• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.1-11
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• 2020

In this study, study on the internal ballistic analysis method for single-chamber dual-thrust rocket motors meeting a dual-thrust profile requirement by tailoring the grain burning area is presented. The analysis method, which can acquire variables required for the performance prediction, considering gradual change of burning rate correction factor and specific impulse in the transition phase, is proposed. Improvements compared to the analysis method in the previous study, which do not consider change in the transition phase, are verified through comparison between the newly proposed method and the method in the previous study. Internal ballistic variables are obtained for four different ground firing test conditions using the proposed method, and the performance prediction for each condition is conducted using these variables. These prediction results and the ground test data are in good agreement, so it is confirmed that the performance prediction of dual-thrust motors with same design geometries based on the proposed analysis method is available.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.379-382
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• 2017

Flow characteristics of dual bell nozzle with pintle were investigated. Thrust and thrust coefficient were compared with the pintle-bell nozzle of the same condition, and difference according to the pintle stroke was investigated. At stroke 0 mm, the thrust of the dual bell nozzle was about 13.18% higher than the bell nozzle, and when the pintle was backward, it was similar to the bell nozzle. The change in expansion ratio with stroke was considered to be more advantageous for a dual bell nozzle that performs altitude compensation through separation and transition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.24-27
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• 2012

In this study, the full scale flight type Dual-Pulse Rocket Motor(DPRM) with the bulkhead type Pulse Separation Device(PSD) was designed, manufactured, and fire-tested. The bursting time and pressure of PSD were analyzed by the pressure, thrust and vibration results of static fire tests and ablation of PSD was measured with 3-D coordinate measuring machine. As a result, PSD requirements, bursting conditions and thermal safety, were satisfied.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.78-79
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• 2002

유도미사일용 추진기관으로 흔히 쓰이는 고체 로켓 모타의 경우 단순 추력형보다 복합 추력형 로켓을 사용하는 것이 효과적인 경우가 많다. 특히 발사초기에 높은 추력이 필요하고 그 후는 지속적이며 상대적으로 낮은 추력만을 요하는 무기체계의 경우 일반적으로 부스터(booster)와 서스테이너(sustainer) 로켓을 별도로 제작/작동시켜 임무를 수행하나 이를 하나의 추진기관으로 통합하여 두 단계의 추력을 동시에 실현하는 이중 추력형 로켓 모타를 이용하게 되면 많은 이점이 있다.