Numerical optimization of two dimensional high lift configuration was performed with flow solver and optimization method based on RSM(Response Surface Model). Navier-Stokes solver with Spalart-Allmaras turbulence model was selected for the simulation of highly complex and separated flows on the flap. For the simultaneous optimization of both flap shape and setting (gap/overlap), 10 design variables (eight variables for flap shape variation and two variables for flap setting) were chosen. In order to generate the response surface model, 128 experimental points were selected for 10 design variables. The objective function considering maximum lift coefficient, lift to drag ratio and lift coefficient at specific angle of attack was selected to reduce flow separation on the flap surface. The present method was applied to two dimensional fowler flap in landing configuration. After applying the present method, it was shown that the optimized high lift configuration had less flow separation on the flap surface and lift to drag ratio was suppressed over entire angle of attack range.

Hypersonic vehicles over Mach 5 need active cooling or thermal management systems to resolve excessive heating problems on their fuselage and engines. Endothermic fuels are widely used these days not only for the energy source but also for a heat sink. Therefore, fuel supply systems of hypersonic vehicles should be mainly composed of adiabatic fuel storage tank, cooling systems for the airframe and engine/nozzle, and fuel supply/injection systems in high pressure, high temperature, and high fuel flow rate conditions. This paper describes a conceptual design process of a hypersonic fuel supply system in order for designing a layout of the system, and identifying components and their specification requirements.

Tail wing is important to designing of civil aircrafts, because it is responsible for aircraft stability and control. Tail wing has a role in aircraft control and makes aircraft fly stably without any pilot control input. Also, designing of tail wing determine trim drag force in whole aircraft. Center of gravity(CG) of aircraft travels with various effects as placement of passenger's seats, location of cargo bay, etc. In designing horizontal tail volume, aircraft CG travel has to be considered to have margin so that it should be sized to provide adequate stability and control for the airplane's entire CG range throughout the flight envelope. Finally, it is essential to have sufficient elevator control to perform stall at forward CG for all flaps down configurations. Such stalls establish the FAR stall speed which airplane take-off and landing performance. This paper deals with the process for tail wing design regarding the aircraft CG travel and results for 95-seat type turboprop aircraft.

In case of cube satellite, it is difficult to realize the same performance as commercial satellite due to its highly restricted unit accommodation space. To maximize the performance of the cube satellite, design concept considering the multi-function of satellite is required. In this paper, mechanism design of cube satellite which is applicable for the holding and release of multi-deployable structures has been proposed and investigated. In addition, a switch mechanism design for the autonomous system operation just after the cube satellite separation from P-POD has also been proposed. The effectiveness of the mechanism design for holding and release of multi-deployable structures has been demonstrated by EM test of the holding and release mechanism.

Passive attitude stabilization method has been widely usde for attitude determination and control of cube satellite due to its advantage of system simplicity. The permanent magnet installed on the cube satellite passively controls the attitude of the satellite such that the satellite is aligned with the earth magnetic field. In this paper, on-orbit thermal behavior of the cube satellite with the permanent magnet attitude stabilization method has been investigated through on-orbit thermal analysis. THe orbit profile obtained from the aforementioned attitude control method has been reflected in the analysis. The analysis results indicate that the thermal design proposed in this study is effective for satisfying the temperature requirements of the commericial mission equipments.

The air data measured from the static pressure, the dynamic pressure and etc. of an airplane is used for calculation of many flight parameters(altitude and airspeed and so on) and these values applied to flight safety and navigation flight. The pitot-static system of the development airplane is calibrated by finding of pitot-static system's error using tower fly-by, trailing cone method and etc. This paper is describing for the introduction of the trailing cone method and major items for test planning, preparation, operation and results for air data calibration flight test performed, considering efficiency and safety during KC-100 development project.

On this study, climb performance related airworthiness requirements for small airplane on KAS Part 23 and flight test techniques for climb performance (Sawtooth climb) are introduced. Also, applicable procedures, test conditions and required test parameters of sawtooth climb flight test techniques are reviewed.

This is a research report about the method of how to maintain qualification of certification flight test crews. KCA(Korea Certification Agency) have completed the KC-100 airplane certification flight tests which is the first time experienced flight tests operation. After the certification flight test, it has been found that annual flying time requirement of 100 hours to the certification flight test pilot is too strict, and other several requirements to maintain the qualification of the certification test crew such as aircraft certification introduction training, initial flight test pilot and flight test engineer certification training, crew resource management training, aviation physiology training, and survival training was difficult to implement in Korean civil aviation environments. In this study, it was suggested that 30 hours of flying time for maintaining certification flight test pilot qualification could be applied to contribute for safe operation of certification flight test and the other training requirements of the certification flight test crew could be fulfilled using self made training courses, existing FAA training courses and Korean Air Force training resources. Therefore, it is recommended that the regulation of maintaining the certification flight test crew qualification should be refined to implement the requirement practically.

This study describes the Federal Aviation Administration(FAA) certification policy for approving the use of Type II, III, and IV deicing/anti-icing fluids on small category airplanes. These fluids can be characterized as non-Newtonian, pseudo-plastic fluids, also known as "thickened" fluids. Deicing fluids are used before takeoff to remove frost or ice contamination, while anti-icing fluids are used before takeoff to prevent frost or ice contamination from occurring for a period of time(referred to as "holdover time") after application. Thickened deicing/anti-icing fluids can affect airplane performance and handling characteristics and their residue may cause stiff or frozen flight controls. This study also describes an approval process that may be used by type certificate holders and applicants for a type certificate under parts 23 to support operational use of these fluids on their airplanes.

The paper presents the comprehensive studies of ISTQB(International Software Testing Qualification Board) for the reliable software development system in term of various aspects. It is critical to understand how the software testing is achieved is to efficiently manage the development process, to reduce the development cost, and to ultimately ensure the safety of the entire software system. This study may provide an enriched understanding about the rationale and true intent the behind software development model and testing design methods of ISTQB on software developer, test analysts, test engineers. In addition, this paper may serve as a useful supplementary material for the avionic engineers to establish the new regulations in avionic industries.

Avionics system designed for the 200 kg-class tiltrotor UAV has been developed. Avionics system for the UAV is the reconstruct system and can be programmed automation controller. This paper focuses on the design aspects of the hardware and presents the ground and flight test results. The hardware aspects of the avionics system include details about the hardware configurations for the interfaces with the Digital Flight Control Computer, sensors and Line-replaceable unit modifications.