ASSESSING THE PERFORMANCE OF A GREEN LIQUID FUEL HYPERGOLIC WITH HYDROGEN PEROXIDE IN A 50 N BIPROPELLANT THRUSTER

Autor(es)

Maschio, Leandro Jose ^[1] ; de Araujo, Emmanuel Peres ^[2] ; Ferroni Pereira, Luis Gustavo ^[3] ; Gouvea, Leonardo Henrique ^[4] ; Vieira, Ricardo ^[1]

Afiliação do(s) autor(es)

^[1] Natl Inst Space Res, Combust & Prop Lab, BR-12630000 Cachoeira Paulista, SP - Brazil

^[2] Univ Sao Paulo, Lorena Sch Engn, Mat Engn Dept, BR-12602810 Lorena, SP - Brazil

^[3] Aeronaut Inst Technol, Chem Dept, BR-12228900 Sao Jose Dos Campos, SP - Brazil

^[4] Aeronaut Inst Technol, Aeronaut & Aerosp Engn Dept, BR-12228900 Sao Jose Dos Campos, SP - Brazil

• Tipo de documento: Artigo Científico
• Fonte: INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION; v. 20, n. 1, p. 21-30, 2021.
• Citações Web of Science: 0

Resumo

The last decades have witnessed an increasing interest in the development of green propellants for propulsion systems. Particularly in the low thrust domain, where a feasible alternative to the storable liquid bipropellant system hydrazine - nitrogen tetroxide is yet to be fully demonstrated, the application of green hypergolic propellants such as ethanol and H2O2 90 wt% appears to be a promising one. This work presents the design and firing test of a 50 N bipropellant thruster based on the H2O2 90 wt% - monoethanolamine-ethanol hypergolic pair catalyzed by Cu2+, previously developed by our research group. The 5 s firing test, conducted under a swirl injection scheme, yielded average values of 50.38 N, 147 s, and 1210 m/s for thrust, I-sp, and c{*}, respectively, with the target value of 5 bar for the chamber pressure being reached after 2 s of operation. Alongside with a c{*} efficiency of 84%, these results suggest that the assessed green hypergolic bipropellant pair may be a promising alternative for applications in the low-thrust range. (AU)