear Burning Stability of Solid Propellants.

Luca¹,

Riva²,

Zanotti³

1983

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“…Rapid depressurization was implemented where mechanisms to open extra ports or to increase the throat area that achieve rapid pressure drop were applied [11,12,13,14]. Both mechanisms necessitate the use of explosive devices namely, explosive bolts, and pyrotechnic valves to achieve the instantaneous depressurization [15,16].…”

Section: Introductionmentioning

confidence: 99%

A novel in-flight thrust modulation technique for SPRM: proof of concept

Abdelraouf,

Mahmoud,

Al-Sanabawy

2023

J. Phys.: Conf. Ser.

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Thrust modulation (termination or reduction) is one of the most sophisticated topics in rocket motors. Thrust termination is employed when combustion must be terminated to ensure proper stage separation, to avoid motor explosion, to attain certain range, or for research purposes. While liquid and hybrid propellant rocket motors have the ability to extinguish thrust, thrust termination in solid propellant rocket motors (SPRMs) need the use of specialized technology. In-flight thrust termination of (SPRMs) can be achieved by sudden and sufficient increase in throat area. Increasing throat area causes high depressurization rate which consequently leads to extinguishing the rocket motor. In contrast, in-flight thrust reduction can be theoretically attained either by reducing chamber pressure to a new equilibrium level or by reducing the divergent section length. The objective of the present paper is to prove the concept of using Linear Shaped Charge (LSC) for thrust modulation; a technique novel to SPRM applications. Thrust termination concept is proved via a set of static firing tests on a standard test motor. In addition, a mathematical model is developed to predict the drop in thrust due to cutting the nozzle at any arbitrary location. The model is validated by comparing with published experiments for thrust termination and reduction. A parametric study is conducted based on model results. It is confirmed that by cutting the nozzle along its divergent section, thrust reduction less than 20% can be attained. Further reduction can be achieved by cutting the nozzle along its convergent section.

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“…5 sideways sandwich (homogeneous binder and oxidizer slabs) condensed-phase geometry enables item (g) predictions ¡ a signi¦cant development ( [45] provides a linearized version of [25]). Unfortunately, the sandwich homogeneous slabs preclude BS AP depletions observed in Steinz and Selzer£s [34] rapid depressurization experiments. Therefore, these heterogeneous propellant models instan-taneous mass burning rate and §ame temperature predictions cannot be robust for either linear or nonlinear processes.…”

Section: Critical Literaturementioning

confidence: 99%

Heterogeneous propellant internal ballistics: criticism and regeneration

Glick

2011

Progress in Propulsion Physics

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Although heterogeneous propellant and its innately nondeterministic, chemically discrete morphology dominates applications, ballisticcharacterization deterministic time-mean burning rate and acoustic admittance measures£ absence of explicit, nondeterministic information requires homogeneous propellant with a smooth, uniformly regressing burning surface: inadequate boundary conditions for heterogeneous propellant grained applications. The past age overcame this dichotomy with one-dimensional (1D) models and empirical knowledge from numerous, adequately supported motor developments and supplementary experiments. However, current cost and risk constraints inhibit this approach. Moreover, its fundamental science approach is more sensitive to incomplete boundary condition information (garbage-in still equals garbage-out) and more is expected. This work critiques this situation and sketches a path forward based on enhanced ballistic and motor characterizations in the workplace and approximate model and apparatus developments mentored by CSAR DNS capabilities (or equivalent).

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Depressurization Extinguishment of Composite Solid Propellants: Flame Structure, Surface Characteristics, and Restart Capability

Cited by 25 publications

References 10 publications

Nonlinear Burning Stability of Solid Propellants.

Nonlinear Burning Stability of Solid Propellants.

A novel in-flight thrust modulation technique for SPRM: proof of concept

Heterogeneous propellant internal ballistics: criticism and regeneration

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