Re0rientatio

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John I. Hochstein and Alfredo E. PatagWaskinstoe, Seate University in St. LouisSt. Louis, Missouri

and

David J. Chato

Lewis Research Center

Cleveland, Ohio

Prepared for the

27th Aerospace Sciences Meetingsponsored by the American Institute of AeromMics and Ammmutics

Reno, Nevada, January 9-12, 1989

g_

'Iii

MODELING OF IMPULSIVE PROPELLANT REORIENTATION

John I. Hochstein" and Alfredo E. Patag*

Washington University in St. Louis

Mechanical Engineering DepartmentSt. Louis, Missouri 63]30

and

David ,]. ChatoNational Aeronautics and Space Administration

Lewis Research CenterCleveland, Ohio 44135

LO

!

L_J

ABSTRArT

The impulsive propellant reorientation process is modeled using theECLIPSE Code. A brief description of the process and the computational model

is presented. Code validation is documentated via comparison to experimen-

tally derived data for small-scale tanks. Predictions of reorientation per-

formance are presented for two tanks designed For use in flight experiments

and for a proposed full-scale OTV tank. A new dimensionless parameter is

developed to correlate reorientation performance in geometrically similartanks. Its success is demonstrated.

INTRODUCTION

The ECLIPSE Code, (Energy Calculations for Liquid Propellants in a Space

Environment), is being developed as one component of the reduced gravity fluidmanagement technology program being conducted by the NASA Lewis Research Cen-

ter (ref. l). The long range goal of a general too] For computational model-

ing of liquid propellant behavior in a reduced gravity environment is beingpursued by stages with each stage corresponding to a problem of current inter-

est to designers of advanced spacecraft. The _bi]ity of ECLIPSE to model jet_nduced mixing in propellant tanks (refs. 2 and 3) and p_ope]lant tank self-

pressurization (ref. 4) has been documented. The Focus of the work beingreported in this paper it the modeling of liquid motion induced by a suddenchange in the acceleration environment.

During coast in Low-Earth-Orbit (LEO), liquid propellants can collect invarious regions of the propellant tank due to atmospneric drag on the space-craft. The process of positioning the liquid ©uer the tank outlet by Firingauxl]iary thrusters is Known as impulsive reorientation or settling. Sinceimpulsive reorientation requires the ewpenditure of propellant, it is impor-tant to optimize the process to minimize the associated propellant require-ments. If the thrust level is too low, the propellant may not ,eposition.it is too high, a large geyser may Form and vapor pockets may be trapped inthe pool. Proper spacecraft design and operation requires a good understand-ing of the process and the parameters which control it.

If

"Work funded by NASA Grant NAG3-578.

Small-scale experiments have been performed in the NASALewis Research Cen-ter drop tower and in the Zero-Gravity Facility to examine liquid motioninduced by accelerations which model the reorientation process. The experi-ments were performed in transparent tanks and the fluid motion induced bythese accelerations was recorded via high-speed photography. These experi-ments identified liquid-vapor interface shapes for a zero-g environment(ref. 5) and records of fluid motion induced in partially filled tanks due toan imposedacceleration were produced (ref. 6), Further studies conducted byI. Sumner(ref. 7) examined the energy expendedto accomplish reorientation.A performance mapfor the reorientation process in these small-scale tanks wasdeveloped. This reference provides substantial detail for a numberof acceler-ation levels and tank fillings and the results reported in this reference haveserved as the basis for code validation.

Prediction of reorientation performance has relied on two tools. The sim-plest is a rigid body dynamics analysis which assumesthe propellant pool tobehaveas a single solid body (ref. 8). Although this analysis is simple toperform, it is such a coarse assumption that large safety factors must be pro-vided when it is used for design purposes. The second tool is described by I.Sumner(ref. 7) and is based on an empirical analysis developed by J. Salzman(ref. 9). The computational procedure is an empirically based approach usinga Neber numbercriteria to preclude geysering and results in calculation of aliquid leading edge velocity. I. Sumner(ref. 7) extended the analysis toinclude small geysers. Although predictions based on this method correlatedwell with reported experimental results, it does not start From first princi-ples and its application is limited to similar geometries and conditions.

a

Bo

F

Fr

g

h

h*

P

R

Re

Se

NOMENCLATURE

acceleration

Bond number

volume-of-fluid function

Frc,Jde number

body force per unit mass, typically gravitational

length dimension, typically tank length

nondimensionalized length

pressure

tank radius

Reynolds number

settling number

t,T time

L

i

u,v x and y velocity components respectively

vf velocity of liquid leading edge

x,y spatial coordinates, cartesian or axisymmetric x in radial direction)

e fractional cell volume open to flow

W dynamic viscosity

kinematic viscosity

switching integer

p density

surface tension

ECLIPSE CODE

The ECLIPSE Code is a descendant of the family of SOLA Codes written at

the Los Alamos Nationa] Laborato,'y. In particula, the N_C_-VOF2D Code (ref.10) was used as the foundation upon which ECLIPSE is being suilt. The base-line code solves the laminar hydrodynamic problem using the Volume-Of-Fluid,(VOF), algorithm to determine the location of the free surface. The computa-tional mode] uses a VOF function, F, to track the free surface, and a cellblockage function, @, to mode] pavtia] cei] DIockage. Equations e×pressingconservation of mass, the force-momentum balance, and the F--transport equationcan be written:

