• Title/Summary/Keyword: Internal Ballistics

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Study on Predicting the Thrust Performance of Solid Rocket Motor with Two Kinds of Propellants (이종 추진제가 적용된 고체 추진기관의 추력성능예측에 대한 연구)

  • Kim, Hanjun;Moon, Kyungje;Cho, Pyungki
    • Journal of the Korean Society of Propulsion Engineers
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    • v.25 no.1
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    • pp.77-83
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    • 2021
  • In the current study, the numerical method was established to predict the performance of a solid rocket motor with two kinds of propellants. On the basis of a numerical study, an internal ballistics analysis code was developed. To verify the internal ballistics analysis code two solid rocket motors were manufactured and tested. The accuracy and applicability of the internal ballistics code for dual-propellant solid rocket motor were verified by comparing the experimental results with the numerical calculation.

Characteristic Property of Combustion and Internal Ballistics of Triple-Based Propellant according to Particle Size of RDX (RDX 입도에 따른 다기추진제의 연소 및 강내탄도 특성)

  • Soojung Son;Wonmin Lee;Woojin Lee;Daegeon Kim
    • Journal of the Korea Institute of Military Science and Technology
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    • v.27 no.3
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    • pp.428-435
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    • 2024
  • The important factors in the design of the gun propellant are impetus, flame temperature and pressure. In this paper, we considered a nitrocellulose based propellant composition that replaced sensitive NG(Nitroglycerin) with RDX(Cyclotrimethylenetrinitramine) and DEGDN(Diethylene glycol dinitrate) which high energy and low sensitivity. Particle size and content of RDX are the two main factors that affect the burning stability of RDX-based propellants. Among them, the characteristics of the propellant according to the particle size of RDX were confirmed. The relative combustion rate(R.Q., Relative Quickness) of the propellant changed according to the RDX particle size, and internal ballistics of properties of propellant were also varied. The particle size of RDX can be confirmed as a major factor in the combustion and internal ballistics characteristics of the propellant.

Analysis of Elements Influencing on Performance of Interior Ballistics (강내탄도의 성능 영향 요소 분석)

  • Sung, Hyung-Gun;Yoo, Seung-Young;Choi, Dong-Whan;Roh, Tae-Seong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.228-236
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    • 2011
  • The analysis of the performance and the internal flow according to various numerical models used for the interior ballistics has been conducted. The internal flow has been mainly affected by the drag model. As results, oscillations of the pressure differences between the breech and the shot base has been reduced with a deceased drag of the propellant. The major performance of the interior ballistics has no relation to the models using Nusselt number for heat transfer coefficient. The negative pressure difference without the heat transfer of the propellant has not been shown.

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Design of Hybrid Rocket (Altitude 15km) Using Liquid Oxidizer ${N_2}O$ (${N_2}O$ 액체산화제를 사용한 고도 15km급 하이브리드 로켓 설계)

  • Heo, Jun-Young;Cho, Min-Gyung;Kim, Jong-Chan;Kim, Soo-Jong;Kim, Jin-Kon;Moon, Hee-Jang;Sung, Hong-Gye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.97-100
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    • 2008
  • A hybrid sounding rocket carrying about 10kg payload reaching up to 15km altitude has been designed. The commercial seamless aluminium tube and liquid ${N_2}O$ without pressurization devices were chosen as rocket motor case and oxidizer supply system respectively. A hybrid rocket engine performing required propulsion impulse is designed with time dependent internal ballistic scheme. Engine performance, aerodynamic characteristics, and trajectory were predicted by a integral technique of internal ballistics and external ballistics. The design results were evaluated by comparison with previous experimental data, technical reports, and literatures.

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Development of Internal Ballistics Analysis Code using HLLC (HLLC를 사용한 내탄도 해석 코드 개발)

  • Yang, Sungmin;Cha, Seung-Won;Lee, Kang-Kyu;Roh, Tae-Seong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.778-780
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    • 2017
  • In order to calculate the performance of the solid rocket motor, the internal ballistics analysis code using HLLC scheme has been developed. The result of applying the analysis code to the actual motor shape has been compared with the experimental results and it is confirmed that the performance of the solid rocket motor has been well calculated.

