A mathematical method to predict the effects of erosive burning in solid-propellant rockets

Lenoir, John M.; Robillard, G.

doi:10.1016/s0082-0784(57)80092-7

Cited by 78 publications

(37 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The ZN method consists of using the steady burning laws and integral energy equations to transform the steady burning laws to a form that is valid for unsteady burning. The nonlinear unsteady burning rate can be modeled using the steady-state burning laws as r b r b T oa ; P; q r (11) where T oa , an "apparent" initial temperature, is introduced and defined to include the unsteady energy accumulation in the condensed-phase region as…”

Section: Pressure-dependent Burning Ratementioning

confidence: 99%

“…This typically occurs in motors with large aspect ratios (L=D) or constricted flow designs such as star-aft grains. This work employs several variations of the LR model, which divides the heat transfer from the flame zone back to the solid propellant into two independent mechanisms [11]. The first, heat transfer from the primary burning zone, depends only on pressure (as discussed earlier in this paper).…”

Section: Erosive Burning Contributionmentioning

confidence: 99%

“…The second, due to combustion gases flowing over the surface, is dependent on crossflow velocity. The model assumes, with both some criticism [12][13][14][15] and some support [16] that the two heat-transfer mechanisms can be treated independently and therefore the burning rates are additive [11,17]:…”

Section: Erosive Burning Contributionmentioning

confidence: 99%

“…It should be noted that for the ZN model, the pressure-dependent burning rate does not depend solely on instantaneous pressure but is a function of heating history through the surface temperature. The LR model defines the erosive burning contribution as [11] …”

Section: Erosive Burning Contributionmentioning

confidence: 99%

See 3 more Smart Citations

Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback

Willcox

Brewster

Tang

et al. 2007

Journal of Propulsion and Power

View full text Add to dashboard Cite

Internal ballistics simulations of solid rocket motors have been conducted with the propellant grain's 3-D burning surface geometry described by a new minimum distance function approach and the internal flowfield represented by 1-D, time-dependent, single-phase compressible flow equations. The combustion model includes erosive burning and unsteady, dynamic burning corresponding to transient energy storage in the heated surface layer of the propellant. The integrated internal ballistics code (Rocballist) is used to investigate the role of these two burning rate augmenting mechanisms in solid rocket motor performance. Two tactical motors are used as test cases. Results indicate that dynamic burning can be the dominant factor in producing a short-duration ignition pressure spike in low-L motors, particularly if the L=D ratio is not too large and the port cross section is nonrestrictive (e.g., center perforated grain). However, when L=D is large and the port cross section is noncircular in the aft section (aft fins/slots), erosive burning can take over in dominating the burning rate to the extent that an otherwise progressive pressure-time trace becomes regressive/neutral. That is, erosive burning can effectively prolong the initial pressure spike in some star-aft motors. The results also show that with sufficiently accurate models of dynamic burning and erosive burning, it is reasonable to expect reliable internal ballistics predictions with suitable simplified flowfield models, thereby realizing significant reductions in computation time compared with 3-D, multiphase reacting flow simulations.

show abstract

Section: Pressure-dependent Burning Ratementioning

confidence: 99%

Section: Erosive Burning Contributionmentioning

confidence: 99%

Section: Erosive Burning Contributionmentioning

confidence: 99%

Section: Erosive Burning Contributionmentioning

confidence: 99%

See 2 more Smart Citations

Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback

Willcox

Brewster

Tang

et al. 2007

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

“…A large number of eros ive burning mode ls have appeared in the literature (37)(38)(39)(40)(41)(42)(43)(44)(45)(46). Of those mode ls , all fall into one of four basic categories .…”

Section: Erosive Burn I Ng Modelsmentioning

confidence: 99%

The Effect of Oxidizer Particle Size Distribution on the Steady and Nonsteady Combustion of Composite Propellants.

Condon¹,

Osborn²

1978

View full text Add to dashboard Cite

The Starting Transient in a Gas-Generator Hybrid Rocket Motor

Osherov

Natan

2000

Propellants Explos. Pyrotech

View full text Add to dashboard Cite

A mathematical method to predict the effects of erosive burning in solid-propellant rockets

Cited by 78 publications

References 2 publications

Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback

Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback

The Effect of Oxidizer Particle Size Distribution on the Steady and Nonsteady Combustion of Composite Propellants.

The Starting Transient in a Gas-Generator Hybrid Rocket Motor

Contact Info

Product

Resources

About