• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.3
• /
• pp.49-56
• /
• 2012

Rupture disks are a kind of safety device in high pressure equipment and they are used to control rupture pressure in the solid rocket motor. In this paper, a series of rupture experiments was performed using rupture disks made of AISI 316L and rupture pressure of rupture disks was calculated through various assumptions in relation between elasto-plastic material properties and true stress-strain curve. Experiment and FEA indicated rupture pressure is determined by size of rupture disks. As a result of elasto-plastic analysis, only multi-linear stress-strain curve was able to calculate meaningful estimations. Experimental results also showed rupture location are decided by the size of rupture disks. Experimental and FEA results will be applied to control rupture pressure of disks.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.666-669
• /
• 2011

The rupture disc shapes of bulkhead type pulse separation device(PSD) are designed for new dual pulse rocket motor. Before final design PSD, that three different rupture disc are tested and confirmed the performance of the discs. Through analyzing the test results the PSD decides, two rupture disc shapes with flow holes of eight circles and eight trapezoids.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.6
• /
• pp.20-28
• /
• 2021

High enthalpy test facilities, such as a shock tunnel, are to be operated at the specific pressure ratio according to the desired test condition. A metallic diaphragm is machined or a forced rupture device is used to open it at a specific pressure ratio. The diaphragm opening procedure takes several hundred microseconds including rupture and deformation. This process is expected to affect the test conditions. In this study, numerical simulation was performed for different materials, thicknesses, and opening ratios. And the characteristics of shock wave generation and the stagnation condition in the tube are investigated. Results show that the final opening ratio and rupturing procedure directly affect the speed of a shock wave, stagnation pressure, and test time.

• Aerospace Engineering and Technology
• /
• v.11 no.2
• /
• pp.122-128
• /
• 2012

Many of the liquid rocket engines use a hypergolic igniter with rupture disc ends located in the combustion chamber ignition line. In this study, the flow coefficient tests of the igniter, which have a solenoid valve upstream, were performed. The tension-type rupture discs for radial and circumferential scores and the igniter with them were tested using water at room temperature. The effects of the score, flow rate, the disc thickness, gas pocket and the solenoid valve on the coefficient were analyzed.

• Journal of the Korean Society for Nondestructive Testing
• /
• v.21 no.3
• /
• pp.313-318
• /
• 2001

To establish nondestructive test method for aerospace composite materials, various composite specimens were tested and analyzed using acoutic emission. The hit rate of acoustic emission closely was rotated with crack initiation and propagation. This report also presents defection capability of crack initiation pressure, initial crack active location, and crack propagation using acoustic emission.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.481-487
• /
• 2011

This paper provides a comparison between finite element analysis results and test data of rupture disc. Rupture disc is safety device of high pressure equipment. Rupture disc of solid rocket motor is a device to control rupture pressure. Rupture discs were made of AISI 316L. By the elastic-plastic analysis, the stress limit of rupture discs were compared to the test results. The results can be used to control the rupture pressure by the change of the disc size.

• The Korean Journal of Rheology
• /
• v.2 no.1
• /
• pp.46-52
• /
• 1990

배추의 조직감 특성을 기계적으로 측정하는 방법을 수립하기 위하여 여러 가지 형 태의 탐침에 의한 침투 및 절단시험에서 나타난는 힘-거리 곡선을 비교분석하였으며 그 결 과를 배추잎의 미세구조와 관능적특성과 연관하여 해석하였다. 배추잎의 침투심험에서 탐침 의 선단각, 선단면적 및 둘레에 따라 힘-거리 곡선의 형태는 크게 달라지며 선단면적과 둘 레가 커질수록 파열력이 크게 증대되었다. 절단시험에서는 표피와 내부유관속 조직을 절단 하는 세 개의 특징적인 피크를-나타내었다. 배추잎의 염장에 의하여 침투시험의 최대 변형 력은 크게 감소된 반면 파열력은 크게 증대되어 최대 변형력에 대한 파열력의 비(a/c) 는 증가되었으며 이것은 탐침의 선단면적과 둘레가 큰경우에 더욱 두드러지게 나타났다. 염장 에 의하여 탄성한계까지의 변형거리가 커졌으며 최초 변형에서의 탄성치(a/l)는 감소하는 경 향을 나타내었다. 절단시험에서는 염장에의하여 외피의 절단력이 상대적으로 증가하였다. 배 추 및 절인배추의 아삭아삭한 정도는 침투시험의 최대변형력과 a/l의 변화와 밀접한 관계가 있으며 질긴 정도는 침투시험의 파열력과 a/c 절단시험의 절단력과 관계가 있으며 아작아작 한 정도는 침투시험의 a/c와 관계가 있는 것으로 판단되었다.

• Journal of the Korean Institute of Gas
• /
• v.17 no.3
• /
• pp.20-26
• /
• 2013

In this research, an empirical study on the designed burst pressure of Type3 composite cylinder was performed by hydrostatic burst test equipment. The designed burst pressure of Type3 composite cylinders, which are 6.8 liter and 31 MPa of service pressure, was estimated with the analysis using the finite element method. In order to confirm its accuracy, the burst test of small Type3 composite cylinders was perfomed through three times. The burst test equipment can pressurize to 400 MPa. As a result of comparison between the designed burst pressure and actual burst pressure, the difference was less than 4 percentage. With a test result, the analysis accuracy was verified. This technique will be applied to both qualification and inspection for the composite cylinder.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.1
• /
• pp.98-106
• /
• 2022

To develop reliable dual pulse rocket motor, vacuum ignition performance at high altitude and design stability for rupture pressure of the Pulse Separation Device(PSD) are required. In this study, rupture pressure analysis method for the membrane type PSD of the dual pulse rocket motor was developed. The PSD rupture pressure formulation was derived from strain-pressure relationships. The PSD vacuum rupture test apparatus and the PSD 1 second vacuum ignition test apparatus were developed, which can simulate the high altitude vacuum environment. Rupture pressure of PSD was analyzed by conducting the PSD vacuum rupture test, and design values of PSD were derived. Finally, vacuum ignition performance and rupture pressure of the designed PSD were validated with PSD 1 second vacuum ignition test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.217-220
• /
• 2010

This paper presents an achieving method of reducing maximum acceleration for the missile by decrease of burst pressure in a nozzle closure. The relation of notch shape and burst pressure for a nozzle closure is examined by experiment. In the point of maximum acceleration reduction for a missile, an improved nozzle closure effects well compared with that of a reference closure by ground burning test of a gas generator.