EHD PUMP Conceptual Design Review University of Nebraska - Lincoln NASA Goddard Space Flight Center

Transcription

1 EHD PUMP Conceptual Design Review University of Nebraska - Lincoln NASA Goddard Space Flight Center

2 Mission Overview Experiment goals Theories of Operation Concept of Operation Experiment Application Past Research Mission Requirements Expected Results

3 Mission Overview Experiment Goals: Effects of micro gravity on interaction of flow fields and electrical fields with and without phase change Effects of micro gravity on electrically driven film boiling Validate concept for space station execution applications. Applications EHD pump for onboard processors EHD pumps for micro and nano scales High heat flux thermal control Multifunctional plates Design Concept

4 Thin Film Evaporation Concept: Minimum Success: Demonstration of EHD Thin Film Liquid Pumping Investigate the effects of gravity on the net electrically generated two phase flow The effects of gravity on electrically driven film boiling Convective boiling heat transfer coefficient in low mass flux levels in the absence of gravity

5 Theories of Operation EHD Force Components Electrophoretic: charge generation by electro-chemical reaction Liquid Pumping Function of electric field, temperature & fluid quality Di-electrophoretic: take advantage of permittivity gradients,e.g, two phase flow. Phase & Fluid Management Thin Film Evaporation Electrostriction: Compressible Flow

6 EHD Electrophoretic Force Generation Asymmetric Geometry leads to higher pressure head: configuration is impractical for spacecraft applications

7 Concepts of Operation Flight Trajectory Acceleration Profile Experiment Operation during Microgravity

8 Experiment Application Breadboard EHD Thermal Control System Thermal Control using liquid thin film evaporation Fluid Management to address hot spots EHD as integrated and embedded subsystem for processor design application of NASA HQ Fluid physics Investigation Technology Development Goal: Electronic Component Thermal Stability to improve reliability & component operational lifetime

9 Past Research

10 Mission Requirements Design based upon laboratory test system ( Slide 3) Power Requirements: ~10W from batteries High Voltage for EHD operation; current <1mA Data Measurements: 20 channels Temperature (Platinum resistors on surface of test article) System Pressure

11 Design Overview Structural Overview Electrical Overview Block Diagrams Payload Layout User Guidelines Compliance

12 Structure Overview Payload consists of three (3) section EHD section Controls and data log section Power and reservoir section Platinum heaters located under EHD pump (slide 3) Silicon wafer over EHD pump for containment; thickness <1mm Damping system for EHD section Reservoir for dielectric fluid

13 Electrical Overview Electrical systems initiated by G-switch upon launch EHD requires HV but current <1mA Controls section requires power for data storage and experiment activation Sensors through all sections will gather data; i.e XYZ Accelerometer, thermo coupler for system and experiment temperature, stress and vibration sensors on damping section

14 Electrical Block Diagram

15 Payload Layout Battery Reservoir Power Management Controls Data Logger EHD Experiment

16 RockSat-C Users Guidelines Compliance EHD Based Thermal Control Experiment will take up a full canister Usable space = 9.3 Dia. X 9.5 H Center of Gravity Payload must conform to a COG that lies within a 1x1x1 inch envelope of the geometric centroid of the integrated canister Approx. weight <10 lb w/o bulkhead screws Total canister weight = 20±0.2 lb Modifications to canister are prohibited Must pass vibration tests

17 Management Schedule Team Organization Faculty/Industry Mentors

18 Schedule Date 10/05/2012 Conceptual Design Review (CoDR) Due 10/17/2012 Online Progress Report 1 Due 10/26/2012 Preliminary Design Review (PDR) Due 11/9/2012 Online Progress Report 2 Due 11/(16 or 30)/2012 Critical Design Review (CDR) Due 1/18/2013 Final Down Select Flights Awarded 1/25/2013 Online Progress Report 3 Due 2/15/2013 Individual Subsystem Testing Reports Due 3/12/2013 Online Progress Report 2 Due 3/29/2013 Payload Subsystem Integration and Testing Report Due 4/15/2013 RockSat Payload Canisters sent to customers 4/26/2013 First Full Mission Simulation Test Report Presentation Due 6/3/2013 Launch Readiness Review Presentations 6/12/2013 Travel to Wallops Flight Facility 6/(14-18)/2013 Integration/Vibration at Wallops 6/20/2013 Launch Day Team meetings will be held twice a week for the duration of the design phase Meetings with GSFC will be every week for the duration of the design phase Progress reports from each subgroup requested at the end of every week.

19 Team Organization

20 Faculty/Industry Mentors Kevin D Cole, PhD UNL AIAA Student Chapter Advisor since 2008 Research on anemometers, fluid plow sensors, hotfilm resistors and properties of thermal protective systems NASA USLI and Lunabotics team advisor Jeff Didion Senior Thermal Engineer Manager, MSD Nanotechnology facility (GSFC) Matt Showalter Associate Branch Head of the Advance Manufacturing Branch (GSFC)

21 QUESTIONS?