Space Launch System Core-Stage Rocket Engine Development for Shock-Tunnel Testing

2018 ◽  
Vol 55 (2) ◽  
pp. 382-402
Author(s):  
Manish Mehta ◽  
C. Mark Seaford ◽  
Robert D. Kirchner ◽  
Aaron T. Dufrene
Keyword(s):  
Rocket Engine ◽  
Shock Tunnel ◽  
Space Launch ◽  
Engine Development ◽  
Tunnel Testing

Post Flight Analysis of SHEFEX I: Shock Tunnel Testing and Related CFD Analysis

2009 ◽  
Author(s):  
Jan Martinez Schramm ◽  
Alexander Wagner ◽  
Jeremy Wolfram ◽  
Klaus Hannemann ◽  
Tarik Barth ◽  
...  
Keyword(s):  
Shock Tunnel ◽  
Cfd Analysis ◽  
Tunnel Testing

BMW Rocket Engine Development

1948 ◽  
Author(s):  
Dietrich Singelmann ◽  
Heinz Mueller
Keyword(s):  
Rocket Engine ◽  
Engine Development

scholarly journals Energetic Compositions Application for the Reduction of the Environmental Pollution Because of Space Vehicle Launches

2017 ◽  
Vol 19 (3) ◽  
pp. 239 ◽  
Author(s):  
V. Trushlyakov ◽  
D. Lempert ◽  
Yuan-Jie Shu
Keyword(s):  
Rocket Engine ◽  
Space Vehicle ◽  
Combustion Products ◽  
Near Earth Space ◽  
The Earth ◽  
Space Launch ◽  
Energetic Compositions ◽  
Heating Up ◽  
Space Activities ◽  
Total Velocity

Technogeneous impact of rocket and space activities on the environment is one of the most actual problems of practical cosmonautics. This technogeneous impact is not only the pollution of near Earth space with space debris (worked-off stages of space launch vehicle (SLV)), but also the pollution of significant areas on the Earth surface with worked-off lower stages of SLV, which fall down after having accomplished their mission. In OmSTU and IPCP RAS it was suggested to apply different self-burning compositions, generating hot gases for the evaporation of the unused residues of liquid propellant in tanks of SLV. Then the mixture of the evaporated compounds together with the gaseous combustion products from gas-generating compositions is used as propellant mixture for the autonomous gas rocket engine. Such a solution would decrease considerably the level of the environment pollution and additionally it increases the energetic characteristics of SLV. For example, in the case of the second stage of SLV «Soyuz-2.1.v» it increases the total velocity by 5%. Also it is proposed to use firing the pyrotechnic compositions like (thermites) for the fairings heating up to the temperature when the fairing material can be ignited in air. It would reduce considerably the amount and the mass of the separating parts of SLV that fall to the Earth.

Sign in / Sign up

Export Citation Format

Share Document