• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2010년도 제35회 추계학술대회논문집
• /
• pp.265-270
• /
• 2010

본 연구에서는 유도무기 동체 내에 고체 추진기관을 삽입하여 장착할 경우 적용할 수 있는 연결장치와 조립체 개념을 제안하였다. 유도탄 동체 내에 추진기관을 삽입하여 장착하는 경우는 동체가 비행중 받는 하중에 더하여 추진기관의 연소에 의해 야기되는 여러 가지 효과 즉, 추력에 의한 축하중, 진동, 연소 중 발생하는 추진기관의 축방향 변형 등을 견디는 구조여야 한다. 본 연구에서 제안된 추진기관 연결장치를 통해 간결하면서도 설계 요구조건을 모두 만족하는 추진기관 장착 시스템을 구성할 수 있었다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2002년도 제18회 학술발표대회 논문초록집
• /
• pp.10-13
• /
• 2002

Pogo is the instability resulting from the interaction between rocket structure and propulsion system of liquid propellant rocket. The coupling of structure and propulsion system can lead to severe problem in rocket. For the analysis of pogo, a time-invariant linearized mathematical model is developed for a selected flight time. Propulsion system is modeled using element representations for each components. The constitutive equation of propulsion system is a homogeneous second-order equation form in the Laplace domain. Rocket structure is modeled using FEM. From the results of modal analysis of structure, the behavior of structure can be represented. System equations for coupling structure and propulsion system are composed of all propulsion system equations and vehicle motion equations reacting on the vehicle by each component of propulsion system. The stability is obtained by the eigen solution of system matrix. The optimization of the design variables such as size, place of accumulator for suppressing pogo instability is carried out. This article of study can be used to determine the degree of stability, and guide the design of pogo suppression system.

• 한국CDE학회논문집
• /
• 제17권5호
• /
• pp.364-374
• /
• 2012

In this paper, we proposed a data structure to represent structural components of solid rocket motors (SRM) in an automated design program. To propose the data structure, we searched the necessary functions for the automated design program should have. In order to design the structural components of solid rocket motors sufficiently with a design program, it should have the functions to represent the shapes of the components, the drawing and analysis models, the design variables, various product structures, interferences, characteristic properties, design equations, and tightening sets. By modifying the data structure of an element object that is a general purpose data structure to represent a general component of a product, a new data structure was proposed to satisfy all the necessary functions with optimum. Finally, a design program for the structural components of solid rocket motors was developed successfully with the proposed data structure.

• International Journal of Aerospace System Engineering
• /
• 제2권2호
• /
• pp.1-5
• /
• 2015

The powder propellant rocket which uses micron-sized particles as fuel is storable and costly. Functions like thrust control and multiple-ignition can be realized by changing powder mass flow rate. In this paper, we discuss the theoretical performance of bi-propellant and mono-propellant powder rocket. When used as the fluidization gas, helium can improve specific impulse dramatically. The stability of the powder feeding device is preliminarily quantified through metal/N2O powder rocket hot fire tests.

• International Journal of Aerospace System Engineering
• /
• 제2권2호
• /
• pp.58-61
• /
• 2015

Combustion instability in solid rocket motors is a long-term open problem since the first rockets were used. Based on the numerous previous studies, it is known that the limit cycle amplitude is one of the key characteristics of the nonlinear combustion instability in solid rocket motors. Flandro's extended energy balance corollary, aims to predict the limit cycle amplitude of complex, nonlinear pressure oscillations for rockets or air-breathing engines, and leads to a precise assessment of nonlinear combustion instability in solid rocket motors. However, based on the comparison with experimental data, it is revealed that the Flandro's method cannot accurately describe such a complex oscillatory pressure. Thus in this work we make modifications of the nonlinear term in the nonlinear wave equations which represents the interaction of different modes. Through this modified method, a numerical simulation of the cylindrical solid rocket has been carried out, and the simulated result consists well with the experimental data. It means that the added coefficient makes the nonlinear wave growth equations describe the experimental data better.

