This ARP addresses the issue of passengers smoking in aircraft lavatories and the need to improve warnings about the danger of fire caused by smoking.

S-9B Cabin Interiors and Furnishings Committee

Fire Suppression System Protects Giant Crawler Transporters

TBMG-580210/1/2009

Stat-X fire suppression system Fireaway LLC Minnetonka, MN 952-935-9745 http://statx.com

Engineering Support for Columbus: a Hydraulic Model of the Air Loop

2009-01-25317/12/2009

On the 11th February 2008, the Columbus pressurized module has been successfully installed into the International Space Station. TAS-I (Thales Alenia Space - Italy) is responsible for the Off-Site Engineering Support to Columbus for ECLSS/TCS. A dedicated test-campaign has been proposed by TAS-I and performed on board Columbus during the first months after its docking to the Space Station, in order to have a Hydraulic Model of the entire Columbus air-loop correlated with real on-board data. A specific tool has been realized for the calculation of the Fans speeds (at ISFA, CFA1 or CFA2 level) to be expected and commanded in case of critical event so that a comfortable and safe environment for both astronauts and payloads can be ensured. The first part of this paper briefly presents the successful results of the employment of a tool previously realized by TAS-I for the calculation of cabin air volume flow rate from air loop telemetry data (primarily fans delta pressure and input current). The second part presents the description of the hydraulic model for the air-loop and its importance in the engineering support of Columbus all along next years.

Audrito, Gianpiero, Parodi, Paola, Antonacci, Massimo, di Francescantonio, Nicola, Mueller, Roland

Deployable Crew Quarters

TBMG-345312/1/2008

The deployable crew quarters (DCQ) have been designed for the International Space Station (ISS). Each DCQ would be a relatively inexpensive, deployable box-like structure that is designed to fit in a rack bay. It is to be occupied by one crewmember to provide privacy and sleeping functions for the crew. A DCQ comprises mostly hard panels, made of a lightweight honeycomb or matrix/fiber material, attached to each other by cloth hinges. Both faces of each panel are covered with a layer of Nomex cloth and noise-suppression material to provide noise isolation from ISS.

Measurement of Smoke Particle Size under Low-Gravity Conditions

2008-01-20896/29/2008

Smoke detection experiments were conducted in the Microgravity Science Glovebox (MSG) on the International Space Station (ISS) during Expedition 15 in an experiment entitled Smoke Aerosol Measurement Experiment (SAME). The preliminary results from these experiments are presented. In order to simulate detection of a prefire overheated-material event, samples of five different materials were heated to temperatures below the ignition point. The smoke generation conditions were controlled to provide repeatable sample surface temperatures and air flow conditions. The smoke properties were measured using particulate aerosol diagnostics that measure different moments of the size distribution. These statistics were combined to determine the count mean diameter which can be used to describe the overall smoke distribution.

Urban, David L., Ruff, Gary A., Mulholland, George W., Cleary, Thomas G., Yang, Jiann C., Yuan, Zengguang

Safety Instructions for Sight-Impaired Passengers

ARP5446 (Historical)6/12/2008

These recommendations are provided to aid the international air transport industry by identifying a standard, minimum amount of safety instructions that should be given to sight-impaired passengers. This document is not meant to address problems associated with communicating safety information to sight-impaired passengers who are also hearing impaired or non-conversant in the language(s) used by the cabin crew to disseminate general safety information to passengers. Aircraft operators are encouraged to customize the safety instructions for their own operations in order to ensure that required safety information is provided to sight-impaired passengers.

S-9B Cabin Interiors and Furnishings Committee

Safety Considerations for Airplane Lavatories

ARP1315D (Historical)9/15/2006

This SAE Aerospace Recommended Practice (ARP) establishes safety recommendations for lavatories in transport category airplanes.

S-9B Cabin Interiors and Furnishings Committee

Lavatory Smoke Detectors

ARP4001A (Historical)2/17/2006

S-9B Cabin Interiors and Furnishings Committee

‘Issues and Behaviors of Airborne Particulate Matters under Microgravity Environment’

2004-01-23287/19/2004

During several ISS missions, there were false alarms at both US and Russian smoke detectors. High local airborne particulate concentrations and interior deposits are considered the causes for such anomalies. Alternatives are proposed to replace or complement these faulty smoke detectors. The entrained zeolite particles may play a role in causing problems with check valves and air save pumps in CDRA and Vozdukh. Another incidence has been the dispersion of particulates out of Metox regeneration oven. Particulate matters with aerodynamic diameter of 15 microns and above, which normally settle down on earth, stay airborne under micro-gravity and thereby cause the above-mentioned nuisances. The motion of such a particle along a gas stream with an initial velocity can be expressed by theoretical equations. Stokes' Law leads to the descriptions of inertial precipitation of aerosols that are important in solving the issues. The relevant parameters such as particle size, and properties as well as movement of particulates under zero gravity without external forces are described in this article.

