Page 1
_L ¸i;!_
MCDONNELL DOUGLAS TECHNICAL SERVICES CO.
tlOUSTON ASTRONAUTICS DIVISION
SPACE SHUTTLE ENGINEERING AND OPERATIONS SUPPORT
DESIGN NOTE riO. 1.4-.4-5
THERMAL BOUNDARIES ANALYSIS PROGRAM DOCUMENT
MISSION PLANNIHG, M!SSIO;I A!_ALYSIS AND SOFTVARE FORMULATION
30 APRIL 1975
'SThis Design Vote is Submitted to LA,,A Under Task OrderIIo. DO103, Task Assignmer;t 1.4-4-A, in Fulfillment ofContract NAS 9-13970.
_7
PREPARED BY: ,,_i _;"--_-z21-_z-_L/_--Fi.-c_.-.._van_
Engineer
488-5660, Ext. 243
.:Task Mana9er488-5660, Ext. 243
APPRGVELJBY: "i/_. ;,, ..... ,/,... i; ._ _-')• .9 I. ,', <',. _ z. " ";'')z
_F.WiYiW'.;_W.............. "_/"tP;; t,!ork Pact'_ge ,_!anage'r488-5C60, Ext. 240
APPItOVFD EY:.,,,..,e'¢/
i,,v-i,---rG-7._;...................Project I',I,p,t.Ior
I,:ission P1._nnin?,
flissicn Ar,clysis a_,dSoftv:are Tovmulation
4_',8-5660, [xt. 2_6
;i!;:j
!
rI
https://ntrs.nasa.gov/search.jsp?R=19760026154 2019-01-27T11:45:26+00:00Z
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DN No:
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1.4-4-52
2.0 INTRODUCTION
The digital program TBAP has been developed to provide thermal
boundaries in the D/M-relatlve veloclty (D-V), dynamic pressure-
relative velocity (q-V), and altitude-relatlve velocity (h-V) planes.
These thermal beundaries are used to design and/or analyze Shuttle
Orbiter entry trajectories. The TBAP has been used extensively in
supporting the Flight Performance Eranch of the NASA in evaluating
candidate trajectories for the Thermal Protection System design
trajectory.
ii
i
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DN No.: 1.4_4-5Page: 3
3,0 DrSCUSSZON
The method used in _BAP to establish therTnal boundaries fs to find
a reference heat rate for a given velocity and altitude, input the
reference heat rate tnto a sfmp;tffed heating mode] resulting in
the definition of the surface temperature for a selected panel or
control point and then iterate on altitude until the panel temper-
ature matches the critical temperature input for that panel D/M
and dynamic pressure are then found corresponding to the altitude-
velocity point. This process is then repeated for a different
velocity until the desired range of velocities is spanned.
The assumptions made in developing TBAP are that simplified heating
models (R-_ferences I and 2) can be used to determine surface t_mp-
erature and that atmospheric density and free stream temperature
can be _odeled using the 1962 Standard Atmosphere.
The reference heat rate for the panels and control points as givenin Reference I is
qref =0'82 (17700)\/'(_--(1V)3.07 (l -;_)flx
where(1)
= stagnation point hoar rate for a one foot sphere (BT{J/ft2/sec),
_) " free str(,e_ density (slu_s/ft3),
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DN No.: 1.4-4-5
Page: 4
and TW
TW
T
and c
V = relative velocity magnitude {ft/sec),
hw - surface enthalpy (BTU/Ibm),
hw = .24 Tw,
ho = total enthalpy (BTU/Ibm),
ho = .24 T + V2
50,063
= wall temperature (°R),
= I000/qref _.25
/= free stream temperature (°R),
(2)
(3)
(4)
= surface emissivity.
NOTE: Since TW, (equation (4)), is not independent of Qref' an initial
value of T is assu_ed and two passes are made through equation (1)l.!
in defining qref"
The individual panel or control point heat rate (Reference l and 2)
for laminar, transitional and turbulent flow are defined by
(s)
, for qoi < P <_ K Roi,(6)
qpanel = ql(lam) = AiCiqref' for P < Roi,
qpanel _"qi(trar_.s)= qi(l_,_,) k'Oi{_"-R'-b)_T:__io.i)I P _.3
and
qpan_l :'('i(tu,'b)= qi(l_.m)c I'-RPoil 3' fc)r )',Roi <..R, (7)
whc,_e Ai :: deflectiun f_,ctor,
Ci = Qi(l,_). ,Fcr the ith par,el
Qref
:: fur.cltoq of ._r]le of atta(:k, c,,
|
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DN No.: 1.4-4-5
Page: 5
R = Reynolds number behtnd a nomal shock
I .,p__ 9
_v
._ Rot = transition onset Reynolds nt_nber for the tth panel,
= function of _,
and Pv = normal shock viscosity coefficient and a, b, c, and K are
Modeling constants. The deflection factor, ^i' (Equation (5)) equals
one for surfaces not on the elevon or body flap and
^i = I.O5 + (g.8- __) r5
where c_= angle of attack (degrees)
F = .0196_ - .0122, for 0 < _ < 4
F = .0276_ - .0443, for 4 < 6 < 8
F = .03C76_ - .11758, for 8 < _ < 15'
r = .04669_ - .2665, for 15 < 6
and 6 : deflection angle (body flap or elevon) for surfaces on the
body flap or elevon.
(8)
Ci and Roi are stored in tables in TBAP as functions of e and interpolated
for the appropriate _. lJv is stored in a table.as a function of V and
interpolated for the approDriate V. The su'rface temperature for the
th panel as defined in Rc.ference 2 is given by
(°pa,_el) .25Ti = 10,00 ......... 460\ .47fi ci
(9)
where _i : surface emissivity for tl,e ith p_nrl.