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Study on Solid Propellant Grain Burn-back Analysis Using Analytical Method (Analytical Method를 이용한 고체 추진제 그레인의 Burn-back 연구)

  • Sohn, Jihyun;Jang, Jinsung;Oh, Seokhwan;Roh, Taeseong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.40-47
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    • 2014
  • The grain burn-back analysis has been performed for the internal ballistics analysis code to be used for the optimal design of the space launch vehicles. The grain burn-back has been used to calculate the burning surface that is essential to the internal ballistics. The calculation of internal ballistics code used in the optimal design is repeated until satisfying the required performance through the change of the design parameter. Therefore, the burn-back method applied to the internal ballistics analysis should be easy to change the design parameter and calculation time should be short. In this study, a burn-back analysis code has been developed using the analysis method. Also, geometric parameters of the grain have been selected and organized. The developed code has been verified by comparison of results of a numerical method.

Performance Prediction and Analysis of a MEMS Solid Propellant Thruster (MEMS 고체 추진제 추력기의 성능예측 및 분석)

  • Jung, Juyeong;Lee, Jongkwang
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.6
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    • pp.1-7
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    • 2017
  • The performance of a MEMS solid propellant thruster was predicted and analyzed through internal ballistics model and CFD analysis. The nozzle throat was $416{\mu}m$, and the area ratio of the nozzle was 1.85. As a result of the internal ballistics model, chamber pressure increased up to 197 bar and the maximum thrust was 3,836 mN. In CFD analysis, the chamber pressure of the internal ballistics model was applied as the operating pressure, and the CFD model was divided into an adiabatic and a heat loss model. As a result, the maximum thrust of the adiabatic model was 14.92% lower than that of the internal ballistics model, and the effect of heat loss was insignificant.

Analysis of Elements Influencing on Performance of Interior Ballistics (강내탄도의 성능 영향 요소 분석)

  • Sung, Hyung-Gun;Yoo, Seung-Young;Lee, Sang-Bok;Choi, Dong-Whan;Roh, Tae-Seong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.4
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    • pp.16-24
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    • 2013
  • The analysis of performance and internal flow according to various numerical models for interior ballistics has been conducted. The initial flow has been mainly affected by the drag model of propellants and their drag degradation reduces oscillations of differential pressure between the breech and the shot base. Models of Nusselt number haven't influenced the major performance of interior ballistics. The negative differential pressure isn't generated in the case without the heat transfer of propellants.

Design, Analysis and Experiment of Potato Gun with a Spherical Projectile (구형 탄환을 이용한 감자총의 설계, 해석 및 시험)

  • Kang, Hong-Jae;Kim, Ji-Hwan;Kim, Young-Sik;Son, So-Eun;Choi, Han-Ul;Choi, Jeong-Yeol
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.10
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    • pp.796-804
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    • 2013
  • The "Potato Gun," a simple heat engine, is fabricated, tested and analyzed as a part of engineering education program of combustion and propulsion classes. Combustor pressure is predicted by the chemical equilibrium analysis of a constant volume combustor. Then, the internal ballistics, the conversion of thermal energy into the mechanical energy of a projectile, is predicted though the expansion process. The trajectory of a projectile is estimated by considering the aerodynamic effect around the spherical projectile. The energy conversion efficiency and the equivalence ratio of the fuel-air mixture could be estimated by the comparison of the experimental results and the theoretical prediction. The present work would be an example of attracting the interest of students for the application of the engineering principles at undergraduate level by recycling the waste materials.

Characteristic Property of Combustion and Internal Ballistics of Triple-Based Propellant including RDX (RDX를 적용한 다기추진제의 연소 및 강내탄도 특성)

  • Son, Soojung;Lee, Wonmin;Lee, Woojin;Kwon, Soonkil;Jung, Jinyoung
    • Journal of the Korea Institute of Military Science and Technology
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    • v.25 no.3
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    • pp.321-328
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    • 2022
  • The current development tend of the gun propellants that they should have low sensitivity and high energy. We studied a nitrocellulose based propellant composition that replaced sensitive NG with RDX and DEGDN which high energy and low sensitivity. The important factors in the design of the gun propellant were impetus and flame temperature. NC-based propellant containing RDX showed similar impetus but low flame temperature compared to KM30A1, a triple-based propellant. The developed propellant composition didn't show any abnormal combustion reaction and the characteristics of ballistic resistance were also confirmed.