[논문]The Experiments for the Enhancement of Regression Rate of Hybrid Rocket Fuel

Shin Kyung-Hoon; Lee Changjin; Yu Yung H.

doi:10.1007/bf02984273

The Experiments for the Enhancement of Regression Rate of Hybrid Rocket Fuel 원문보기

Journal of mechanical science and technology, v.19 no.10, 2005년, pp.1939 - 1949

Shin Kyung-Hoon (Department of Aerospace engineering, Konkuk University) , Lee Changjin (Department of Aerospace engineering, Konkuk University) , Yu Yung H. (Department of Aerospace engineering, Konkuk University)

Abstract ▼ AI-Helper

Many studies have been conducted to increase regression rate of solid fuel in hybrid rocket. One of them resorts to swirl flow since it can extend the residence time of oxidizer in the fuel grain. Also, metal wires may lead to increase the regression rate of solid fuel as shown in solid propellants. In this study, a series of experiments was designed to investigate the enhancement of regression rate of solid fuel by embedded metal wires and by fuel port grain. And fuel port was designed with a helical configuration to attempt to induce swirl flow. PMMA with gaseous oxygen is the solid fuel used for investigation. Test results showed that embedded metal wires turned out to be ineffective method because only $3-4\%$ increases in regression rate were observed. However, fuel port grain configuration yields higher burning performance of up to $50\%$ increase in regression rate. Also pitch number as well as total impulse was found to be a design variable.

주제어

AI 본문요약
AI-Helper

* AI 자동 식별 결과로 적합하지 않은 문장이 있을 수 있으니, 이용에 유의하시기 바랍니다.

문제 정의

So, it is natural to seek a solution to overcome the disadvantage of unbalanced combustion volume of solid fuel by using other applicable options such as swirl generation and secondary oxidizer injection. In the aspect, this study concentrates on the subject to improve swirl effect over the whole length of the port by _니sing the internal helical grain configuration.
This study aims to assess the effectiveness of various methods on the increase in the regression rate of hybrid rocket fuel, PMMA. Embedded metal wires and a helical fuel port grain configu ration were experimentally tested.

제안 방법

A baseline test was conducted with PMMA fu_이 and gaseous oxygen in order to verify experi mental setup and test procedure. Yuasa et al.
In this study, two different methods were tested and evaluated the effectiveness on the augmenta tion of regression rate of PMMA fuel; embedded metal wires and swirl flow generated by helical grain configuration. Both methods are easy to apply to any locations along the fuel port where the enhancement is needed.
Another effort to in crease the regression rate was done by Risha, Boyer, Wehrman, and Kuo (2002). Their experi ments were designed to evaluate the effect of the addition of nano-sized energetic powder on the regression rate augmentation. Test results rev ealed that the addition of 13% of energetic pow ders showed an increase of up to 63% in mass burning rate compared to the pure HTPB fuel.

대상 데이터

and test configuration. The fuel used in the test is PMMA (Poly Methyl MethAcrylate) and the gaseous oxygen is used as an oxidizer. In the design stage of hybrid rocket motor, the combus tion pressure is determined at 300 psi for safety reason.

데이터처리

Also several configurations with different pitches were tested at various oxidizer flux condi tions. Results of each method are compared with baseline test results and analyzed.

성능/효과

Table 2 summarizes test results of metal wires for the increase in regression rate of PMMA fuel. In the results, it was found that total percentage of increase in regression rate with embedded wires ranges from 2.14% to 3.7%, which are negligibly small increases compared to those observed in the solid propellant. Silver wires were found to be more effective in enhancing the heat transfer rate to solid fuel compared to the regression rate with copper wires.
Their experi ments were designed to evaluate the effect of the addition of nano-sized energetic powder on the regression rate augmentation. Test results rev ealed that the addition of 13% of energetic pow ders showed an increase of up to 63% in mass burning rate compared to the pure HTPB fuel. Although, however, the addition of AP/A1 turn ed out to be an effective method in increasing regression rate, it should be noted the use of additives may deteriorate the safety feature of hybrid fuel.
Tamura, Yuasa, and Yamamoto (1999), Yuasa, Shimada, Imamura, Tamura and Yamamoto (1999), and Yuasa, Yamamoto, Hachiya, Kitagawa, and Owada (2001) designed a swirl injector for oxi dizer stream and tested the effect of swirl strength on the regression rate. Test results showed the average regression rate increased up to 200% as swirl number increases. However, it was also found that the enhancement of regression rate is severely localized near the inlet of fuel port.
George, Krishnan, Varkey, Ravindran, and Ramachandran (1998) conducted a series of ex periments with solid fuel, HTPB modified by AP and Al additives. Test results showed the re gression rate increased considerably up to 180% compared to that of baseline fuel (pure HTPB). Also, Frederick, Moser, Knox, and Josh (2004) tested hybrid propellants to evaluate the effect of the addition of AP on the augmentation of the regression rate of HTPB based fuel.
For metal wire method, two different metal wires such as silver and copper were used. Test results, however, showed only up to 3% increase in regression rate for all metal wires regardless of wire diameters and material types. The amount of increase in regression rate with metal wires is negligibly small when it is compared to that observed in solid propellant, which is in the order of several hundred percentage increase.
Test results, however, showed that a fuel with pitch 3 revealed that the highest increase in vol ume burning rate ( V) was 5.075 cm³/s equivalent to 35% increase compared to that of baseline case, which is less than surface area (&) increase of 50%, And the increase in volume burning rate becomes approximately equal to surface area in crease as pitch number increases. So, for example, the difference between volume rate and surface area increase becomes almost negligible at pitch 12 showing 114.
Also, Frederick, Moser, Knox, and Josh (2004) tested hybrid propellants to evaluate the effect of the addition of AP on the augmentation of the regression rate of HTPB based fuel. Their results showed the similar results as observed in the reference (George et al., 1998) and the addition of AP of up to 25% produced the increase of 150- 300% in regression rate. Another effort to in crease the regression rate was done by Risha, Boyer, Wehrman, and Kuo (2002).