Using Equ;_tions I throuTjh 9, a re,]ula falsi r_.,thuJis used to solve for
Page 6
DN No. : 1.4-4-5
Page: 6
the altitude at which panel temperature Is equal to a critical
temperature.
That is
hi÷1 = hi + [AA-_] (Tc" TI)i
^his initialized vith an altitude hi, A-T
Ah hi " hi'l
= Y_Ti_l '
and an iteration proces_ continued until T i converges to T c
calculated numerically by
within an
input convergence criterion.
(I0)
(ll)
The dynamic pressure is defined by
1 pv2.
, (Fouation 3)In TBAP the free stream density, p, and temperature T
are conlputed using the SVDS (Reference 3) subroutine ATMOS which
represents the 1962 S_andard atmosphere. The drag acceleration is
defined by
D/H = _ CDS .
m
where CD = drag coefficient
S = referer,ce area
and m --, vehicle _:ass.
(12)
(13)
is cc,._;putedusiw_.gthe "
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DN No.: 1.4-4-5
Page: 7
4.0 INPUT DESCRIPTION
The TBAP input data consists of data from the SVDS base data tape
(Reference 3) for an entry run and data for the following variables
which are in common arrays.
il
COMMON COHMO_I
VARIABLE TYPE * BLOCK LOCATION
ALPHA R BLCK GMDATI (78)
_.IASS R BLCK G_IDATI (128)
V R BLCK XLEC (507)
H R BLCK GNDATI (70)
NC2M I GEN2 WORK2 (330)
NVAL I GEN2 tlORK2 (331)
DT R GEN2 WORK2 (I07)
DV R GEN2 WC}RK2 (105)
NP I GEN2 $CORK2 (I08)
IOP I CErI2 I!ORK2 (llO)
V;I R G_,w2 _!;'RY2(IO,i)
DESCRIPTION
Pitch angle of attack (RAD)
Vehicle Mass (slugs)
Initial velocity (ft/sec)
Geodetic altitude (ft)
Convergence interval for
temperature iterator
Number of values for angle-of-attack table
Specified tolarance factor
for temperature iterator
Increment velocity (ft/sec)
TPS panel or control poi,tnumber
Option for atmospheric ITlodel
= 0 1962 U.S. Standard
atmosphere
= l July atr_;osphereat 30 Dea.tlorth l.atitude
= 2 Jan. ab',_sphere at 30 Deg.rlorth t_,titude
--3 ,luly at:;_.snhereat 60 D_.g._orth Latitude
--- 4 Jan. at;;_osphere at 6n Deg._iorth Latitude
r'axir:un_velocity (ft/sec)
Page 8
DN No.: 1.4-4-5Page: 8
COMMON COMMONVARIABLE TYPE * BLOCK LOCATION
IALP I GEN2 WORK2 (Ill)
TC R GEN2 WORK2 (If2)
VALT (1), R GEN2 _ORK2 (150)
I = 1, NVAL
VALP (1), R GEN2 WORK2 (114)
I = 1, NVAL
NBAP I GEN2 WORK2 (200)
TSTOP I GNDAT2 GNDAT2 (2)
TNAX I GNDAT2 GtlDAT2 (3)
IBAP I GEN2 WORK2" (199)
DESCRIPTION
Option for angle-of-attack
= 0 ramped schedule
= 1 constant schedule
Critial temperature (DEG)
Velocity Table (ft/sec)
Angle-of-attack Table (DEG)
Flag determining thermal
boundary option
= 0 Does not call TBAP
= l Calls TBAP
Maximum Phase Time (sec)
Haximum Case Time (sec)
Flag for TBAP driver option
= 0 Do not use TBAP driver
= l Use TBAP driver
* NOTE: Type "R" denotes REAL.
Type "I" denotes INTEGER.
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DNNo.: 1.4-4-5
Page: 9
5.0 OUTPUT DESCRIPTION
Figure 1 gives an example of the intialization data which is output
from TBAP. Table I defines the data in Figure I.
Figure 2 gives an example of line printer output of thermal boundary
data for a given panel from TBAP. Tab]e II defines the data in
Figure 2.
Plots of thermal data from TBAP (see Appendix A Figures 3, 4, 5) are
presented in the D/H-relative velocity, altitude-relative velocity,
and dynamic pressure-relative velocity planes respectively for control
point 2 (body flap).
Page 10
DN No. : 1,4-4-5
Page: 10
.......... Row1 - 2
NC2H
NVAL
TABLE I.
INITIALIZATION DAT
Input Identification
Maximum number of iterations on critical temperature
Humber of values for angle-of-attack table
Row 3 - 4
Input Identification
REF AREA
WEIGHT
VSTART
VSTOP
DELTA V
DT
Reference Area (ftz)
Weight (Ibs)
Initial velocity (ft/sec)
Final velocity (ft/sec)
Velocity increment (ft/sec)
Specified tolarance factor for temperature iterator (°F)
Row 5 - 6
Input identification
CG (I)
CG (2)
CG (3)
Center of mass X-component (in)
Center of mass Y-co_,_ponent (in)
Center of _,ass Z-coi_Iponent (in)
Page 11
0c_
$,C_
)='- C_
! o)i •I(+
41.
C_C)
'4[ C3,)-= ¢._
.==J C_)toC)
!+
0
,) o.
oO
tl 0
,0
I- +
_" Cb
LJ -2 %.*) _.r- _ r't
:_ •
4,
_J
1
DN Pl0. :
;
+
1.4-4-5Iq
I:
!
I
I
+I+
1
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c)
4-.)
N• +r
lb.,-.
°I')"
_=
(+..' o
QJ
l )J
i
LU
(Z3)-4
Lt..
