PSU NASA TeamFinal Report

Chris ChurchillChantelle Hansen

Nathan JoyMatthew Thomas

Faculty Advisors:Dr. Graig Spolek

Dr. Mark Weislogel

Presentation Overview

• Mission Statement• Design Process• PDS Summary• Final Design Summary• Summary

Mission StatementTo test the effects on flow regimes and rivulet

coalescence of noncircular cross-section conduits in microgravity by varying the interior corner and testing them across a range of air to water ratios.

Design ProcessInitial Concept

Schematic for low-g apparatus.

Project Design Specification Summary

• Performance: Equivalent hydraulic diameter and flow rates to previous research.

• Environment: Function in micro-g environment and withstand up to 2 g’s.

• Installation: Experiment is electrically & mechanically compatible with the aircraft.

• Safety/reliability: Have safety factor greater than 2.• External Constraints: Satisfy requirements for PSU

Capstone Project and NASA.• Timelines: Low-g rig completed and shipped to

Houston by June 3rd.

Final Design Summary: Performance

To prove that the flow rates are the same as Barajas:Water flow• Linear syringe pump provides a known constant

flowAir Flow• Hot film anemometer mounted

in a pipe to measure air velocitiesfrom 1 m/s to 50 m/s.

Final Design Summary: Performance

Rivulet Flow

Slug Flow

Plug Flow

Final Design Summary Environment

Structural analysis was performed on all components to verify the low-g rig can withstand up t0 2 g’s

Final Design Summary Installation

Cargo tie-down straps are used to ensure mechanical compatibility.

Experiment is electrically compatible. Power Source Load Analysis

System Wire Number

Wire Gauge Nominal Current Draw

Maximum Current Draw

Name Power Source A Light Source 1 18 AWG 1.8A 1.8A

Voltage 115V, 60Hz Single Phase

Camera 2 18 AWG 1.0A 1.0A

Wire Gauge 12 AWG 12-V DC Power Supply

3 18 AWG 0.5A 1.5A

Max. Current 20A Syringe Pump 4 18 AWG 0.5A 1.0A

Computer 5 18 AWG 1.7A 1.7A

Air Pump 6 18 AWG 1.6A 1.6A

Total 7.1A 7.1A

Maximum Current Draw 7.1A

Final Design Summary Safety/reliability:

Ensure all components have a safety factor greater than 2.

Verify that enclosure can withstand up to 9 g’s.

Final Design Summary Timeline

Final Design Summary

Prototype Model

Final Design SummaryCompleted Prototype

Final Design SummaryCompleted Prototype

Summary

All requirements set by NASA and PSU have or will be met.

All construction of the apparatus is complete and ready for shipment to Houston.

Trials of the apparatus in 1-g indicate that the low-g tests should produce good flow results.

In one week, we will verify whether the NASA low-g aircraft will live up to its moniker.

Questions?