DOCSLIB.ORG

Transhab Inflatable Habitat Kriss J. Kennedy Space Architect

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Transhab Inflatable Habitat Kriss J. Kennedy Space Architect https://ntrs.nasa.gov/search.jsp?R=20160011581 2019-08-29T16:29:50+00:00Z University of Houston SPACE ARCHITECTURE Case Study: TransHab Inflatable Habitat Kriss J. Kennedy Space Architect September 28, 2016 1 TransHAB Inflatable Prototype Module Space Architecture 2 NASA TransHab Concept • TransHab was a light weight inflatable habitation module for space applications • Original 1997 concept for light weight habitat module for human mission transit to Mars • Proposed to the International Space Station (ISS) Program as a replacement for a Hab Module 3 TransHab (Inflatable Space Habitat) DESIGNED 1997 4 Transportation Constraints Inflated TransHab TransHab Launch Package Robotic Arm Removal & Installation on ISS 5 Node 1 U.S. LAB Node 3 Nadir ISS TransHAB TransHAB on the ISS 6 ISS TransHAB Level 4: Pressurized Tunnel ISS TransHAB Functions • Private Crew Quarters • Galley & Dining Level 3: Crew • Meeting area for entire ISS crew Health Care • Health Care & Exercise • Hygiene • Stowage Level 2: Crew Quarters & • Crew Accommodations Mechanical Room • Environmental Control & Life Support System (ECLSS) • Communications Level 1: Galley & • Command, Control & Data Handling Wardroom • Protection during Solar Particle Events 7 ISS TransHab Architecture Hatch Door Inflatable Shell Level 4: Pressurized Central Structural Tunnel Core 20” Window (2) Ergometer Level 3: Crew Health Treadmill Care Inflatable Outfitting Compression Ring Integrated Water Level 2: Crew Quarters Tank and Mechanical Room Soft Stowage Array Level 1: Galley and Wardroom Wardroom Table 8 Level 1 zenith Leave Floor Open for Return Air to Mech Integrated Floor Strut into Rm. Above Fabric Floor Above SOFT STOWAGE LEVEL 1 ISS RACK HAND GALLEY WASH UTILITY UTILITY CHASE 'A' CHASE 'B' 62" PASS THRU aft ISS RACK PASS THRU ISS RACK ABOVE forward REFRIG/ ABOVE REFRIG/ FREEZER FREEZER #1 #2 ISS RACK GALLEY WARDROOM window nadir 9 Galley / Wardroom Area zenith Leave Floor Open for Return Air to Mech SOFT STOWAGE Integrated Floor Strut into Rm. Above Fabric Floor Above SYSTEM SOFT STOWAGE GALLEY AREA ISS RACK HAND GALLEY WASH WARDROOM UTILITY UTILITY TABLECHASE 'A' CHASE 'B' 62" PASS THRU aft ISS RACK PASS THRU ISS RACK ABOVE forward REFRIG/ REFRIG/ ABOVE REFRIG/ FREEZER KEY PLAN FREEZER FREEZER #1 #2 ISS RACK GALLEY WARDROOM AREA GALLEY RACK REFRIG/ FREEZER WARDROOM window GALLEY AREA nadir 10 Level 2 zenith Leave Floor & Clg. Open for Return Air to Mech Rm. Integrated Floor Strut into Fabric Flooring LEVEL 2 MECHANICAL ROOM AIR CQ #5 CQ #6 DUCT Door 42" aft forward CQ #4 PASSAGE TO CQ #1 PASS THRU GALLEY TO BELOW ISS RACK WATER Door TANK CQ #3 CQ #2 OPEN TO WARD- ROOM BELOW OPEN TO WARD- ROOM BELOW OPEN TO WARD- OPEN TO WARD- ROOM BELOW ROOM BELOW FLOOR STRUT INFLATABLE OUTFITTING nadir COMPRESSION RING 11 Private Crew Quarters Provides: (design for 0g) 11.0' • 6 Crew Quarters 3.35' m zenith UTILITY LINES • 81.25 ft3 of Volume: • 27% Larger than ISS Rack • ISS Rack Crew Quarter = 64 ft3 +/- (without bump out) CREW CREW • Private Space QUARTER QUARTER #5 #6 • Quiet Space • Sleep Area ATU Integrated into Door Panel • Personal Stowage Area CREW CREW aft QUARTER QUARTER forward • Radiation