The Phoenix Project. Modifying International Space Station to Support the Vision for Space Exploration. NASA Vision for Space Exploration

Transcription

1 Modifying International Space Station to Support the Vision for Space Exploration ENAE 484 Spring 2006 NASA Vision for Space Exploration 2 Manned missions to Mars following sustained human presence on the moon Unknowns: Can we sustain a crew of 6 for a 3-year Mars mission? How will humans respond to prolonged partial gravity? How will humans conduct experiments on the Martian surface? What equipment is necessary to experiment in partial gravity? Building a space station in Low-Earth Orbit (LEO) to answer these questions would cost nearly as much as a manned mission to Mars.

2 International Space Station (ISS) 3 ISS scheduled for completion in 2010 Science modules Structural components (nodes and trusses) Money Invested USA $ 100B Russia $? Europe $ 10B Japan $ 8B Canada $ 2B Image: Can we exploit this resource for simulating Mars missions? Space Station Phoenix 4 Convert ISS into a new space station, maximizing use of existing ISS components Station will be capable of: Supporting a crew of 6 for 3 years without re-supply Testing human response to partial gravity: 0g to 1g Station construction will begin 1 January 2017 Partial gravity testing finished by 1 January 2024 Mars mission simulation by 1 January 2027 SSP will accomplish this for $ 13.38B

3 Mars Mission Simulation 5 Fast transit mission profile 5 month 0g transit phase 21 months at!g on Mars surface 4 month 0g return Self-sufficiency 3 year supply of all consumables No re-supply, except in case of emergency Physiological Experiments 2 crewmembers 6 hours/day Endurance: treadmill use in I-suit Dexterity: tool workstation Adjustment: 0g to!g transition Gravity Test 6 Study various effects of long term exposure to partial gravity Gravities: 25%, 50%, and 75% of Earth gravity Topics of study Plant growth Cell biology Life science Human physiology Rodent physiology Mars equipment testing

4 Choosing a Rotation Rate 7 Lackner study demonstrated that 10 rpm can be tolerable if spatial disorientation is mitigated with head movements during acceleration Discomfort due to vestibular and ocular sense of Coriolis acceleration forces 4.5 rpm chosen to strike a balance between minimizing the Coriolis force disturbance to the crew and minimizing the size of the rotating arms Overall Structure 8 Inflatable Transfer Tube Stability Arms Townhouse B Townhouse A Non-Rotating Sections

5 Townhouse A (Crew Habitat) 9 New modules/components: Node 3B, PMA 3 Leonardo (Crew Quarters) Cupola Node 3A Raffaello (Galley) Donatello (Exercise/Medical) Node 3B PMA 3 Russian RM (Crew Quarters) Crew Quarters m 2 of floor space per person Removable curtains provide privacy Each bed is 2 m x 1 m Sleeping restraints for 0g Beds lofted desks and personal storage underneath At least 1.4 m 3 of additional storage per crew member under floor Bed 1 Bed 2 MPLM: Leonardo Curtain Dividers

6 Galley m Microwave/ Heater Food Prep Area Cleaning Supplies Pantry/ Games TV/DVD 3.2 m Trash Compactor Trash Water 1.75 m Fridge/ Freezer Food Drawers Foldable Table Food 0.73 m 0.97 m MPLM: Raffaello Food and Water 12 Daily Food Ration : 1.55 kg, m 3 Total Food : 11,200 kg, 23 m 3 Water Recovery System UPA Urine Processor Assembly WPA Water Processor Assembly In order to save water for laundry, disposable clothing will be used. Worst Case Mass of Water Consumables Mars Simulation Emergency Supply 7,930 kg 1,630 kg Maximum Water Required: 9,560 kg