: 0 {])

au au 8u 1 aPaT* vG : g, - ; a,

02 ?u :}-u 1 ;3u,v T* -T*_ -- (2)

8v av L]v 1 OlD ._-at * u_jx + V_iy _y o Oy v _ &,, /'l_ av.-- = * * --_-. _ 8;) (3)

.}_)- .)yC ',,- J

:I

}F ;)F ;}F.}-{ * u,j7 * ',..... ' (4)

The equations are d ;;cretized ,_sing fin_te-.Ji_feTence o,ocedures appliedto a staggered grid with velo<itie; defined _t the cell faces and pre._%ure atthe cell center. The "_,)L'A algorithm is :,':,ed t-; :ha,,-.," *he s)lution througntime. The '/OF algo,,ithm ]i useq t_ ,let_,m qe b, th the, ":,CatiOf tnd the ]')Ca',

radius of curvature {:,f *he FTee ,Lit fat_ "h_ ' I _ r ' 1 t _[ '_ i S then Jsed to L)m-pute an appropriate %urFace teq';ior_ to ,p which is _:nlD,'J:Sed,?n tPe fie:d a; Jqeqijilalent pressure. The ;ol,,tion ,aalICrie,; tqFC, L;r_h t;lle artd an a_ltomat'cstela-size adjustment !imited by staLilit i c,ite, ia i: D"nviJed (iJetai's S F t_estability criteria used in ECLIPSE can be _O,Jnd iq ,el ll).

3

Although many features such as heat transfer and thermodynamic models have

been added during the development of ECLIPSE, only minor modifications to the

baseline code were required to study impulsive reorientation. The routine

which provides an initia! 1ow-g fluid configuration has been modified so that

the liquid can be positioned at either end of the tank. A set of variableshave been incorporated to impose a time dependent acceleration environment on

the fluid in the tank. The ability to terminate execution based on a criteria

for completion of reorientation has been incorporated into the code, Finally,

additional output options have been added to enhance the tracking of variables

of specific interest to the study of the reorientation process.

CODE VALIDATION

Six cases were selected from I. Sumner (ref. 7) to serve as verification

that ECLIPSE accurately models the impulsive reorientation process. A summaryof the test conditions is presented in table I. The fineness ratio, FR, is

the ratio of tank axial length to tank radius. The percentage of the tank

occupied by liquid is recorded in the column labeled FL. TCTFE is trichloro-trifluoroethane, R is the tank. radius, and the balance of the variables are

self e×p]anatory. These cases were selected to provide a range of geyser

formation from large to nonobtervable.

A typical computational mesh used to model these cases is presented in fig-

ure I. The liquid is shown at the top of the tank in a zero-g configuration.The mesh has been refined near the maximum tank radius (i.e., tank wall) in

order to assure a smooth transition of the flow from the barrel tecticn into

ti,e head. Although all figures presented in this report show a full cross-

section through the tank, the code solves the problem ]n cylindrical coordi-

nates the settling acceleration and resulting flow is axisymmetric. Therefore,

only half the number of cells depicted are required to perform the

computations.

A sequence of flow fields computed for the conditions specified for Test S

is displayed in figure 2. A compar]son between computational prediction and

experimental observation of geyser tip location as a function of time is pre-

sented in figure 3. ECLIPSE predicts formation of a geyser with a maximum

height of 3.2 cm wh£reas I. Sumner- (ref. 7)reports a maximum geyser height of3.3 cm. ECLIPSE predicts dissipation of the geyser into the rising free sur-

Face at a0proximately 1.05 sec wherea I. Sumner (reg. 7) reports this event

at approximately l.!O sec. A compari

experimental observation of geyser ti

1 is shown in figure 4. A. Pata] _re

herein, presents comparison_ between

table [ and the computational predict

was o0tained with a single e,,zeotion

on between computational p;edictien andlocation as a fjnction of time for" Test

12_ in _is thesis on the work presented

he data from *he experiment listed in

_ns. It: gene,-al, reasonable agreeme.nt

The paran_ete"] _ecified for Test 8 corn-

bine to induce large lead_ng edge ve ccities as the 'i.quid moves a;ong the

tank wail_. At geyser inception at the bottom r,f tr, e tank., the free surfacemodel in ECLIPSE fails to trac_ :or,e:tl, the f-_r,na'{on of ] pool and the ini-

tial growth of the gey:e,. Comlo,Jted -_l)w #ields for Test 8 are shcwn in fig-ure 5. It should be ncted that "he _inetic ere,g7 ;mpa, ted to the liquid iS

hign. AS ;uch, _t iS highly irle_ficierlt and w©uld requi,-e an e_cessi,,e e_pen-ditu:e of propellant to produce these c.mditiof, s in a ,ea _ spacecraft. Since

the current study is fo<u;ed on )ptimization _.:f the ,eorientation process, tne

Inability of ECLIPSE to successfully model Test 8 is not viewed as a signifi-

cant handicap.

