Preliminary Analysis of Hybrid Rockets for Launching Nanosats into LEO

Autor(es)

Costa, Fernando de Souza ^[1] ; Vieira, Ricardo ^[1]

Afiliação do(s) autor(es)

^[1] INPE, LCP, BR-12630000 Cachoeira Paulista, SP - Brazil

• Tipo de documento: Artigo Científico
• Fonte: Journal of the Brazilian Society of Mechanical Sciences and Engineering; v. 32, n. 4, p. 502-509, OCT-DEC 2010.
• Citações Web of Science: 2

Resumo

This work determines the preliminary mass distribution of hybrid rockets using 98% H(2)O(2) and solid paraffin mixed with aluminum as propellants. An iterative process is used to calculate the rocket performance characteristics and to determine the inert mass fraction from given initial conditions. It is considered a mission to place a 20 kg payload into a 300 km circular equatorial orbit by air launched and ground launched hybrid rockets using three stages. The results indicate total initial masses of about 7800 kg for a ground launched hybrid rocket and 4700 kg for an air launched hybrid rocket. (AU)

• Processo FAPESP: 07/03623-8 - Bancada de testes de propulsores híbridos de baixo empuxo
• Beneficiário: Fernando de Souza Costa
• Modalidade de apoio: Auxílio à Pesquisa - Regular