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International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (SASE)

  • Semi Annual
  • /
  • 2383-4986(pISSN)
  • /
  • 2508-7169(eISSN)

Domain

  • Machinery ＞ Aircraft System
  • Machinery ＞ Space Launch Vehicle

Aim & Scope

The International Journal of Aerospace System Engineering(IJASE) provides a broad coverage of the materials and aerospace engineering technology, which include aerodynamics, aerospace telecommunications, airworthiness and maintenance, avionics, combustion and propulsion, flight dynamics, guidance and control, flight simulation and operations, sattelites, space exploration, structural dynamics and aeroelasticity, structures and materials, system engineerings, thermomechanics, tests including the ground and flight test of aerospace systems. The society for Aerospace System Engineering(SASE) is the society for aerospace engineerins and scientists in korea, and has published the international English language journal ‘IJASE’ and the Korean language journal ‘Journal of Aerospace System Engineering(JASE), which are indexed by KCI.

Volume 1 Issue 1

  1. Park, Soon Sang;Park, Jung Shin;Kwak, Jae Su 1
    https://doi.org/10.20910/IJASE.2014.1.1.001 PDF
    In this paper, the effects of the anti-vortex hole angle and blowing ratio on the flat plate film cooling effectiveness were experimentally investigated. For the film cooling effectiveness measurement, pressure sensitive paint technique was applied. The experiments were conducted for cylindrical and anti-vortex film cooling holes, and three blowing ratios of 0.25, 0.5, and 1.0 were tested. Two anti-vortex hole angles of 0 and 15 degree with respect to the flow direction were considered. For the cylindrical hole case, the film cooling effectiveness decreased as the blowing ratio increased because of the coolant lift-off. For the angle anti-vortex hole cases, however, higher blowing ratio resulted in higher film cooling effectiveness due to the reduced actual blowing ratio and diminished kidney vortex. For all blowing ratio, the angled anti-vortex hole case showed the highest film cooling effectiveness.
  2. Kang, Myoungcheol;Kho, Seonghee;Ki, Jayoung 10
    https://doi.org/10.20910/IJASE.2014.1.1.010 PDF
    This study presents technical description of the operating program development that operates the test bench for functional test of EECU. The test bench is capable of testing, simulation and adjustment of the EECU software using the operating program. The test bench is for the Development Project of the EECU platform for FADEC system. The operating program is consists of 3 modules which are the test bench operating module, cockpit simulator module and SILS module. The operating module mainly carries out the EECU test with manual operation and operating scenarios. Also that record and process the test data. The cockpit simulator module is capable of implementation of virtual cockpit control input and engine status display. The SILS module can simulate engine and EECU operation in software environment.
  3. Park, Gwanglim;Oh, Kyungwon;Kong, Changduk;Park, Hyunbum 16
    https://doi.org/10.20910/IJASE.2014.1.1.016 PDF
    Recently, various kinds of study on light weight structure are performing in the world. The Al honeycomb sandwich structural type adopt for improvement of lightness and structural stability to major part structure of aircraft or spacecraft. Adhesion badness properties of adhesive and adhesion properties of fillet mainly studied about al honeycomb structure. But study for adhesive properties of sandwich construction with surface treatment of Aluminum alloy barely performed. In this study, adhesive film was used between Al and honeycomb core of honeycomb panel[1]. The study for adhesive properties of sandwich construction with surface treatment of AA 5052 skin was performed.
  4. Lee, Haseung;Park, Gwanglim;Kong, Changduk;Park, Hyunbum 21
    https://doi.org/10.20910/IJASE.2014.1.1.021 PDF
    In this study, an investigation on mechanical properties of flax natural fiber composite is performed as a precedent study on the design of eco-friendly structure using flax natural fiber composite. The Vacuum Assisted Resin Transfer Molding-Light (VARTML) manufacturing method is adopted for manufacturing the flax fiber composite panel. The VARTML is a manufacturing process that the resin is injected into the dry layered -up fibers enclosed by a rigid mold tool under vacuum. In this work, the resin flow analysis of VARTM manufacturing method is performed. A series of flax composite panels are manufactured, and several kinds of specimens cut out from the panels are tested to obtain mechanical performance data. Based on this, structural design of chemical storage tank for agricultural vehicle was performed using flax/vinyl ester. After structural design and analysis, the resin flow analysis of VARTM manufacturing method was performed.
  5. Lee, Seok-Soon;Lee, Dong-Wook;Park, Min-Hyeok;Choi, Jin-Gyu;Nam, Kwang-Sik;Zhao, Shang 29
    https://doi.org/10.20910/IJASE.2014.1.1.029 PDF
    A displacement measurement system that uses fiber-optical common-path interferometry has been developed. The system includes fiber-optic devices and a collimator attached to a linear translation stage. The interferometry effect was detected with a photodetector whose signal was measured on an oscilloscope. Experiments showed that vibration of the stage disturbed the signal by causing nanoscale interference. Under stable conditions, the measured distance was the almost the same as the value calculated from the linear translation stage parameters.
  6. Jeon, Su-Hyeon;Jang, Su-Eun;Jung, Hyun-Mo;Cha, Jin-Yeong;Oh, Hyun-Ung 34
    https://doi.org/10.20910/IJASE.2014.1.1.034 PDF
    The STEP Cube Lab (Cube Laboratory for Space Technology Experimental Projects) is a 1U cube satellite developed by the Space Technology Synthesis Laboratory of Chosun University to be launched in 2015. Its mission objective is twofold: to determine which of the fundamental space technologies researched at domestic universities, will be potential candidates for use in future space missions and to verify the effectiveness of the technologies by investigating mission data obtained from on-orbit operation of the cube satellite. In this paper, a structural design concept based on the 1U standard to achieve the mission objective is introduced. The validity of the design has been demonstrated by quasi-static analysis and modal analysis. In addition, a non-explosive separation device triggered by burn wire heating, which is one of the main mission payloads is introduced.
  7. Kim, Sungsu;Park, Hyunbum 44
    https://doi.org/10.20910/IJASE.2014.1.1.044 PDF
    This study proposes a development for the nano silver adhesive, which is applicable to high efficiency LED(light-emitting diode) light. The important issue of LED light is heat exhaust from LED. Generally, the middle area of LED light is increased up to 380K. Therefore, the bottleneck between LED chip and heat sink are caused by high temperature. In this work, the adhesive material between LED Chip and heat sink was newly developed for improvement of bottleneck. The nano silver was adopted to solve heat problem of chip on board package for LED light. In order to evaluate the performance of the nano silver adhesive, the thermal analysis was performed. Moreover both adhesive performance and heat exhaust were verified through the prototype test. From the experimental test results, it is found that the developed nano silver adhesive has the high performance.