7 Hygiene 13 Hamilton Sundstrand Waste Collection System Functions at all gravity levels from 0g to 1g Solids compacted Waste contingency bags will be provided in case of failure A Comfort hygienic set provided to each crew member; contains personal hygienic supplies Wet towels will be used instead of a traditional shower Reduces water consumption Astronauts have preferred this method in reduced gravity conditions Image: SSP Atmospheric Parameters 14 SSP Cabin Volume Major Atm. Composition Cabin Pressure Temperature Range Relative Humidity Airborne Particulates Ventilation SSP Daily O 2 Consumption [kg O 2 /per day] 2000 m 3 79% N 2, 21% O to 14.7 psi 18.0 ºC to 24.0 ºC 25% to 70% 3.5 x 10 6 max counts/m m/s to 0.20 m/s SSP Daily CO 2 Production [kg CO 2 /per day] Metabolic Crew O 2 Req (x6) Metabolic Crew Product 1.00 (x6)

8 Atmospheric Life Support 15 N 2 Generation/Supply O 2 Generation/Supply CO 2 Removal from Cabin CO 2 Reduction Disassociation of liquid hydrazine (N 2 H 4 ) Solid Polymer Water Electrolysis (SPWE) 2-Bed Molecular Sieve Sabatier Reactor N 2 H 4 Disassociation SPWE N 2 O 2 Pressure Control Assembly S S P H 2 2-BMS CO 2 H 2 O C A B I N Sabatier H 2 O H 2 O Crew Package Tank CH 4 (Vented) Atmospheric Life Support Racks 16 Oxygen Generation System (OGS) ON ISS kg/day H 2 O Needed to generate O 2 using SPWE Air Revitalization System (ARS) ON ISS 4.88 kg/day H 2 O Reclaimed by Sabatier Image: OGA Graphic, Hamilton Sundstrand Space Systems International, 2005 Image: ISS AR Rack, NASA/TM /VOL1 Mass Power Mass Power 711 kg kw 480 kg 1.90 kw OGS: SPWE and Sabatier ARS: 2-BMS, Trace Contaminant Control System, Mass Spectrometer -OGS and ARS located together on Node 3 of both Townhouse A and B-

9 Emergency Systems Caution and Warning System (CWS) Provides visual and audible cues to the following emergencies: Fire Hazardous Atmosphere Depressurization General Caution Currently on all ISS modules as push button panels Fire Detection/Suppression (FDS) Photoelectric smoke detectors are located on node/cabin vents Upon fire detection, ventilation is automatically ceased to fire location Fire can be suppressed using onboard CO 2 portable fire extinguishers (PFE) 17 Image: NASA/TM /VOL1 All FDS systems existing on the ISS Image: Whitaker, Ov erv iew of ISS U.S. Fire Detection and Suppression Sy stem, NASA/JSC Two-Fault Atmosphere Supply Backup O 2 Generation LiClO 4 Candle 18 Auxiliary System Second OGS LiClO 4 Candles Portable Breathing Apparatus (PBA) Duration Full Mission 28 days 15 min/pba PBA Backup CO 2 Removal Auxiliary System Second ARS LiOH Canisters Duration Full Mission 28 days Image (Top Right): Molecular Ltd. Image (Lower Right): PBA, Whitaker, Overview of the ISS US Fire Detection and Control System

10 Townhouse B (Science) 19 New modules/components: Node 3C JEM PM Node 2 Columbus (Mars Simulation Module) JEM ELM-PS Node 3C U.S. Lab (Destiny) Racks in Science Townhouse 20 Human Research Facilities 1 and 2 Microgravity Science Glovebox Plant Biotechnology Facility Mars Research Equipment Test Facility Rodent Research Facility Japanese Multi-User Experiment Facility Image: Image:

11 Townhouse Support Structure (TSS) 21 Common Berthing Mechanisms (CBMs) not designed to support modules under gravity Reinforced with I-beam frames Inflatable Transfer Tubes 22 Shirtsleeve environment for transferring crew between townhouses Cover 90 m span in two sections, each connecting to a townhouse and the central node Maximum pressure differential of 14.7 psi Inflatables up to much lighter than solid aluminum pressure vessel Crew has choice of motorized lift and rope later for movement through tube Total interior volume: 330 m 3 Total interior surface area: 610 m 2 Total soft-goods mass: 1240 kg

