Numerical Analysis of Different Injectors for Kerosene/Hydrogen-Peroxide and Ethanol Amine/Hydrogen-Peroxide for Satellite Thruster Hindustan Institute of Technology and Science

Format:

Book

Conference/Event

Author/Creator:

Chidvilas, N.V., author.

Contributor:

Balaji, Kota

G., Dinesh Kumar

Suraj, V.

Conference Name:

International Conference on Trends in Automotive Parts Systems and Applications (2023-12-21 : Kuniamuthur, Coimbatore, India)

Language:

English

Physical Description:

1 online resource cm

Place of Publication:

Warrendale, PA SAE International 2024

Summary:

In a satellite thruster the function of injector plays a major role in controlling the combustion. This paper presents the numerical simulation of two most used injectors namely, impinging doublet, and triplet using Ansys fluent. The injectors are designed for the non-toxic, green propellants used in satellite thrusters. The present study focuses on the design and simulation of the injectors with 2 variant of green propellants id est, Kerosene/Hydrogen-peroxide and Ethanol Amine/Hydrogen-peroxide. The objective of the study is to investigate the performance of the two injectors in terms of atomization, combustion efficiency and thrust generation. Theoretical design calculations were performed for a 20 N bi-propellant satellite thruster. A comparative study on the condensed combustion products and injector was carried out using NASA CEA Run code and Ansys fluent, respectively. The ethanol amine/hydrogen-peroxide injector showed better performance in terms of combustion efficiency. The study provides valuable insights for the design of injectors for satellite thrusters, which can help in improving the performance of space propulsion systems

Notes:

Vendor supplied data

Publisher Number:

2023-01-5180

Access Restriction:

Restricted for use by site license