Materials Science Research Rack-1 (MSRR-1)

by on 12 May 2015in Physical Sciences

MSRR Rack Level

  • Structural Attachment: 2 Experiment Modules (EM)
  • Power: 6000W, with 5000W 120/28 V dc power supplied tthe Ems
  • Thermal Control: 6000W Payload heat rejection – water
  • Data: 2 Ethernet; 2 MIL-STD-1553B
  • Vide: 1 NTSC feed from each payload source
  • Vacuum Exhaust System: 1 Payload connection supplies from both EMs
  • Vacuum Resource: 1 Payload connection supplies from both Ems

MSRR Payload Level (Allocation per EM Position)

  • EM ALPHA
    • Structural Attachment: 140kg, including cage on-orbit
    • Power: 10 A @ 28Vdc, 10 A @120Vdc
    • Thermal Control – Air: 0 W
    • Thermal Control – Water: 0 W
    • Data: 1 MIL-STD-1553B; 1 Ethernet
    • Vide: 1 NTSC Feed
    • Vacuum Exhaust System/Vacuum Resource: 1 each (Shared)
    • Operation of resistance heated Furnace Inserts with up t8 individually controlled heaters qualified for maximum temperatures of 1400 °C
  • Material Science Laboratory (MSL) – EM BETA
    • Structural Attachment: 340kg on-orbit
    • Power: 10 A @ 28Vdc, 5/10 A @120Vdc
    • Thermal Control – Air: 0 W
    • Thermal Control – Water: 4800 W
    • Data: 1 MIL-STD-1553B
    • Vide: 1 NTSC Feed
    • Vacuum Exhaust System/Vacuum Resource: 1 each (Shared)
  • Low Gradient Furnace (LGF)
    • Hardware/Facility Curator: European Space Agency (ESA)
    • Type of Processing: Bridgman
    • Gradient Zone Length: 200 mm
    • Maximum Processing Temp: 1400°C
    • Minimum Processing Temp: 500°
    • Temperature Stability Control: ±0.02°K (T>1073°K)
    • Sample Ampoule/Cartridge Size: OD 26mm; Length 470mm
    • Number of heating zones: 7
    • Sample Instrumentation: Up t12 thermocouples inside the sample cartridge plus pressure transducer
    • Realtime Science Data Capture (format): N/A
    • Translation Velocity: 10.5-0.2mm/sec
    • Translation Stability: ±1.5%
    • Levels of Containment: 2
  • Solidification and Quenching Furnace (SQF)
    • Hardware/Facility Curator: European Space Agency (ESA)
    • Type of Processing: Bridgman
    • Gradient Zone Length: 250 mm
    • Maximum Processing Temp: 1400°C
    • Minimum Processing Temp: 500°
    • Temperature Stability Control: ±0.01°K (T>773°K)
    • Sample Ampoule/Cartridge Size: OD 16mm; Length 470mm
    • Sample Instrumentation: Up t12 thermocouples inside the sample cartridge plus pressure transducer
    • Realtime Science Data Capture (format): N/A
    • Translation Velocity: 10.5-0.2mm/sec
    • Translation Stability: ±1.5%
    • Levels of Containment: 2
  • Sample Cartridge Assemblies (SCAs)
    • Leak-tight containers for materials samples, sensors for process control & safety, and stimuli
    • LGF-type SCAs and SQF-type SCA qualified for maximum temperatures of 940 °C and 1065 °C, respectively
    • Both LGF and SQF SCAs can accommodate up ta maximum of 12 thermocouple’s

Toward Understanding Pore Formation and Mobility During Controlled Directional Solidification in a Microgravity Environment (PFMI)

by on 12 May 2015in Physical Sciences
  • Type of Processing: Bridgman
  • Maximum Thermal Gradient*: up to 110 °C/min
  • Transparent Gradient Zone Length: 2.5 cm to 0.5 cm selectable
  • Maximum Sample Outside Diameter: 10mm
  • Maximum Sample Length: 23 cm
  • Maximum Sample Process Length*: 12 cm
  • Maximum Heater Temperature: 130 °C
  • Cold Zone minimum Temperature: 5 °C
  • Heater Stability Control: ± 1 °C
  • Translation Velocity:  0.5 micrometers/sec to 100 micrometers/sec
  • Translation Stability: ± 5%
  • Sample Ampoule Dimensions:  OD 12.75 mm, Length 28 cm
  • Sample Instrumentation: up to 6 Type K thermocouples inside the ampoule
  • Temperature Data Recording Rate: up to 1/sec
  • Video: S video record rate 30 fps, zoom 22:1, two camera views
  • Commanding Remote commanding of heater/cold zone temp, and camera zoom/focus
  • Depends on the sample material & configuration

