초록 ▼

○ 로버 주 구조물 소재의 구조 성능 요구 조건 및 달 탐사 로버 기본 설계 확보 완료
○ 로버 복합재료를 위한 우주용 수지 및 고강도/고강성 섬유 보강재 선정.
○ 고점도 내열 수지를 이용한 복합재료 성형 공정 개발.
- 저점도 특성을 위한 기본 수지 formulation 확립 및 고내열, 저열팽창 특성 향상을 위한 경화도 제어 기술 개발
- 발열 제어를 위한 공정 최적화 연구
- 복합재료 경화 조건 확립
- 로버 주 구조물용 복합재 평판 제조.
○ 로버 주 구조물 적용 가능성 확인을 위한 시

○ 로버 주 구조물 소재의 구조 성능 요구 조건 및 달 탐사 로버 기본 설계 확보 완료
○ 로버 복합재료를 위한 우주용 수지 및 고강도/고강성 섬유 보강재 선정.
○ 고점도 내열 수지를 이용한 복합재료 성형 공정 개발.
- 저점도 특성을 위한 기본 수지 formulation 확립 및 고내열, 저열팽창 특성 향상을 위한 경화도 제어 기술 개발
- 발열 제어를 위한 공정 최적화 연구
- 복합재료 경화 조건 확립
- 로버 주 구조물용 복합재 평판 제조.
○ 로버 주 구조물 적용 가능성 확인을 위한 시제 제작 완료
○ 복합재 설계를 위한 물성 데이터 확보 및 Outgassing 특성 평가 완료

Abstract ▼

S U M M A R Y
Korean lunar explorer will be launched by korean launcher KSLV-2 in the 2020s in accordance with national space development strategy. Korean lunar explorer is composed of two unmanned orbiter and lander and the lander has a lunar rover. They should be developed as small size and lig

S U M M A R Y
Korean lunar explorer will be launched by korean launcher KSLV-2 in the 2020s in accordance with national space development strategy. Korean lunar explorer is composed of two unmanned orbiter and lander and the lander has a lunar rover. They should be developed as small size and light weight within 550kg of launch mass due to launcher's loading capability. In particular, the lunar rover must be less than 20kg in weight including, so-called, scientific payload. A structure of the lunar explorer and rover is required to have sufficient stiffness and strength under launch and operational environment as well as to accommodate mission equipment.
In recent years, lots of studies on the planetary rover systems have been performed around space advanced agencies such as NASA, ESA, JAXA, etc. Among the various technologies for the planetary rover system, the mobility system, navigation algorithm, and scientific payload have been focused particularly. The requirements of the Korean lunar rover’s mobility system as well as the constitutional materials are derived by means of considering mobility and stability from the status of overseas research and development of the planetary rover systems.
In order to reduce the total weight of the rover, it is necessary to adapt carbon fiber-reinforced composite materials replacing conventional metallic materials for rovers such as aluminum, titanium, steel due to the relatively excellent specific strength and modulus. In this work, we are focusing on the new composite for the rover's main structure by studying a matrix resin for the space environment and developing the resin formulation and a fabrication process of vacuum-assisted resin transfer molding (VARTM).
The experimental results showed that the proper formulation containing a cyanate ester-type resin and a catalyst and the curing condition for the high thermal resistance and stability as well as the good mechanical properties were developed. With this resin system, the composite was fabricated by the VARTM which is very favorable to making a complex structure compared to a conventional autoclave process.
The developed composite also showed the good outgassing properties of total mass loss (TML) and collected volatile condensable materials (CVCM) that must be qualified for the space materials. The real rover's main structure with the composite was fabricated in accordance with a structural design for Korean lunar rover indicating that this composite has possibility to apply to the rover.