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This paper discusses the current state of technology in reduced gravity fire suppression. The focus is on the unique issues associated with the CEV and future spacecraft including operation in reduced gravity and enriched oxygen ambients. Inert gas agents such as carbon dioxide, nitrogen and helium have different minimum extinguishing concentrations (MEC) in microgravity compared to normal gravity; in most instances the MEC in microgravity being higher than in normal gravity. This means that designs based on terrestrial standards will not offer the same factor of safety in microgravity. The results also show that the MEC is a strong function of ambient oxygen concentration in reduced gravity (as expected).

This paper presents a new portable metabolic device (PUMA-Portable Unit for Metabolic Analysis) developed at the NASA Glenn Research Center. PUMA is a battery-operated, wearable unit to measure metabolic rate (minute ventilation, oxygen up-take, carbon dioxide output and heart rate) in a clinical setting, in the field or in remote, extreme environments. The critical sensors in PUMA are located close to the mouth and sampled at 10 Hz to allow intra-breath measurements. PUMA transmits metabolic data wirelessly to a remote computer for data analysis and storage. In addition to it's primary function as a portable metabolic measurement device, the PUMA sensors can also be easily adapted to other applications, including future EVA suits where they could measure metabolic rate for a suited crew member. The first section of the paper discusses the specific technologies and innovations of PUMA.

Material flammability is an important factor in determining the pressure and composition (fraction of oxygen and nitrogen) of the atmosphere in the habitable volume of exploration vehicles and habitats. The method chosen in this work to quantify material flammability is by its ease of ignition and the minimum (critical) radiant heat flux for ignition. Piloted ignition delay tests were conducted in the Forced Ignition and Spread Test (FIST) apparatus subject to various atmospheric pressures and oxygen concentrations. The ignition delay time was measured as the time it takes a combustible material to ignite after it has been exposed to an external heat flux. In these tests, polymethylmethacylate (PMMA) was exposed to an oxidizer flow velocity of 1 m/s and a range of externally applied heat flux levels from 8 to 14 kW/m2.

A Lattice-Boltzmann approach is used to simulate the aerodynamics of complex three-dimensional ice shapes on a NACA 23012 airfoil. The digitally produced high fidelity geometrical ice shapes were created using a novel laser scanning technique in the NASA Icing Research Tunnel. The geometrically fully resolved unsteady simulations are conducted on two ice shapes representing a roughness type and a horn type icing on the leading edge of the airfoil. Comparisons between simulation and experiment of lift, drag, and pitching moment as well as pressure distributions indicate overall a good qualitative agreement in capturing the aerodynamic degradation. Especially for the horn-type ice shape, the quantitative agreement is also mostly very good. Analysis of the flow structures indicates furthermore a good capturing of the three-dimensional separation behavior of the flow.

This paper discusses the unique aspects of fire suppression in reduced (micro- and Lunar/martian) gravity environments. It builds on a trade study conducted by the Fire Prevention Detection and Suppression group at the NASA Glenn Research Center that examined the efficacy of fire suppressants in reduced gravity. The first part of the present paper reviews the differences in flame characteristics between terrestrial and extraterrestrial fires and how these characteristics change the action of a fire suppressant. Special emphasis is placed on enriched oxygen ambient environments, a condition that will routinely exist on future spacecraft and extraterrestrial habitats. The most important difference between normal gravity and reduced gravity fires is the increase in the minimum suppressant concentration (for gaseous agents in a total flooding application) required to extinguish a fire in reduced gravity compared to normal gravity.

This paper presents a fire suppression analysis for the Altair project. The architecture of the Altair systems relevant to fire safety is briefly reviewed. This is followed by an outline of a fire safety analysis of the spacecraft including an outline of a probabilistic risk analysis (PRA). The particular emphasis of this analysis is the change in risk as the vehicle moves to lower pressure, higher operating voltage and increased oxygen mole fraction. The analysis shows that all of these changes increase the likelihood and intensity of a fire. The paper then outlines the options for a suppression system followed by a trade analysis of the different options. The candidate systems include inert gas agents (nitrogen, carbon dioxide and helium), water-based systems (spray, mist and foam) and chemically active agents. Chemically active agents are included for reference purposes since they are not likely candidates for the Altair vehicles.