Page 12
DN N0. :Page:
1.4-4-512
?oo??oooo?oo?_??????oo???_?oo??_o...... .. .. .. ..LODO_O0000_0_000000_00000 O00DOOQO
4J
t:::
0
(l)
I--
q..0
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4.a
4J
dhi
L_
[email protected] _.OF THE)RIO_AL PAGE IS POOR
Page 13
DN No. : 1.4-4-5Paqe: 13
TABLE II
THERMAL BOUNDARY DATA
Row I - 2
Input identification
NP TPS panel or control point number
lOP Option for atmospheric model
= 0 19G2 U.S. Standard atmosphere
= l July atmosphere at 30 degrees north latitude
= 2 Jart. atmosphere at 30 degrees north latitude
= 3 July atr,_sphere at 60 degrees north latitude
= 4 Jar,. atmo._phere at 60 degrees north latitude
IALP Option for angle-of-attack
= 0 ramped schedule
--l constant schedule
TC Critical temperature (°F)
if
Row 3 - 34
Output identification
REL VEL
ALTIIUD_
n/_
D t"_ ,e" "j_,i_.TY
REY '_'
Relative velocity (ft/sec)
Altilude (ft)
Drac! eccele)'atior'.(it/sec _)
• r', _ _, I _'_.2Dw_;."li_ Pr_ssu, e (l,_./_)
D_ns-;t. (_Iuq/T;]_)
Hu),:: _I sho,.k r,(:y_)<Ids nu:,!._,_:)"(_iii)
t,'_Ch n:_,,_,l,er (_:[J)
_)',_ S!:rfzc:.;te_'p,erat.L:re(°F)
Page 14
DN No. : 1.4-4-5
Page: 14
TABLE II (CONT'D)
...T_I_A L BOUt.__ARY DATA
Row 3 - 34 (cont'd) ........ . .................
Output Identlf_c&tlo_- _ " "....
FLOW Flow characteristic
= 1 Laminar
- 2 Transitional
• 3 Turbulent
BDF
ELV
Body flap setting (DEG)
Elevon setting (DEG)
ALP Angle-of-attack (DEG)
Page 15
DNNo.: 1.4-4-5Page: 15
6.0 SUBROUTINEDOCUMENTATION
The following sections define TBAP subrnuttnes. The subroutines
ATMOS and AR140C are current SVDS (Reference 3) routines and hence
are not documented in this note.
6.1 INTGI2
6.1.1 PURPOSE: INTGI2
Subroutine INTGI2 calls the BAP routine.
6.I.2 INPUT
NBAP Flag determining thermal boundary option
= 0 Does not call TBAP
= I Calls TBAP
6.1.3 OUTPUT
i
None applicable to BAP
6.1.4 ALGORITHM
None Applicable to BAP
6.1.5 CALLI?IG SE_
Call INTGI2
6.1.6 CO_ISTANT REOUIRED
None required
6.1.7 SU_RpUTINE_______RE_OU__IR__ED
RAP
Other routines not applicable to nAP
* i;OTF:Only the portion of IrITGI2 applicable to TRAP is documented
in this desi(m note.
Page 16
Dtl No.: 1.4-4-5Page: 16
he first executable statementT " r to call"is to detemtne whetheeAR
The ren_ainderof subroutine
IHTGI2 is unchanged-(see Reference 3)
Page 17
ON No.: 1.4-4-5Page: 17
........ ° ....
PURPOSE: BAP is the executive routine used to sequence other
routines tn calculat|ng thermal boundaries.
6.2.2 It_JT:
NP
Y
VM
DV
IALP
DT
NC2M
6.2.3 OUTPUT:
TPS panel or control point number
Initial velocity (ft/sec)
Maximum velocity (ft/sec)
Velocity increment (ft/sec)
Angle-of-attack option flag
= 0 ramped schedule
= I constant schedule
Temperature convergence criterion (°F)
Cor'ergence interval specification
Input identification labels
QBAR Dynamic Pressure (Ibs/ft 2)
MACH Mach number (ND)
H Altitude (ft)
DOll Dra9 acceleration (ft/sec 2)
V Relative velocity (ft/sec)
I_ r', !Write EI,_)r_LEon Ut_iT 8
6.2.4 AtGORIFI!H
See flewchart Sec. 6.2.8
Call BAP
Page 18
_N Ho.: 1.4-4-5age: 18
6.2.6
6.2.7
H - 160000. Inital altttude
_AL = 0 Flag tn AR140Cto eltmtrmteCa11AROCAL
SUBROUTINE RE_
TABLE
ATHOS
ARI40C
HTRATE
TPS
TI
Page 19
b
6.2.8 FLO.WCHART
.... i_̧ .L_............ L
DH No.: 1.4-4-5
Page: 19
;.Ir_RODUCIBILITY OF THE
_RI01INAL PAGE 18 I_)OR
Page 20
[ _j//./. TP5 ]
^,c/./"-....
t1_ = H
tt:: !t -t !00.
Tpo = TP
_LCoMPelTE _'L:T :
DN No.: 1.4-4-5
Page: 20
L
r:
.........fJo b...-.,,.......:/ -, \
"b,:'''
Page 21
6.2.8 FLOt_ICHART(COtlTTNUED)
_url _-/t t (H- /io,)_ (1C -
Te)/(Tp-7_o._Ho= HTPO = TP
tt -OetM¢ = Nr.,_ 1
I DoM: _,i_ • co_-JL__LM_..n_s ..I
___ r:5 VL VM
,, _i-_-:,!:......
DN No. : ].4-4-5
Page: 21
Page 22
Page: 22
6.3 TPS
6.3.1 PURPOSE..__.__'.
6.3.2 INPUT:,....,....,...,..
IREN
KNTTPS
NPANEL
RHOSL
Ar. sw(3)
IV
MTPS
t_TPS
VT
T4OOK
IC,AI'
TPS
Subroutine TPS calculates normal shock Reynolds
number and the stagnation point convective heat
rate for a one foot radius sphere.
