Theoretical prediction of erosive burning characteristics of solid rocket propellant based on burning rate dependence of pressure and initial temperature and its energetic characteristics

Jojić, B.; Blagojevic, D.-J.

doi:10.2514/6.1976-697

Cited by 5 publications

(1 citation statement)

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“…Yet a more complex burn rate equation takes also in the account the velocity vector of the combustion gases that "wash" the surface of the solid propellant [14][15][16][17][18][19][20]:…”

Section: Interior Ballistics Modelmentioning

confidence: 99%

Solid Rocket Motors Internal Ballistic Model With Erosive and Condensed Phase Considerations

Mingireanu

Jula

Micloş

et al. 2018

The International Conference on Applied Mechanics and Mechanica

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Solid rocket motors are used for propulsion units of both suborbital and orbital aerospace vehicles. Their main advantages are their simplicity, low cost and reliability. Due to attainable high thrust they have a wide application as boosters (as space shuttle boosters, Delta rocket boosters). They were also used as main stages, retrorocket units, stage separation control units, main propulsion units for suborbital vehicles. An interior ballistics model is implemented and applied for a double base and composite propellant boosters to be used for a boosted dart suborbital vehicle. Erosion and condensed phase are taken into account and numerical results are shown in comparison with experimental data obtained on test firings for each motor. The advantages of the implementation are that it offers a fast calculation of the main parameters of the solid rocket motor unit (thrust, burn time, specific impulse, total impulse). The solid fuel characteristics and the geometry of the motor are contained within two input files while the results of the calculations are presented to the user in a several output files. The motors are built using steel as a casing material and test firings are performed on a horizontal test bench.

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“…Yet a more complex burn rate equation takes also in the account the velocity vector of the combustion gases that "wash" the surface of the solid propellant [14][15][16][17][18][19][20]:…”

Section: Interior Ballistics Modelmentioning

confidence: 99%

Solid Rocket Motors Internal Ballistic Model With Erosive and Condensed Phase Considerations

Mingireanu

Jula

Micloş

et al. 2018

The International Conference on Applied Mechanics and Mechanica

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Excessive Subsurface Heat Release As a Possible Cause of the Negative Erosion Effect during Combustion of Homogeneous Solid Propellants

Gusachenko

Зарко²,

Kiskin³

2022

Combust Explos Shock Waves

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A Model of Erosive Burning of Composite Propellants

King¹

1978

Journal of Spacecraft and Rockets

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(1) a result in high velocity flows of product gases across burning propellant surfaces (notably, nozzleValues of (r aft/rfore)iajtial as a function of the less rocket motors) is leading to increased occurerosivity constant ( k3) and the burning rate expon-:ence of erosive burning. In this paper , a physieat ( n ) are presented in Table I for y = .1.25. As cally realistic picture of the effect of such crossmay be seen, for the case of no erosion (k 3 = 0) -flows on composite propellant combustion , based on the af t end will recede more slowly than the fore the bending of columnar diffusion f lames by the end , due to lower pressure at the aft end. As k 3 crossflow , is presented. This bend ing results its increases , the r af~/rfore ratio also increases , shifting of the diffusion flame heat release zone going through unity (generally desirable) at a valuẽ~1 toward the surface , with consequent increased heat of k 3 which depends on the burning rate exponent. feedback flux from this flame to the surface andThe results of Table I give some indication of the thus increased burning rate. A relatively simple sensitivity of nozzleless motor design to the eroanalytical model based on this picture is developed sive burning characteristics of the propellant and for prediction of propellant burning rate as a functhus point out the importance 'f information regardtion of pressure and crossflow velocity, given only ing the propellant 's erosive burning characteriszero-cross flow burning rate versus pressure data, tics to the designer. Model predictions and experimental results are compared , with reasonably good agreement being found . performance repeatability and thrust misalignment. Development of a better understanding of the More than in any conventional motor , the exact eraeffects of crossflows on solid propellant combustion sive burn rate behavior must be held constant from is needed for accomplishment of accurate motor perbatch to batch if reproducibility is not to be a forsnance predictions in terms of both mean iatericr • problem. The performance sensitivity of a nozzleballistics analysis and prediction of motor stability less motor to erosion is due to the fact that the characteristics. With such understanding, the motor maximum erosion occurs at the choke point in the designer can either dasign his grains to compensate base. Since this point is the effective throat area , for mean erosive burning effects on grain burn patand the throat area versus time is thus a function tern , or , knowing how propellant formulation paraof regression rate , the result is a chamber pressure meters affect erosion sensitivity, vary propellant history which varies strongly with erosion, parameters in such a way as to optimize these e f f e c t s . A review of the literature indicates that there is In a nozzleless motor , two parameters which no unifying predictive model for erosive burning of affect bu rning rate , prcasure and crossflow velocity, solid prop~llants,~~ vary strong ly from the fore end to the aft end of the grain ...

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Theoretical prediction of erosive burning characteristics of solid rocket propellant based on burning rate dependence of pressure and initial temperature and its energetic characteristics

Cited by 5 publications

References 1 publication

Solid Rocket Motors Internal Ballistic Model With Erosive and Condensed Phase Considerations

Solid Rocket Motors Internal Ballistic Model With Erosive and Condensed Phase Considerations

Excessive Subsurface Heat Release As a Possible Cause of the Negative Erosion Effect during Combustion of Homogeneous Solid Propellants

A Model of Erosive Burning of Composite Propellants

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