Protection #4 42" PASSAGE TO GALLEY #1 81.25cf Sleeping Restraint CREW CREW QUARTER QUARTER #3 #2 37" 4" (10 CM) I-BEAM LONGERONS nadir SHEAR PANEL W/ WATER TANK Crew Personal Unit: Entertainment & Work Substation Unit: Light Weight Frame and Fabric That Packages Into a Box. Typical Crew Quarter 12 ECLSS Equipment Area zenith Leave Floor & Clg. Open for Return Air to Mech Rm. SOUND ABSORBENT & Integrated Floor Strut into Fabric Flooring FIRE RETARDANT FABRIC CEILING MECHANICAL ROOM AIR CQ #5 CQ #6 SHELL DUCT Door INNER WALL ECLSS aft 42" PASSAGEEQUIP. TO forward CQ #4 CQ #1 PASS THRU GALLEY TO BELOW KEY PLAN ISS RACK WATER Door TANK CQ #3 CQ #2 OPEN TO WARD- ROOM BELOW OPEN TO WARD- ROOM BELOW SOUND ABSORBENT & FIRE RETARDANT OPEN TO WARD- OPEFABRICN TO WAR D -FLOORING ROOM BELOW ROOM BELOW MECHANICAL ROOM FLOOR STRUT INFLATABLE OUTFITTING nadir COMPRESSION RING 13 Level 3 zenith LEVEL 3 Leave Floor Open for Return Air to Mech Rm. Private Integrated Floor Strut Medical into Fabric Flooring Movable Area Movable Partition Partition SOFT SOFT STOWAGE STOWAGE ISS RACK CHeCS #1 UTILITY CHASE 'A' UTILITY CHASE 'B' Movable Partition PASS THRU aft ISS Rack PASSAGE TO TO BELOW forward Full Body CREW QUAR- TERS Changing Cleanser Area ISS RACK Movable Partition ISS RACK CHeCS #2 ERGOMETER TREADMILL EXERCISE AREA window nadir 14 Crew Health Care Area zenith Leave Floor Open for Return Air to MechLevel Rm. 4: Pressurized Tunnel to ISS Private Integrated Floor Strut Medical into Fabric Flooring Movable Area Movable Partition Partition SOFT SOFT STOWAGE STOWAGE ISS RACK CHeCS #1 UTILITY CHASE 'A' UTILITY CHASE 'B' Movable Partition KEY PLAN PASS THRU aft ISS Rack PASSAGE TO TO BELOW forward Full Body CREW QUAR- TERS Soft Changing Cleanser CHeCS Area ISS RACK Stowage Movable Partition System ISS RACK CHeCS #2 EXERCISE AREA Treadmill Sound Absorbent & ERGOMETER Fire Retardant Fabric TREADMILL Flooring Ergometer EXERCISE AREA window nadir 15 TransHab Specs PASSIVE CBM • Overall Length = 10.5 m MM/OD Protection • 7.67' OA Deployed Width = ~8.3 m LEVEL 4 PRESSURIZED TUNNEL 2.338 m • Internal Diameter = 7.6 m TO ISS NODE 3 • Packaged volume = 342 m3 • Deployed volume = ~161 m3 8' • ConOps 2.438 m • Packaged around Hard Core • During Launch-goes to vacuum except Tunnel 34.51' • Removed from Cargo Bay & Berthed to ISS10.519 m 7' 2.134 m • Slowly inflated with warmed air. Equalize & stabilize. • Crew unpack and assembly. • Checkout and verify operational 8' 2.438 m SHELL Vol = 11631 ft3 (329.37 m3) TUNNEL Vol = 446 ft3 (12.63 m3) AIR INFLATION SYSTEM Total Vol = 12077 ft3 (342.0 m3) & TANKS UNPRESSURIZED TUNNEL 2.74x larger an ISS Lab/Hab Module 7' 2.134 m 11' 3.353 m 7' 2.134 m Vol. (4414 ft3, or 125 m3) 25' 7.62 m 27'-2" 8.28 m 16 Structural Overview 17 General Structural Configuration Multi-Layer Inflatable Shell • Multi-Layer Insulation Blankets • Micrometeoroid / orbital debris Protection • Optimized Restraint Layer • Redundant Bladder With Protective Layer Central Structural Core • 2 Tunnels • Composite Core With Integral Water Tank • Repositionable Composite Isogrid shelves • Floor Struts With Fabric Flooring 18 Structural Hard Core 19 Deployed Internal Structure Overview Inflatable Compression Ring Composite Longerons Composite Deployable Beams Fabric Tension Floors Composite Shear Panels / Shelves Inflatable Stiffeners 20 Subsystems Packaged in Core Life Support Area for Packaged Systems Consumables and Outfitting Systems Longerons Avionics Packages Core Panel Shelves Core Panel Shelves (Sheer Panels-Stiffeners) 21 Multi-Functional Layered Inflatable Pressure Shell 2 Windows External Structural Internal Thermal Restraint Layer: Scuff Kevlar or Vectran Blanket Barrier MOD Redundant Shielding Bladders 22 Inflatable Restraint Layer “basket weave” manufacturing approach. Manually labor intensive and many opportunities for human error. 