Reynold's number computational option flag
Number of integration step sizes since the
last TPS Model Computational update
Numberer TPS panels and control points
Density at sea level (slug/ft 3)
Ratio for density at altitude to density at
sea level
Vehicle number
Thermal Protection Option
= 0 TPS is not simulated
= l Initialization pass of TPS
= 2 Execute TPS logic (Initialization completed)
= 3 Print TPS sun_ary
Ntm_ber of SVDS integration cycles per TPS
integration step
Relative Velocity (ft/sec)
Ti_e at altitude of 400000 feets
Array of current atn_osphere data
Option for T_AP driver
"= 0 [)o not use IBAP driver
= 1 Use IBAP driver
Page 23
DH No. : 1.4-4-5......:.... Page: 23
..... 6.3.3 OUTPUT-:
Z
QREF
REN
Stagnation point heat rate (BTU/ftZ-sec)
Reynolds number behtnd a nomal shock
_ 6.3.4 _I___.M
" i i:_"_,_......... - "..... See flowchart Sec. 6.3.8
6.3.5 CALLING SE_
Call TPS
I
le
Page 24
DN No. : 1.4-4-5
Page: 24
DATA
I23
5
DAIA
I
Z
3
li
5
6
6.3.6 CONSTANTS RE_
Relative velocity table corresponding to vise array
VESI600,olDO_,,1500,_2000,o2500,o3000,,3500"o_O00"l_SO0,_
50UO,oSS_.,6_GO,t6500,t7000,t75OO,tSCOO*tSSOO*s9000"t950O*tICO00,,10590.,ltOOO,,ilSO_,lt2000,,12500''I3000''13500"ol_O00-
i14600,,15_C0.,15500,=160_0,o16500,p_7000'o|7500oo|6CO0'1
2_C3_))22C_0,,25000.,_5_C}_,)25800,)26GC0")260_ D')26100'o
30000,1 .........................................................................
Coefficient of viscosity VS relative velocity
VISC/,31OE-6,,35IE-6,,39qE'6,,460E'6,,S41E'6o,6_6E'bI'7_SE'6.
,_50E-6t,?5|E.6_,IO65E-5J'IITE-So,12_L-5D'I3UE-5''I_lE-5o
,15&_E-51,1655E-SD,I735E-_o,I_IE-SI,Ie65E'SI'192L'So'|965E'SI
,2L.51°2_3E-5_°210E-5,oZI7E-5_,227_[I-5,,2'_OE'So,25LE'SJ
,261E-5,,26_F.S_,275E.51-2_2E-Soo2_gE-5_°2925E'5_'297E'5_
,3E-5,,311L-S,°323E-5.,3qsE-S_'3N?E'5_°3_E'S_'3_IE'So'337E'5.
o286E-S_o2_6E-_/
6.3.7 SUBROUI'I_IEREQUIRED
None
Page 25
6.3.8 FLOWCHART
,.:_,-_RODUCIBIMTY OF THE
._RIOINAL PAGE IS POOR
BHTTp_ (_.Vl)= RglTF£ (..zVt ) -t- t I
:\
L
! KoTros_:a_ = _ I
_l_to___.___
I
7"T/_'S.C_,'i) = __,_r- c !I A_t,:[:r,'rx = 0 !
:_.,iI
L(_.T(.J,)_: _::,..r,_..... lII .1. .h
I I I
I
• .-/:"_'_, ::-. ._.._, ]
Lc ,,, _-_ • -I: '..,'.-L .Li_ ....
t ,
DN No. :Page:
1.4-4-525
Page 26
I
I
I
1
t
I
I
I
I
I
I
I
I
DN No.:Page:
I .4-4-526
/
t
Page 27
/
£
6,3.8 FLO,.!CHART(C01'ITINUFD_'/"_
<,.. Io::t "....'/EC,.. , _--""I
._ ._,--_L!_r:-, 7qooi_-t Ol][),p . _--
"__ 4 -.----}_,_w.,.- "',_q_-, -_ _
, '_ _
!-- - ,,,,,__:_.,___/
_)"'_ VE5
',..... _" :_ ,,,__1_-"-1""_'(_ /
I t, w_u...l) -t.'_,_(:oj
--_;
V- ,. \_ _-'_',_,t. .............. [, - ............. ,J:
_'L_...........i:C: :£L
DN No.: 1.4-4-5
Page: 27 i
Page 28
6.3.8 Ftf);ICIIART(cp_iTi-_1-u_b-i...............................................
sL_
jT;-2--N
IIII
I
I
I
I|--
F__..... _......
[.cc.<,:!:_,.'.c!._J
......:'-TIT......
..... J" .....
DN No. :
Page:
1.4-4-5
28
Page 29
Page: 29
-5
6.4 HTRATE
6.4.1 PURPOSE"
6.4.2 INPUT:
ALPHA
NPANEL
QDOTC
IV
REY
DELVTR
IBAP
NP
6.4.3 OUTPUT:
QDT
IFS
P_HS
HTRATE
Subroutine HTRATE determines the flow characteristic
(laminar, transltlonal, or turbulence) for a given
panel and computes the corresponding he_t rate.