Chu, Richard R.

A New Electrical Mobility Particle Sizer Spectrometer for Engine Exhaust Particle Measurements

2004-01-13413/8/2004

Electrical mobility has a long history as a tool for measuring the particle size of engine exhaust emissions. This paper gives a review of these methods as well as more current methods for making exhaust particle measurements. Each of the methods discussed has a limitation especially for making fast (sub-second) measurements. A new instrument is discussed that has been developed by TSI based on a technique developed over the last two decades by the University of Tartu - Estonia. A description of the instrument, the Engine Exhaust Particle Sizer™ (EEPS™), is given as well as engine dynamometer data showing a comparison between the current standards for engine exhaust measurements, the Scanning Mobility Particle Sizing (SMPS™) system and the Condensation Particle Counter (CPC). The EEPS compares favorably with the SMPS and CPC while providing sub-second response.

Johnson, Tim, Caldow, Robert, Pöcher, Arndt, Mirme, Aadu, Kittelson, David

Integrated Humidity and Carbon Dioxide Analysis For International Space Station Using SINDA/FLUINT

2000-01-23637/10/2000

The air interchange performance between the modules is an important factor in the atmosphere revitalization system of International Space Station (ISS) to maintain a habitable environment for the crew during on-orbit activities. A SINDA/FLUINT model of the integrated ISS air quality control system was constructed in support of pre and in-flight predictions of cabin air temperature and humidity, and CO2 partial pressure. This model calculates masses and partial pressure for the major gas constituents, such as O2, N2, CO2, and H2O. This model also simulates the effect of crew activities and their location in the station. The elements are linked together in terms of air interchange in the models via Inter-module ventilation (IMV). The air in each volume is assumed to be perfectly mixed. Latent loads and IMV air are assumed to be immediately and uniformly distributed throughout the cabin air volume of each element. This paper presents a description of the model and analysis generated using this model.

Son, Chang H.

Thermal Comfort, Ventilation Efficiency, Contaminant Removal Effectiveness and Safety in the Columbus Cabin

2000-01-22987/10/2000

Columbus is being built as the European contribution to the International Space Station (ISS) Program. The ECLS subsystem is developed by DaimlerChrysler Aerospace/Dornier under a contract from Alenia Aerospazio. This paper will survey the qualification test results of the Columbus cabin ventilation subjective test conduction up to February 2000.

Haidl, Thomas, Lehr, Bernd, Raatschen, Willigert

MPLM - Environmental Control System Design Evolution

9723137/1/1997

The Mini Pressurised Logistics Module (MPLM) has the important job of servicing the Space Station via the National Space Transportation System (NSTS). During the previous and the on-going Alenia design activities, a continous effort is spent to optimize the MPLM performance characteristics with a possible mass reduction. The aim is to reach the best compromise between different needs: the payload requirements, the functional ground and flight operational constraints (three units qualified for 25 flight missions each), the total mass available for the payload. This paper has the objective to document the recent configuration changes and activities of the last couple of years. The two subsystems involved in this evolution are the Thermal Control (TCS) and the Environmental Control (ECLSS). Most of the MPLM equipment has already passed the Critical Design Review (CDR) step and the update situation for each piece of equipment is listed in this paper. Also at S/S level intensive test activities have been accomplished to support the actual MPLM ECS configuration. A general overview of the tests performed is presented in this paper.

D'Auria, R., Antonacci, M., Moscatelli, A.