23 Packaging & Folding 24 Notional Shell Structural Interface Due to export control and patent license agreements NASA can not share the details. Inflatable Shell Assembly and Integration • Load Frame for restraint layer straps interface, Clevis Pins • Bladder Attach Ring • Bladders (redundancy) Bonded to Ring • Bladder Peel Guard Ring • Scuff Layer Interface 25 Notional Window Detail Due to export control and patent license agreements NASA can not share the details. Window Assembly and Integration • Bladder Ring • Load Frame for restraint layer straps interface • Exterior cover • Interior cover • Scratch pane • Pressure panes • MMOD debris pane 26 Goal 1: MMOD Test • Requirement: HAB shall have a minimum of 0.9820 Probability of No Penetration (PNP) • Designed and Build MMOD Shield • Made test shots • Shot after Shot • Current shell configuration tested projectiles up to 1.7 cm diameter • Due to the large size of TransHab, the Shielding required to meet the PNP is larger than the standard modules. 27 MMOD Testing Scientific American Frontiers TV: Alan Alda 28 Full-Scale Testing Shell Dev. Unit-1 (30psid ) Shell Dev. Unit-2 (60psid ) Shell Dev. Unit-3 Full-scale Deployment in a Vacuum Environment 29 Full Scale Development Unit MMOD Layers Tunnel Fairing Restraint Layer Triple Redundant Core Structure Bladder Core Fairing Support Stands Tunnel Fairing and Support Spacer 30 TransHab Full Scale Shell Development Unit (SDU-3) First Inflation: November 17, 1998 31 TransHab Full Dia. Shell Development Unit (SDU-2) •Focused on Restraint Layer –Fabric to hard structure interface –Manufacturing Processes •Built Shell to test Restraint & Interface Stresses •Built Test Unit for Hydrostatic Test to S.F. = 4.0 – Full Diameter w/ Reduced Hgt. – Non-Flight like Core and Bladder – Pressurized w/ Water to Equivalent of 4X Operating Pressure and Held for 5 Minutes 32 Full Scale Shell Development Unit (SDU-3) Vacuum Test Demonstrated: • Folding of Shell • Packaging for Shuttle Payload Bay • Operation in a Vacuum • Deployment of Shell • Inflation of Module 33 SDU-3 Installation of MM/OD Gores 34 TransHab Full Scale Shell Development Unit (SDU-3) Vacuum Deployment Test: December 21, 1998 35 36 Summary • TransHab started out as a Mars Transit Habitat (Trans-Hab) tiger team concept in 1997. • So well liked, we were asked to redesign it as a Govt Furnished Equipment project for an ISS habitat. 1998 • Moved into Rapid design and testing to “proof feasibility.” 1999 • Developed engineering test units, tested 3 important high-risk areas people had concerns with for inflatables. Mitigated the risks. • Proof-of-Concept that inflatable structures could be used as an alternative for space habitats. • Revolutionized how the aerospace industry thinks about space habitats. • Demonstrated “human-centered” design and Human Systems Integration—space architecture. 37 38.
