The Thermal Energy Storage Flight Experiment was designed to characterize void shape and location in LiF-based phase change materials in different energy storage configurations representative of advanced solar dynamic systems. Experiment goals and payload design are described in outline and graphic form

Namkoong, David

English

NASA Technical Reports Server

'-.. 
POWER TECHNOLOGY DIVISIO. I\V\SI\ 
AEROSPACE TECHNOLOGY DIRECTORATE 
l', 
.. 
The 
E 
o&-.al Energy S 
• erlme 
age F"· 
David Namkoong, Principal Investigator 
Andrew Szanis~A'" 
NASA Lewis Research Center 
• 10 
, 
~ (';' , 
,<~ 
-
,~ 
"tJ x. 1 , 
-~ 
Presented at the NASA / DOD Flight Experiments Technical Interchange 
Octnhfl!w- li.Q_ 1M2 ,.-
...... 
t,/\' 
" 
z 
CD 
W 
• 
I\) 
co 
;:j 
Q 
https://ntrs.nasa.gov/search.jsp?R=19930019531 2020-03-24T07:37:35+00:00Z
Heat Pipe Performance 
EXDerimen 
Flight Experiments Technical Interchange Meeting 
Sponsored b 
Space Technology Interdependency Group 
October 5-9, 1992 
Mo 
George Fleischman 
Hughes Airc 
.. 
'. 






i 
CRYOGENIC HEAT PIPE EXPERIMENT 
Y 93 PL 
• SUPPORT FLIGHT OPERATIONS 
• REDUCE FLIGHT DATA AND RESOLVE ANY ANOMALIES 
• PERFORM POST FLIGHT TESTS ON EXPERIMENT AND HEAT PIPES 
. 
• INCORPORATE RESULTS INTO GROOVE ANALYSIS P 
AND SUBMIT TO COSMIC 
• COMPLETE FINAL REPORT 
,~ 
CRYOGENIC. HEAT PIPE EXPERIMENT 
URRENT STATUS 
.• DELivERED TO KSC A~D INSTALLED ON S:;JTTLE 
. 
• FINAL INTERFACE VERIFICATION TEST COtv1PLETED 
• ALL DOCUMENTATION COMPLETE 
• LAUNC~ , ) l.'E ~N NOVEMBER 16, 199 
1' : - 'I 
'. 
! 
CR\TOHP INSTRUMENTATION 
TPE QUANTITY N 
Platinum Resistance 26 13 each heat pipe system 
Thermom ter (PRTs) 
Therm istors 24 UE , , pillars, 
heat pipe ructur , cryo-
coolers, I ctronic 
Thermistors 9 (HH) EBP, Cani ter, & CECM 
Mounting Brackets 
Pressure Transducers 1 Canister Internal Pressure 
Current Monitors 13 CECM 
Voltage Monitors 18 1 for bus voltage, 17 for 
temperature calibration 
Heaters (Kapton foil) 11 4 per heat p~pe ; 3 survival 
Thermostats 33 Tri-seri s circuit for each 
heater 
I 
I 
HAC HEAT P 
TEST 
LDOWN 
350~------~----~~----~----~--~--~----
50·~~~~~--~~~~--~----~~~--~~~ o 1 234 5 6 7 8 9 
TIME (HOURS) 
, 
/ 
HEAT INPUT WICK HEAT OUTPUT 
VAPOR FLOW 
---'Iloo.. '. 
I I 
EVAPORATOR LIQUID RETORN CONDENSER 
HEAT P]PE - CONCEPT 
'-. 
z 
o
 
-~ CI: LI.I a. o A. : o > CI: V • • u -~ ~ Y.I :c u '" 
,
 
-·s 
,,-
.
 
c 
c
-
~
­
_
e
o
; 
=-~ 
::--
::&
':--
..... 
-=
 
,
 .
 
E
-
.
.
.
 
c 
,
,=
 
~
~
 
E-rI.l 
J I I 
~I 
• 
ASCENT -
ORBIT 
CRYOHP OPERATIONS SCENARIO 
Vent to 2 PSIA 
Hitchhiker Avionics On 
Surviv~1 Heaters On 
Vent to 10-4 Torr or Less 
CRYOHP On 
Cooldown TRW Heat Pipe 
o Start Up . 
Cooldown 
o Transport/Recovery 
Cooldown 
I 
o Transport/Recovery/Minimum Temperature 
Cooldown Hughes Heat Pip 
Repeat 
Cooldown TRW Heat Pipe 
Repeat - Total Five Cycles Each Pipe 
CRYOHP Off 
Descent 
...... , 
" 
,:..--
.. 
.
 
