Burn-rate Measurement on Small-scale Rocket Motors

Maggi, F.; Luca, L.T. De; Bandera, A.; Subith, V. S.; Annovazzi, A.

doi:10.14429/dsj.56.1899

Cited by 6 publications

(4 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, this is rarely pressure-independent and most of the time; value of n is different in different pressure ranges. A similar explanation of power law is advocated by other contemporary and subsequent literature [2][3][4][5][6][7][8] . The references dealing with influence of pressure on burning rate of solid rocket propellant do indicate variation of burning rate with temperature.…”

Section: Prior State-of-the-artsupporting

confidence: 55%

Estimation of Pressure Index and Temperature Sensitivity Coefficient of Solid Rocket Propellants by Static Evaluation

Shekhar¹

2009

DSJ

View full text Add to dashboard Cite

Burning rate of a solid rocket propellant depends on pressure and temperature. Conventional strand burner and Crawford bomb test on propellant strands was conducted to assess these dependent parameters. However, behaviour of propellant in rocket motor is different from its behaviour in strand form. To overcome this anomaly, data from static evaluation of rocket motor was directly used for assessment of these burningrate controlling parameters. The conventional empirical power law (r=a o exp[p{T-T o }]P n ) was considered and a method was evolved for determination of pressure index (n) and temperature sensitivity coefficient (p) of burning rate for solid rocket propellants from static evaluation data. Effect of pressure index and temperature sensitivity coefficient on firing curve is also depicted. Propellant grain was fired in progressive mode to cover a very wide pressure range of 50 kg/cm 2 to 250 kg/cm 2 and propellant burning rate index was calculated to be 0.32 in the given pressure range. Propellant grain was fired at +35 °C and 20 °C temperatures and temperature sensitivity coefficient of burning rate was calculated to be 0.27 % per °C. Since both the values were evaluated from realised static evaluation curves, these are more realistic and accurate compared to data generated by conventional methods.

show abstract

Section: Prior State-of-the-artsupporting

confidence: 55%

Estimation of Pressure Index and Temperature Sensitivity Coefficient of Solid Rocket Propellants by Static Evaluation

Shekhar¹

2009

DSJ

View full text Add to dashboard Cite

show abstract

“…Figure 2 illustrates the combustion chamber setup and the equipment utilized for the sample combustion tests under pressure. The applied pressure during the combustion of a sample plays a substantial role in its burning rate (rb) according to Saint Robert's/Vieille's law [23]. This empirical relationship (Equation (1)) offers valuable insights into the intricate aspects of combustion behaviour and kinetics:…”

Section: Methods and Equipmentmentioning

confidence: 99%

“…Equation (1) allows for the correlation of the linear burning rate (rb) with pressure P in megapascals (MPa), enabling its application across a range of operating conditions. The applied pressure during the combustion of a sample plays a substantial role in its burning rate (r b ) according to Saint Robert's/Vieille's law [23]. This empirical relationship (Equation ( 1)) offers valuable insights into the intricate aspects of combustion behaviour and kinetics:…”

Section: Methods and Equipmentmentioning

confidence: 99%

Thermal Characteristics Enhancement of AN/Mg/NC Composite Using Activated Carbon/Cobalt Oxide as Highly Effective Catalytic Additive

Yelemessova,

Kydyrbekova,

Yerken

2023

J. Compos. Sci.

View full text Add to dashboard Cite

Our study examined the potential of using activated carbon/nanosized cobalt oxide (AC-Co3O4) as a new catalytic additive to improve the efficiency of the parent ammonium nitrate/magnesium/nitrocellulose (AN/Mg/NC) composite. These findings demonstrate a significant improvement in the thermal characteristics of AN/Mg/NC/AC-Co3O4 compared to the initial AN/Mg/NC. Raman spectra confirmed the multilayered nature of AC. Fourier-transform infrared spectroscopy (FTIR) analysis confirmed the presence of cobalt oxide in the synthesized additive. Differential scanning calorimetry (DSC) revealed the catalytic effect of AC-Co3O4 on the AN/Mg/NC composite, resulting in the reduction in the decomposition peak temperature (Tmax) from 277.4 °C (for AN/Mg/NC) to 215.2 °C (for AN/Mg/NC/AC-Co3O4). Thermal gravimetric analysis (TG) determined the overall mass losses (%) for AN/Mg/NC (70%), AN/Mg/NC/AC (75%), and AN/Mg/NC/AC-Co3O4 (80%). This analysis highlights the significant role of AC-Co3O4 in enhancing the energy release during decomposition. Moreover, the use of the differential thermogravimetric (DTG) technique demonstrated the two-step decomposition pathways attributed to the multi-component system. Finally, the combustion tests under the pressure of 3.5 MPa validated the catalytic efficiency of the AC-Co3O4 additive, which enhanced the burning rate (rb) of the AN/Mg/NC/AC-Co3O4 composite from 10.29 to 19.84 mm/s compared to the initial AN/Mg/NC composite. The advantageous nature of the AN/Mg/NC/AC-Co3O4 composite with a lowered decomposition temperature can be applied in rocket propulsion systems, where the precise control of combustion and ignition processes is crucial.

show abstract

“…This kind 2 International Journal of Aerospace Engineering of behavior imposes strict requirements on acceptance criteria and reliability. For example, unexpected variations of the propellant properties due to casting effects have been highlighted by different experimental and modeling works and were found to be responsible for the hump behavior in pressure traces of small-scale rocket motors [4][5][6][7]. Another example is represented by rocket burnout.…”

Section: Introductionmentioning

confidence: 99%

Monte Carlo Uncertainty Quantification Using Quasi-1D SRM Ballistic Model

Viganò

Annovazzi

Maggi

2016

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Compactness, reliability, readiness, and construction simplicity of solid rocket motors make them very appealing for commercial launcher missions and embarked systems. Solid propulsion grants high thrust-to-weight ratio, high volumetric specific impulse, and a Technology Readiness Level of 9. However, solid rocket systems are missing any throttling capability at run-time, since pressure-time evolution is defined at the design phase. This lack of mission flexibility makes their missions sensitive to deviations of performance from nominal behavior. For this reason, the reliability of predictions and reproducibility of performances represent a primary goal in this field. This paper presents an analysis of SRM performance uncertainties throughout the implementation of a quasi-1D numerical model of motor internal ballistics based on Shapiro’s equations. The code is coupled with a Monte Carlo algorithm to evaluate statistics and propagation of some peculiar uncertainties from design data to rocker performance parameters. The model has been set for the reproduction of a small-scale rocket motor, discussing a set of parametric investigations on uncertainty propagation across the ballistic model.

show abstract

Burn-rate Measurement on Small-scale Rocket Motors

Cited by 6 publications

References 4 publications

Estimation of Pressure Index and Temperature Sensitivity Coefficient of Solid Rocket Propellants by Static Evaluation

Estimation of Pressure Index and Temperature Sensitivity Coefficient of Solid Rocket Propellants by Static Evaluation

Thermal Characteristics Enhancement of AN/Mg/NC Composite Using Activated Carbon/Cobalt Oxide as Highly Effective Catalytic Additive

Monte Carlo Uncertainty Quantification Using Quasi-1D SRM Ballistic Model

Contact Info

Product

Resources

About