Based on the evidence presented in the preceding paragraphs, it was con-

cluded that ECLIPSE is a suitable tool for modeling pulsed settling.

SCALE MODEL OTV TANKS

One component of the NASA Lewis reduced gravity fluid management technology

program is deve|opment of a flight experiment to examine a variety of fluidmanagement issues. When the computational modeling effort was initiated, this

experiment was known as the Cryogenic Fluid Management Facility (ref. I),

(CFMF), but has since been renamed the Cryogenic On-Orbit Liquid Depot, Stor-

age, Acquisition and Transfer Satellite (ref. 13), (COLD-SAT). The original

design used a O.25-scale model of a propellant tank proposed by Boeing for a

space based Orbit Transfer Vehicle, (OTV). This tank was selected as a proto-

type for studying the effect of acceleration level on reorientation perform-

ance. The design of the experiment relied or_ two Shuttle Reaction ControlSystem (RCS) thrusters to provide an acceleration environment of 7.85 cm/s2,

(8xlO-3g).

For the code validation phase, the investigator reviewed graphical dis-

plays of the flow field evolution and judged settling to be achieved when asufficient quantity of liquid had collected into a oooI at the "bottom" of the

tanK. To eliminate the subjective nature of this evaluation, a measurable

parameter was defined. Since the depth of the pool at the tank centerline canbe tracked as the flow field evolves, the liquid is considered settled when

this depth exceeds 20 percent of the total tank length. The settling time is

defined as the elapsed time between initiation of thrust and satisfaction of

this criterion. Although a few apparently anomalc__Js:ettling times were Dre-dicted at the lower thrust levels, the settling crite,ion worked well For the

majority of cases.

Figure 6 shows the shape and dimensions of the 0.25 tank as well as the

computational mesh used to analyze the propellant motion within it. The analy-

ses were performed for a tank 50 percent Full of liquid hydrogen with a]l of

the propellant initiallj collected at the top of the tank. Figure 6 shows the

corresponding shape of the initial free surface. Figure 7 displa2s a sequenceof flow fields which occur during the reorientation process with a 8_IO- g set-

tling force. The liquid leading edge moves rapidly towards the bottom of the

tank. A large geyser forms within 8 sec of thrust initiation. The geyser isso severe that the liquid rebounds from the top of the tank befoTe collecting

into a pool after app,owimately 16 sec has elapsed. The liquid motion hasbeen solviolent significant vapor pockets have been encapsulated in the Pool.

[f this process occurred in a real propulsion application, it might be nec-

essary to extend the thruster Firing period to ins.J,e that the vapor pocketsare expelled From the pool before the main rocket is started.

I. Sumner's rrDort indicates that optimal ,eorientation For the 0.25 tanwshould occur for an acce]era_on level of app,c,imately 3.5K10 -3 cm/s 2,

(3.7(IO-5g). This levei is predicted to be op*imal in the sense that it _ini-

mlzes expenditure of propellant. Figure 8 p,e.sents a seq,J?nce of Flow Fields

corresponding to this acceleration level. The liquid movessmoothly towardthe bottom of the tank collecting into a sizeable pool within 1.5 min. A mod-erate geyser was Formedbut fewer vapor pockets were trapped within the pool.After approximately 3 min, almost all of the liquid has collected in the bot-tom of the tank. I. Sumner(ref. 7) proposed that the reorientation processbe judged complete wheneither the geyser settles back into the pool or theliquid film has cleared the tank wall. The propellant expenditure to accom-plish reorientation is roughly proportional to the vehicle delta-v incurredduring reorentation. The value to delta-v is easily computedby multiplyingthe specified acceleration by the elapsed time required to accomplish reorien-tation. Using the RCSthrusters results in a vehicle delta-v of ]25 cm/swhereas the optimal acceleration level corresponds to a delta-v of 6.5 cm/s, afuel savings factor of almost 20:1.

