Converting in-situ resources such as CO2, which is the main component of the Mars atmosphere, into methane for rocket propellants can significantly reduce the cost and risk of human exploration while at the same time enabling new mission concepts and long-term exploration sustainability. Methanation of CO2, also called a Sabatier reaction, is hence a key enabling technology required for sustainable and affordable human exploration of Mars.

Improved Hall Thrusters Fed by Solid Phase Propellant

TBMG-22415

07/01/2015

Hall thrusters normally use Xe propellant, which is expensive and scarce in the solar system. The weight of Xe is such that typical Hall thrusters are limited in specific impulse to approximately 3,000 s. The objective of this program was to improve and demonstrate Mg Hall thruster systems. Mg is abundant in the solar system and has an atomic mass approximately one-fifth that of Xe, which means much higher specific impulse is achieved than with Xe at typical thruster operating conditions (power, voltage).

Pulsed Plasma Lubricator (PPL) Technology for the In Situ Replenishment of Dry Lubricants in Extreme Environments

TBMG-19374

04/01/2014

NASA missions employing mobility systems and other moving mechanical assemblies for application on Mars, the Moon, and in deep space depend on the reliable operation of these assemblies and their tribological components. Wet lubricants are sometimes used in space applications, but in order to avoid solidification, they often require active heating due to the extreme cold temperatures that are encountered. Dry lubricants, such as molybdenum disulfide (MoS2), are more commonly chosen for space mechanisms because they are not subject to the low-temperature limitations of wet lubricants while also providing superior lubricating properties. A major drawback of dry lubricants is low wear resistance that eventually leads to failure of the assembly as the lubricant is removed.

2013 Create the Future Design: Aerospace & Defense Category Winner

TBMG-1773711/01/2013

Graphite Coating, Thin Lubricating Film Impingement Applied

AMS2525D (Historical)07/10/2013

This specification covers a coating consisting of finely-powdered graphite in a heat-resistant inorganic binder.

AMS B Finishes Processes and Fluids Committee

Rob Mueller, Lead Senior Technologist, Kennedy Space Center, FL

TBMG-1645505/01/2013

Rob Mueller is the Lead Senior Technologist for the RASSOR (Regolith Advanced Surface Systems Operations Robot) project, as well as all Kennedy Space Center (KSC) Human Robotics Systems. The RASSOR mining robot will collect soil (known as regolith) on the moon or Mars so it can be processed into rocket propellants, breathable air, water, and other consumable commodities as well as manufacturing and construction materials feed stocks.

Molybdenum Disulfide Coating, Thin Lubricating Film Impingement Applied

AMS2526D (Current)01/12/2013

This specification covers requirements for a coating consisting of finely-powdered molybdenum disulfide in a heat-resistant inorganic binder applied to parts.

AMS B Finishes Processes and Fluids Committee

Standard Electrical and Logical Interface for Airborne Fuzing Systems

AS5716A (Current)12/03/2012

This interface standard applies to fuzes/fuzing systems (referred to as fuzing system hereafter) in airborne weapons that use a MIL-STD-1760 type interface. It defines the powers, the discrete signals and the serial data interface for the communications at the interface between the fuzing system and the remainder of the weapon, including the weapon control unit. The Class 1 interface is an electrical only interface that facilitates use of MIL-STD-1760 type platform store interfaces for the fuze to monitor intentional release and defines the fuze interface bus communications protocol to allow sending and receiving data from fuzing systems. Class 2 interfaces add a defined connector and additional interfaces to facilitate the exchange of compatible fuzing systems. Class 3 interfaces add further interface definitions to facilitate the exchange of AS5680A compatible fuzing systems components. The bus communications protocol provides a means by which the weapon may set mission parameters

AS-1B Aircraft Store Integration Committee

Fuel-Cell Power Source Based on Onboard Rocket Propellants

TBMG-817107/01/2010

The use of onboard rocket propellants (dense liquids at room temperature) in place of conventional cryogenic fuel-cell reactants (hydrogen and oxygen) eliminates the mass penalties associated with cryocooling and boil-off. The high energy content and density of the rocket propellants will also require no additional chemical processing.

Fuel-Cell Power Source Based on Onboard Rocket Propellants

TBMG-TB-00817107/01/2010

This high-energy density power source is an alternative to radioisotopes or primary batteries. The use of onboard rocket propellants (dense liquids at room temperature) in place of conventional cryogenic fuel-cell reactants (hydrogen and oxygen) eliminates the mass penalties associated with cryocooling and boil-off. The high energy content and density of the rocket propellants will also require no additional chemical processing.

Standard Electrical and Logical Interface for Airborne Fuzing Systems

AS5716-TEST-REC (Historical)02/11/2010

This interface standard applies to fuzes/fuzing systems (referred to as fuzing system hereafter) in airborne weapons that use a MIL-STD-1760 interface. It defines the powers, the discrete signals and the serial data interface for the communications at the interface between the fuzing system and the remainder of the weapon, including the weapon control unit, for Class 1 interfaces. Future issues of the standard will provide for additional fuzing system related functionality defined as Class 2 and Class 3 interfaces. For future issues of this standard, the connector definition is contained in AS5680. This standard does not impose any safety requirements and does not supersede or replace any existing applicable safety standards.

