Design of Propellant Composite Thermodynamic Properties Using Rocket Propulsion Analysis (RPA) Software

Reaktor Pub Date : 2022-07-12 DOI:10.14710/reaktor.22.1.1-6
A. Pinalia, Bayu Prianto, Henny Setyaningsih, Prawita Dhewi, R. Ratnawati
{"title":"Design of Propellant Composite Thermodynamic Properties Using Rocket Propulsion Analysis (RPA) Software","authors":"A. Pinalia, Bayu Prianto, Henny Setyaningsih, Prawita Dhewi, R. Ratnawati","doi":"10.14710/reaktor.22.1.1-6","DOIUrl":null,"url":null,"abstract":"Rocket Propulsion Analysis (RPA) is software for predicting the performance of a rocket engine. It is usually used in conceptual and preliminary design. Heat capacity and specific impulse are two properties related to the performance of a propellant. This work aimed to design AP/HTPB-based solid propellant composite with various compositions and predict the heat capacity and specific impulse using the RPA software. The materials used were ammonium perchlorate (AP) as the oxidizer, Hydroxy-Terminated Polybutadiene (HTPB) as the fuel binder, Al powder as the metal fuel, and other additives. Four propellants with different formulations were prepared and tested for heat capacity and specific impulse. The experimental heat capacity was obtained using a differential scanning calorimeter (DSC), while the specific impulse was obtained using a bomb calorimeter. The same propellant formulations were used as the input to the RPS to predict the heat capacity and specific impulse. The results show that the experimental heat capacity of the propellant ranges from 1.576 to 4.08 J g–1 K–1, and the simulation result ranges from 1.78 to 3.48 J g–1 K–1. The overall average deviation is 16.3%. The predicted specific impulse at vacuum and sea level ranges from 231.3 to 234.0 s and from 219.8 to 220.9 s, respectively. Meanwhile, the experimental specific impulse at vacuum and sea level varies from 236.2 to 240.3 s and from 228.5 to 232.9 s, respectively. The overall average deviation is 3.7%. Therefore, the RPA is reliable for predicting specific impulse of propellant, but it is not accurate enough for predicting the heat capacity of propellant composite.","PeriodicalId":20874,"journal":{"name":"Reaktor","volume":null,"pages":null},"PeriodicalIF":0.0000,"publicationDate":"2022-07-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Reaktor","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.14710/reaktor.22.1.1-6","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
引用次数: 0

Abstract

Rocket Propulsion Analysis (RPA) is software for predicting the performance of a rocket engine. It is usually used in conceptual and preliminary design. Heat capacity and specific impulse are two properties related to the performance of a propellant. This work aimed to design AP/HTPB-based solid propellant composite with various compositions and predict the heat capacity and specific impulse using the RPA software. The materials used were ammonium perchlorate (AP) as the oxidizer, Hydroxy-Terminated Polybutadiene (HTPB) as the fuel binder, Al powder as the metal fuel, and other additives. Four propellants with different formulations were prepared and tested for heat capacity and specific impulse. The experimental heat capacity was obtained using a differential scanning calorimeter (DSC), while the specific impulse was obtained using a bomb calorimeter. The same propellant formulations were used as the input to the RPS to predict the heat capacity and specific impulse. The results show that the experimental heat capacity of the propellant ranges from 1.576 to 4.08 J g–1 K–1, and the simulation result ranges from 1.78 to 3.48 J g–1 K–1. The overall average deviation is 16.3%. The predicted specific impulse at vacuum and sea level ranges from 231.3 to 234.0 s and from 219.8 to 220.9 s, respectively. Meanwhile, the experimental specific impulse at vacuum and sea level varies from 236.2 to 240.3 s and from 228.5 to 232.9 s, respectively. The overall average deviation is 3.7%. Therefore, the RPA is reliable for predicting specific impulse of propellant, but it is not accurate enough for predicting the heat capacity of propellant composite.
基于火箭推进分析(RPA)软件的推进剂复合材料热力学特性设计
火箭推进分析(RPA)是用于预测火箭发动机性能的软件。它通常用于概念设计和初步设计。热容量和比冲是与推进剂性能有关的两个性质。本工作旨在设计不同成分的AP/ htpb基固体推进剂复合材料,并利用RPA软件对其热容量和比冲进行预测。采用高氯酸铵(AP)作为氧化剂,端羟基聚丁二烯(HTPB)作为燃料粘结剂,铝粉作为金属燃料,以及其他添加剂。制备了4种不同配方的推进剂,并对其热容和比冲进行了测试。实验热容用差示扫描量热计(DSC)计算,比冲用弹式量热计计算。使用相同的推进剂配方作为RPS的输入来预测热容量和比冲。结果表明,推进剂的实验热容范围为1.576 ~ 4.08 J g-1 K-1,模拟热容范围为1.78 ~ 3.48 J g-1 K-1。总体平均偏差为16.3%。预测的真空比冲和海平面比冲分别为231.3 ~ 234.0 s和219.8 ~ 220.9 s。同时,真空和海平面的实验比冲分别在236.2 ~ 240.3 s和228.5 ~ 232.9 s之间变化。总体平均偏差为3.7%。因此,RPA对推进剂比冲的预测是可靠的,但对推进剂复合材料热容量的预测不够准确。
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
自引率
0.00%
发文量
15
审稿时长
2 weeks
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
确定
请完成安全验证×
copy
已复制链接
快去分享给好友吧!
我知道了
右上角分享
点击右上角分享
0
联系我们:info@booksci.cn Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。 Copyright © 2023 布克学术 All rights reserved.
京ICP备2023020795号-1
ghs 京公网安备 11010802042870号
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术官方微信