Development of a Small Launch Vehicle with Hybrid Rocket Propulsion

2018 ◽  
Author(s):  
Yen-Sen Chen ◽  
Bill Wu
Keyword(s):  
Launch Vehicle ◽  
Hybrid Rocket ◽  
Rocket Propulsion

Conceptual stage separation from widebody subsonic carrier aircraft for space access

2014 ◽  
Vol 118 (1209) ◽  
pp. 1279-1309 ◽  
Author(s):  
U. Mehta ◽  
J. Bowles ◽  
S. Pandya ◽  
J. Melton ◽  
L. Huynh ◽  
...  
Keyword(s):  
Trajectory Analysis ◽  
Launch Vehicle ◽  
Preliminary Design ◽  
Interference Effects ◽  
Technical Issue ◽  
Rocket Propulsion ◽  
Stage Separation ◽  
Computational Fluid Dynamics Simulations ◽  
Launch Systems ◽  
Dynamics Simulations

Abstract Stage separation is a critical technical issue for developing two-stage-to-orbit (TSTO) launch systems with widebody carrier aircraft that use air-breathing propulsion and launch vehicle stages that use rocket propulsion. During conceptual design phases, this issue can be addressed with a combination of engineering methods, computational fluid dynamics simulations, and trajectory analysis of the mated system and the launch vehicle after staging. The outcome of such analyses helps to establish the credibility of the proposed TSTO system and formulate a ground-based test programme for the preliminary design phase. This approach is demonstrated with an assessment of stage separation from the shuttle carrier aircraft. Flight conditions are determined for safe mated flight, safe stage separation, and for the launch vehicle as it commences ascending flight. Accurate assessment of aerodynamic forces and moments is critical during staging to account for interference effects from the proximities of the two large vehicles. Interference aerodynamics have a modest impact on the separation conditions and separated flight trajectories, but have a significant impact on the interaction forces.

Theoretical analysis of hydrides in solid and hybrid rocket propulsion

2012 ◽  
Vol 37 (2) ◽  
pp. 1760-1769 ◽  
Author(s):  
Filippo Maggi ◽  
Gabriela Gariani ◽  
Luciano Galfetti ◽  
Luigi T. DeLuca
Keyword(s):  
Theoretical Analysis ◽  
Hybrid Rocket ◽  
Rocket Propulsion

scholarly journals Structurisation and visualisation of design space for launch vehicle with hybrid rocket engine

2016 ◽  
Vol 2 (1/2) ◽  
pp. 26
Author(s):  
Kazuhisa Chiba ◽  
Masahiro Kanazaki ◽  
N.A. Shin' ◽  
ya Watanabe ◽  
Koki Kitagawa ◽  
...  
Keyword(s):  
Design Space ◽  
Rocket Engine ◽  
Launch Vehicle ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

scholarly journals Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

Aerospace ◽  
2021 ◽  
Vol 8 (9) ◽  
pp. 234
Author(s):  
Adam Okninski ◽  
Pawel Surmacz ◽  
Bartosz Bartkowiak ◽  
Tobiasz Mayer ◽  
Kamil Sobczak ◽  
...  
Keyword(s):  
Hydrogen Peroxide ◽  
Research Network ◽  
Main Stage ◽  
Launch Vehicles ◽  
Hybrid Rocket ◽  
Space Propulsion ◽  
Sounding Rockets ◽  
Hybrid Propulsion ◽  
Rocket Propulsion ◽  
Rocket Technology

This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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