Burning Rate Measurement of KNSu Propellant Obtained by Mechanical Press

Foltran, Antonio Carlos; Moro, Diego Fernando; Silva, Nicholas Dicati Pereira da; Ferreira, Ana Eliza Gonçalves; Araki, Luciano Kiyoshi; Marchi, Carlos Henrique

doi:10.5028/jatm.v7i2.431

Cited by 7 publications

(6 citation statements)

References 1 publication

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“…Fructose, Glucose and Lactose are used as fuel in this experiment. Minuscule fructose, glucose and lactose particles along with oxidizers catch fire in a flash due to their high proportion of surface area to volume [6,8,10].…”

Section: Materials 21 Fuelmentioning

confidence: 99%

“…A few researchers tried to study the thermodynamics and ballistic characteristics of sugarbased propellants. Foltran et.al [6] experimented to study the performance of a coldmanufactured mechanical press with a mixture of 65% Potassium Nitrate and 35% Sucrose. For the propellant grain fabrication, the characteristic properties like density and burning rate and compression pressure were also studied.…”

Section: Introductionmentioning

confidence: 99%

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Investigation on solid propellant test and time calibration for complete combustion

Tigga,

G.,

P.S.N.

2023

E3S Web Conf.

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A solid propellant is simple and reliable rocket fuel. Once ignited, the propellant cannot be stopped since they burn until they run out. Solid fuel rockets are widely used in military applications such as missiles, model rockets, boosters for satellite launchers and so on because they can be stored for long periods of time without degrading the propellant. The primary objective of this research is to study the burnout mass of solid propellants using various propellants and catalysts. Potassium Nitrate (KNO3) was chosen as an oxidant in the experiment because of its compatibility with other ingredients and low-cost affordability. KNO3 was used as an oxidizer in a 65% ratio with 34% of the fuel and 1% of the catalyst. KNO3, fuel ingredients like Fructose, Glucose and Lactose with catalysts Copper and Aluminum were taken in powdered form. Cylindrical stainless steel with one closed end was taken to fill the cavity, and a concentric hole was made for constant burning. This propellant-filled chamber is fixed strongly in a position so that it does not propel during fuel combustion when thrust is formed. The obtained result shows that the longest burnout mass was secured by burning Glucose with Copper powder and KNO3 for 136 s when compared to the shortest burnout mass was secured by burning Lactose with Aluminum powder and KNO3 mixture to 57 s. The highest temperature of the mixture was Lactose with Copper powder and KNO3 resulted in 518 °C when compared to the lowest temperature of the mixture was Glucose with Copper powder and KNO3 was 211.75 °C.

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Section: Materials 21 Fuelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Investigation on solid propellant test and time calibration for complete combustion

Tigga,

G.,

P.S.N.

2023

E3S Web Conf.

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“…Several attempts were made by some authors towards improving the thermodynamics and ballistic properties of sugar-based propellants. Foltran [18], worked on the performance of KNSU, whose composition is 65 wt % KNO3 and 35 wt % C12H22O11, cold-manufactured by mechanical press. The behaviour of density (ρ) and burning rate (r) as function of compression pressure (Pc) for the propellant grain manufacturing was also determined.…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

Adeniyi

Nkere

Adetoro

et al. 2021

EJENG

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The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delivered specific impulse, delivered characteristic velocity, and the chamber pressure. The formulations tested were potassium nitrate–sucrose propellant (65% KNO3 and 35% sucrose (C12H22O11)) (KNSU); potassium nitrate-sorbitol propellant (65% KNO3 and 35% sorbitol (C6H14O6)) (KNSB); modified potassium nitrate-sucrose propellant (65% KNO3, 32% sucrose (C12H22O11)), and 3% carbon (C) (MODKNSU); potassium nitrate-sucrose-sorbitol propellant (65% KNO3, 25% sucrose (C12H22O11)), and 10% sorbitol (C6H14O6) (KNERK); potassium nitrate-sucrose-sorbitol-carbon propellant (65% KNO3, 24% sucrose (C12H22O11), 10% sorbitol (C6H14O6), and 1% carbon (C)) (MODKNERK); and finally a propellant made from KNO3, sucrose (C12H22O11), sorbitol (C6H14O6), carbon (C) and iron II oxide(Fe2O3) combinations in 65, 30, 3, 1, 1% proportion respectively. The novel result obtained from these experiments was applied to boost the performance of a KNSB rocket propellant motor during a rocket launch experiment. Both static and dynamic rocket motor internal ballistic parameters were then compared. The measured delivered motor average thrust and the effective propellant burn times were recorded as: (164.15N, 3.97s); (102.95N, 6.53s); (65.66N, 9.38s); (79.09N, 3.77s); (243.98N, 3.77s) and (92.6N, 5.89s) respectively. The MODKNERK, was established to produce a most efficient motor and with the full delivery of its ballistic energy. It was also established, that the ballistic and rocket motor efficiency of a lower energy rocket motor can be improved by starting the ignition of such motor with fast burning dual-fuel rocket propellant (MODKNERK).

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“…The choice of this propellant is based on the ease of obtaining its components as well as their preparation. In addition, KNSu preparation is a DOI : https://dx.doi.org/10.26808/rs.st.i9v6.01 International Journal of Advanced Scientific and Technical Research ISSN 2249-9954 Available online on http://www.rspublication.com/ijst/index.html Issue 9 volume 6 Nov -Dec. 2019 safe handling process and this propellant also promotes relatively high specific impulse compared to black powder (Foltran et al, 2015). In general, KNSu consists of a mixture of 65 wt% of potassium nitrate and 35 wt% of sucrose.Additives in the basic formulation of KNSu are commonly used to increase the specific thrust of this propellant.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of use waste aluminum on the burning of solid rocket propellant

Baldissera¹,

Khün²,

Telöken³

et al. 2019

IJASTR

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Solid propellants based on potassium nitrate (KNO 3) and sucrose are widely used in rocketry, because they are inexpensive and easily obtainable compounds and also generate high specific thrust. In this study, the performance of propellants based on a mixture of 65 wt% KNO 3 and 35 wt% sucrose, named KNSu, was evaluated.Aluminum waste particles were loading at 2.5 wt%, 5 wt% and 7.5 wt%. Aluminum was used as a powder with an average particle size of 35 μm. Rocket engines were developed and the thrust versus time curves obtained for the samples studied. The results showed that the utilization of 5 wt% caused a 30% increase in both the specific impulse and the average gas ejection velocity when compared to KNSu. The incorporation of 2.5 wt% and 7.5 wt% caused a reduction in the specific impulse and other properties evaluated when compared to KNSu. Based on the results obtained, it is possible to state that the insertion of aluminum waste from the metalworking industry may contribute to the increase of the performance of rockets that use KNSu as a solid propellant.

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Burning Rate Measurement of KNSu Propellant Obtained by Mechanical Press

Cited by 7 publications

References 1 publication

Investigation on solid propellant test and time calibration for complete combustion

Investigation on solid propellant test and time calibration for complete combustion

Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

Evaluation of use waste aluminum on the burning of solid rocket propellant

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