Thermal and Environmental Control of the Crew Transport Vehicle

9723147/1/1997

Following the objectives of the European Space Agency, specific studies have been performed concerning a Crew Transport Vehicle (CTV) based on the Ariane 5 launcher. This vehicle is designed to transport a maximum crew of 4 members to/from the International Space Station, with a limited amount of payloads. It is mainly composed of: Crew Module (CM), capable of withstanding the severe environmental conditions of the atmospheric re-entry, offering an adequate habitable environment for the crew all mission time long. Resource Module (RM), where most of provisions and electrical equipment (e.g. batteries) supporting the vehicle orbital life is stored; the truncated cone shape external surface of RM is entirely exploited for mounting dedicated fluid radiators. Transfer Vehicle (TV), a propulsion module designed to supply means and resources for the vehicle orbital manoeuvres and attitude control from launcher separation up to de-orbitation, when the RM + TV composite is jettisoned. The thermal control of the CTV requires the adoption of technical solutions compatible with extremely different environmental conditions (ranging from the cold boundaries of orbital exposure to the high aerothermal fluxes during re-entry) and various operational modes (the vehicle is fully active in free-flying phases, but it is in dormant mode when ISSA docked, with most of equipment switched off). Temperature and humidity in the habitable compartment are controlled by a dedicated section of the Environmental Control and Life Support Subsystem. An air loop is designed to collect the cabin heat loads due to crew metabolism, external environment and part of the spacionics dissipation. These loads are then transferred via a Condensing Heat Exchanger to a couple of hot redundant water loops (Active Section of Thermal Control Subsystem) which also receive the thermal power released by the electronic equipment mounted on cold plates. The resulting global heat loads are transported to the available heat sinks, which may be different depending on the various mission phases. During ascent and re-entry, waste heat dissipated by means of evaporators and / or managed through the vehicle thermal capacitance. In orbital conditions a set of radiators, connected to a low freezing temperature coolant loop, provides the necessary rejection to space. Passive thermal control provisions are complementarily adopted, including Multilayer insulation, foam blankets and heaters. The major design features of the CTV Thermal Control are highlighted, taking into account the interface subsystems (e.g. Electrical Power Supply, DMS / GNC, Thermal Protection), the mission timeline, and the constraints related to the failure tolerance criteria adopted.

Bottacini, M., Fenoglio, F., Ferro, C., Loddoni, G.

CFD Modelling on Fire Detection and Suppression in a Columbus Rack

9416076/1/1994

The Columbus fire suppression procedure is based on a centralized CO2 distribution system which injects the CO2 stored in a tank into the volume where the fire has to be extinguished. The fire is detected in each volume by means of the so-called REP (Rack Essential Package), which contains a fan and the smoke sensor. In order to assess the Fire Detection and Suppression design concept and to identify possible critical areas, Alenia Spazio - with the support of Flowsolve UK, and on behalf of EUROCOLUMBUS - has performed an analysis using a Computational Fluido-Dynamic (CFD) tool. The rack containing the water pump assembly and other electronic equipment has been chosen for the study. As far as the Fire Detection is concerned, the simulation intends to predict the flow field established in the rack by the ventilation system and the transport of smoke by this velocity field from a supposed point source. The smoke from any fire within the rack must be transported to the sensor so the fire can be detected within a “reasonable” time. The Fire Suppression System has more stringent targets to meet: the CO2 must reach a 50% concentration by volume everywhere in the rack within 60 seconds. The aim of the CFD simulation was to study various combinations of CO2 nozzle and pressure relief vent positions and numbers so that the configurations which fulfill the 50% requirement can be determined. The simulation has been performed using the 1.6.5 version of the PHOENICS general-purpose CFD code.

Veneri, Ruggero, Parodi, Paola

Columbus APM Environmental Control System Overview: Space Station and APM Restructuring Consequences

9413056/1/1994

This paper describes the main changes affecting the APM Environmental Control System (ECS) as a consequence of the Space Station Freedom (SSF) restructuring and Columbus APM overall reconfiguration. The main purposes of this reconfiguration are: minimize the number and complexity of the interfaces with Space Station Freedom (SSF) centralize avionics command and monitoring tasks revisit the failure tolerance concept of some ECS functions unify/standardize similar functions in the two subsystem adjust lifetime requirements and simplify maintenance concept of equipment. The APM ECS consists of the following functions: active thermal control (ATCS) passive thermal control (PTCS) atmosphere pressure and composition control air revitalization and cabin ventilation temperature and humidity control vacuum and venting nitrogen supply fire detection and suppression. The new ATCS configuration provides a cooling capability for a reduced number of P/L racks by means of its moderate loop. No modification is envisaged on the low temperature loop. Failure cases on both SSF thermal buses and APM ATCS have been considered and assessed, resulting in an optimization of the ATCS operation in off-nominal modes. Due to the adoption of a new APM launcher (ARIANE 5) instead of NSTS, the Negative Pressure Relief function is no longer required. A new cabin loop architecture is considered based on the use of three fans for air distribution in the APM thermal conditioning and air exchange with the adjacent SSF node (Intermodule Ventilation). As far as the Vacuum and Venting system is concerned, the only changes are the reduction of the connected lateral P/L racks and the deletion of the venting interface with the SSF. The same lateral P/L racks are also connected to the Nitrogen Supply system with the deletion of the relevant interface valves. The main change in the Fire Detection system concerns the new location of smoke detectors within the cabin loop. The Fire Suppression system is impacted due to the reduction of the number of enclosures requiring a fire suppression capability. Optimization in heater control has been achieved, while the decentralized valve control concept has been deleted in favour of a centralized one via Power Distribution Unit (PDU).