Angle-of-attack (RAD)
Numberof TPS panels and control points
Stagnation convective heat rate (BTU/ft2-sec)
Vehicle number
Reynolds number behind a normal shock
Angle of deflection (body flap and elevon) (RAD)
Option for TBAP driver
= 0 Do not use TBAP driver
= 1 Use IBAP dFiver
TPS panel or cuntrol point number
Heat rate (BTU/ft2-sec)
F1ov_ ch_racteristic
: 1 (l_,::_inar flow)
= 2 (trcn._itional flow)
= 3 (turbulence flow)
REynolds r,_::'bcr eL t_?nsition
See fl ,,' H . .4.o,,c,.art Sec 6 9
6.4.5 C/J ii'n _,_c!;[,;,-_-. . ._ _ ..... .1.L'._' .'...__:,.
Call }'TI'ATF.
o;;set
Page 30
Page: 29
6.4 HTRATE
6.4.1 PURPOSE:
6.4.2 INPUT:
ALPHA
NPANEL
QDOTC
IV
REY
DELVTR
IBAP
NP
6.4.3 OUTPUT:
QDT
IFS
RENS
6.4.4 ALGOF',ITH!I
See flo_vch._rtSec. 6.4.9
&.4.5 CAI.LIrIGSEOUE'ICE
Cal I IITP,ATE
HTRATE
Subroutine HTRATE detemines the flow characteristic
(laminar, transitional, or turbulence) for a given
panel and computes the corresponding heat rate.
Angle-of-attack (RAD)
Numberof TPS panels and control points
Stagnation convective heat rate (BTU/ft2-sec)
Vehicle number
Reynolds number behind a normal shock
Angle of deflection (body flap and elevon) (RAD)
Option for TBAP driver
= 0 Do not use TBAP driver
= I Use TBAP driver
TPS panel or control point number
Heat rate (BTU/ft2-sec)
Flow characteristic
= I (laminar flow)
= 2 (transitional flow)
= 3 (turbulence flo_V)
Reynolds number at transition onset
Page 31
J
!
I
DN tlo. :
6.4.6 CONSTANTS REQUIRED Page:
LA_It'JAK ¢DOTL/QDOT STAG V S ALPHA AND PANEL NUHBER
DA1A
I_ATA
DATA
OJTA
OAI'A
DATA
DA1A
DATA
I;ATA
DAIA
(C(I.KI)K=I.13} l*551_,.5170).4850o.45_O,._qOO)._310,oq390o
(C(2)KIoK=I,I 3).................... /*15qOt°162G)'lTqO,o|9B_)o2|60)=2300,.2300o,23_C,o230_o'23_O,o23R_P.2550s.3GSO/
(C(3tK)tK=I,I3) /•02H_o'OS701"Q8991"|22Gto|370oelS301olbTO,.*lBlO,,1920..19_Ot.1900)*lSOO,,13BOl •
(CIq)K}'K=I.I 3} ..../'C200)'_3q0,'_559.'0839''I000,.I170,.1350.
.ISlO,.1660oolBIO..I?_01.2050,.223_/
(C(SjK}JK=I'I3}_!OG29_t*O32Gj'_H23.'C62GJ*G759,'DSBG,,Io00.. _ 1
*II00.*121G,o1320.*1430).15_0,.1750/
(C(6,K)tK=Itl3) Io0290,*_300,*034_o.0_3C).0530)*063_,.0_7V,"07BOoo_B70,*9960,oiO_D,*lI_O).]310/
(C(7*K)tK=I)I 3) I'_02C,'3610,*3210,.28_O,.2e70,.Z530,.2_Ot).
*2300).2230).22_Co.2200,.2200).22C0/
(C(8,K}sK=|,I3} l*2R35)'2q62t*2flVD).25|B).Z535,*Z550,,2_bS.
.2582).2509)'2617,,2637,.2660,.Z713/
(C{9,KI,K=I.I 3) I*0970)o_989)o1080..I26G),I_30.oI750,.ZIND,
DATA(C(II)KI)K:I)I3)/O.O271)*_.oGS29,.O6571t.97L,43,.0771_,.383,,I
Page 32
DN No.: 1.4-4-5
Page: 31
Alpha table corresponding to LA.HINAR QDOTL/QDOT STAG
DATA ALP/IO * ° 150 °2o* °2SW °27"So3_0932.S °3S* °37*5°qOe °qZera°qca_ _SQ'/
Reynolds number at transition - onset VS Alpha and Panel number ...
DATA (_IRANSIIoL}, L=! ttq)i23.3_00.,183000..|37000..116000''76000''
• 77CC0, 16COC0 i =16000, 13gI_CQ" i 26_00, 122000" _ 22000e _22000" t ..........
, 2?C"JOelDATA If4TRAN%I2,L) _ L==I 'lq|tla_'P'_JOO''l_SOOO'tBlOOO'w6?OOO'e6OO00"*
i 5 | C,_O, o_SCg_, 139000" 13_000i °29C00" ' 26DOOe i23000i 120000° I
• 15EoOilDAta (f<trANsi:_,u),L=i'|qi/e6SOO''bS300''_S200''_0800'''_4_OO'"
"o 29_0,,2582_+ '22500-* ' 177C0. I i79C0" t 16200" I 1.500Q=_ | Li ] O0" ' ........
• 17_0004DATA (kTRANS I't 'L ) 'L=I ' I q | / IS6gO" = 16000" . 17000" ' 18000. 120300" I
• 2'tSO0.,26_iO_'t2&lO0• i2_g_O" i2200'0,121_0_'120300"=19500°i
DAIA (_T rAt_5¢S't') tL=l _ I g) ll'r]_O0" s lOlO0" ' 106000 = I I lOO° _ 121CG. .
• 13S,300,1=t2C_ • _ 1 u'lO0• ' 137[_o" ' 13 i O0 • ' 12700 . '`! 2'100. _ 123_0 " ' .........