As the design of COLD-SATevolved, the tank scale and shape were changedto more accurately emulate current ©TV design concepts and to minimize tankthermal mass. The resulting tank geometry is presented in figure 9. This isa O.215-scale n_)del of a tank known as the Boeing Short SB OTV. Analysestherefore shifted to this new tank using the computational meshshownin fig-ure 9. Acceleration environments between2×]O-b and I cm/s2 were studied fora tank 50 percent full of liquid hydrogen. Figure lO presents a sequenceofflow field depicting the reorientation process for an imposedacceleration of3.92xi0 -2 cm/s2, (4.OOx]O5g). Settling time and vehicle delta-v werefocused upon as the key parameters representing settling performance.

Settling time is of obvious interest for the scheduling of orbital maneu-vers. Vehicle de]ta-v is used as measureof efficiency since it is directlycorrelated to the propellant expenditure. Figure l] displays the relationshippredicted between settling time and acceleration leve; The anomolousset-tling times encountered at someof the lower accelerations have not yet beenfully investigated, but are believed to be a resonance Detweenthe accelera-tion level and the geyser rise velocity. A somewhatarbitrary settlina crite-ria was useo in this study and mayalso contribute to anomoloussettlingtimes. Figure 12 displays the re]ation._hip between vehicle delta-v and accel-eration level.

FULL-SCALEOTVTANK

Upon completion of the small-scale tank _alyses, attention was focused on

a full-scale Boeing Short SB OTV. Modeling o,- the reorientation processes inthis tank covered a range of acceleration environments from 1.57xio -4 cm/s2

(l.6OxlO-7g) to 7.85xi0 -I cm/s 2 (8.OOxlO -_ g) and included tanks 25, 50, and

75 percent Filled with liquid hyorogen. The same mesh was used For these

analyses as was used for the scale model of the same shape. Figure 13 showc a

sequence of velocity fields predicted For a 75 percent Full tank subject to animposed acceleration environment of 1.96xlo -2 cm/s 2 (_.OOxlO -5 g). Figures 14

to 16 display the relationship between settling time and acceleration levelFor the three fill levels. Again, anomolies are encountered at the lower

accelerations. Figures 17 to 19 display the relationship between vehicle

delta-v and acceleration levei the trends are not surprising, but ECLIPSE

now provides a Far more accurate tool for trading settling time versus propel-lant expenditure than was oreviously available.

DIMENSIONLESS SCALING OF REORIENTATION

Since ECLIPSE provides a tool capable of modeling the reorientation proc-ess in both scale model tanks and full-scale tanks, it became possible to

search for a dimensionless parameter capable of scaling experimental results

from small-scale tanks to full-scale spacecraft tanks. In particular, theresults for the scale model Boeing SB OTV tank and for the fu11-scale tank

were used as the basis for this investigation. Following the investigators,the first attempt at correlation used the Bond number based on tank diameter

as the scaling parameter. The data did not collapse using this scalingparameter.

Various combinations of what were thought to be the relevant dimensionless

variables (Bo, Ne, Fr, Re) were tried. The most successful attempt at corre-

lating delta-V was a nondimensional grouping this paper defines as settlingnumber.

1/2Se : _(Ra> = Settling Number (5)

0

The Settling Number can be written as a function of 'sore recognized dimen-sionless parameters

!/2Se = (BoNe)

Nhen viewed in this light, it is seen as re_resenting the ratio of viscous andgravitational forces to surface tension forces.

The proof of a proposed ccrlelating parameter ]s in tr, e viewing the"_sults. Figure 20 shows the relation_ili0 between vehicle de!ta-_ and Se for

e Boeing Silort $80TV _ith a t.qnk ill!ling )f 5,) se, cent. A s!ng!e straight

line passes through all 24 data point_, br,_.ort._natel/, the ana;/ses Derformed

for the scale model tan_ included only a few cases with 25 and 75 percent fill-

ings. Although these analyses alto cgrre!a..te into a straight l_ne, they are

too few to claim as support For the correla*_in_ parameter. They are howeverdistinctly different lines from each other and groin the 50 Derceet case.

Therefore, it appears tqat Se is a suitable cot<elating !0ararqete,- for relating

reorientation performanle from sma!l-scale __9 ful!-scale geometrically similartanks, containing the s,_me fluid and with the ;._me vo]ume Fract!on of liquid.

SUMMAR{ OF _ESULTS

The ECLZPSE Code has been used to mode I the process of :.mOu:sive reorienta-

tion. The accuracy of :OmpL_tatiortal prediction'_ was eva',bated o/ com!0a,-isonto e.perimentallv obtained data for weqrienrat in in smal-sca_e tanks _ith

shapes tyP]cal of space:r-aft _rope!lant t:_nk; The model correctl 7 o,eJ]cted

the extent of geyser fsmatiof and the elap,,ed time reclL_ired to _lccomD]iSn set-

tling. Based on the cynlaa, iq.:r';, ECI [PSi: wa; ,Jdge:J t:> be a su_tao]e tool for

studying impulsive ,eo, ientati::m in c,/,?gen!< r..,.)i)e 1 ant tarl, s.

replaced with one producing an optimal acceleration environment, propellantexpenditure could be red,Jced by a factor of almost 20. For the other tank arange of acceleration environments was investigated and a summary of theresults is reported.