12 Central Axis 23 Propulsion Package S6 Truss PIRS Central Axis does not spin with rest of station Counter Rotating Assembly (CRA) Pressurized Mating Adapter (PMA) 5 Node 1 CRA P6 Truss Propulsion Package Stability Arm 24 Required for station stability (Moment of Inertia) Acts much like the stabilizer bar on a two-blade helicopter rotor U.S. Airlock PMA 2 PMA 1 Crew Tank Package PMA 4 MLM Zvezda

13 Spin Stability 25 Y Z X About the principal axes, the moment of inertia tensor The angular difference between the principal and geometric z-axis 0.3 On the z-axis, center of gravity 1.03 m below center of Node 1 Center of gravity on Node 1 in the x-y plane (required for docking) within 0.08 m on the y-axis within 0.01 m on the x-axis Docking Stability Higher stability needed during docking Requires large torques for short durations prior to dock, when station is spinning ISS chemical thrusters and tanks and mount them along x-axis Will require 375 kg of propellant (N 2 O 4 / UDMH) Following thruster firing: Max ground accelerations = 12% perceptible levels Max inertial truss deflection = 1.94 º Normal operation (nutation from thruster inaccuracy damped out) Max ground accelerations = 6.6% perceptible levels Max inertial truss deflection = 0.60º

14 Propulsion and Station Spin 27 P&W T-220HT Hall-Effect Thruster Operates with a specific impulse of 2,500 s Will produce 12N Liquid xenon propellant 8 thrusters will be used for spinning Desired Gravity!g #g "g!g Current Gravity 0g 0g #g "g Time (hours) g!g 28.8 Station Orientation 28 SSP stays at ISS orbit Orientation is orthogonal to Earth-Station orbital radial direction while its rotation axis projection onto Earth-Sun orbital plane points toward center of the Sun Reduced solar array movement Compensate for Earth gravity gradient by positioning smallest moment of inertia axis toward Earth s center Reduced thermal loads and gradient Fewer communication antennas Station Orbit Earth Orbit Rotation Axis Earth Station Plane Sun Earth Plane

15 Attitude and Orbit Maintenance 29 Main perturbations Magnetic field force, Solar radiation pressure and Docking torques Xenon mass Not Spinning Perturbation (kg/year) 3,010 Docking (kg/dock) 0.14 Spinning Drag causes a "v of 108 m/s per year Total Xenon Mass : 24,600 kg Power Systems 30 Solar panels: SLASR (Stretched Lens Array Square-Rigger) Power (EOL): 294 kw Mass: 1,275 kg Area: 1,400 m 2 Batteries: Ni-H 2 90% efficiency 40% depth of discharge Mass : 3,330 kg Image:

16 Communications 31 Four directional antennae relay two HDTV channels and 16Mbps of data through the TDRSS network to the ground. Antennas A backup system provides low bandwidth communication to TDRSS and directly to the ground with antennae that are omni-directional, ensuring that contact with SSP will never be lost. Communications with approaching vehicles accomplished through existing systems on Destiny Thermal Systems 32 Need to dissipate 164 kw of heat 165 kw of heat dissipation 8 PVR radiators 1,060 kg each 11.5 kw rejection each 6 HRS radiators 1,220 kg each 11.8 kw rejection each Total radiator mass: 15,800 kg

17 Overall Structure 33 Inflatable Transfer Tube Stability Arms Townhouse B Townhouse A Non-Rotating Sections Construction Stage I 34