Load more

Recommended publications
  • Project Selene: AIAA Lunar Base Camp
    Project Selene: AIAA Lunar Base Camp AIAA Space Mission System 2019-2020 Virginia Tech Aerospace Engineering Faculty Advisor : Dr. Kevin Shinpaugh Team Members : Olivia Arthur, Bobby Aselford, Michel Becker, Patrick Crandall, Heidi Engebreth, Maedini Jayaprakash, Logan Lark, Nico Ortiz, Matthew Pieczynski, Brendan Ventura Member AIAA Number Member AIAA Number And Signature And Signature Faculty Advisor 25807 Dr. Kevin Shinpaugh Brendan Ventura 1109196 Matthew Pieczynski 936900 Team Lead/Operations Logan Lark 902106 Heidi Engebreth 1109232 Structures & Environment Patrick Crandall 1109193 Olivia Arthur 999589 Power & Thermal Maedini Jayaprakash 1085663 Robert Aselford 1109195 CCDH/Operations Michel Becker 1109194 Nico Ortiz 1109533 Attitude, Trajectory, Orbits and Launch Vehicles Contents 1 Symbols and Acronyms 8 2 Executive Summary 9 3 Preface and Introduction 13 3.1 Project Management . 13 3.2 Problem Definition . 14 3.2.1 Background and Motivation . 14 3.2.2 RFP and Description . 14 3.2.3 Project Scope . 15 3.2.4 Disciplines . 15 3.2.5 Societal Sectors . 15 3.2.6 Assumptions . 16 3.2.7 Relevant Capital and Resources . 16 4 Value System Design 17 4.1 Introduction . 17 4.2 Analytical Hierarchical Process . 17 4.2.1 Longevity . 18 4.2.2 Expandability . 19 4.2.3 Scientific Return . 19 4.2.4 Risk . 20 4.2.5 Cost . 21 5 Initial Concept of Operations 21 5.1 Orbital Analysis . 22 5.2 Launch Vehicles . 22 6 Habitat Location 25 6.1 Introduction . 25 6.2 Region Selection . 25 6.3 Locations of Interest . 26 6.4 Eliminated Locations . 26 6.5 Remaining Locations . 27 6.6 Chosen Location .