Reorientation in a fu|l-scale OTV tank was modeled for three different

tank fillings across a range of acceleration environments. A summary of theresults for these cases is presented.

A dimensionless parameter called the Settling number, Se, is proposed forcorrelating the reorientation process between geometrically similar tanks withthe same liquid volume fraction. To test the proposed parameter, computationalpredictions of vehicle delta-v acquired during settling for- a full-scale space-craft tank and for a 0.2!5-scale model were plotted against Se. All datapoints fall into a single ;tralght line, supporting the validity of Se as theappropriate correlating parameter.

.

°

.

,

.

.

.

,

.

REFERENCES

Aydelott, J.C., Carney, M.,]. and Hochstein, ].[., "NASA Lewis ResearchCenter Low-Gravity _luid Management Technology Program," NASA TM-87!45,]985.

Hochstein, O.I., Gerhart, P.M. and Aydelott, ].C., "Computational Modelingof Jet Induced Mixing of Cryogenic Propellants in Low-G " NASA TM-837031984. ' '

Hochstein, J.[., ,]i, H.C. and Aydelott, ].C., 'Temperature Fields Due toJet Induced Mixing in a typical OTV rank," AIAA Paper 87-2017, June 1987.

Hochste]n, J.[., ]i H.C.. and _ydel,:_>t:, ].C., "Effect of Subcooling onthe On-Orbit Pressu, ization Rate of Cryogen c Propellant Tankage," AIAAPaper 86-1253, June 1986.

Masica, N.J., Derdul, .].D. and Petrash D.A., "Hydrostatic Stability ofthe Liquid-Vapor Interface in 4 Low-Acceleration rield " NASA TN D-24441964. ' '

Nasica, N..J. and Sa;zrnan, ].A., "An E<perimental Investigation of theDynamic Behavior o£ the Liquid-Vapo,- Interface Under AdverseLow-Gravitational Conditions," Fluid Mecnan!cs and Heat Transfer UnderLow-Gravit_,_, Lockheed, Palo Alto, CA, 1965, pp. 2-! to 2-18.

Sumner, I.E., "Liquid Propellant Reor;entatior) [n _ Low C) a,_ityEnvironment," NASA rM-78969, 1918.

Dalzell, J.,F., "Special Topics. Part [. Liquid Impact on TankBulkheads,' _.TheD'njn_..... c: .......Behavi_, of Liq_,.kids in............Movinj Containers, H.N.Abramson, ed., q_ _P-;!)6, 1966, p_) _53-372.

Salzman, .].A. an(_ _t,:r_. N.J., "[,perimeq'al Investigation of LiquidPropel lant Reorie,,-ati,_n,' N_.5_ TM _'- '._;S:_. I')6l

lO. Torrey, M.D., Cloutman, L.D., Mjolsness, R.C. and Hirt, C.N.,

"NASA-VOF2D' A Computer Program for Incompressible Flows with Free

Surfaces," Los Alamos National Laboratory Report, LA-IO612-MS, Dec. 1985.

If. Hochstein, J.I., "Computational Modelling of Jet induced Mixing inCryoQenic Propellant Tanks in Low-G," Doctoral Dissertation submitted to

the University of Akron, Akron, Ohio, May 1984.

.2. Patag, A.E., "Pulsed Settling For Low-Gravity Liquid Propellant

Reorientation," Masters Thesis submitted to Washington University,St. Louis, Missouri, May 1988.

13. Kroeger, E.W., "Cryogenic Fluid Management Program Flight Concept

DeFinition," Proceedings of Cryogenic Fluid Manaqemert Technolo_o_g.y_Norksho_, Vol. I, NASA CP I0001, 1987.

TABLE I. - I.E. SUMNER'S TEST CONDITIONS MODELED USI_G ECLIPSE

Test

l567

12

R, FR FluidCm

1.65 4.00 TCTFE2.00 2.25 Ethanol

2.00 2.25 Ethanol2.00 2.25 Methanol2.00 2.25 Methanol3.22 2.14 Ethanol

FL,percent

71622951

71l

acm/,

I6 729 42g 429 ,_2q108

Bo I Geyser2I

,

_.,) I Small4.2 I S_nall

4.2 Large4.1 Moderate

Large_,oneI

, i

V

ORIGINAL PA,GE I$

,OF. pOOR Q,,;At,IT3F

%x

i

l I I 12.0 10 0 1.0

X AXIS. x 10 o

f l(iURt I. IYPICAI £ORPUIAIIONAI Ri',;H fOR _,RAIt

S(AL f i) TAN_S.

J

_.,,,,

10

, i

9.0

I

6.8

2.3

o--x

_. 9.0

4.s

2.'_ --

0

ORIGINAL PAGE IS

,OF.POO_ QUALITY

...... , ....... _l, ii, .......

