Spacecraft Fire Experiment-I (Saffire-I) - 11.30.16

Overview | Description | Applications | Operations | Results | Publications | Imagery

ISS Science for Everyone

Science Objectives for Everyone
Fire is extremely dangerous on a spacecraft, so most controlled flame growth experiments have been limited to small sizes. The Spacecraft Fire Experiment-I (Saffire-I) intentionally lights a large-scale fire inside an empty Cygnus resupply vehicle after it leaves the International Space Station (ISS) and before it re-enters Earth’s atmosphere. Instruments measure flame growth, oxygen use and more, improving understanding of fire growth in microgravity and safeguarding future space missions.
Science Results for Everyone
Information Pending

The following content was provided by David L. Urban, Ph.D., and is maintained in a database by the ISS Program Science Office.
Experiment Details

OpNom: Saffire

Principal Investigator(s)
David L. Urban, Ph.D., Glenn Research Center, Cleveland, OH, United States

Co-Investigator(s)/Collaborator(s)
Gary A. Ruff, Glenn Research Center, Cleveland, OH, United States

Developer(s)
NASA Glenn Research Center, Cleveland, OH, United States

Sponsoring Space Agency
National Aeronautics and Space Administration (NASA)

Sponsoring Organization
Technology Demonstration Office (TDO)

Research Benefits
Space Exploration

ISS Expedition Duration
March 2016 - September 2016

Expeditions Assigned
47/48

Previous Missions
This experiment has not flown previously but benefits from the material flammability testing conducted in the MSG facility by the BASS (Burning and Suppression of Solids) Experiment.

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Experiment Description

Research Overview

  • Despite years of experience in manned spaceflight, NASA has a limited degree of verification of the current approach for spacecraft fire protection.
  • This is a direct result of the inability to study fires of practical size in low-gravity.
  • Ensuring reliability of the fire safety of future spacecraft requires experiments that provide a realistic examination of the risk.
  • These experiments cannot be conducted in an inhabited spacecraft.
  • Data obtained from the experiment are used to validate modeling of spacecraft fire response scenarios.
  • The data represent the first dataset that can be used to validate spacecraft fire growth and spread models.
  • The tests evaluate NASA’s normal-gravity material flammability screening test for low-gravity conditions. These tests have a long history but their representation of the low-gravity fire risk has not been validated.
  • This testing provides the first practical scale low-gravity fire testing.
  • Spacecraft Fire Experiment-I (Saffire-I) increases the reliability of the fire safety on all future spacecraft.

Description

Despite decades of research into combustion and fire processes in reduced gravity, there have been very few experiments directly studying spacecraft fire safety under low-gravity conditions. Furthermore, none of these experiments have studied sample and environment sizes typical of those expected in a spacecraft fire. Prior experiments have been limited to samples no larger than 10 cm in length and width. This stands in stark contrast to the full-scale fire safety testing that has been conducted in habitable structures on earth including mines, buildings, airplanes, ships, etc. The large differences between fire behavior in normal and reduced gravity results in a lack of experimental data that forces spacecraft designers to base their designs on terrestrial fires and fire standards. While this approach has been successful thus far, there is inherent risk due to the level of uncertainty. Despite their obvious importance, full scale spacecraft fire experiments have not been possible because of the inherent hazards involved in conducting a large fire test in a manned spacecraft. To address this knowledge gap, experiments in an expendable spacecraft are proposed and conducted without risk to crew or crewed spacecraft.
 
