Keyword: Liquid propellants

Briefs: Propulsion
Non-Catalytic Ignition System for High-Performance Advanced Monopropellant Thrusters

Anon-catalytic pyrotechnic ignition system was developed for advanced green monopropellant systems operating with hydroxylammonium nitrate (HAN)-based monopropellant AF-M315E. This technology will provide increased performance and new operating regimes for...

Articles: Automotive
Standards for Comfortable Seats

In the beginning, safety trumped comfort in spacecraft designs for human space travel. Early space capsules were small and had a seat-driven design in which most of the...

Briefs: Mechanical & Fluid Systems
Six-Degree-of-Freedom Control With Only Eight Thrusters

Typical spacecraft thruster configurations are often unable to provide full six-degree-of-freedom control and may have unwanted interaction between their attitude control and trajectory control functions, have undesirably high instantaneous electrical power demands, and use more thrusters...

Briefs: Manufacturing & Prototyping
Aluminum Rocket Engine Injector Fabricated Using 3D Additive Manufacturing

Liquid rocket engine injectors can be extremely expensive to manufacture and hard to iterate to achieve high performance. Internal sealing points can also be the source of reliability issues. The technology disclosed here covers the application of a 3D additive...

Briefs: Electronics & Computers
Wireless Integrated Microelectronic Vacuum Sensor System

NASA Stennis Space Center’s (SSC’s) large rocket engine test facility requires the use of liquid propellants, including the use of cryogenic fluids like liquid hydrogen as fuel, and liquid oxygen as an oxidizer (gases which have been liquefied at very low temperatures). These fluids...

Briefs: Manufacturing & Prototyping
High-Pressure Lightweight Thrusters

Returning samples of Martian soil and rock to Earth is of great interest to scientists. There were numerous studies to evaluate Mars Sample Return (MSR) mission architectures, technology needs, development plans, and requirements. The largest propulsion risk element of the MSR mission is the Mars Ascent...

Briefs: Physical Sciences

Heat flow is a fundamental property of a planet, and provides significant constraints on the abundance of radiogenic isotopes, the thermal evolution and differentiation history, and the mechanical...

Briefs: Physical Sciences
Oxygen-Methane Thruster

An oxygen-methane thruster was conceived with integrated igniter/injector capable of nominal operation on either gaseous or liquid propellants. The thruster was designed to develop 100 lbf (≈445 N) thrust at vacuum conditions and use oxygen and methane as propellants. This continued development included refining the...

Briefs: Manufacturing & Prototyping
Technique for Configuring an Actively Cooled Thermal Shield in a Flight System

Broad area cooling shields are a massefficient alternative to conductively cooled thermal radiation shielding. The shield would actively intercept a large portion of incident thermal radiation and transport the heat away using cryogenic helium gas. The design concept...

Briefs: Physical Sciences
Catalytic Microtube Rocket Igniter

Devices that generate both high energy and high temperature are required to ignite reliably the propellant mixtures in combustion chambers like those present in rockets and other combustion systems. This catalytic microtube rocket igniter generates these conditions with a small, catalysis-based torch. While...

Briefs: Mechanical & Fluid Systems
Plasma Igniter for Reliable Ignition of Combustion in Rocket Engines

A plasma igniter has been developed for initiating combustion in liquid-propellant rocket engines. The device propels a hot, dense plasma jet, consisting of elemental fluorine and fluorine compounds, into the combustion chamber to ignite the cold propellant mixture. The igniter...

Briefs: Mechanical & Fluid Systems

A class of self-adjusting injectors for spraying liquid oxidizers and/or fuels into combustion chambers has been proposed. The proposed injectors were originally intended for use in...

Briefs: Robotics, Automation & Control

Precision X-Y stages were developed for integration into a new analytical measurement tool for use in the development of digital inks or other fluids to be jetted from ink jet...

Briefs: Robotics, Automation & Control

An improved system for densifying (by cooling) the liquid hydrogen and liquid oxygen used as propellants for the space shuttle has been proposed. These propellant liquids are...

Briefs: Robotics, Automation & Control
Mars Ascent Propulsion System

A report presents an overview of continuing efforts to develop an advanced propulsion system for a spacecraft that would ascend from Mars to bring samples to Earth. The system is required to be smaller and to weigh and cost less, in comparison with a conventionally designed system of equal capability. The...

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