.... : ii? ........

(a)SCALIN(,VELOCITYVECTOR, (b)SCAtIN(,VELOCITYVICTOR,0.218CM/SEC.... TIME, 9.28CM/SfC -I'II'W,0.001 s(c, 0.2SI SEC.

'_,__

I

I I I I _J I I I__J2.0 1.0 0 1.0 2.0 2.0 1,0 0 I .0 2.0

X AXIS, x I0 °

c) SCAIIN(, VILIO(IIY VICTOR, (d) SCAIIN(, VIIOCIIY VICTOR,

15.1 CM/SfC .... lllV(, Iq.2 CMISlc ..... IIMI,

0.(,00 SfC. 0.8',0 SiC.

IIqURl 2. PROPItIANI I'IOIION l(.)R IISl S: NOIf: VlIOCIIY VlLiORS

SCAIII) I0 MAXIMUM V[IOCIIY IN l lIll).

(

i

11

3.2

2.8

2.4

2.0

1.6

1.2

.8,6

LOCATION OF

' SURFACE OF

,_1 z_ GEY_.R TIP SETTLES

N INTO SURFACE OF

-----fl ..... -. _-COt_LECTED L;OU1D

L3. CYL | NDEICAL/HE MI SPHER ICA[

INTERS[CT ION

0 SUMNER'S DATA

/_ CODE PREDICTION

A

.7 .8 .9 1.0 1.1 1.2

lIME fROM START O_ RIORIENTAIION, SEC

FIGURE 3. GEYSER TiP {{)CATION VERSUS TIM[ fOR lEST 5,

L

el:

g

>-

I

1.6

1. _ _-

1"2-- l

1.O

.8

LOCATION Of SURFACE

Of COILECT[D LIQUID_

RICAI

f_ INIE RSEcI ION

/ _-GfYSIR liP SflI{{'S

INTO SURfACI Of

COIIICIED lIQUID

0 SUMNIR'S [)AIA

A COD( PRID]CIION

I l L_ t.q 1,0 1.l 1,2 1.f

liFl[ tROM SIAR! O_ R[ORI[NIAIION, see

f IfiURI 4. (;[YSIR lip lOCAl ION V_RSUS IlMI IOR

I{SI 1.

1,4

J

%

OR|G_AL PAGI_ IS

oF vOOl_ QUAMT_

9.0

6.8

q.5

0 --

x 9.0

B.8

q.q

0 --

I

///, i

(a) SCALING VELOCITY

VECTOR, 2.65 CM/SEC

-TIME, 0.05 sEC.

I I I).0 1.0 0 1.0

iil

%

_(,. d:-¸

<b) SCALING VELOCITY

VECTOR, 33.5 CM/SEC

= -lIME, 0.G5 SEC.

I/_/ y,\

J/!l,i',, t!

iI:, i!:

i

I I I I I I2,0 -2.0 -I.0 0 1.0 2.0

X AXIS, x I00

(d) SCAIING VHOCIIY (e) SCARING V|tOCIIY

V|(IIOR, 7(}.1 CM/SF( VICTOR, 20._ CMIsEc

-IIMI, 0.35 sic. -IIW, 0.90 s_c.

-\_-_

,,, ,H

i!i,l li:_H I

;i_ ii

I

(C) SCALING VELOCITY

VFCIOR, 6B.S CM/S[C

"lIME, 0.15 SEC,

!/?' -,,!

¢/ 'i \'

I 1 1 1 J2.0 1.0 0 1.0 2.0

(f) SLAIIN(. VFLO(IIY

VI CIOR, _. _GxlO il

CM/Se C "I llql,

O. _4 ';_ C,

FIGURE 5. - PROPELLANT MOIION fOR IESI 8.

C',_" -"')'. ' .... # ......

%x

>,.

1,5

1,1

. l|

0 m

o

X-AXIS, x 101

FIGURE _). BOI_ING SB OTV PROPI:IIANITANK, 0.25 SCAIF.

14

II

i

1.5

1.1

.4 D

_o 0 --

x

_. 1.5 --

1.1 --

Ok/GINAL PAGE IS

OF. POOR QUALITY

'i,4

(a) SCALING VELOCITY VECTOR, 29.0 CM/SEC

= -TIME, 4.0 SEC.

I

_// \\--.

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(b) SCALING VELOCIIY VECfOR, 26.1 CM/SEC

-TIME, 8.02 SFC.

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/,\ \

\ _"/ _" % /i\\ _ J / \ \ -_ . ; /

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( 1 I t5.¢ 2.1 0 2.1

(c) SCAI IN()VTIO(.IIY VICTOR, 27.6 (:m/sic

TIME, 10.1 sfc.

ILiURI 7. - PROPI_tlANT MOIION WITH A

IN I IllD.