The NASA Advanced Exploration Systems program funded a project to develop and demonstrate spacecraft fire safety technologies in relevant environments. The keystone of these demonstrations is a large-scale fire safety experiment conducted on an International Space Station (ISS) re-supply vehicle after it has undocked from the ISS and before it enters the atmosphere. The project team from NASA John H. Glenn Research Center (GRC) is augmented by an international topical team assembled by the European Space Agency (ESA). Each member of this team brings expertise and funding from their respective space and research agencies for their activities. This participation of members from other countries and space agencies not only brings additional skills to the science team but also facilitates international cooperation in the development of an approach to spacecraft fire prevention and response for future exploration vehicles. No single experiment can address the range of issues that need to be resolved to fully understand the spacecraft fire risk and to ensure the safety of future flights. The goal of the topical team is to leverage the international capabilities of the team to develop a suite of ground-based and space flight spacecraft fire safety experiments to expand the impact of the flight experiments. The current experiment has been designed to address two objectives. The first objective is to understand the flame spread and growth of a fire over an amount of flammable material consistent with what is likely to be in a spacecraft cabin through the development of an experiment for a sample material approximately 1 meter long. This is at least an order of magnitude larger than any prior low-g flame spread experiment. The second objective is to examine the flammability limits of materials in low gravity to determine if NASA’s material selection methods are a reasonable predictor of low-gravity flammability.
 
The unique objectives of Spacecraft Fire Experiment-I (Saffire-I) necessitated the use of an ISS expendable resupply vehicle such as ESA’s ATV, JAXA’s HTV, or Orbital Sciences Corporation’s (Orbital’s) Cygnus vehicles. Early in the development of the project, the European Space Agency (ESA) became interested in this experiment. As a result, the ATV was the initial vehicle for which an experiment concept was developed. While many factors could go into the selection of a vehicle such as available volume, power availability, communication, etc., the schedule and resources eventually become the most significant. With the planned ATV flights ending with ATV-5, it became unlikely that an experiment could be developed and integrated with the vehicle within that schedule. Since Orbital’s eight Cygnus flights were planned to begin in 2013 and extend through 2016, Cygnus was a more promising vehicle for the successful completion of this experiment. Programmatic requirements drives the project to plan for three experiments to be performed on three consecutive flights of Cygnus. The first experiment would take place on the 5th Cygnus flight.
 
The concept for this experiment focuses on conducting two types of material combustion tests that are performed on different flights using the flow duct design. The experiment package consists of a flow duct and an adjacent avionics bay. The avionics bay is connected to the side of the flow duct. The top and bottom structures on the experiment module are the fan unit on the top and the flow straightener unit on the bottom. The airflow is from the bottom to the top of the experiment module. The flow duct/avionics bay assembly is a rigid structure and will be secured with the standard stowage straps. This duct enables a more uniform flow across the samples, maintain a clear flow path within the experiment module, and prevent burning debris from interacting with the rest of the cargo.
 
The experiment package has a range of diagnostics to monitor the test conditions. The ambient temperature and the oxygen and CO2 concentrations are measured at the intake of the flow duct with temperature measurements also made just upstream of the fans. A pressure transducer also delivers the pressure time-history. Flow anemometers are placed at selected locations in the inlet flow and thereby quantify the oxidizer flux in the duct. Two video cameras provide top views of the entire sample. The sample is periodically illuminated by a LED source to allow the measurement of the pyrolysis length.
 
For the flame spread sample, the flame stand-off distance is measured using several thermocouples placed at varying heights above the sample surface. These are woven into the sample and then bent so they are perpendicular to the surface. Finally, a calibrated radiometer measures the broadband radiative emission from the sample to provide an estimate of the radiative flux from the burning zone towards the surroundings.
 
The first and third tests (Saffire-I and III) investigate flame spread and growth in low-gravity to determine if there is a limiting flame size and to quantify the size and growth rate of flames over large surfaces. The flame propagates over a panel of thin material approximately 0.4 m wide by 1.0 m long. The ignition method is a hot wire along the upstream edge. This material is expected to burn at the anticipated cabin atmosphere. The objective of this test is to quantify the flame development over a large sample in low-gravity. The objective of the second set of tests (Saffire-II) is to investigate the low-gravity Maximum Oxygen Concentration (MOC) flammability limits in long-term low gravity. The configuration for these experiments consists of nine samples of varying materials (denoted flammability samples) each having dimensions of approximately 5 cm wide by 30 cm long installed on the same panel in place of the single sample. These samples emulate the configuration used in NASA-STD-6001 Test 1. Each sample is ignited at the bottom using a hot wire. The oxygen concentration in the vehicle is expected to be nearly 21% by volume—the same as in the ISS when the hatch is closed. The materials would be selected to be near their normal-gravity or hypothesized low-gravity maximum oxygen concentration in 21% O2. This complicates the selection of sample materials because most materials relevant for spacecraft do not have normal-gravity flammability limits near 21% oxygen by volume. Camera images would be the primary diagnostics for these tests as the intended result is primarily to determine whether the flame propagates or self-extinguishes.

