Numerical Simulation of the Nonstationary Burning of a Solid Propellant in the Combustion Chamber of a Controllable Solid-Propellant Propulsion System

Krainov, A. Yu.; Poryazov, V. A.; Moiseeva, K. M.

doi:10.1007/s10891-022-02629-1

Cited by 2 publications

(1 citation statement)

References 6 publications

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“…Yu. Krainov et.al [13] studied the slowly varying combustion of solid propellant in the combustion chamber of a controllable solid-propellant rocket motor was designed to simulate using the conjugate physical-mathematical model of the combustion of a ballistic powder with regard to the processes occurring in the condensed and gas phases of the powder at the fourth-kind initial conditions on the edge of its charge. S. A. Bitkin et.al [14] had researched the mathematical model, numerical technique, and parametric study findings for the parameters of a multi-nozzle solid-fuel motor provided with mass flow rate stepper regulators.…”

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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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: 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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Study of gas dynamics of combustion of mixed solid fuel under pressure fluctuations on the surface of the fuel

Krainov

2024

CPM

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Based on the coupled combustion model of mixed solid fuel, unsteady combustion of fuel was studied when the pressure was changed in the combustion chamber of a model controlled small solid fuel engine. Modeling of engine thrust control system was carried out in two ways: by changing the critical section area of the nozzle over time according to a given law and by changing the area of the burning surface of the fuel according to a given law. It is found that with a sharp increase in pressure, the combustion rate increases above the quasi-stationary value, which leads to an increase in the pressure in the combustion chamber above that calculated from the quasi-stationary rate. With a sharp decrease in pressure, the combustion rate decreases to a value less than the quasi-stationary rate at the corresponding pressure. The decrease in the combustion rate leads to a decrease in the pressure in the combustion chamber below that calculated from the quasi-stationary rate. At small values of the characteristic relaxation time of the combustion chamber, a sharp decrease in pressure in the combustion chamber will lead to the extinction of the charge combustion.

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Numerical Simulation of the Nonstationary Burning of a Solid Propellant in the Combustion Chamber of a Controllable Solid-Propellant Propulsion System

Cited by 2 publications

References 6 publications

Investigation on solid propellant test and time calibration for complete combustion

Investigation on solid propellant test and time calibration for complete combustion

Study of gas dynamics of combustion of mixed solid fuel under pressure fluctuations on the surface of the fuel

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