\

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J L_.

X AXIS, x 101

r s , / 7 '_

I I

1 l 1 12. " 0 2 ! '_. '_

SCAI ING V[I 0( I f Y Vl C fOR, b {. _; ( ml',l

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H.O X 105(): NOIF: VIIOCII'Y V_(IIORS SCAIFD I0 MAXIRUM VIIOIIIY

0

1,5 -

1.11

(a) SCALING VELOCITY VECTOR, 3.85 x I0-4 cM/s_-c

- TIME, 0.001 SEC.

(b) SCALING VELOCITY VECIOR, 1,_ CM/StC

-TIME, 60.2 SEC.

z"/_/ I i d'h_ \ \ \_\ '

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16

ORJGINAL PAGE IS

_E POOR QUALITy

8 --

%

x

• q --

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r_' , ,--_ 7 -,-4 - r _ .... +-.....

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7']_];7-";FINEIIESSRATIO (tlO) 0,81; 77i.';;

..................... _ :--:t;+ + -_.+ ; 7 _"'3 ;.";_;]7"7'

I + I I Iq.6 -2. '_ 0 2. 5 q.b

X-AXIS, x 101

f IGURE 9. - BOIING SHORT SB OTV PRfW-'I!!aNT !a.NiK,O.215 S_AtE.

17

®,li

m

6

><

4

2

'I I/Xg" "_ '

(,:1) SCALING VELOCITY VECTOlt, q x 10-50_'SEC:--_TIE, 0.001 SEE,

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?:t,i !\',_,L

-4_. JS-f.-

_c) SCALING VELO(ITY VECTOR, 1.54 ce_/s_c

-lIME, _0.0 sec.

8 --

14:--

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(b) SCALING VELOCITY VECTOr, 1.23 CM/SEC

TII_, 10.0 $EC.

,'1b'_/ Li',:'

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(d) SCALING VELOCITY '_C(_. 1.41 ¢_',/s_c

- -TIME. 40,0 s_c

/

I,

,!

--L

.L1il-.-:..:,:,,

I...... I 1 i I 1 1 1 1_l ,_ 7.'I 0 2.'I 4.6 4.6 -2.'1 0 2._

X AXIS, x 101

_e) ,_EA| ltlt ", VftO(_lIY Vl;LIOI_, 2.11 CM/'_-C (f) SEAl I_v VfLuEIfY ViCing. 1.68 ct,_-,:

-II_[, _).I skc. -lllqJ, bO.1 s[c.

I I',IIR| I0. PR(_°fLIA_l PiOTiON IOIR 0.215 SCAII _ IN(, SB OIV (501 I_ULL, I_IP0!_ D AC(ILiRAIION IS_. L2 _ I0 2 (.M/S2).

I4,6

ORJGI'q,_,. PA';F. 1,_

O_ IIDOR _UAL/TY

18

ORIGINAL PAGE IS

L_ I-'OOR QUALITY

tn

(nM-

160 --

120 --

80 -

/40

0

0

0

0

o%

10-4 10-5 I0-2 10-1 100

a, CM/S2

f IGURE 11. - SETTLING HME VERSUS ACCELERATION, SMALL-SCALE IANK; FILL LEVEr = 50 PERCENI.

0

0

0

;-- 0

I0 '_ TO i I0 2 10 I 100d, rMIs)

' I(,¢IR(12, DflrA V VFRSII$Af,C_IIRAIION, _P'IAIISC,_,IFlANK:_III IIv[i 50 P[RCINI.

J_ JLT.,_

19

_hqr_j_, PAGE LS

OE POOR QUALIT_

2.8 --

1.9 --

.9

0 --

2,8 --

%

x

• 1.9 --

iT

1.9,--

0 I

...... _y ......

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CM/SEC _---_TIME, 0.001 SEE.

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I_;_

f/

J

jl I

(b) SCALING VELOCITY VECIOR, 1.05 CM/SEC

:--_TIM[, _0.0 SEC.

../ ....... i IIZ _'_

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- TIME, 90.2 s[c.

. -. . .

[ 1___ I ___[ J [_-J L--IT I2.1 I.l 0 1.1 2.I 2,1 1.1 0 1.1

X AXIS, x 102

,el SEAl INli VflO(llY VICTOR, _4.2_ CMIsI(; If) S(.AIIN(, VII(XIIY VICTOR. _.92 r_Isf_

-IIMI, 121 0 SI<. " [I_l, ISO.O '_I(.

I IUUR[ I(. PROPIIIAN! MOIION fOR full SLy{If BOIIN(, SIi OIV (I _, PIR('INI I'UII, I.% x 10 2 cM/J).

J2.1

20

i_.b'

.. _. .+ _ • ,. T_4,..

