지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 발행연도
- 2013
- 저작권
- 부산대학교 논문은 저작권에 의해 보호받습니다.
이용수6
이 논문의 연구 히스토리 (3)
- 이 논문의 후속연구가 궁금하신가요?
- 연관 학술논문 또는 학술발표를 통해 보다 발전된 연구결과를 확인하실 수 있습니다.
- 이 논문의 연구 히스토리 확인하기
초록· 키워드
오류제보하기
The development of composite rocket propellants in past was mainly directed to thermoset polymers. However, the thermoset composite propellants have the complication in formulation and fabricating process to adapt tp rocket system requirements.
In contrast to the thermoset propellant, the modified PVC and PEBAX(polyether block amide) composite propellants is being developed as the advantages of the simplification in the manufacturing process, the low cost of the raw material, and stability of the handling process.
This paper carried out in three ways by the PEBAX binders.
The tensile strength of thermoplastic propellant produced by using the PEBAX polymer was tested in accordance with JANNAF (Joint Army Navy NASA Air Force) Interagency Propulsion Committee standards. The BATES were performed in order to analyze the characteristics of this propellant. By applying the different ratio of binder, oxidizer and aluminum powder, the test indicated that the tensile strength and the burning rate were in inverse proportion to each other.
Comparison of combustion characteristics for the PEBAX and PVC binders was performed. PEBAX binder indicated higher burning rate and specific impulse than PVC binder. After the burning test, it shows that the nozzle of motor using grain which is made of PEBAX binder is less damaged than PVC binder’s nozzle. The nozzle of motor with using grain which is made of PVC binder is deposited by aluminum oxide.
The LiF(lithium fluoride) was added to PEBAX binder by negative catalyst for burning rate. In additon, of increase of LiF decreased burning rate. The AP(ammonium perchlorate) composite propellant of burning rate decreased as LiF added.
In contrast to the thermoset propellant, the modified PVC and PEBAX(polyether block amide) composite propellants is being developed as the advantages of the simplification in the manufacturing process, the low cost of the raw material, and stability of the handling process.
This paper carried out in three ways by the PEBAX binders.
The tensile strength of thermoplastic propellant produced by using the PEBAX polymer was tested in accordance with JANNAF (Joint Army Navy NASA Air Force) Interagency Propulsion Committee standards. The BATES were performed in order to analyze the characteristics of this propellant. By applying the different ratio of binder, oxidizer and aluminum powder, the test indicated that the tensile strength and the burning rate were in inverse proportion to each other.
Comparison of combustion characteristics for the PEBAX and PVC binders was performed. PEBAX binder indicated higher burning rate and specific impulse than PVC binder. After the burning test, it shows that the nozzle of motor using grain which is made of PEBAX binder is less damaged than PVC binder’s nozzle. The nozzle of motor with using grain which is made of PVC binder is deposited by aluminum oxide.
The LiF(lithium fluoride) was added to PEBAX binder by negative catalyst for burning rate. In additon, of increase of LiF decreased burning rate. The AP(ammonium perchlorate) composite propellant of burning rate decreased as LiF added.
목차
제 1 장 서론 11.1 연구배경 11.2 선행연구 21.3 연구목적 5제 2 장 이론적 배경 62.1 열가소성 고체추진제의 특징 62.2 열가소성 고체추진제의 제조공정 82.3 원재료의 특성 102.4 연소속도 분석방법 14제 3 장 실험장치 및 실험방법 183.1 인장시험 183.2 연소속도 측정 203.2.1 BATES MOTOR 203.2.2 지상연소시험장치 21제 4 장 열가소성 고체추진제의 실험결과 244.1 바인더 함량에 따른 인장강도 및 연소특성 분석 244.2 바인더 종류에 따른 연소특성 분석 304.3 첨가제 함량에 따른 연소특성 분석 36제 5 장 결과 및 고찰 41참고 문헌 44ABSTRACT 46
최근 본 자료
댓글(0)
0