AS-1B Aircraft Store Integration Committee

Standard Electrical and Logical Interface for Airborne Fuzing Systems

AS5716 (Historical)

02/11/2010

AS-1B Aircraft Store Integration Committee

Tungsten Disulfide Coating, Thin Lubricating Film, Binder-Less Impingement Applied

AMS2530 (Historical)01/05/2010

This specification covers a coating consisting of tungsten disulfide without binders and not requiring a curing process.

AMS B Finishes Processes and Fluids Committee

Prototype Rocket Engine for a Nanosat Launch Vehicle

TBMG-493912/01/2008

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 are introduced and mixed in the combustion chamber utilizing a combination of triplet and unlike doublet injector elements. In addition, film cooling is provided in order to extend the life of the ablative chamber. Ignition is accomplished with solid propellant ports mounted on the side of the chamber.

Perspective on Research in Laser Propulsion

TBMG-491910/01/2008

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 proof-of-concept experiments and associated studies under the auspices of the Air Force Research Laboratory during the years 1996 through 2007. The document briefly discusses the basic physical principles and engineering concepts of laser propulsion as demonstrated in the proof-of-concept experiments, in which a model rocket denoted a laser lightcraft was lofted to altitudes exceeding 200 ft. (about 61 m). In these experiments, a CO2-laser beam of pulse energy of 400 J at a repetition rate of 25 Hz was used to vaporize a solid propellant (Delrin® polyoxymethylene) to generate thrust. There is a brief discussion of energy-conversion efficiency in laser propulsion. This is followed by an analysis of the

Graphite Coating, Thin Lubricating Film Impingement Applied

AMS2525C (Historical)11/21/2007

This specification covers a coating consisting of finely-powdered graphite in a heat-resistant inorganic binder.

AMS B Finishes Processes and Fluids Committee

Molybdenum Disulfide Coating, Thin Lubricating Film Impingement Applied

AMS2526C (Historical)10/05/2007

This specification covers a coating consisting of finely-powdered molybdenum disulfide in a heat-resistant inorganic binder applied to parts.

AMS B Finishes Processes and Fluids Committee

Simulating Flights of Future Launch Vehicles and Spacecraft

TBMG-118202/01/2007

Marshall Aerospace Vehicle Representation in C (MAVERIC) is a computer program for generic, low-to-high-fidelity simulation of the flight(s) of one or more launch vehicle(s) or spacecraft. MAVERIC is designed to accommodate multi-staged vehicles, powered serially or in parallel, with multiple engines, tanks, and cargo elements. Engines can be of jet or conventional rocket types, using either liquid or solid propellants.

Embedded Sensors for Measuring Surface Regression

TBMG-7707/01/2006

The development and evaluation of new hybrid and solid rocket motors requires accurate characterization of the propellant surface regression as a function of key operational parameters. These characteristics establish the propellant flow rate and are prime design drivers affecting the propulsion system geometry, size, and overall performance. There is a similar need for the development of advanced ablative materials, and the use of conventional ablatives exposed to new operational environments. The Miniature Surface Regression Sensor (MSRS) was developed to serve these applications. It is designed to be cast or embedded in the material of interest and regresses along with it. During this process, the resistance of the sensor is related to its instantaneous length, allowing the real-time thickness of the host material to be established. The time derivative of this data reveals the instantaneous surface regression rate.

Dual-Laser-Pulse Ignition

TBMG-1198701/01/2006

A dual-pulse laser (DPL) technique has been demonstrated for generating laser-induced sparks (LIS) to ignite fuels. The technique was originally intended to be applied to the ignition of rocket propellants, but may also be applicable to ignition in terrestrial settings in which electric igniters may not be suitable. Laser igniters have been sought as alternatives to such conventional devices as electrical spark plugs and torch igniters for the following main reasons:

Dual-Laser-Pulse Ignition

TBMG-645701/01/2006

Self Contained Atmospheric Protective Ensemble (SCAPE) Suits Redesign and Implementation at Kennedy Space Center

2005-01-295907/11/2005

The Self Contained Atmospheric Protective Ensemble (SCAPE) suits, worn at the Kennedy Space Center (KSC) have been updated from the original 1970's design. The suits were renamed Propellant Handlers Ensemble (PHE) but are still commonly referred to as SCAPE. Several modifications to the suit were done over the last 20 years to improve the design for operational use. However, anthropometric changes in the user population over time have not been addressed. The following study addressed anthropometric concerns in the current SCAPE population. It was found that all suits had at least one area in which the recommended upper limit was exceeded by technicians. The most common areas to exceed the upper limit were: waist circumference, chest circumference and upper thigh circumference. Forearm circumference posed the least concern unless using long gauntlet glove which cause the twist lock ring to be located at the forearm rather than the wrist.

