침식연소를 고려한 고체로켓의 비정상 내탄도 해석 기법

다국어 초록 (Multilingual Abstract)

A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning with the variance of local velocity and pressure along the grain surface of a solid rocket combustor. To validate the model of concern in the study, both cases of non-erosive and erosive burning were compared with the previous researches with marginal accuracy. It was quantitatively investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect the erosive burning characteristics.

참고문헌 (Reference)

1 Sutton, G. P., "Rocket Propulsion Elements, 7th ed" John Wiley & Sons Inc. 2001

2 윤창진, "PE-GOX 하이브리드 모터의 연소특성 및 성능 예측 기법 Part Ⅱ : 내탄도 성능" 한국추진공학회 11 (11): 79-85, 2007

3 K. Srinivasan, "Numerical studies on erosive burning in cylindrical solid propellant grain", Springer -Verlag" 44 : 579-585, 2008

4 Hong-Gye Sung, "Lecture Note : Adavnced Rocket Propulsion" Korea Aerospace University 2008

5 James Moss, "Experimental Program to Assess Erosive Burning in Segmented Solid Rocket Motors" 2007

6 D. R. Greatrix, "Erosive Burning Model for Composite-Propellant Rocket Motors with Large Length-to- Diameter Ratio" 33 (33): 1987

7 J. P. Renie, "Erosive Burning" 21 (21): 1983

8 Beddini, R. A., "Effect of Port Flow on Solid Propellant Erosive burning, AIAA Paper 78-977" 1978