• 1;'330.1DATA (kTRAr'S (6 .L ) 'L=| ' lq ) / ] 21 _0. _ I I tO'De s IF'Ju'_O* j 100000 'gP'DO" '
• _600",95C_' ,9900. ,9.00.19300" ,930C•,9Z03" ,9200,,920C'I
DATA (RTRAN5 (7' L ) 'L=I ' 1_' ) /3_'7_C'" ' 3 I _O0' '245C:0" 'z I _'Oo" ' 19HC'O" '
i |7._00.' 16COC, , lq6Oo.' 133_9''12300" ,I 1200, ' 10200,, ,9300"'7500"I
DATA (_TR^NSI_'L) , L=t ' lq ) i2SrJgO" _ 19600, = 15_0_• _ 13500' ' |2500" '
• I I_gO., 113r'_. ,I"J600" ,q_OO•,_)P'_'O''78_''6700''_500°'3100"/
DATA-i_ T RAhS (9 ,L ) ,L=I _ Ig )/201C_- • _ 153"_0 ' ' IO6_C,. ,93000 = 9O_.U, ,930G,,
- 9700, , l_5_r_" _ ! _5(_0 • . 9_.,C0. ,6900• ,gSO0, ,3g_. ,2700' /
DATA (;_TRA;,S(IC,L)'L=| 'lq)/9200_5:_''7e_o''71oO•'b_6D''S7SOe'
• 5rJ'_'3, ,I121_.,,35 _O" ,302_.,2670.,2q3_0 ,23_,.'3. IZ38a,l
D A 1 .s, (kTRANS( I l ,L ) ,L=I , l_ |18 I_ O• ' 6790' '53¢30" '=t/NO" '_ 150' ' 3600. '
c,_ BO 199 1730•,|5BD', lSoO'' l_IBO'/• _) t"..;O " 126-,.. , ,22 I I _• 'DAIA (;<TRAhSII2oLI=L=IoI'4) 115g_O'°1220C•'9_tO'_'_8200e=7200''6700''
" _) _, 3 0 , I ('f'O_ . , S r_ 0 0 I ' 3 i _ 0 n . , 3200. ,27_0. iZZOO, , lOOO,/
DAT._l-.l;_Af,5(1)_t.),|.=l,tg)ll_"tq_'3'O'l ......................................
L)._T ._ (:'TRAr;SII_iILI,L=I,I_III 9.42(19_'I
CIAtA (_,:'P._::s(IS_LI,L_-I _l_i)/l_'2_'_4L I'3"I
L}ATA (vII.:A_,'_,IIe,,LIiL=I Jlql/t:l'37"JvJ
L_A T A { ;.: I ",,a,,S I17 iL | =t..-.t l | q ) t l q'_r=,N'3rJ'J •/ .
DAT _ {:._r;:A',_'.',(I_,L) ,L=I , i _1 I | _¢r,_O00°t
L'AI_ (*(t_A;:_tlV_L)_L=tt|'i)/3_70, '_3_'0'_650" _23_'-'2_NC1"_1750"_
. . ., _,; • o6bO•/, 1,I.j..,.,126_,,1._9_•,95(}o o8=,0, ""J.o720
t,_T_ {.i!R''._(2.;;vL),L=I oI_)11_II¢/30 '/
._'_* i._IK,,_'!%(21 _LI,L=L ,Ig|/l'tiS'300'/
.._T'. . T;_',5(22_L.I,L=l i l'l)/t_. 1362 "J:3"l
_'::: _ ;'.,:,',';',{23,L)oL=I o1'_1/1'v,67'22C't /
.'',:_ i ::',_'.T, 12'-_lL) iL" l i1't)/$'_''77'_30'/;r';_ _ T'.AhSl2"_,Ll,L--.l,l")/_,'ir,O•,Ht_7[_','3 _1200'2920o°2gB0"°2100°°
• I' _, , 1c.!,?. , 136'._, , I 2F!" ' ' : lVO' ' I::Z3' '92_" 'UeO' I
" _ i T_.:i':,_2t, I!_I,L_I Ilqlll'liC;20_'/'j ; .T.vA?,,_127 iV ) ILi: | I I it | /'; $!'_t_ • I .)lt'_ • I 26rio " ' Z _tl r'] t I 2CI_'_J • I | 7 _CI I I
• I.i. 1117=,3.,1_7 :.i91 _' if; t"l• , 7't0 • 17 !_ " i 7Q:} ' /f_ _" °' (7 ".
' I,%'( '7 I = I , I 't • O_ ](;_' ° .lib)O• I_i|(i'J• I )t,_'Oi t, • I;':. 2 ,L.) t. ) IL't'F?''6'l?_J
-" " "')Z"', 71700,2t A'• il90].1
, •. _ onsc t.
_i_ _ 'It I', o2'_ _22 r,,2 -_' I ,7 r,,_._ 32 _,35 ,37,5,'_C o't2 _.,,
i ,¸
Page 33
ON No. : 1.4-4-5Page: 32
6.4.7 SUBROUTINE REQUIRED
None
4
Page 34
.k
-- 6.4.8 FLO_,_CHhRT ........ - -
®
,.PRODUCIBII,I'[_OF THEOIII(IINAI, PAOE Ig POOR
q _
Cet_lt'tt_ :_-'"]
L-Z,:',:,.1
I _:) fOrT), |
|__ _C_Lrr_2"_.I, --- j
fj:.:.,,f,.-_
CT_T-_,_.__ _L_o_
DN No. : 1.4-4-5Page:' 33
,,,,.
Page 35
DN No.: 1.4-4-5Page: 34
6.5 Tl
6.5.i PURPOSE:
6.5.2 INPUT:
QDT
NPANEL
NP
IV
6.5.3 OUTPUT:
CoIlI;_ion
TARY
6.5.4 ALGOR!THH
6.5.5
6.5.6
6.5.7
TI
Subroutine TI computes the surface temperature as
a function of heat rate.
Heat rate (BTU/ft2-sec)
Array of TPS panels and control points
TPS panel or control point number
Vehicle number
Array of panel surface temperatures (°F)
See flowchart Sec. 6.5.8
CALLI,qG SEQUEIICE
None
CO_ISTAT;TSRE_II P,ED__
C = .24710577 E + 13
SU_F_OUTIICEREQUIRED
Nor;e
3,
Page 36
'V
4...• o
" d)!