Solidification Using a Baffle in Sealed Ampoules (SUBSA) Furnace

by on 12 May 2015in Physical Sciences

Operated in the Microsciences Glovebox (MSG)

  • Type of Processing: Gradient Freeze
  • Minimum Cool down Rate: 0.5 °C/min
  • Maximum Thermal Gradient: up to 110 °C/min (Depends on the sample material & configuration)
  • Transparent Gradient Zone Length: 8 cm
  • Maximum Sample Outside Diameter: 12mm
  • Maximum Sample Length: 30 cm
  • Maximum Sample Process Length: 13 cm (Depends on the sample material & configuration)
  • Maximum Heater Temperature: 850 °C
  • Heater Stability Control:  ± 0.15 °C
  • Sample Ampoule Dimensions: OD 16 mm, Length 30 cm
  • Sample Instrumentation: up to 4 Type K thermocouples on the outside of the ampoule
  • Temperature Data Recording Rate: up to 1/sec

Video

  • S video record rate 30 fps
  • Zoom 22:1
  • One camera view

Commanding

  • Remote commanding of heater temperature and camera zoom/focus

Light Microscopy Module (LMM)

by on 12 May 2015in Life Sciences, Physical Sciences

Specifications

  • Light Microscopy Module (LMM) is housed within and used in conjunction with the glovebox in the Fluids Integrated Rack (FIR)
  • Remotely controlled, automated microscope
  • For Physical and Biological experiments

Microscope

  • Modified commercial off-the-shelf (COTS) Leica RXA microscope
  • Objectives: 2.5x,10x, 20x, 40x, 50x, 63x, 63x oil, and 100x oil
  • New or different objectives may also be flown as needed

Imaging

  • Confocal imaging
  • Digital black and white low noise scientific camera
  • High resolution black and white microscopy, bright field, epifluorescencent (EPI), and fluorescent techniques

Fluids Integrated Rack (FIR)

by on 12 May 2015in Physical Sciences

Specifications

  • Housed in the Fluid and Combustion Facility (FCF)
  • Mounted in an International Standard Payload Rack (ISPR), with an Active Rack Isolation System (ARIS)
  • Light Microscopy Module (LMM) is housed inside the FIR

Accommodates the following areas of research

  • Boiling heat transfer
  • Multiphase flow
  • Liquid vapor interface control
  • Liquid and vapor evaporation and condensation
  • Colloids
  • Human Health and performance
  • Medical technology
  • Biosciences

Volume ~ 0.7 m3 (1100mm x 895mm x 495mm on the front of the OB)
Mass ~ 300kg depending on FIR be utilized

Electrical Power Control Unit (EPCU)

  • Nominal 672 W/1600W max at 28Vdc
  • 1450 W at 120Vdc

Thermal Cooling

  • 3 kW water (MTL)
  • 1300 W air (provided at 20oC to 30oC)

Video

  • Common Image Processing Unit (C-IPSU) – IEEE 1394 FireWire &
  • Analog Frame Grabber Interfaces for PI provided cameras
  • C-IPSU – Image processing & storage units for real time and post processing of image data
  • Illumination – White Light & 150mW 532nm Nd:YAG LASER*
  • Analog Color Camera*

Control & Data Acquisition

  • Fluid Science Avionics Package (FSAP) – Standard control and data acquisition interfaces (e.g. analog & digital Inputs/Outputs, motion control, RS-422)
  • 540 GB of Data Storage

Combustion Integrated Rack (CIR)

by on 12 May 2015in Physical Sciences

Specifications
Housed in the ISS Fluids and Combustion Facility (FCF) Chamber

  • 100 Liters capacity
  • Operating pressure: 0.02 to 3 atmospheres and contains pressures up to 9 atmospheres
  • 8 Sapphire windows
  • Supplies gaseous fuel, oxidizers and diluents to the combustion chamber

