Assessment of using electric pumps on hybrid rockets

Name: Assessment of using electric pumps on hybrid rockets
Author: Gegeoglu, K., Kahraman, M., Üçler, Çağlar, Karabeyoglu, A.

İsim	Assessment of using electric pumps on hybrid rockets
Yazar	Gegeoglu, K., Kahraman, M., Üçler, Çağlar, Karabeyoglu, A.
Basım Tarihi:	2019
Basım Yeri	- American Institute of Aeronautics and Astronautics Inc, AIAA
Tür	Belge
Dil	İngilizce
Dijital	Evet
Yazma	Hayır
Kütüphane:	Özyeğin Üniversitesi
Demirbaş Numarası	978-162410590-6
Kayıt Numarası	b829f8d5-d6b1-4d50-86ec-b72d853f884a
Lokasyon	Professional Flight Program
Tarih	2019
Örnek Metin	In small hybrid rockets, liquid oxidizer is fed into the combustion chamber by pressurizing the oxidizer tank to achieve the desired injector pressure. However, larger applications employ propellant pumps to keep the propellant tank mass at reasonable levels. Conventionally, pumps are implemented on rockets by means of turbopumps. However, turbopumps are complex systems with serious development time and costs. With the current advancements in batteries and electrical machinery, pumps driven by electric motors become viable actors. In the case of hybrid rockets, operation of a single liquid propellant with a single pump has significant advantages compared to their use in the bipropellant liquid engines. In this paper, an example case of an upper stage hybrid rocket system is introduced and a propellant pump is designed using CFD modeling. The advantage of using electric motor driven pumps has been established via weight analysis and a comparison between alternative feed systems. Turbopump system is not considered due to its complexity as an alternative system. Therefore, comparison is limited to the cold gas pressurization feed system. It has been shown that a significant advantage in total feed system weight is achieved not only with a high-head pump but also with a low-head pump with assistive pressurization. A 69.9 % mass reduction for double-stage pump system and a 45.2 % mass reduction for the single-stage pump system was calculated compared to the reference pressure-fed system.
DOI	10.2514/6.2019-4124

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Assessment of using electric pumps on hybrid rockets

Yazar Gegeoglu, K., Kahraman, M., Üçler, Çağlar, Karabeyoglu, A.

Basım Tarihi 2019

Basım Yeri - American Institute of Aeronautics and Astronautics Inc, AIAA

Tür Belge

Dil İngilizce

Dijital Evet

Yazma Hayır

Kütüphane Özyeğin Üniversitesi

Demirbaş Numarası 978-162410590-6

Kayıt Numarası b829f8d5-d6b1-4d50-86ec-b72d853f884a

Lokasyon Professional Flight Program

Tarih 2019

Örnek Metin In small hybrid rockets, liquid oxidizer is fed into the combustion chamber by pressurizing the oxidizer tank to achieve the desired injector pressure. However, larger applications employ propellant pumps to keep the propellant tank mass at reasonable levels. Conventionally, pumps are implemented on rockets by means of turbopumps. However, turbopumps are complex systems with serious development time and costs. With the current advancements in batteries and electrical machinery, pumps driven by electric motors become viable actors. In the case of hybrid rockets, operation of a single liquid propellant with a single pump has significant advantages compared to their use in the bipropellant liquid engines. In this paper, an example case of an upper stage hybrid rocket system is introduced and a propellant pump is designed using CFD modeling. The advantage of using electric motor driven pumps has been established via weight analysis and a comparison between alternative feed systems. Turbopump system is not considered due to its complexity as an alternative system. Therefore, comparison is limited to the cold gas pressurization feed system. It has been shown that a significant advantage in total feed system weight is achieved not only with a high-head pump but also with a low-head pump with assistive pressurization. A 69.9 % mass reduction for double-stage pump system and a 45.2 % mass reduction for the single-stage pump system was calculated compared to the reference pressure-fed system.

DOI 10.2514/6.2019-4124