Colorado Space Grant Consortium DemoSat-B Colorado State University Matthew Jui, Ian Patterson, Mark Spowart, Todd Wallis July Colorado Space Grant Consortium DemoSat-B Colorado State University Matthew Jui, Ian Patterson, Mark Spowart, Todd Wallis July Launch Readiness Review 1

2 Mission Statement – The CO 2 measurement with respect to altitude system (CMAS) will accurately record carbon dioxide levels up to 80,000 feet. Mission Statement and Goals Objectives Payload will measure concentration of CO 2,RH, temperature and pressure at intermittent altitudes Payload will operate by itself for 200 minutes and take data for both ascent and descent Optional Objectives Payload will visually record weather conditions through an attached camera or video camera Topic Background Multiple organizations have conducted similar research but with different techniques. (sample from aircraft, and Space observation)

Benefits to NASA: The low cost, light weight carbon dioxide measuring system would give NASA a mobile way to accurately record atmospheric CO 2 levels with respect to altitude. 3

Design: The design features a low weight polyurethane shell that tightly houses central components Currently spent $ of the budget, and weight is at.91 kg 4 Diagram showcasing air flow through the system Picture showing actual structure with central components mounted inside

Expected Results: Due to the season during which launch will take place, we expect to see a nearly constant concentration of atmospheric carbon dioxide for the duration of our flight Due to the effects of pressure changes on our carbon dioxide measurement system, we have to use empirical calculations to correct for pressure changes, this will limit the validity of the data retrieved to between 70,000 to 80,000 feet 5 Graph highlighting the loss of coherent data with lowering pressure, data taken during a vacuum chamber test

Level of Readiness: 6 First different shell prototypes were tested using the given procedures. Polyurethane shells were filled with ballast until it weight 1.5kg.

7 Testing was continued in a vacuum chamber where a series of dwells were performed over what was deemed to be critical pressures, this was done so as to test both the circuitry in a vacuum as well as the validity of our empirical pressure correction

8 A bubble test was then performed to measure the flow rate of the pump, a flow rate of.3 SLPM was required for accurate carbon dioxide data

9 Picture showing the integration of flight chord tube, inlet air tube, and start switch

10 After a series of battery tests, it was found that the use of six 9 volt batteries would insure power for a 200 minute flight

11 Questions?