Oxidizers Bottles:

  • liter up to 80% O2
  • 2.25 liter up to 50% O2
  • 3.8 liter up to 30% O2
  • Quick disconnects used for easy attachment to manifolds

Maximum oxidizer flow rates

  • 30 slm per manifold
  • 90 slm total
  • Maximum fuel flow rate 2 slm
  • Adsorber Cartridge removes unacceptable gases, including water vapor and particulates from the combustion event
  • Provides the vent path to the ISS Vacuum

Exhaust System

  • 3 Column Gas Chromatograph

High Resolution/High Frame Rate Camera

  • High Resolution Mode: 1024×1024 pixels at 7.5, 15, or 30 fps
  • High Frame Rate Mode: 512×512 pixels at 60 or 110 fps
  • Automated Tracking – 9 x9 mm Instantaneous FOV (IFOV)
  • Focus over 30 mm object depth; 5mm/s focus speed
  • Resolution is 20 lp/mm at 50% contrast in HR mode

High Bit Depth/Multi-Spectral Camera

  • 1024×1024 pixels at programmed rates of 7.5, 15, or 30 fps
  • 12 bit dynamic range
  • Field of View: 50 mm square or 80 mm diameter
  • Resolution: 10 lp/mm maximum (0.05 mm)
  • Liquid Crystal Tunable Filter: 650-1050 nm spectral range

Low Light Level Packages (UV and IR)

  • FOV: UV 42 or 100mm; IR 45mm
  • 54 Frames per second
  • UV package uses industry standard Gen II intensifier
  • UV Spectral range: 220-850nm
  • IR package uses industry standard Gen III intensifier
  • IR spectral range: 400-900nm

Illumination Package

  • 80mm diameter Collimated Beam
  • Diffuse Laser Diode source
  • 10 mw coupled power
  • 655 nm peak wavelength

ISS Fluids and Combustion Facility (FCP)

by on 12 May 2015in Physical Sciences

Specifications
Houses the Combustion Integrated Rack (CIR) and Fluids Integrated Rack (FIR)

Electrical Power Control Unit

  • Two 120 VDC, 50 Amp inputs on the rear of the EPCU
  • Six 120 VDC, 4 Amp outputs on the rear of the EPCU
  • Forty eight 28 VDC, 4 Amp output channels located in twelve connectors on the front of the EPCU (3KW total 28 Volt power)
  • Input/Output Processor (IOP)

Communication Interface between the rack and ISS

  • ISS Low Rate Data Link, Medium Rate Data Link, High Rate Data Link & Video Interfaces
  • Serves as the main controller and data acquisition system for the rack via internal rack Ethernet
  • Provides rack to rack interface to the FIR via fiber optic cable

Image Processing & Storage Unit (IPSU)

  • Stores digital image data received from a camera
  • IEEE 1394 FireWire Interface for camera control and image acquisition
  • Analog video (RS-170) input
  • Analog video output from scan converter that converts digitally acquired data to an RS-170A signal
  • Two 36 GB hard drives per IPSU

FOMA Control Unit (FCU)

  • Provides power conditioning & data control for all FOMA hardware
  • Monitors all pressures, temperatures, and mass flow rates from the
  • FOMA during gas blending and experiment operation
  • Controls gas chromatograph for chamber sampling

Tec-Masters, Inc.

by on 1 May 2015in Physical Sciences, Technology Development

Tec-Masters, Inc. (TMI) has 20 years’ experience designing, developing, prototyping, assembling, integrating and operating flight hardware for NASA. TMI has developed and supported scientific investigations, high temperature materials processing, and control avionics payloads flown aboard the Shuttle and the International Space Station (ISS). TMI also supports ongoing flight operations of the Microgravity Science Glovebox (MSG) facility aboard the ISS including systems engineering, payload integration/verification, thermal and structural analyses. TMI’s engineering services include:

Engineering Design & Development:

  • Hardware and Software Requirements Definition
  • Software Development for Payload Control and Ground Support Equipment
  • Experimental Sample Materials Containment Systems Development
  • CAD Drawings Generation
  • Light Machining Support
  • Optical Inspections
  • Data Acquisition Systems Development
  • Video and Optical Systems Development
  • Rapid Prototypes Development
  • Certified Flight Hardware Development