후속연구

Thus, the optimal grain configuration should be determined by considering both regression rate behavior and total impulse characteristics. And further study will focus on the issue what configuration of fuel port is suitable to generate swirl flow as well.

참고문헌 (14)

Frederick, R. A., Moser, M. D., L. Knox, R. and Josh, J., 2004, 'Ballistic Properties of Mixed Hybrid Propellants,' AIAA paper 2004-3824, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
George, P., Krishnan, S., Varkey, P. M., Ravindran, M. and Ramachandran, L., 1998, 'Fuel Regression Rate Enhancement Studies In HTPB/GOX Hybrid Rocket Motors,' AIAA paper 9835064, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Humble, R. W., Henry, G. N. and Larson, W. J., 1995, Space Propulsion Analysis and Design, McGraw-Hill, Inc., Chap, 7
Knuth, W. H., Chiaverini, M. J., Gramer, D. J. and Sauer, J. A., 1998, 'Experimental Investigation of A Vortex-Driven High-Regression Rate Hybrid Rocket Engine,' AIAA paper 98-3348, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Knuth, W. H., Chiaverini, M. J., Gramer, D. J. and Sauer, J. A., 1998, 'Development and Testing of a vortex-driven, High-regression Rate Hybrid Rocket Engine,' AIAA paper 98-3507, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Knuth, W. H., Chiaverini, M. J., Gramer, D. J. and Sauer, J. A., 1999, 'Solid-Fuel Regression Rate and Combustion Behavior of Vortex Hybrid Rocket Engines,' AIAA paper 99-2318, 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
King, M. K., 1989, 'Analytical Modeling of Effects of Wires on Solid Motor Ballistics,' AIAA paper 89-2784
Kubota, N., Ichida, M. and Fujisawa, T., 1982, 'Combustion Processes of Propellants with Embedded Metal Wires,' AIAA Journal, Vol. 20. pp. 116-121

상세보기
Risha, G. A., Boyer, E., Wehrman, R. B. and Kuo, K. K., 2002, 'Performance Comparison of HTPB-Based Solid Fuels Containing NanoSized Energetic Powder in a Cylindrical Hybrid Rocket Motor,' AIAA paper 2002-3576, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Sutton, G. P. and Biblarz, O., 2001, Rocket Propulsion Elements, 7th ed., John Wiley & Sons, Chap. 15
Tamura, S., and Yuasa, S. and Yamamoto, K., 1999, 'Effects of Swirling Oxidizer Flow on Regression Rate of Hybrid Rockets,' AIAA paper 99-2323, 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Yuasa, S., Shimada, O., Imamura, T., Tamura, T. and Yamamoto, K., 1999, 'A Technique for Improving the Performance of Hybrid Rocket Engines,' AIAA paper 99-2322, 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Yuasa, S., Yamamoto, K., Hachiya, H., Kitagawa, K. and Owada, Y, 2001, 'Development of a Small Sounding Hybrid Rocket with a Swirling-Oxidizer-Type Engine,' AIAA paper 01-3537, 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibits
Zennin, A. A., Glaskova, A. P., Leipunskyi, O. I. and Bobolev, V. K., 1969, 'Effect of Metallic Additives on the Deflagration of Condensed System,' Twelfth Symposium (International) on Combustion, Combustion Institute, Pittsburgh, PA, pp. 27-35

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 관리번호, 논문명, 저널/프로시딩명, 저자 , 발행년, 권, 호, 시작페이지, 끝페이지, 발행기관 관리번호, 논문명, 대등논문명, 저자 , 저널/프로시딩명, 발행기관, 발행년, 발행언어, 권, 호, 시작페이지, 끝페이지, ISBN, ISSN, 주제분야, 키워드, 초록(한글), 초록(영문), 저자(소속기관)
저장형식	Text(ASCII format) Excel format RefWorks Direct Export RIS format (for Reference Manager, ProCite, EndNote), Scholar's Aids, Mendeley
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	총 건의 자료가 검색되었습니다. 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오. ~ Text(ASCII format) Excel format

연합인증

The Experiments for the Enhancement of Regression Rate of Hybrid Rocket Fuel 원문보기

Abstract ▼ AI-Helper

주제어

AI 본문요약
AI-Helper

문제 정의

제안 방법

대상 데이터

데이터처리

성능/효과

후속연구

참고문헌 (14)

이 논문을 인용한 문헌

관련 콘텐츠

원문 보기

원문 URL 링크

오픈액세스(OA) 유형

이 논문과 함께 이용한 콘텐츠

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

연합인증

The Experiments for the Enhancement of Regression Rate of Hybrid Rocket Fuel 원문보기

Abstract ▼ AI-Helper

주제어

AI 본문요약 엑셀 다운로드 AI-Helper

문제 정의

제안 방법

대상 데이터

데이터처리

성능/효과

후속연구

참고문헌 (14)

이 논문을 인용한 문헌

관련 콘텐츠

원문 보기

원문 URL 링크

오픈액세스(OA) 유형

이 논문과 함께 이용한 콘텐츠

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

AI 본문요약
AI-Helper