.,ft...
t
"|'tlo
i',jJ,,_¢_v_____l
-. f"
'1"_
[--___u_,,_x___>:_.::_i!_ez_1
?
....F,;,;;....
DN I'lo.: 1.4-4-5
Page: .36
Page 37
ON Plo.. 1.4.4_5Page: 37
NVAL
X(I), I = 1, NVAL
Y(z), z = 1, PIv_LX/
6.6.3
Subroutfne TABLE fs a lfnear fnterpolatfon routfne.
NUmber of Values
Zndependent varfabTe array
Dependent varfab]e array
Independent varfab]e
Y1
Dependent var_ab}e6.6.4 ALG_RITH_f
See flowchart Sec. 6.6.8
_+_ __
C_11 TABLE (PIVAL, X, ,', Xl, Yl)
_'_.+__N= 1
6,6.7 SUE_OUTIPIr D_
f_one
Page 38
I
0
_o
<\._,,-i/_
lT;;---i-7.,-rz-1,,I._
I,_,_:"__r-lI
Page: 38
Page 39
¢
, /,_'.
I '*',_'"" /
• ,;f,;.._._,.,_j(b,./ ....::,tY)-'= g(,._ .r ( 'f
(_(.N,-.t')-- x(_))-(XP -/.<ff_)
DN No.: 1.4-4-5Page: 39
!
Page 40
DN No.: 1.4.4-5
Page: 40
7.0 REFERENCES
1 James W. Tolin, Jr., "Shuttle Orbiter Thermal Protection System• II
Simplified r.lathV,odel for the 089B Vehicle.
2. G. W. Mauss, "RI/Houston Simplified Weight Syntheses Program
Content," Rock_,;ellIn':ernational Internal Letter SEH-ITA-74-
156, llove;:_ber4, 1974.
3. Software Development Branch, "Space Vehicle Dynamic Simulation
(SVL)S) Program Description," Johnson Space Center Internal Note
No. 73-FI.I-85,May 23, 1973.
4. J. K. Isherwood, "Generalized Plot Program, TRiCPLT User's Manual,"
TRW Document ll176-H594-RO-O0, August, 1970.
,!
Page 41
APPENDIX A
PROGRA_,_GIP
I i
Page 42
DN No.: I•4-4-5Page: A-I
l.O GENERATE INPUT PROGRAM
GIP is an auxiliary program which accepts a tape of thermal
boundaries data from TBAP and plots the thermal boundaries using
the TRWPLT (Reference 4) routine• The GIP was written to facilitate
the method of inputting data into the TR!4PLT routine. An example
of the printed output from GIP is given in Figure I. Examples of
thermal boundaries which were plotted using GIP and TRWPLT are
presented in Figures 2, 3, and 4.
I•I PURPOSE:
GIP accepts a data tape froi_1TBAP, processes the data, and outputs
calcomp or micrefilm plots•
1•2 It',PUT:
ICCOKP
KU;_IT
I;TRAU
F,C!',C,
CI'.:;!.T
XLL:;_:
L,'..CL
Type plot indicator
= 0 Ca]comp
= 1 Hicrofilm
D_t,z tape it;put unit
TaIJU type selector
= 0 Input (',_t_tape. was generated u_ing FOP.TRAH
;;rifr:s _.:_'_er.ents.
NTF,,,_,,S_-. , (je1:_':;rated usi1:9 '_""
vri t_ _*"_,'. .....ts
Plot _y:;'!:_,l =el_.ctor
_',_]Itipliceti','e factor
ll:,i_,l:'endent_.xis idcntification
[:(,;.:.r::ic,_:[exit ic!_,_tLifi.'.:,:tic,,;
L .#,
Page 43
1.2 INPUT:
TITLE
IPNF
JANF
NVAR2
L
M
1.3 OUTPUT:
ICCO_IP
KUNIT
NTRAN
NCHAR
CMULT
XLABEL
YLA_EL
TITLE
IPRINT
hOi i',[C
ON rio.: I.4-4-5
Page: .A-2
(continued)
Graph title
Total number of file; on data tape for a given plot
Actual file number
Dependent variable
= 2 Altitude (ft/sec)
= 3 Drag acceleration (ft/sec:)
= 4 Dynamic pressure (Ibs/ft:)
Number of cards to specify scale parameters
Number of cards to specify axis identification
Calcomp/microfilm indicator
Data tape input unit
Tape type selector
Plot symbol selector
Multiplicative factor
Independent axis identification
Dci_endent axis identification
Plot title
Pri,_t i_di(::_tor
= -I PriP,t Fiot titles c,nly
- 0 Su;;p:'+'_,sprint
- l Print plot title._,and data r,eir_ts
: n Print titles and first r_data p_ints (i,_ l)
U_,.t_tape /,_,'r_:_,_tindict:for
: _ T,:!',c,,,n',aiz_,3I',_c tl,_,non? t3?c. of rr,c_:;d.
:= "l "I<:1"_:(c.; ..;ii,S el:IV or, c' '(.-jI'" cf r_.t,._r,_.
Page 44
DN No.: 1.4-4-5
Page: A-3
1.3 OUTPUT: (continued)
LINGER
SKIP
NOADV
PLOT
ENDLST
ENDPLT
ENDRUN
REWIND
End-of-file frame advance indicator
= 0 Frame or graph will be advanced normally.
- 1 The variables specified by the first PLOT card
following the ENDFIL card will be plotted on the
current plot.
Number of end-of-file marks to forward positioned over
Frame advance indicator
= 0 Frame or graph will be advanced normally.
