고정익 군용 항공기 주요 구조물의 최적 배치 규칙에 관한 연구 = A Study on the Optimal Design Layout Rules for Fixed Wing Military Aircraft Primary Structure

다국어 초록 (Multilingual Abstract)

The primary structure of fixed wing military aircraft must efficiently transfer and support the flight and ground handling loads encountered during operation.
The primary structure of fixed wing military aircraft should also be arranged to efficiently transfer loads and minimize structural weight while considering ease of manufacture, the sequence and method of assembly, and accessibility for planned and unplanned maintenance.
In addition, when laying out the primary structure, the mating concept between structural components(fuselage to wing and empennage) and major systems(engine, landing gear) should be defined.
When developing a new fixed wing military aircraft, the optimized structural layout, from the initial development stage through the detail design stage and including the OML(Outer Mold Line) finalization, is very important in determining the aircraft’s performance.
In my thesis, through a case study of the structural arrangement of the primary structure in successfully developed and operated fixed wing military aircraft, I derived the rules governing the factors affecting structural arrangement.
The longeron, the longitudinal primary structure on the top of the fuselage, is a major structural element, like a human spine.
From the forward equipment bay to the aft fuselage, such as the sill longeron on the crew station, aerial refueling receptacle, or speed brake, the accessibility for system mounting and maintenance of the internal fuel tanks and the mating of the fuselage and the vertical stabilizer.
The keel beam, the primary structural element of the fixed wing military aircraft’s fuselage bottom, derives its arrangement from the available space for the landing gear bay, arresting hook support structure, engine installation accessibility, and other major systems.
The bulkheads, which are the primary structure in the lateral direction of the fuselage, derive their arrangement from the available space in the equipment bay, crew station, and internal fuel tanks area.
The roles and rules for the arrangement of the wing spars and ribs are also derived.
The aft fuselage structural arrangement from the engine-fuselage joint types is derived.
The results of the case study are expected to be helpful in the development of new fixed wing military aircraft in the future.

목차 (Table of Contents)

• Ⅰ. 서 론 1
• 1.1 연구 배경 1
• 1.2 문헌 조사 2
• 1.3 연구 목적 21
• Ⅱ. 본 론 22
• 2.1 운용 중인 고정익 군용 항공기 구조 배치설계 사례 연구 22
• 2.2 운용 중인 고정익 군용 항공기 구조 배치설계 사례 분석 결과 61
• Ⅲ. 결 론 69
• 참 고 문 헌 70
• 별 첨 72