    [Show full text]
  • The “Farm:” an Inflatable Centrifuge Biology Research Module on the International Space Station
    The “Farm:” An Inflatable Centrifuge Biology Research Module on the International Space Station M.Thangavelu1, L. Simurda2 As the sole manned laboratory in Low Earth Orbit, permanently operating in microgravity and largely unprotected by the Earth's atmosphere, the International Space Station serves as an unparalleled platform for studying the effects of low or zero-gravity and the space radiation environment on biological systems as well as developing, testing and certifying sturdy and reliable systems for long duration missions such as ambitious interplanetary expeditions planned for the future. Earth- bound research, automated research aboard satellites and short missions into low- altitude orbits cannot replicate long-term ISS experiments. Abandoning or de- orbiting the station, even in 2020, leaves the international scientific and engineering community bereft of a manned station in orbit and destroys any opportunity for conducting long-term microgravity and radiation experiments requiring human oversight in space. The United States should invest in extending the station's life by a minimum of 15 years from present by attaching an inflatable "Farm" centrifuge module to equip biologists, psychologists and engineers with the tools required to investigate these questions and more. At a time when humankind has only begun exploring the effects of the space environment on biological systems, it is essential that we not abandon the only empirical research facility in operation today and instead begin vigorously pursuing research in this area that is of vital importance to all humanity, not only in the basic and applied sciences but also in international collaboration. I. Introduction In June 2010, President Barack Obama announced a novel vision for NASA and proposed extending the life of the International Space Station (ISS) until at least 2020.
    [Show full text]
  • The Annual Compendium of Commercial Space Transportation: 2012
    Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2012 February 2013 About FAA About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2013) NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. • i • Federal Aviation Administration’s Office of Commercial Space Transportation Dear Colleague, 2012 was a very active year for the entire commercial space industry. In addition to all of the dramatic space transportation events, including the first-ever commercial mission flown to and from the International Space Station, the year was also a very busy one from the government’s perspective. It is clear that the level and pace of activity is beginning to increase significantly.
    [Show full text]
  • Deployable Modular Frame for Inflatable Space Habitats
    70th International Astronautical Congress (IAC), Washington D.C., United States, 21-25 October 2019. Copyright ©2019 by the International Astronautical Federation (IAF). All rights reserved. IAC-19,B3,8-GTS.2,4,x48931 DMF: Deployable Modular Frame for Inflatable Space Habitats Vittorio Netti1, * 1University of Houston, [email protected] *Corresponding author Abstract Inflatable Space Modules for space exploration are now a reality. In 2016, Bigelow Aerospace tested the first inflatable module Bigelow Expandable Activity Module (BEAM) on the International Space Station (ISS), achieving success. This technology has higher volume limits than other launchers, substantially changing the previous concepts of construction and life in space. Nevertheless, inflatable modules technology lacks a reliable and functional platform to efficiently use all this space. Due to its limited dimension, the International Standard Payload Rack (ISPR), currently used on ISS, is not suitable for this purpose. The project aims at developing a new standard for payload rack in the inflatable space modules: the Deployable Modular Frame (DMF). The DMF expands itself radially from the center of the module, starting from four structural pylons. It creates a solid infrastructure allowing for the configuration of a variety of spaces, including storage space, laboratories, workstations and living quarters. The DMF consists of two main parts: the Deployable Frame (DF) and the Modular Rack (MR). Once the frame is deployed, it provides four linear slots suitable to install the modular racks. The rack is the basic element that allows for the storage of equipment inside the frame. Once they are installed, the racks can slide on the frame’s rails, dynamically changing the space inside the module.
    [Show full text]
  • MASTER's THESIS Space Radiation Analysis
    2009:107 MASTER'S THESIS Space Radiation Analysis - Radiation Effects and Particle Interaction outside Earth Magnetosphere using GRAS and GEANT4 Lisandro Martinez Luleå University of Technology Master Thesis, Continuation Courses Space Science and Technology Department of Space Science, Kiruna 2009:107 - ISSN: 1653-0187 - ISRN: LTU-PB-EX--09/107--SE Space Radiation Analysis: Radiation Effects and Particle Interaction outside Earth Magnetosphere using GRAS and GEANT4 Master’s Thesis For the degree of Master of Science in Space Science and Technology Lisandro M. Martinez Luleå University of Technology Cranfield University June 2009 Supervisor: Johnny Ejemalm Luleå University of Technology June 12, 2009 MASTER’S THESIS ABSTRACT Detailed analyses of galactic cosmic rays (GCR), solar proton events (SPE), and solar fluence effects have been conducted using SPENVIS and CREME96 data files for particle flux outside the Earth’s magnetosphere. The simulation was conducted using GRAS, a European Space Agency (ESA) software based on GEANT4. Dose, dose equivalent and equivalent dose have been calculated as well as secondary particle effects and GCR energy spectrum. The results are based on geometrical models created to represent the International Space Station (ISS) structure and the TransHab structure. The physics models used are included in GEANT4 and validation was conducted to validate the data. The Bertini cascade model was used to simulate the hadronic reactions as well as the GRAS standard electromagnetic package to simulate the electromagnetic effects. The calculated total dose effects, equivalent dose and dose equivalent indicate the risk and effects that space radiation could have on the crew, large amounts of radiation are expected to be obtained by the crew according to the results.
