초록 ▼

신개념 비행체 통합설계/형상관리
- 설계목표 및 예산 / 일정 관리
- 비행체 통합설계 및 형상설계완료 (외형 및 내부배치 완료)
- 형상정보의 일치성 확보 및 관리 (ICD, 3D모델, 도면, BOM)
- 비행체 상세설계 결과종합 및 물리적 / 전기적 인터페이스 종합관리
- 시험평가단계의 다양한 기술이슈/위험항목 발굴 및 관리
- 비행체 지상통합시험 및 비행시험 절차 수립
- 3단계 형상 개발을 위한 외형 및 탑재장비의 설계개선사항 종합/형상개정
공력/성능 해석 및 시험
- 비행체

신개념 비행체 통합설계/형상관리
- 설계목표 및 예산 / 일정 관리
- 비행체 통합설계 및 형상설계완료 (외형 및 내부배치 완료)
- 형상정보의 일치성 확보 및 관리 (ICD, 3D모델, 도면, BOM)
- 비행체 상세설계 결과종합 및 물리적 / 전기적 인터페이스 종합관리
- 시험평가단계의 다양한 기술이슈/위험항목 발굴 및 관리
- 비행체 지상통합시험 및 비행시험 절차 수립
- 3단계 형상 개발을 위한 외형 및 탑재장비의 설계개선사항 종합/형상개정
공력/성능 해석 및 시험
- 비행체 풍동시험 및 공력DB 구축
- 비행체 상세 공력해석 및 성능분석
- 축소기 지상 및 비행시험 지원
- 비행체 지상 및 비행시험 준비
기체구조 설계종합
- 구조 및 진동시험 검토 및 승인
- 구조설계/해석/시험 평가 종합 분석
- 설계 최적화(작업성, 유지보수성) 및 경량화
- 구조시제기 1대 및 비행시제기 2대 제작
로터/드라이브 시스템 개발
- 로터/드라이브 장치 상세 설계
- 로터/드라이브 장치 제작
- 아이언버드를 이용한 로터/드라이브 시스템 성능 및 내구성 시험
- 타시스템과의 연동 및 지상시험
- 비행시험 준비
자동비행시스템 개발
- 자동비행 시스템 개발 및 시험
- 자동비행 시스템 통합 및 지상시험
- 자동비행 시스템 성능분석 및 개선
추진시스뎀 개발
- 추진시스템 성능시험
- 추진시스템 통합 및 지상시험
- 추진시스템 성능분석
착륙장치 개발
- 착륙장치 상세설계 완료
- 착륙장치 제작 완료
- 착륙장치 낙하시험 수행 및 ADAMS 해석과의 보정 수행

Abstract ▼

A detailed design and manufacture of an advanced air vehicle was accomplished, which has the capabilities of VTOL(Vertical Take-Off and Landing), the high speed cruise and the autonomous flight. The trade-off study among various VTOL vehicle configurations was throughly performed and, the sizing tec

