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Keyword: Propellants

News: Test & Measurement

Industry Invited to Participate in AeroTech Aerospace and Defense Technical Program

SAE International is inviting global participation in its AeroTech® aerospace and defense technology conference and exhibition, which is for the first...

Briefs: Electronics & Computers

Pulsed Microwave Plasma Instrumentation for Investigation of Plasma-Tuned Multiphase Combustion

Strategies to control solid rocket propellant regression rate require a robust throttling technique applicable to high performance propellant...

Briefs: Mechanical & Fluid Systems

Measuring Propellant Stress Relaxation Modulus Using Dynamic Mechanical Analyzer

Structural analysis of solid rocket motors is challenging for several reasons, but the most important of these is the complex behavior of the propellant. The...

Briefs: Propulsion

Combustion Characteristics of Hydrocarbon Droplets Induced by Photoignition of Aluminum Nanoparticles

In the study of combustion characteristics of liquid rocket fuels, it is customary to either study the combustion of liquid fuel droplets...

Articles: Aerospace

Electric Rockets and the Future of Satellite Propulsion

Humans have been using rocket propulsion for almost a millennium, starting with Chinese rockets and “fire arrows” in the 13th century and continuing to the modern era's powerful...

Technology Update: Defense

Production of Satellite with First All-Electric Propulsion System Advances

Boeing is “running on schedule” as it continues to achieve production milestones for the first of its all-electric-propulsion 702SP (small platform)...

Briefs: Mechanical & Fluid Systems

Variable-Thrust, Multiple-Start Hybrid Motor Solutions

Interceptor boost propulsion has traditionally been dominated by solid rocket systems due to their responsiveness and high mass fraction capabilities. However, increased costs of...

Briefs: Mechanical & Fluid Systems

Prototype Rocket Engine for a Nanosat Launch Vehicle

A paper discusses a prototype rocket engine for a suborbital Reusable Nanosat Launch Vehicle (RNLV). The engine must operate with thrust levels from 3,000 to 5,000 lbf. The engine is comprised of three major subassemblies: the injector, igniter, and the combustion chamber nozzle. Propellants...

Briefs: Physical Sciences

Advanced Concepts for Space Access

A paper summarizes commonly proposed advanced launch concepts, including both concepts that employ propellant and propellant-less concepts. A wide range of advanced launch concepts have been proposed in an effort to revolutionize space access through either a significant reduction in launch costs or significant...

Briefs: Physical Sciences

Perspective on Research in Laser Propulsion

A document summarizes the history of research on laser propulsion, starting with the first publication of the laser-propulsion concept in the year 1969, proceeding through studies of laser propulsion within the broader context of advanced propulsion systems in general, and culminating in...

Briefs: Mechanical & Fluid Systems

Thermal Design and Analysis of a Rocket-Engine TAN Injector

A subscale thrust-augmented-nozzle (TAN) rocket engine was designed, built, and hot-fire tested to demonstrate the validity of the TAN concept. As described in more detail in the...