    [Show full text]
  • Water Walls Architecture: Massively Redundant and Highly Reliable Life Support for Long Duration Exploration Missions
    WATER WALLS ARCHITECTURE: MASSIVELY REDUNDANT AND HIGHLY RELIABLE LIFE SUPPORT FOR LONG DURATION EXPLORATION MISSIONS Michael T. Flynn, Principal Investigator, NASA Ames Research Center Co-Investigator Team Dr. Marc M. Cohen, Arch.D, Astrotecture™, Renee L. Matossian, Space Architect, Astrotecture™, Dr. Sherwin Gormly, PhD, Desert Toad LLC, Dr. Rocco Mancinelli, PhD, Bay Area Environmental Research Institute Dr. Jack Miller, PhD, Consultant Jurek Parodi and Elysse Grossi, Universities Space Research Association 1 1. Abstract ............................................................................................................................ 4 2. Introduction ...................................................................................................................... 4 2.1 Long Duration Life Support ........................................................................................... 5 2.1.1 A New Approach ................................................................................................................. 5 2.1.2 Limitations of the Current Approaches ................................................................................ 5 2.1.3 Key to Success: Incrementally Consuming the System - Not Driving it to Failure................. 6 2.2 Background .................................................................................................................... 6 2.3 Water Walls and Spacecraft Arcbitecture..................................................................... 9 3. System-Integration Challenge
    [Show full text]
  • Bigelow Aerospace
    Board Summary Bigelow Aerospace Date: July 11, 2018 1899 West Brooks Avenue, North Las Vegas, NV 89032 Main Location: Carson City Blair Bigelow, Vice President of Corporate Strategy Aerospace Manufacturing Business Type: Expansion County: Clark County Development Authority Representative: Kylie Rowe - LVGEA APPLICATION HIGHLIGHTS - Bigelow Aerospace is considering expanding its current operations in North Las Vegas. - The expansion would accommodate the company's new project: the development and manufacture of Bigelow Aerospace's flagship spacecraft, the B330, an entirely autonomous platform outfitted with two dissimilar propulsion systems and entire suite of environmental life support systems. - The B330 is the only spacecraft of its kind being developed in the world. PROFILE Bigelow Aerospace is an American space technology company that manufactures and develops expandable space station modules. These NASA heritage systems are soft-bodied modules that launch in a compressed configuration but expand greatly once they reach space. Such inflatables provide for greater volume, safety, opportunity, and economy than the aluminum alternatives. Bigelow Aerospace's newest product, the B330, is a fully autonomous stand-alone space station which is complemented with a complete suite of life support systems, launches at 1/3 of the expanded size, provides 330 cubic meters of internal volume, and houses up to six crew memembers. To date the company has successfully launched two subscale spacecraft called Genesis I & II into orbit as well as the Bigelow Expandable Activity Module (BEAM), which is attached to the Tranquility module of the International Space Station. In October 2006, Bigelow Aerospace received the Innovator Award from the Arthur C. Clarke Foundation.