A detailed design and manufacture of an advanced air vehicle was accomplished, which has the capabilities of VTOL(Vertical Take-Off and Landing), the high speed cruise and the autonomous flight. The trade-off study among various VTOL vehicle configurations was throughly performed and, the sizing technique and the conceptual design/analysis technology were successfully acquired. As a result, the tiltrotor configuration was selected as our baseline configuration and the advanced tiltrotor air vehicle was designed and manufactured which is three times faster than conventional helicopter and has 5 hour endurance, 200km mission range.
- Integrated Design Part -
At first, the technical performance parameters were care fully selected and monitored which represent the key performances of the developed aircraft. The integrated design was performed based on CATIA 3-D digital mockup. The ease of assembly, disassembly and maintenance was also tested using 3-D digital mockup. The second generation demonstrator was also designed to improve the first generation demonstrator.
- Aerodynamic Design and Analysis Part -
The wind tunnel test of 40% scaled model was performed including the proprotor test and the full aircraft unpowered/powered test. The database of the aerodynamic coefficient was also generated for the performance analysis and the flight simulation. The dynamic stability of the Smart UAV was assessed based on the results of the powered dynamic stability wind tunnel test. The CFD including the powered effect of the proprotor was also performed to investigate the variation of the aerodynamic characteristics induced by the wake of the proprotor. The performance analysis code for the tiltrotor type aircraft was also developed to analyze the performance of the Smart UAV according to the various types of missions.
- Airframe Structure Part -
The detailed design of the airframe structure was performed based on the outcomes of the preliminary design. The airframe for the structural load test was manufactured and tested under the 11 ultimate load conditions and the structural integrity was validated through this load tests. Based on the results of the load tests, the redesign of the airframe structure was performed and the weight of airframe was reduced from 186 kg to 171 kg through this redesign. Finally, the 2 airframes for the real flight were manufactured.
- Rotor/Drive System Part -
The detailed design, manufacture and the assembly of the rotor and drive systems were finished through the international cooperative research. The performance and integrity of the systems were validated by performing the ironbird ground test. The design philosophy of the rotor system was applied to the 40 % scaled Smart UAV rotor system and the performance and integrity of the 40% scaled rotor system were validated through the fight tests.
- Automatic Flight Control Part -
The nonlinear simulation program was improved by updating the aerodynamic coefficients. The SAS was designed for the fixed wing mode, conversion mode and the helicopter mode and the conversion scheduler was finely tuned. The control laws were designed for the attitude/speed/altitude holding mode, the point navigation mode and the pre-programed flight mode. The designed automatic Hight control system was modified and applied to the 40 % scaled Smart UAV in order to validate the performance and integrity of the flight control system. The flight test of the small scale Smart UAV was performed successfully including the automatic take-off and landing, conversion and the point navigation. Based on this small scale fight test, the flight control system for the full scale Smart UAV is under developing.
- Propulsion/Engine Part -
The purchase of 3 PW-206C engines was completed. The intake, nozzle and the ejector were designed to install the PW engine to the Smart UAV. The detailed design and system setup was successfully performed for the signal sensing, electrical part, starter/generator, oil cooling system, power lever control linkage. The propulsion systems including the engine and sub-assemblies were successfully installed to the fight demonstrators. Finally, the engine run ground test was performed and through this test, the performance and integrity of the propulsion system were fully validated.
- Landing Gear Part -
The detailed design of landing gear was completed. The hydraulic oleo type landing gear was manufactured and tested successfully. The landing gear controller was designed and manufactured including the up-lock, down lock and weight-on-wheel switch. It's functional integrity is still on verification.

목차 Contents

• 제 1 장 연구개발과제의 개요 ...19
• 제 2 장 국내외 기술개발 현황 ...21
• 제 1 절 해외 기술개발 동향 ...21
• 제 2 절 국내 기술개발 동향 ...32
• 제 3 장 연구개발수행 내용 및 결과 ...36
• 제 1 절 신개념 비행체 통합설계/형상관리 ...36
• 제 2 절 스마트무인기 공력/성능 해석 및 시험 ...44
• 제 3 절 기체구조 설계종합 ...51
• 제 4 절 로터/드라이브 시스템 개발 ...87
• 제 5 절 자동비행시스템 개발 ...93
• 제 6 절 추진시스템 개발 ...155
• 제 7 절 착륙장치 개발 ...160
• 제 4 장 목표달성도 및 관련분야에의 기여도 ...165
• 제 1 절 2단계 연구개발목표 및 달성도 ...165
• 제 2 절 연차별 연구개발목표 및 달성도 ...170
• 제 3 절 최종목표 대비 2단계 주요성과의 기여도 ...191
• 제 4 절 2단계 주요 기술개발 성과 ...192
• 제 5 장 연구개발결과의 활용계획 ...201
• 제 1 절 기술개발 시 예상되는 파급효과 및 활용방안 ...201
• 제 2 절 과학기술적 응용 잠재력 ...205
• 제 6 장 연구개발과정에서 수집한 해외과학기술정보 ...208
• 제 7 장 참고문헌 ...209