= l The variable in the PLOT list will be plotted
on the same graph as the previous plots.
Specifies variable to be plotted
Plot list temination symbol
Plot input termination symbol
Job termination symbol
Rewind the input data tape
1.4 CAtLIrIG SEQUEflCE
tIot applicable
1.5
1.6
co!zsTj_;i_TS I F:ED
r!VAFcl= 1
tio_e
J
|
Page 45
DN No.: 1.4-4-5- Page: A-4 F¸
1.7 FLOWCHART
e.
i:
¢,
.I
_I__!___L_- _ I _latlve velocity
- -- --II . Basic Inputs
, such as:_L I ICCOMP, KUNIT,
.......'q_........, I---- I NTRAN, rlCHAR, ,
db-AI' 1
NVAR2 Dependent plot
varlable
</'- p_:, ....... ,"',,- "} I
t
_:::!::::___t...."\ 2:"..............:]'
[.
1t f,]",\/
Page 46
1.7
8
FLOWCItART (COItT'D) -DN No.: 1.4-4-5Page: A-5
Page 47
1.7 FLOWCHART(CONT'D)DN No. : 1.4-4-5Page: A-6.
Page 48
1.7 FLOWCIIART(COl'If'D)z
i
r
( .............._2
DN 11o.: 1.4-4-5Page: A-7
i
t
Page 49
°.
",°
DN _1o. : 1.4-4-5Page: A-8
Q
t
ItI
1I
i,
I Z
• e • _ e_ e • • e _ e e • e • •
I
•EPRODUCIBILITY OF THE
ORI(RNAL PAGE 18 POOR
f
Page 50
,l¢
DN No.: 1.4-4-5Page: A-9
|lOOll,
80OIIO,
Igeeit.
|4elel.
9OOOi.
.. 0
I_llullr _._. tOmvnO a, Pelm! ! ixlaa_"L |OVlOiiltS NOV PLInll .
- BODY FLAP - -!- - - ]- 7-- - !-- "-_- _ -
crtttcal Temperature= eSO0°li /i // / _ !/J/ i! )1
.............! i ,,..... 1 -_-_._ _. _:-=-- ......tl,-_
.... ....i "!/1 II I i' It tit I' !.1 l_:........... _.1_..... t,/.......t L_i.........,_._t,,,_-i...._...... ,_....'_,_".........._............i --I _.! !l ll,!,,t,!t,, _,t,li tt,
................[ii i f_/ t1 i ! it i ! ! it i ! Li ! i I i i I i i ! 1!I....... i .......t l...... ..,__[...........;....... :__......... .__,_..l.__,...... ,.........!ii'.......................................... 1......-,---I...... '..... ;_...... i.........._=........... _-1......... ,r trt i11 t !1- 'l;_!,il i!I ',ltlti'ii '.
l ] !'l 1 Iii_iiiilliii!liiili l!!:
............ i ......I!tt1"--t.....11-1......!ll--' :_i._._.lll...........Ill' ...............i i ! I i 1 I i ! !t i i ii'l....... _................... :
li I 1, .1 i .,l t ,, ,,,1-.,..1 i I I l'i_ii il 1 ,:
..... I -t-r..... l'tr _iil-!.,!i tri_ii',li;',l_, _: < ,/ lli[/tilllll, i_ ;!iiii!i '.iliiiiLli,!
.......................... ;.....;._._.,.__.,. l_,.........=_'_i__;.._i....-_......'.......',................[ " ' i ! i [ I : , I ' ' ! ', iI tl/i,_i,t ,,t, ,,,, .,..,,i,_ _,,.
.....L..... !.._l!_L]._L.!!....l_.!.!_.i !_!._'..!]_. !__!.__/.t..]L i_!__I_.i_Z _l.'.i-__.liliittilil!!i,lliili_iti_lii':i _,.... L .................... _ .............................. _..., ........ _'......................... ; .... • .......... ;. ..............
IlifLt 11 I'_ llEL_CIII,I#¢
7
i!
,>,i;
l l,.'i;o 2. [;,".",it _ rf T; ....... ] [i_'<._, T_'i,.L il'_ li/V ! '._i'-.
fl ll Ill iillnlililllllini/li/miilllillll
Page 51
IHit.
t
I
|
C
¢ It
_ti L
t|
i
!
I
0
i
o
r Iot$
le,
t
DD ,_!o.: 1.4-4-5Page: A-IO
;|Iui| _. COIIIOL POIII! | I'mtlIRIL |PUIOiII|$ OIV PLIIII! o
__BODY FLAP .... ] ........................ !_
Critical Temperature = 2500 ° I i ! / I......--.--__,,-_--t---t--t--t-_--j................ ......... ......
Deflection Angle = 16.3 ° I ' '
- /
_.t
" 'i ........L I'-! !1 I _ _ 1fi..........., i !.... _! _.!..... , ,i i!!-!- . I .ii !--il -!--ip,!-J ....!-.! 1l I' ,..... f ............ I 1!:!ii' ,,,,,,,, •............................ ,,-.-, .......... ; ; .... , ....... :--L. #_ I ..... l ..... _"
tli I ! _,_ l-t-.......... =..' . :._ l..j__i_ i ..... !. ; '. : ..... '._.___-_',.__' __I..'--I - !--
I l!!t l,i! _I !ilii]i.iil_(il'li( %#l_'tllv,l/ _.
l i,:'_,v.:: 3, L',,,,:;I_. c,f "it;,.-l (:',ta
ORI(IINAL PAGE IB POOR
[I_,L in {;/V Ii_'.ii,-,,
Page 52
I11
iL
*l
T
DII ,_'o.• I .4-4-5
II Page: A-If
Firu,'c q. "" _,", of "i r,_:-I ... f' ill .,. ,._.,, , _'.i.;_.
:>,