Payload Integration:

  • Requirements Compliance Verification
  • Testing and Analysis
  • Integration Documentation
  • Safety Verification and Certification

Payload Operations:

  • Operations Concept Development
  • Crew Procedures
  • Crew Training
  • Real Time Console Operations

Post Flight Operations:

  • Data Analysis
  • Ground Sample Processing
  • Lessons Learned

Facilities:

TMI has developed a general purpose Research and Development (R&D) Lab to support experimentation, prototype development, assembly and evaluation, light machining and fabrication of components, assemblies and complete systems in support of flight and ground hardware/software development, and verification testing. TMI’s R&D Lab is equipped with:

  • A machine shop for light machining and small parts fabrication
  • Work areas with ESD protection for electronic design, fabrication, test, calibration, and verification activities
  • Stereo and metallurgical microscopes, both equipped with digital photo capability for inspection activities
  • Chemistry capabilities to support special cleaning of experiment/test parts and flight test ampoule preparation
  • CAD capabilities to support drawings as well as stress and thermal analyses
  • LabVIEW data acquisition system

NanoRacks LLC

by on 1 May 2015in Earth Science and Remote Sensing, Life Sciences, Physical Sciences, Technology Development

NanoRacks, LLC was formed in 2009 to provide quality hardware and services for the U.S. National Laboratory onboard the International Space Station. The company operates the first commercial laboratory in low-earth orbit. Today, NanoRacks has three research platforms onboard, which can house plug and play NanoLabs using the CubeSat form factor for inside the Space Station. Additionally, the NanoRacks External Platform, manufactured by Airbus DS, has recently launched to the ISS with first customers expected to use the platform in early 2016. To date, NanoRacks has launched over 350 customer payloads to the International Space Station, including domestic and international educational institutions, research organizations and government organizations. This has propelled NanoRacks into a leadership position in customer utilization in low-earth orbit and beyond.

NanoRacks’ low-cost model puts microgravity research projects within the budgetary realm of hundreds of universities, smaller organizations, and first-time commercial space research users.  Our U.S. National Lab facilities provide turnkey opportunities for your microgravity research. This currently includes:

  • Three NanoLab Platforms
  • NanoRacks Plate Reader
  • NanoRacks Microscope-3
  • BioRack-Centrifuge
  • NanoRacks MixStix.

Full Spectrum of Capabilities for Small Payloads:

NanoRacks provides everything you need to conduct repeatable microgravity research on the Space Station and soon, beyond.

  • 20 years of space program experience
  • Partnerships with payload integration organizations
  • Full service NASA safety system

Extensive Interaction/Experience with:

  • NASA Payloads Office
  • NASA Safety
  • NASA MOD
  • Interface Control
  • Document Generation
  • Full Service Verification Capabilities
  • Experts at minimizing verification waste

Techshot

by on 1 May 2015in Life Sciences, Physical Sciences, Technology Development

For more than 25 years, Techshot has been developing professional-grade space research equipment.

Analytical Containment Transfer Tool (ACT2)

Great for:

  • Safe doubly-contained sample transfers to orbit, from orbit, and between equipment in space
    • Freezable down to -80°C
    • Standard Luer connector

Advanced Space Experiment Processor (ADSEP)

Great for:

  • Cell culturing—includes the only space-based rotating wall bioreactor available
  • C. elegans research
  • Protein crystal growth
  • Your research with ~ 2,300 cc of volume, an empty cassette could be your blank canvas for whatever’s important to you. Multiple cassettes can be processed per mission.

Bone Densitometer – the Only DXA Scanner in Space

Great for:

  • Rodent research up to 30 grams
  • Fish and other animals

Multi-use Variable-gravity Platform (MVP) – Dual Centrifuges Simultaneously Providing 0-2g Each

Great for:

  • Cell culturing (adherent and suspended)
  • Drosophila
  • Plants
  • Fish
  • Custom Solutions

If you don’t see what you need here, let’s talk. Many more technologies for research in space are in various stages of development by Techshot.

Services

  • Turnkey professional spaceflight equipment development
  • Spaceflight integration services (your hardware or ours, we’ll get it up there)
  • On orbit experiment monitoring and management via our payload operations control center
  • Total mission management, we take care of everything for you