Development of strand burner for solid propellant burning rate studies

Aziz, Azrina Abd; Mamat, Rizalman; Ali, Wan Khairuddin Wan

doi:10.1088/1757-899x/50/1/012048

Cited by 4 publications

(4 citation statements)

References 4 publications

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“…The burning speed is calculated as per the following formula by Eq. 1, as mentioned in references [8].…”

Section: Burning Rate Calculationmentioning

confidence: 93%

“…Additionally, the pressure exponents as the main ballistic parameter could be calculated using the empirical Vielle equation represented by Eq. 2, [8].…”

Section: Burning Rate Calculationmentioning

confidence: 99%

“…Figure 3 demonstrate how to obtain the burning rate from Eq. 3 [8]. If the logarithm of pressure to burning speed indicates liner relationship within the measured pressure range, the pressure exponent of burning speed in this pressure range can be calculated as per the following equation:…”

Section: Figure 3 Typical Curve Of Burning Ratesmentioning

confidence: 99%

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Evaluation of solid propellant burning rate by using strand burner and static firing tests

Nour Eldin,

Adel,

Elsabbagh

2024

J. Phys.: Conf. Ser.

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The main objective of this paper is to compare the different methods used to measure the burning rate of hydroxyl-terminated polybutadiene (HTPB) propellant. The burning rate measurement is carried out under varying crosslinking density, which is determined by the curing ratio, i.e., the equivalent ratio of diisocyanate to total hydroxyl (NCO/OH) ratio. Four batches with different curing ratios were produced using fixed production processes. To measure the burning rate, cured solid propellant strands were tested using the acoustic wave emission method at different pressures ranging from 4 to 10 MPa and also by using static firing test of subscale motors. The study showed that there was little difference between the results obtained from the acoustic wave emission method and subscale motors.

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“…The burning speed is calculated as per the following formula by Eq. 1, as mentioned in references [8].…”

Section: Burning Rate Calculationmentioning

confidence: 93%

“…Additionally, the pressure exponents as the main ballistic parameter could be calculated using the empirical Vielle equation represented by Eq. 2, [8].…”

Section: Burning Rate Calculationmentioning

confidence: 99%

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Evaluation of solid propellant burning rate by using strand burner and static firing tests

Nour Eldin,

Adel,

Elsabbagh

2024

J. Phys.: Conf. Ser.

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“…The burning rate is a mainly characteristic parameter controlling the ballistic behavior of the solid rocket propellants and it is an operative factor for assessment the efficiency of the overall rocket motor design [1][2][3] . The burning rate of rocket propellants is subject to an exponential relation so it must be controlled throughout the burning period to avoid catastrophic rise in chamber pressure or abnormal, interrupted, unstable burning or chuffing phenomenon [4] .…”

Section: Introductionmentioning

confidence: 99%

Burning rate measurement of composite propellant using acoustic wave emission in comparison with other techniques

Elsaka

Elbasuney

Mostafa

et al. 2020

Eng. Sci. and Milit. Techno.

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The burning rate of rocket propellants is one of the most important parameters having a direct influence on itsballistic characteristics, so accurate measurement of thisparameter is an active approach for achieving optimum design of the solid rocket motors. In this paper, acoustic emission technique was applied for measuring the burning rate of a composite propellant and tests were performed on a wide Pressure range(5 -9 MPa) at ambient temperature.3 % as a deviation co-efficient of acousticemission technique wasinvestigated by comparingthe burning rate results obtained by this technique and those obtained byactual burning of a small-scale test motors at 6.894MPa (1000 PSI) and curves obtained from previously mentioned techniques were analyzed.This paper reports that theacoustic emission technique is a simple, effective, economic, time-saving, reliable technique with a high accuracy nearly equivalent to the active field resultsand it is suitable for quality control of large-scale productions of composite propellant..

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Pressurized windowed burner chamber performance for solid rocket propellant: Preliminary study

Hakim,

Putra,

Ardi

et al. 2023

AIP Conference Proceedings

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Development of strand burner for solid propellant burning rate studies

Cited by 4 publications

References 4 publications

Evaluation of solid propellant burning rate by using strand burner and static firing tests

Evaluation of solid propellant burning rate by using strand burner and static firing tests

Burning rate measurement of composite propellant using acoustic wave emission in comparison with other techniques

Pressurized windowed burner chamber performance for solid rocket propellant: Preliminary study

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