Open Access. Powered by Scholars. Published by Universities.®

Aerospace Engineering Commons™

Open Access. Powered by Scholars. Published by Universities.®

2016

Rocket

Articles 1 - 3 of 3

Full-Text Articles in Aerospace Engineering

Senior Design - Hybrid Rocket Conceptual Design, Hardeo Chin Nov 2016

Senior Design - Hybrid Rocket Conceptual Design, Hardeo Chin

Hardeo Chin

Hybrid rockets utilize rocket motors which contain both liquid and solid propellant. They provide numerous benefits compared to solid and liquid rockets such as being mechanically simpler, having denser fuels, and providing higher specific impulse. Generally, the oxidizer is liquid and fuel is solid because solid oxidizers are dangerous and are lower performing than their liquid counterparts. Hybrid systems avoid the significant hazards of manufacturing, shipping, and handling that solid rocket motors possess. The conceptual design report herein separately assesses the structural and propulsive needs for a mid-power rocket with a G-motor

Go to article

Throttleable Gox/Abs Launch Assist Hybrid Rocket Motor For Small Scale Air Launch Platform, Zachary S. Spurrier May 2016

Throttleable Gox/Abs Launch Assist Hybrid Rocket Motor For Small Scale Air Launch Platform, Zachary S. Spurrier

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

The ability for an aircraft-based launch platform to place an orbital payload onto a nominal launch trajectory at a higher energy state -- altitude, velocity, flight path angle, and azimuth --using highly-efficient air breathing propulsion instead of a much lower-efficiency rocket system, offers the potential for a significantly smaller launch vehicle. An airborne platform also provides the ability to launch from multiple locations and allows for significantly increased "system responsiveness." The NASA Armstrong Flight Research Center’s Towed Glider Air-Launch System (TGALS) is a small-scale flight research project investigating the feasibility for a remotely-piloted, towed, glider system to act as a …

Go to article

Design Of A 500 Lbf Liquid Oxygen And Liquid Methane Rocket Engine For Suborbital Flight, Jesus Eduardo Trillo Jan 2016

Design Of A 500 Lbf Liquid Oxygen And Liquid Methane Rocket Engine For Suborbital Flight, Jesus Eduardo Trillo

Open Access Theses & Dissertations

Liquid methane (LCH4)is the most promising rocket fuel for our journey to Mars and other space entities. Compared to liquid hydrogen, the most common cryogenic fuel used today, methane is denser and can be stored at a more manageable temperature; leading to more affordable tanks and a lighter system. The most important advantage is it can be produced from local sources using in-situ resource utilization (ISRU) technology. This will allow the production of the fuel needed to come back to earth on the surface of Mars, or the space entity being explored,making the overall mission more cost effective by enabling …

Go to article