    [Show full text]
  • Outer Space the Moon Mars Earth Gravity Radiation Primary Atmosphere Temperature
    Introduction Abstract Introduction Isolated, confined, and extreme (ICE) environments exist as the inhabited areas of the Isolated, confined, and extreme (ICE) environments are the most universally challenging Earth or the space above it that pose the greatest challenges to human health. Individuals places in which anyone could attempt to survive, but can provide enormous scientific and can survive in these places, but the environments present inherently challenging conditions economic benefits for those who do live and work within them. The harsh environmental that make survival difficult or even dangerous. The most familiar extreme environments are conditions and psychological difficulties experienced within ICE environments currently limits considered the open desert, the ocean, and the poles. These are areas with harsh weather the amount of time individuals can spend at Earth’s poles, at sea, or in space to roughly and almost no potable water, and they offer very little in terms of shelter. a year. Enabling humans to survive for a longer duration while remaining physically and The most immediate threats are physical in the form of environmental conditions psychologically healthy is the central goal of architecture for ICE environments. or the vacuum of space, which could prove lethal. Drilling platforms must deal with high These environments offer access to resources such as oil and gas and enable seas and polar research stations must allow for survival through long winters without unique scientific exploration and discovery. Addressing the difficulties those living in outside assistance. The necessity of dealing with one’s physical environment is paramount; ICE environments face will increase overall productivity and health.
    [Show full text]
  • 22 May 2002, ESA/ESTEC, Noordwijk, the Netherlands
    Modular Inflatable Space Habitats First European Workshop on Inflatable Space Structures 21 – 22 May 2002, ESA/ESTEC, Noordwijk, The Netherlands Andreas Vogler, dipl. Arch ETH(1) (1)University of Technology Munich Arcisstrasse 21 D-80290 Munich, Germany Email:[email protected] ABSTRACT In space we find an extreem vacuum. Human beings need an atmosphere to survive. This makes inflatables most apt for use in human space flight. Savings in weight and packaging volume are perfect for getting them off ground. With the development of TransHab, NASA made a big step forward in proofing the technology-readiness of using inflatables for human space habitat. Protection of micro-meteorites and radiation proofed to be even better than in the aluminium ISS Module. The shape of TransHab was based on a toroid. The sphere is the natural shape of a flexible skin with an inside pressure and naturally combining maximum volume with minimum surface (insulation/protection etc). It is astonishing why this very efficient shape has not been used more often for space applications. This paper will investigate on a concept level the possibilities of a sphere for use in microgravity and planetary habitats. Possibilities for habitats for 1-2 person, 6 persons and up to sixty and more, all using the same basic standard modules and morphology. Even a whole self-sufficient space station with artificial gravity where the big structure resembles - like in a fractal system - the smallest unit will be proposed. INTRODUCTION Inflatable structures have always been a obvious alternative for space structures, since they combine stability with a high volume/weight ratio.
    [Show full text]
  • Inflatable Technology: Using Flexible Materials to Make Large Structures Douglas A
    Inflatable technology: using flexible materials to make large structures Douglas A. Litteken* NASA Johnson Space Center, 2101 NASA Parkway, Houston, TX, USA 77058 ABSTRACT Space structures are one of the most critical components for any spacecraft, as they must provide the maximum amount of livable volume with the minimum amount of mass. Deployable structures can be used to gain additional space that would not normally fit under a launch vehicle shroud. This expansion capability allows it to be packed in a small launch volume for launch, and deploy into its fully open volume once in space. Inflatable, deployable structures in particular, have been investigated by NASA since the early 1950’s and used in a number of spaceflight applications. Inflatable satellites, booms, and antennas can be used in low-Earth orbit applications. Inflatable heatshields, decelerators, and airbags can be used for entry, descent and landing applications. Inflatable habitats, airlocks, and space stations can be used for in-space living spaces and surface exploration missions. Inflatable blimps and rovers can be used for advanced missions to other worlds. These applications are just a few of the possible uses for inflatable structures that will continued to be studied as we look to expand our presence throughout the solar system. Keywords: Deployable structures, inflatable structures 1. INTRODUCTION The dream of human exploration beyond our home planet has excited and inspired generations across the world. The dreams of taking vacations to the Moon, visiting cities on Mars, or traveling through black holes to discover new life in other galaxies have been described in fiction stories for decades.