Gargioli, Eugenio, Balocco, Paolo, Leiseifer, Hans Peter, Sarri, Giuseppe

Comparison Testing of the Space Shuttle Orbiter and Space Station Freedom Smoke Detectors

9322917/1/1993

This paper describes the results of a series of tests that were conducted to compare the performance characteristics of the smoke detectors currently used on the Space Shuttle Orbiter and those recently developed and baselined for use on Space Station Freedom. The objective of the tests, sponsored by the National Aeronautics and Space Administration (NASA) at Johnson Space Center (JSC), was to determine if there were significant improvements in the latest sensing technology being developed for the Space Station program which could benefit the Shuttle program.

Steisslinger, H. R., Hoy, D. M., McLin, J. A., Thomas, E. C.

SAFETY CONSIDERATIONS - SMOKING IN LAVATORIES OF TRANSPORT AIRCRAFT

AIR4740 (Historical)5/5/1993

This SAE Aerospace Information Report (AIR) discusses the question of smokers and their opinions and intentions toward smoking in lavatories of transport aircraft during flight. The study has implications for instructions and warnings given to passengers.

S-9B Cabin Interiors and Furnishings Committee

Development of the Fire Detection System for Space Station Freedom

9211527/1/1992

A flexible fire detection system is required in order to monitor Space Station Freedom pressurized volumes, including spaces which may be inaccessible to the crew, or may be unattended for long periods of time. The system uses flame detectors to survey open areas for radiation at wavelengths and intensities characteristic of combustion, and uses smoke detectors to monitor particulates in open areas and in air circulation ducts. This paper briefly reviews the design of the system and the detectors and presents results of development testing of the smoke detectors. The duct-type smoke detector has met all Space Station Freedom performance requirements.

Armstrong, Mark, McLin, John, Fuhs, Susan, Buchmann, Oscar, Hu, Raymond

LAVATORY SMOKE DETECTORS

ARP4001 (Historical)1/18/1990

This ARP is to describe key features for the lavatory smoke detector. Consideration has been given to existing requirements of the FAA, to recommendations of aircraft operators and manufacturers. The ARP is deliberately not specific in all areas in order to maximize potential supplier's freedom to use the state-of-the-art design and manufacturing technologies. Safe, reliable, and effective lavatory smoke detectors remain the primary goal of the ARP.

S-9B Cabin Interiors and Furnishings Committee

Selection of the DC-9 Fire Detector System

6401951/1/1964

This paper discusses the Douglas DC-9 Fire Detector System and the considerations involved in making the selection. Areas of interest that are covered include: the importance of reliable fire detection to commercial airplane operators, a reliability approach to system selection, primary reasons for selection of the particular DC-9 system, the operation of the DC-9 equipment, and the design concepts considered in the installation of the system in the airplane to reduce component failure. A discussion of improvements in the system over current installations with respect to its ability to discriminate between a fire and a system malfunction of any kind will be presented.

Wilson, Robert F.

Fire Detection - Reliability and Costs

6401961/1/1964

A major challenge in jet aircraft is reliability and costs associated with continuous fire detection systems on jet aircraft. Systems are not foolproof, and are set off by overheating as well as by fire. False alarms which, for safety's sake, must be treated as reality, represent unnecessary delays and increases in maintenance costs. A solution is not derived, but evaluation of the merits of separating, physically and electrically, thermal detection from fire detection is suggested.

LeBoeuf, E. J., Mead, R. S.

The Vendor’s View of Fire Detection

6402121/1/1964

Fire detector performance statistics for 1963 are reviewed in a manner to bring out the variability in performance from poor to excellent of similar aircraft by different operators, and to compare in-flight false warnings as reported to FAA with the total number of fire detector failures which appear at preflight or during flight. Causes of fire detector system failures and false warnings are described for each of the currently used types of continuous fire detectors. Failures can be prevented, or at least greatly reduced, by the improvements in installation and maintenance practices described, as proven by the few excellent performance records revealed in the statistics. Fail-safe operation is discussed as an adjunct to failure prevention, and methods of achieving fail-safe operation are described.

Jones, Roger B.

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