2000i

1500

1000

500 --

A

A

AA

o I I ILIIh[ 1 ll,lih[ i t?Illl_ I IAJilhl

10-q 10-3 i0-2 10-I 100

a, cM/s 2

FIGLJRE lq. SETTLING [11_ VERSUSACCELERATION, FULl

SCALE TANK: FILL LEVEL 25 PERCEN].

1200 ?

I I l lllh]

i0-4 10-3

%?

I i lllih[ l

10-2

a, cp,_'s2

10- I 100

FIGURE 15. - SETrLING lll_ 7FRSUS ACCELERATION, FULL-SCALE TANK; FILL LEVEL -: 50 PERCENT.

4OO

bOO--

soo- 0 00

- 00

100 --

o I , t llllll

I0 _l I0 _

0

0

O0o

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'.If.All IAli(; f III IfVtl /'J PIIRCEIII.

20 --

10

A

A

A A_A

0 - 1 , I_l,i_ Lx_LJ_LIJ.IJ___t , i,l,l,I i , 1,1_1,1

10 4 10 I 10 2 I0 1 10 0

d, c_l_ 2

I IrJlJRI 11. lltl IA V VIRSIJ!; fI(CLtIRAIION, tlill _CAII

IAlil(; flit tlVtl 25 PtRClI'tl.

21

V

V

V

VV

V

V

FIGURE 18. - DELIA-V VERSUSACCELERATION,FULL-SCALE

TANK; FILL LEVEL = 50 PERCENT.

20

15

>" 10

_ 0

o , ,_,,,_o_,_,,,_,l°_,,,,,,,d , ,,,,,,,I10-4 10-3 i0-2 10-I 100

a. CM/S2

FIGURE 19. - _LTA-V VERSUSACCELERATION FULL-SCALE

TANK: FILL LEVEl 7S PERCENT.

20

15u_

> 10

Z_ FULL SCALE

I-30.215 SCALE

?

Z_

I I I8 I0xi0 q

fIGURE 20. DIIIA V VFRSUS Sf, FIll IEVFI SO PI-RC[NI.

22

NallOflal AetonaUhcS drlO

Space Administration

1. Report No. NASA TM- 101440AIAA-89-0628

4. Title and Subtitle

Modeling of Impulsive Propellant Reorientation

Report Documentation Page

5 Report Dale

7. Author(s)

John I. Hochstein. Alfredo E. Patag, and David J. Chalo

9 Performing Organizatson Name and _ddress

National Aeronautics and Space Adnlinistr_:-iiop

Lewis Research Cent:r

Cleveland, Ohio 44135-3191

12 Sponsoring Agency Name and Address

National Aeronautics and Space Administration

Washington, D.C. 20546-0001

15. Supplementary Notes

6. Perlorming Organization Code

It. Performing Organization Report No.

E-4545

¢0.-WorkU-.it-No.....................

5(_ 48 -2 I

................. it 1 Contract o," Grant NoI I

I

type of Reportand Per,od d0vered...... i

Technical Menlorandurn i

[

1i4[ Spons0rmg Agency C-ode ................

i

i

Prepared for the 27th Aerospace Scicnccs Meeling sponsored h_ the American Instilute _1 Aeronautics and

Astronautics, Rcno, Nevada, Januar) 9 12, It)blt). John I. fhwhstein and Alfrctlo E. Patag, Washington State

University in St. Louis, Mechanical t','nginccring l)_'parilnent, ('anlpus Box 1185, ()ne Brt,_kitigs Drive, St. l,ouis,

Missouri 63130 (_ork funded under NASA (;rant NA(;3 578), I)avid J. C|l:th_, NASA I,c_is Research Center......................

16 Abstract ........

The impulsivc propellant rc_lv-icntati,m pr4wc,,_ is nlodclcd u_mg Ihc I-('l.ll'Sl. ('odc A hliel dc,,ciiplion el lhc

p" )tess and the coniputulioiial illlldcl is prcscnlcd ('t_tlc _alidalion is thlculiiCnlalcd _,ia _.lllllpalisiln Ill ck|)cli-

mentally derived data lhr small-scale tanks. Predictions of rcoricnlalion perhlrlllailce girt." presented for tw_ tanks

designed |tlr use ill flight experiments and for a prolu_scd full scale ()'iV lank. A nev, dimensionless parameter in

developed m correlate rc_ricnlati_m pcrll_rlllanc'c in gc_Hnclrh:;.lll_ ',ilnilar tanks. Its stlcccss in dclnOnslralcd.

#. f.

1" Ko,, Words Su(lcllJStpd t)y Auth,)rlslt

Prol)c llallt tlrlClllalltin

I._,_ £r:iXll_, lhlid iticch,inic_

19 Security Clasmf (of this rpp<lri)

Irlc liissllicd

NASA ro_i lill6 <, ' _

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tl, I [ )tilllitildlflrl _t_llpfnf* lq

( 'lit l:t_llit'd I 'lilllliilt'tl

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