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Applications

Space Applications
The Saffire-I experiment provides a new way to study a realistic fire on an exploration vehicle, which has not been possible in the past because the risks are too high. Instruments on an unmanned cargo vessel measure oxygen, carbon dioxide, heat, pressure and flame growth, and two video cameras provide views of the flame. Results determine microgravity flammability limits for several spacecraft materials, help to validate NASA’s material selection criteria, and how microgravity and limited oxygen affect flame size. The investigation is crucial for the safety of current and future space missions.

Earth Applications
Studying fire in small, sealed environments such as the Cygnus cargo supply vehicle benefits fire safety and prevention efforts on Earth, including inside mines, airplanes or submarines. Although the Saffire-I investigation is targeted toward spacecraft fire safety, results improve general understanding of fire behavior, which benefits people on Earth.

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Operations

Operational Requirements and Protocols

The Saffire experiments are conducted in three consecutive flights of the Cygnus vehicle. Since Cygnus undergoes a destructive re-entry, three Saffire experiment units (Saffire-I, -II, and –III) are constructed and all data must be downlinked. Even with these three flight opportunities, the experiment is very limited in the amount of data and test conditions that can be investigated. In Saffire-I and –III, the sample material is a single large sample (approx. 0.4 m wide by 0.94 m tall) to demonstrate the development and spread of a large-scale low-gravity fire. Once started, the entire burn of each of these samples is recorded, the data compressed, and downlinked. Nine smaller samples are burned on Saffire-II each having a dimension of 5 cm wide x 25 cm long. These are burned sequentially with the camera recording images only from the sample being burned. Once started, these experiments run automatically. Because of limitations in time available for downlinking, a maximum of 20 gigabits of data can be downlinked.
 
The Saffire-I experiment begins only after Cygnus is unberthed from the ISS. Prior to unberthing, the crew must check that the inlet and outlet ends of the flow duct be clear of any stowage bags being deorbited.

Saffire-I mission operations begin when Cygnus unberths from the ISS. The Cygnus Flight Operations Team (FOT) establishes the vehicle in a lower, circular orbit. Based on this new orbit, ground station contact times are calculated and the experiment start is confirmed and coordinated with the Saffire FOT. From Cygnus undock until experiment start takes about 1 day.
 
The experiment operations are be conducted in two phases. The first phase consists of turning on power to the experiment avionics, checking the experiment is initialized successfully, starting the experiment run, and recording and compressing the resulting data. The second phase consists of downloading all experiment data via downlink passes at various ground sites. The data is examined for quality and files are retransmitted if necessary. When a complete set of data files has been successfully retrieved, or the timeline has reached a predetermined maximum duration, the experiment avionics power is switched off and the Cygnus vehicle deorbits.
 
Cygnus burns up on re-entry into the Earth's atmosphere. Consequently, the flight unit is permanently disposed of during this process. No specific disposal processes are expected if the experiment hardware is burned up upon re-entry.

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Decadal Survey Recommendations

Information Pending

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Results/More Information

Information Pending

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Results Publications

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Ground Based Results Publications

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ISS Patents

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Related Publications

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Related Websites

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Imagery

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The Saffire Logo. The Cygnus vehicle is shown. The three bright stars represent the three Saffire units. The streak above the Earth represents Cygnus destructive re-entry and the fate of the Saffire hardware.

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Saffire Experiment Module (top cover removed for clarity). Hardware consists of a flow duct containing the sample card and an avionics bay. All power, computer, and data acquisition modules are contained in the bay. Dimensions are approximately 53- by 90- by 133-cm.

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Saffire experiment module with foam packing and straps as it will be mounted in Cygnus.

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