• 한국항공우주학회지
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• 제35권10호
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• pp.934-939
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• 2007

추력방향제어는 발사 직후 비행체를 임의의 방향으로 급선회해야 할 경우에 초음속 노즐의 배출가스 방향을 조절하여 측력과 모멘트를 형성시키는 방법이다. 본 연구에서는 압축공기를 이용한 비 연소시험으로 초음속유동 시험장치를 이용하여 기계적 편향판인 램프 탭의 설치위치에 따라 성능연구를 수행하였다. 밀도변화에 따라 유동장을 관찰할 수 있는 쉬리렌 장치를 이용하여 램프 탭 내부에서 발생하는 유동장 구조와 경사충격파의 위치 등을 가시화하였다. 아울러 각 방향에 작용하는 제어 힘, 추력손실 및 표면 압력 분포 등을 도시분석하였다.

• 한국유체기계학회 논문집
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• 제10권6호
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• pp.32-37
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• 2007

Aerodynamic forces and moments have been used to control rocket propelled vehicles. If control is required at very low speed, Those systems only provide a limited capability because aerodynamic control force is proportional to the air density and low dynamic pressure. But thrust vector control(TVC) can overcome the disadvantages. TVC is the method which generates the side force and roll moment by controlling exhausted gas directly in a rocket nozzle. TVC is classified by mechanical and fluid dynamic methods. Mechanical methods can change the flow direction by several objects installed in a rocket nozzle exhaust such as tapered ramp tabs and jet vane. Fluid dynamic methods control the flight direction with the injection of secondary gaseous flows into the rocket nozzle. The tapered ramp tabs of mechanical methods are used in this paper. They installed at the rear in the rocket nozzle could be freely moved along axial and radial direction on the mounting ring to provide the mass flow rate which is injected from the rocket nozzle. In this paper, the conceptual design and the study on the tapered ramp tabs of the thurst vector control has been carried out using the supersonic cold flow system and schlieren system. This paper provides the thrust spoilage, three directional forces and moments and distribution of surface pressure on the region enclosed by the tapered ramp tabs.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회B
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• pp.3068-3073
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• 2007

Aerodynamic forces and moments have been used to control rocket propelled vehicles. If control is required at very low speed, Those systems only provide a limited capability because aerodynamic control force is proportional to the air density and low dynamic pressure. But thrust vector control(TVC) can overcome the disadvantages. TVC is the method which generates the side force and roll moment by controlling exhausted gas directly in a rocket nozzle. TVC is classified by mechanical and fluid dynamic methods. Mechanical methods can change the flow direction by several objects installed in a rocket nozzle exhaust such as tapered ramp tabs and jet vane. Fluid dynamic methods control the flight direction with the injection of secondary gaseous flows into the rocket nozzle. The tapered ramp tabs of mechanical methods are used in this paper. They installed at the rear in the rocket nozzle could be freely moved along axial and radial direction on the mounting ring to provide the mass flow rate which is injected from the rocket nozzle. In this paper, the conceptual design and the performance study on the tapered ramp tabs of the thurst vector control has been carried out using the supersonic cold flow system and shadow graph. Numerical simulation was also performed to study flow characteristics and interactions between ramp tabs. This paper provides to analyze the location of normal shock wave and distribution of surface pressure on the region enclosed by the tapered ramp tabs.

• 한국추진공학회지
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• 제7권3호
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• pp.45-52
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• 2003

원추형 초음속 노즐 확산부에 이차유동이 음속으로 분출될 때 나타나는 노즐 내부 유동장에 대한 수치적 연구가 이루어졌다. 대수-난류모델과 $\kappa$-$\varepsilon$ 모델을 사용한 레이놀즈-평균 Navier-Stokes 방정식을 계산함으로서 노즐 내부에서 나타나는 충격파와 경계층의 간섭에 의한 3 차원 유동장을 해석하였다. 얻어진 수치해석의 결과는 동일한 조건에서 수행된 실험결과와 잘 일치하고 있음이 판명되었다. 이차유동의 분출압력 변화가 충격파와 경계층의 간섭과 함께 노즐내부 유동장 구조에 미치는 영향을 평가하였다. 아울러 충격파 간섭 후방에서 나타나는 와류유동 구조와 벽면 압력분포에 관한 정보를 얻었다.