    [Show full text]
  • Developing a Habitat for Long Duration, Deep Space Missions
    GLEX-2012.05.3.8x12222 DEVELOPING A HABITAT FOR LONG DURATION, DEEP SPACE MISSIONS Michelle A. Rucker NASA Johnson Space Center, USA, [email protected] Shelby Thompson, Ph.D. Lockheed Martin/Johnson Space Center, USA, [email protected] One possible next leap in human space exploration for the National Aeronautics and Space Administration (NASA) is a mission to a near Earth asteroid (NEA). In order to achieve such an ambitious goal, a space habitat will need to accommodate a crew of four for the 380-day round trip. The Human Spaceflight Architecture Team (HAT) developed a conceptual design for such a habitat. The team identified activities that would be performed inside a long-duration, deep space habitat, and the capabilities needed to support such a mission. A list of seven functional activities/capabilities was developed: individual and group crew care, spacecraft and mission operations, subsystem equipment, logistics and resupply, and contingency operations. The volume for each activity was determined using NASA STD-3001 and the companion Human Integration Design Handbook (HIDH). Although, the sum of these volumes produced an over-sized spacecraft, the team evaluated activity frequency and duration to identify functions that could share a common volume without conflict, reducing the total volume by 24%. After adding 10% for growth, the resulting functional pressurized volume was calculated to be a minimum of 268 m3 (9,464 ft3) distributed over the functions. The work was validated through comparison to Mir, Skylab, the International Space Station (ISS), Bigelow Aerospace’s proposed habitat module, and NASA’s Trans-Hab concept.
    [Show full text]
  • SKYLAB II B Griffin Making a Deep Space Habitat from a Space Launch System Propellant Tank
    Future In-Space Operations Colloquium SKYLAB II B Griffin Making a Deep Space Habitat from a Space Launch System Propellant Tank March 27, 2013 Brand Griffin “Skylab II, Making a Deep Space Habitat from a Space Launch System Propellant Tank,” B. Griffin, D. Smitherman, K. Kennedy, L. Toups, T. Gill, and S. Howe, AIAA Space 2012 Conference, Pasadena, CA, September 11-13, 2012, AIAA 2012-5207 1 Habitat for Humans Beyond LEO B Griffin Deep Space Habitat Crew of 4 Three 60 day missions L4 Grow to 180 day missions EM L2 Moon L1 L3 ES L2 (Telescopes) Earth Different than ISS No rapid return Costly, infrequent reupply L5 More Hab than ISS Lab Skylab II Deep Space Habitat from an SLS Propellant Tank 2 2 Skylab moved astronauts out of the couch B Griffin • Post Apollo (used Apollo assets) • Launch mass 77,088 kg (169,950 lb) • First US Space Station • “Dry” Workshop (3rd stage propellant tank) • 1973 Saturn V launch (fully provisioned) • Included telescope, airlock and docking • Occupied by 3 crews, 3 astronauts each adaptor • Crew duration: 28, 59 and 84 days • LEO ~ 440 km altitude, 50° inclination • Last crew 1974, re-entered 1979 Airlock Module Orbital Work Shop Multiple Docking Adaptor Apollo Telescope Mount 03/27/2013 Skylab II Deep Space Habitat from an SLS Propellant Tank 3 Heavy Lift, Large Diameter, Single Launch B Griffin 03/27/2013 Skylab II Deep Space Habitat from an SLS Propellant Tank 4 SLS Upper Stage H2 Tank B Griffin 03/27/2013 Skylab II Deep Space Habitat from an SLS Propellant Tank 5 ISS-Derived Deep Space Habitat B Griffin
    [Show full text]