| Full text | |
| Author(s): |
Maschio, Leandro Jose
[1]
;
de Araujo, Emmanuel Peres
[2]
;
Ferroni Pereira, Luis Gustavo
[3]
;
Gouvea, Leonardo Henrique
[4]
;
Vieira, Ricardo
[1]
Total Authors: 5
|
| Affiliation: | [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
Total Affiliations: 4
|
| Document type: | Journal article |
| Source: | INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION; v. 20, n. 1, p. 21-30, 2021. |
| Web of Science Citations: | 0 |
| Abstract | |
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) | |