• 한국항공우주학회지
• /
• 제31권3호
• /
• pp.58-64
• /
• 2003

포고(pogo)는 액체추진 로켓에서 로켓 구조와 추진기관 사이의 상호작용에 의해 발생하는 불안정성을 말한다. 이러한 불안정성은 경우에 따라 로켓에 심각한 문제를 야기할 수 있으므로 액체추진 로켓 설계시 반드시 고려되어야 할 사항이다. 본 연구세어는 추진기관의 구성품을 선형화된 전달함수로 구성하고, 로켓 구조는 유한요소법을 이용하여 모델하였다. 양 시스템이 공유하는 변위, 가속도, 힘을 이용하여 구조-추진 연계 시스템을 구성하였다. 연계시스템의 고유치 해석을 통하여 포고현상의 발생 여부를 예측할 수 있으며, 안정도 여유(stability margin)를 구할 수 있다. 완충기(accumulator)를 사용하여 포고현상을 제어할 수 있는 방법을 제시하였으며 완충기의 위치와 크기를 설계변수로 두어 시스템의 안정도 여유를 크게 하기 위해 최적화 과정을 수행하였다.

• 한국전산유체공학회:학술대회논문집
• /
• 한국전산유체공학회 2008년도 춘계학술대회논문집
• /
• pp.510-513
• /
• 2008

The traditional computational fluid or structure dynamics analysis approaches have contributed to solve many delicate engineering problems. But for the most of recent engineering problems which are influenced by fluid-structure interaction effect strongly, traditional individual approaches have limited analysis abilities for the exact simulation. Owing to above-mentioned reason, nowadays fluid-structure interaction analysis has become a matter of concern and interest. FSI analysis require several unprecedented techniques for the combining individual analysis tool into integrated analysis tool. The Arbitrary Lagrangian-Eulerian(ALE, in short) method is the new description of continum motion,which combines the advantages of the classical kinematical descriptions, i.e. Lagrangian and Eulerian description, while minimizing their respective drawbacks. In this paper, the ALE description is adapted to simulate fluid-structure interaction problems. An automatic re-mesh algorithm and a fluid-structure coupling process are included to analyze the interaction and moving motion during the 2-D axisymmetric solid rocket interior FSI phenomena simulation.

• 한국항공우주학회지
• /
• 제42권6호
• /
• pp.488-494
• /
• 2014

유도탄 발사 시 화염은 발사 장치 및 인접 구조물에 심각한 손상을 야기할 수 있다. 본 연구는 유도탄 발사 시 함정과 유도탄의 초기 운동에 의해 유도탄의 화염이 인접 구조물에 미치는 영향을 분석하기 위하여 수행하였다. 이를 위해 함정과 유도탄의 초기 운동에 영향을 미치는 각 인자들을 확률분포로 정의하고 Monte Carlo 해석 기법을 이용하여 통계적으로 발생할 수 있는 유도탄 이탈 영역을 분석하였다. 그 후 유도탄의 화염이 인접 구조물에 가장 큰 영향을 미치는 유도탄 이탈 궤적에 대해 CFD기법을 이용하여 유동-운동해석을 수행하였다. 이와 같은 방법으로 유도탄 발사 시 함정과 유도탄의 초기 운동에 의해 유도탄 화염이 인접 구조물에 미치는 영향을 분석하였다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2006년도 제27회 추계학술대회논문집
• /
• pp.237-240
• /
• 2006

Hybrid propulsion systems provide many advantages in terms of stable operation and safety. However, classical hybrid rocket motors have lower fuel regression rate and combustion efficiency compared to solid propellant rocket motor. Accordingly, the recent research efforts are focused on the improvement of engine efficiency and regressionrate in the hybrid rocket engine. The present study has numerically investigated the combustion processes and the flame structure in the hybrid rocket engine. The turbulent combustion is represented by the flamelet model and Low Reynolds number $k-{\varepsilon}$turbulent model is employed to reduce the uncertainties for convective heat transfer near solid fuel surface having strong blowing effect. Numerical results suggest that the present approach is capable of realistically simulating the combustion characteristics of the hybrid rocket engines.

• 유체기계공업학회:학술대회논문집
• /
• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
• /
• pp.245-248
• /
• 2006

Hybrid propulsion systems provide many advantages in terms of stable operation and safety. However, classical hybrid rocket motors have lower fuel regression rate and combustion efficiency compared to solid propellant rocket motor. Accordingly, the recent research efforts are focused on the improvement of engine efficiency and regression rate in the hybrid rocket engine. The present study has numerically investigated the combustion processes in the hybrid rocket engine. The turbulent combustion is represented by the flamelet model and Low Reynolds number $k-{\varepsilon}$ turbulent model is employed to reduce the uncertainties for convective heat transfer near solid fuel surface having strong blowing effect. Based on numerical results, the detailed discussions have been made for the effects of oxygen injection methods and oxygen injection flow rate on flame structure and regression rate in the vortex hybrid rocket engines