.
 
CR O
HP 
-
F
l
.
 
CO
O
tER ARRA 
G
E
lfE
 T 
'. 
CRYOHP SUBSYSTEM IMPLEMENTATION 
r"'''' .... QQ[r 
---
Cryogenic Co ole rs 
,---
I~' -!._..:..... -1-' --L.I-=-~==C=_ -.. _~:l 
Ele(tronic Module 
.. 
...... -
Cryogenic Coo lerl 
Hea t Pioe Interlac 
Heat 
~ltm-
Bumper 
ssembl 
'. 
CRYOHP DESCRIPTION (cont.) 
• Heat Pipes 
Two Independent Designs 
ially Grooved Aluminum Extrusion '. 
• T 
• Hughes 
u 
tupfor 100 
• 
..... , 
CRYOHP DESCRIPTION 
o Shuttle/HH Carrier Flight Exoeriment ionics) Less Than 345 Ibs 
o HH Canister 
ified Upper End Plate (UEP) 
o Thermal Mas 
o Radiator 
o Flown on CPUGAS and CPL/HH-l 
Uninsulated Top Plus Sides 
Vented Can (Valves in Lower End Plate (LEP» 
16 Psia Prior to Launch 
2 Psia Differential Pressure Relief Valves on Ascent 
Solenoid and Butterfly Valves Provide FIiJtht Vacuum 
HH Avionics 
Provides Power, Signal, Command, and Data 
3 HH Ports ~equired 
....... , 
.. 
,. 
,I "-==:::- "::::: 
1oF== ~:=:::::::=~;;; 
CRYOGENIC HEAT PIPE EXPERIMENT 
OBJECTI\o, 
~ 
CONDUCT A SHUTTLE EXPERIMENT TO DEMONSTRATE THE 
RELIABLE OPERATION OF TWO OXYGEN HEAT PIPES 
MICROGRAV.-ry . 
L 
1. DEMCt\,:,rRATE STARTUP OF THE' PIPES FROM THE SUPER-
CRr. :dAL STATE. 
2. MEASURE THE HEAT TRANSPORT CAPACITY OF THE PIPES 
3. MEASURE EVAPORATOR AND CONDENSER FILM COEFFICIENTS 
4. WORK SHUTTLE SAFETY ISSUES 
APPROACH 
../ FLY T'NO AXIALLY GROOVED OXYGEN HEAT r ~ IPES ATTACHED 
TO MECHANICAL STIRLING CYCLE TACTICAL COOLERS 
../ 'NT cf3RATE EXPERIMENT IN HITCHH'IKER CANISTER 
../ FLY ON SHUTTLE AND CONTROL FROM GROUND 
....... , 
..... -
.;-
'. 
,I 
CRYOGENIC HEAT PIPE EXPERIMENT 
ACKGRO 
• NO MICRO-GRAVITY DATA AVAILABLE FOR OXYGEN" OR NITROGEN 
HEAT P"IPES 
• POOR WICKING AI\O LOW TRANSPORT MAKE O-G EXTRAPOLATION 
DIFFICULT 
• RELIABLE START UP FROM SUPER CRITICAL TEMPERATURE 
NEEDS TO BE DEMONSTRATED 
• MICRO-GRAVITY INFORMATION ON CRYO «100 K) HEA7 PIPES 
IDENTIFIED AS CRITICAL TECHNOLOGY NEED BY NASA AND THE 
AIR FORCE - 1988 THERMAL FLUIDS IN SPACE WORKSHOP AND 
IN STEP 88 WORKSHOP 
• OXYGEN AND NITROGEN PIPES BUILT AND EVALUATED 
./ 
I 
J 
I' -:=.=: ::- _.- 'I 
'-
'. 
" ~I.I flUWI:H ,t=(;ffIVULUb' u,.,"/:SIUIV 
AEROSPACE TECHNOLOGY DIRECTORATE 
TES FLIGHT SCHEDULE 
ACTIVITIES 
91 
MAJOR MILESTONES 
* ~, Ah. I NON ADVOCATE REVIEW ____________ J 
I 
I FUGHT EXPERIMENT REVIEW _ _ _ _ _ _ _ _ _ _ _ _ J 
1 PREUMINARY DESIGN REVIEW _ _ _ _ _ _ _ _ _ _ _ _ _ J 
1 
FINAL PROTOFUGHT PAYLOAD DESIGN REVIEW - - _ _ - - - - - - - - - - j 
I 
PRE-SHIP REVIEW ____________________ _ _____ I 
UNCH J 
....... , 
~LU4,pm-2 


Thermal Energy Storage Flight Experiment in Microgravity

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server