18 Construction Stage II 35 Construction Stage III 36

19 Mission Timeline 37 Crew # Gravity 0 Stage I II III Phase Construction Month Sep Jul Jan Year I Partial Gravity Experimentation Jul % 11 50% II May % III Mar Transit 38% Mars Mission Simulation July Feb Surface Return Aug Apr 2026 Reserve Time Mission Complete: Jan 2027 Launch Details 38 Manned Crew Launch Vehicle (CLV) Carries Crew Exploration Vehicle (CEV) Cargo Boeing Delta IV Family Payload ( kg ) Cost Vehicle Delta IV Medium+ 4,2 Delta IV Medium+ 5,2 Delta IV Medium+ 5,4 Launches Capacity 11,750 10,250 13,500 Utilized 11,169 9,446 11,122 ( $M $ ) 138 $ 150 $ 160 Delta IV Heavy Total , , , ,559 $ 3,302 $ 3,750 Image (Left): Exploration System Architecture Study. National Aeronautics and Space Administration. NASA-TM , November 2005 Image (Right): Delta IV Payload Planners Guide. Boeing Corporation. MDC 00H0043, October 2000

20 Conclusion - Costs and Savings 39 Budget $20B Category Research & Development Manufacturing Ground Control Cargo Launches Manned Launches Total Cost ($2006) $ 1.47B $ 1.85B $ 1.77B $ 3.75B $ 4.50B $ 13.38B Under budget by 33% ($ 6.62B) Using 79% (360,000 kg) of ISS mass Recovering a significant portion of ISS investment Building SSP without ISS requires additional $ 99B Outreach 40 3 Focus Areas -Campus -Community -Educational (K-12) 200*+ hours of outreach! 100% Team Participation * Not including public PDR & CDR

21 Things that Worked Well 41 Set up centralized fora for mass changes and graphics needs Despite large class size, a large fraction of the class was involved in each major decision Individuals who demonstrated mixed organizational and technical abilities bubbled up to take on leadership roles ( and more work! ) PDR and CDR were thorough and concise. Criticism was constructive and not due to incorrect technical analysis OUTREACH effort was outstanding Things that Worked Well 42 The use of Blackboard for communication between team members/groups

22 Things that didn t work so well.. 43 Failed to adequately define the job of Systems Integration Took too long to get a preliminary design Person keeping track of the mass distribution was different from the person making the solid models NOT ENOUGH TRADE STUDIES. WE DID NOT PREPARE A PROPER TRADE STUDY REVIEW. RASC-AL presentation was created from CDR, instead of being made separately Only students helped create the RASC-AL abstract, poster, and presentation. Advice Get as much 484 project information from Dr.Akin/Dr.Bowden ASAP Once in groups, establish lines of inter-group communication (POC s) Rein in Independent Thinkers DO NOT dwell on CDR to create your RASC-AL presentation. (Different audience!) Have an agenda for every 484 class meeting Start Outreach program EARLY. Do not hesitate to contact professors/industry If you can produce hardware. DO IT 44

23 Akin s Law #1 45 Engineering is done with numbers. Analysis without numbers is only an opinion. Akin s Law #3 46 Design is an iterative process. The necessary number of iterations is one more than the number you have currently done. This is true at any point in time.

24 Akin s Law # 3 (example) 47 Akin s Law # 3 (example) 48

25 Akin s Law # 3 (example) 49 Akin s Law #4 50 Your best design efforts will inevitably wind up being useless in the final design. Learn to live with the disappointment.

26 Akin s Law #9 51 Not having all the information you need is never a satisfactory excuse for not starting the analysis. Akin s Law #11 52 Sometimes, the fastest way to get to the end is to throw everything out and start over.

27 Akin s Law #13 53 Design is based on requirements. There's no justification for designing something one bit "better" than the requirements dictate. Akin s Law #18 54 Past experience is excellent for providing a reality check. Too much reality can doom an otherwise worthwhile design, though.

28 RASC-AL 2006 Cape Canaveral 55 RASC-AL 2006 Cape Canaveral 56