Low toxic nitromethane based monopropellant for gas generator cycle air turbo ramjet engine

IF 5.4 2区工程技术 Q1 ENGINEERING, AEROSPACE

Propulsion and Power Research Pub Date : 2022-09-01 DOI:10.1016/j.jppr.2022.08.001

Ryojiro Minato

{"title":"Low toxic nitromethane based monopropellant for gas generator cycle air turbo ramjet engine","authors":"Ryojiro Minato","doi":"10.1016/j.jppr.2022.08.001","DOIUrl":null,"url":null,"abstract":"<div><p>The present study proposes ethanol-nitromethane mixture as a safe, storable, and low toxic monopropellant for a gas generator cycle air turbo ramjet engine and evaluates its propulsion performance. The present study proposes that nitromethane is mixed with ethanol to adjust gas generator combustion temperature. The author developed the computational code for the present analysis and verified its accuracy. The specific thrust of ethanol-nitromethane is nearly identical to that of ethanol-liquified oxygen and is higher than methanol-hydroxylammonium nitrate aqueous solution and hydrazine. Hydrazine has the highest Isp among the propellants in the present analysis. However, Isp of ethanol-nitromethane is nearly equal to that of ethanol-liquified oxygen and higher than those of methanol-hydroxylammonium nitrate aqueous solution, and hydroxyl terminated polybutadiene-ammonium perchlorate. With the propellant-to-air ratio range in the present study, ethanol-nitromethane has the stoichiometric condition at the ram combustor around the propellant-to-air ratio range from 0.2 to 0.25 and can obtain high ram combustion temperature. This result is favorable for ethanol-nitromethane because it improves the specific thrust and the specific impulse. Therefore, ethanol-nitromethane can be a promising low-toxic liquid monopropellant for the air turbo ramjet engine.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 3","pages":"Pages 311-324"},"PeriodicalIF":5.4000,"publicationDate":"2022-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000608/pdfft?md5=ed90d9d54f55b7904ed39981ba83c8fe&pid=1-s2.0-S2212540X22000608-main.pdf","citationCount":"1","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Propulsion and Power Research","FirstCategoryId":"5","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S2212540X22000608","RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q1","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}

引用次数: 1

Abstract

The present study proposes ethanol-nitromethane mixture as a safe, storable, and low toxic monopropellant for a gas generator cycle air turbo ramjet engine and evaluates its propulsion performance. The present study proposes that nitromethane is mixed with ethanol to adjust gas generator combustion temperature. The author developed the computational code for the present analysis and verified its accuracy. The specific thrust of ethanol-nitromethane is nearly identical to that of ethanol-liquified oxygen and is higher than methanol-hydroxylammonium nitrate aqueous solution and hydrazine. Hydrazine has the highest Isp among the propellants in the present analysis. However, Isp of ethanol-nitromethane is nearly equal to that of ethanol-liquified oxygen and higher than those of methanol-hydroxylammonium nitrate aqueous solution, and hydroxyl terminated polybutadiene-ammonium perchlorate. With the propellant-to-air ratio range in the present study, ethanol-nitromethane has the stoichiometric condition at the ram combustor around the propellant-to-air ratio range from 0.2 to 0.25 and can obtain high ram combustion temperature. This result is favorable for ethanol-nitromethane because it improves the specific thrust and the specific impulse. Therefore, ethanol-nitromethane can be a promising low-toxic liquid monopropellant for the air turbo ramjet engine.

查看原文本刊更多论文

燃气发生器循环空气涡轮冲压发动机低毒硝基单推进剂

提出了一种安全、可储存、低毒的乙醇-硝基甲烷混合推进剂用于燃气发生器循环空气增压冲压发动机，并对其推进性能进行了评价。本研究提出将硝基甲烷与乙醇混合以调节燃气发生器的燃烧温度。作者编制了本分析的计算程序，并对其准确性进行了验证。乙醇-硝基甲烷的比推力与乙醇-液氧的比推力基本相同，高于甲醇-硝基羟铵水溶液和肼。在本分析的推进剂中，联氨具有最高的Isp。而乙醇-硝基甲烷水溶液的Isp与乙醇-液氧水溶液的Isp基本相等，高于甲醇-硝酸羟铵水溶液和端羟基聚丁二烯-高氯酸铵水溶液的Isp。在本研究的推进剂空气比范围内，乙醇-硝基甲烷在推进剂空气比0.2 ~ 0.25附近的冲压燃烧室具有化学计量条件，可以获得较高的冲压燃烧温度。这个结果对乙醇-硝基甲烷有利，因为它提高了比推力和比冲。因此，乙醇-硝基甲烷是一种很有前途的低毒液体单一推进剂。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

Propulsion and Power Research Multiple-

CiteScore

7.50

自引率

5.70%

发文量

期刊介绍： Propulsion and Power Research is a peer reviewed scientific journal in English established in 2012. The Journals publishes high quality original research articles and general reviews in fundamental research aspects of aeronautics/astronautics propulsion and power engineering, including, but not limited to, system, fluid mechanics, heat transfer, combustion, vibration and acoustics, solid mechanics and dynamics, control and so on. The journal serves as a platform for academic exchange by experts, scholars and researchers in these fields.