1 / 13

Integrated Carbon Dioxide and Moisture Removal System for NASA's ECLSS

The Integrated Carbon Dioxide and Moisture Removal System (CMRS), led by Dennis Arnold, is designed for NASA's Exploration Life Support System (ECLSS). This innovative air filtering device operates in spacecraft environments by efficiently removing carbon dioxide, moisture, ammonia, and heat, ensuring a breathable atmosphere for astronauts. Evolving from past systems like those used in the Apollo Command Module and ISS, CMRS incorporates advanced amine chemical formulations to enhance efficiency, minimize power requirements, and eliminate the need for backup lithium hydroxide canisters. Future development focuses on optimizing design and manufacturing processes.

newton
Télécharger la présentation

Integrated Carbon Dioxide and Moisture Removal System for NASA's ECLSS

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Coeus Engineering Integrated Carbon Dioxide/Moisture Removal System for NASA-ECLSS

  2. Dennis Arnold - Team Leader, Research Jessica Badger - Coordinator, Research Julia Thompson - Research April Snowden - Research Team Organization

  3. What is a Carbon Dioxide/Moisture Removal System? • Air filtering device used in spacecraft environments • Removes carbon dioxide, moisture, ammonia, and heat from the air • Maintains breathable atmosphere

  4. Past Carbon Dioxide Removal Systems • Apollo Command Module • Shuttle • Shuttle EDO • ISS • CRV

  5. Apollo Command Module • Used heat exchanger with fine capillary wick for water removal • Used LiOH canisters for CO2 removal • Extensive ground support needed for launch • Not a good design for long duration missions

  6. Shuttle • Used condensing heat exchanger (CHX) and rotary gas separator to remove water and heat • Needed LiOH canisters to provide CO2 removal • Needed antibacterial coating on CHX

  7. Shuttle EDO • Uses CHX to remove water • Uses RCRS to remove CO2 • Requires large bed to meet removal requirements • Needs fan, and an air save compressor • Needs extra LiOH canisters

  8. ISS • Uses CHX to remove water to a waste water recovery system • Thermally regenerated molecular sieve removes CO2 • Two beds • 30 min cycle time • Requires too much power (800 W compared to 140 W) • CHX biofouling problem (mold) • Backup LiOH canisters required

  9. CRV • Calcium Oxide canisters for water removal • LiOH canisters for CO2 removal • Non-condensing heat exchanger • Removes heat only • Long storage life • Short usage time

  10. Proposed Space Launch Initiative (SLI) System • CO2 and water removal performed by newly developed amine chemical formulations • No CHX required • No rotary gas/ liquid separator required • Vastly improved efficiency • No backup LiOH canisters required • Absorbent beds are smaller, thus cycle times are longer

  11. Our Primary Focus • CO2 & Moisture Removal System (CMRS) Bed Design • Heat transfer • Mass transfer • Pressure drop • Surface area for chemical support • Manufacturing ease • Mechanical reliability

  12. Future Plans • Meet with John Graf • Obtain RCRS assembly drawings • Obtain absorption rates of water and CO2 for new chemical • Obtain manufacturing requirements and tolerances • Develop computer model of heat transfer and mass flow rates through bed

  13. Questions? • Preguntas? • Questionne? • Bопрос? • Kwestie? • Ninau? • Swali? • Spørsmål? • Förhöra?

More Related