Validation with Numerical Simulations of a Simplified Model of a Hybrid Rocket Motor

Frunzulică, Florin; Stoia-Djeska, Marius; Mingireanu, Florin

doi:10.1002/pamm.201510205

Cited by 1 publication

(2 citation statements)

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“…The main steps of the SRM simulation code are: -Read geometrical dimensions of the SRM from INPUT.DAT -Read fuel geometry from FUEL_GEOMETRY.DAT -Compute initial burning surface (the code can handle end burn and tubular geometry but has additional modules that can be used for other geometries) Next it follows a repetitive loop until the end-burning condition is met (pressure in the SRM casing lower than a threshold value): BL Proceedings of the 18 th Int. AMME Conference, 3-5 April, 2018 -Compute initial burn rate based on initial pressure -Integrate pressure equation ( 13) using RK-4 module -Write output data in the OUTPUT.DAT file The burn rate in the above steps can be either given by equation (2) or (3). The choice can be specified by a user in the INPUT.DAT file.…”

Section: Interior Ballistics Modelmentioning

confidence: 99%

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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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Section: Interior Ballistics Modelmentioning

confidence: 99%

“…Solid rocket motors (SRM) have a wide application as propulsion units for various aerospace vehicles either for suborbital or for orbital flight [1][2][3][4]. SRMs are widely used due to their simplicity, reliability and low cost of operation.…”

Section: Introductionmentioning

confidence: 99%