Mock, Jessica, Miller, Darcy

Membranes on Mars for In-Situ Resource Utilization Processes

2004-01-231607/19/2004

The goal of this project is the development and characterization of synthetic membranes for the separation and purification of CO2 from the Martian atmosphere for in-situ resource utilization (ISRU) applications such as in-situ propellant production. Candidate materials should have high selectivity for carbon dioxide over nitrogen and argon, and a glass transition temperature of -40 °C or less to remain in rubbery state at low temperature for high permeance (flux/driving force). Membrane materials we identified include the rubbery polymers poly(dimethyl siloxane) (PDMS) and the copolymer poly(dimethyl, methylphenyl siloxane) (PMPS). Pure and mixed gas permeation experiments with CO2, N2 and Ar were performed with these membrane materials in the temperature range -25 to 21 °C. In experiments with the commercially available PDMS membranes, the pure gas CO2 permeability increases from 1932 Barrers to 2755 Barrers as the temperature decreases from 22 to -30 °C. The ideal CO2/N2 separation

Jha, Praveen, Way, J. Douglas, Srinivasan, Ananth, Mason, Larry W.

Novel Acoustical Polyolefin Foams

2001-01-155604/30/2001

Novel acoustical materials have been developed. The materials are thermoplastic foams extruded from blends of a polypropylene (PP) resin with an ethylenic polymer resin. One material is an open-cell sheet product made from a blend of a PP resin and a polyolefin elastomer (POE). Another is a large-celled plank foam of substantially closed-cell structure made from a blend of a polypropylene resin and a low density polyethylene (PE) resin. The foam materials are of lightweight, hydrophobic, dust free, recyclable and withstand the temperatures prevailing in automotive uses.

Park, Chung P., Burgun, Sandrine, Brucker, Michel, Subramonian, Suresh

Graphite Coating, Thin Lubricating Film Impingement Applied

AMS2525B (Historical)07/01/2000

This specification covers a coating consisting of finely-powdered graphite in a heat-resistant inorganic binder.

AMS B Finishes Processes and Fluids Committee

Molybdenum Disulfide Coating, Thin Lubricating Film Impingement Applied

AMS2526B (Historical)07/01/2000

This specification covers a coating consisting of finely-powdered molybdenum disulfide in a heat-resistant inorganic binder.

AMS B Finishes Processes and Fluids Committee

Engine; Rocket, Solid Propellant 5 Second Duration, 4500 Pounds Thrust

AS8581 (Current)03/01/2000

This specification established the requirements for a 5 second duration, 4500 pound thrust (when determined at 60°F) solid propellant rocket engine hereinafter specified as 5 S-4500.

Aerospace Council

GFSSP — Program for Analyzing Flows in a Complex Network

TBMG-672401/01/2000

The Generalized Fluid System Simulation Program (GFSSP) version 2.01 is a general-purpose computer program for analyzing steady-state and time-dependent flowrates, pressures, temperatures, and concentrations in a complex flow network. The program is capable of modeling phase changes, compressibility, mixture thermodynamics, and external body forces, such as gravity and centrifugal.

Hybrisol Rocket Engines

TBMG-211209/01/1999

"Hybrisol" denotes a proposed rocket engine that would contain hybrid and solid-propellant parts within a single combustion chamber. ["Hybrid" as used here denotes a type of rocket engine in which a solid fuel is burned by use of a liquid or gaseous oxidizer and the flow of the oxidizer can be throttled to control the engine. Unlike conventional solid rocket propellants, a solid fuel for a hybrid rocket engine can be made relatively inert in the absence of the oxidizer and therefore presents little hazard of explosion or inadvertent ignition.] Inside a hybrisol rocket engine, there would be two concentric tubular energy-storage layers: an outer layer of conventional solid rocket propellant and an inner layer of solid hybrid fuel (see figure).

H-ISP - A Hybrid Inflator Simulation Program

1999-01-106903/01/1999

A hybrid-inflator simulation program, H-ISP, has been developed to facilitate the evaluation of hybrid inflators for airbag systems. Based on fundamental principles of species mass and energy conservation and gas dynamics, this program can simulate the complex thermo-chemical processes of a hybrid inflator, including solid propellant combustion, single-phase or two-phase flow, multiple chemical species with temperature- and composition-dependent thermal properties, and heat transfer phenomena. In this paper, we present the theory, computer program structure and usage of H-ISP with an example.

Kang, Jian, Wang, J. T.

Safety Criteria for Pneumatic Starting Systems

AIR1639A (Current)

03/01/1999

This SAE Aerospace Information Report (AIR) presents safety criteria for pneumatic type engine starting system design and component hardware. Included are safety criteria in design of both starter control valves and starters as well as in design of airframe control systems. Safety topics concern starter valve operation and material application, airframe controls and instrumentation installations and starter rotor integrity and containment.

AE-6 Starting Systems and Auxiliary Power Committee