STARS: An integrated general-purpose finite element structural, aeroelastic, and aeroservoelastic analysis computer program

186 Pages·5.7 MB·English

by  Gupta, Kajal K

NASA Technical Memorandum 101709
Revised
STARS---An Integrated General-Purpose
Finite Element Structural, Aeroelastic, and
Aeroservoelastic Analysis Computer Program
i?¸!!
K.K. Gupta
G3t :_9
January 1991
!onal Aeronautics and
:iceAdministration

Errata and addendum to
STARS An Integrated General-Purpose
Finite Element Structural, Aeroelastic, and Aeroservoelastic Analysis
Computer Program
NASA TM 101709 - Revised
The following corrections should be made to the manual:
Page 41 should read]
__iIi:
E_DI END2 END3 END4 PXl/PX2 PYIIt:'Y2 PZIIPZ2 IvKI/MX2 MYI/MZ2 I_I_
• i NO. SYT SMYT SMB SYB SKYB
i_ _• _q35 END6 END7 I_D8 SMX SYY SZZ S0(Y _/Z SZX
1 1 4 0.785577E+03 0.000000E+00 O.000000E+00 0.0(XXXX_+00 0._+00 0.O00000E+O
-0.785577E+03 O.00[XXX)E+00 0.000000E+O0 O.000000E+O0 0.000000E+00 0.O00000E+O0
2 2 4 -0.756511E-02 0.000000g÷00 O.0000(]OE+00 0.0(XXXDE+O0 O.O00(_0E+O0 0.O00000E÷00
0.756511E-02 0.O000OOE+00 0.O00000E+O0 0.(XXXXDE+00 0._+00 O.O00000E+00
3 2 5 0.464123E+03 0.O0(XX_E+DO 0.[XXX)0OE+O0 0.0000(]OE_O0 O.(XXX)0(_+00 O.000000E+OO
-0.464123E+03 O.(X)OOOOE+00 0.O00000E+O0 O.000000E400 O.(XXX]OOE+00 O.O00000E+O0
4 3 5 0.807432E-01 0.O00000E+00 O.OCKXXX_+00 0.O00000E+O0 0.000000£+00 0.000000E+00
-0.807432E-01 O.000000E+00 0.000000E+00 O.000000E+00 O.000000£44_0 0._+00
5 3 6 -0.I16939E+04 0._+00 0.0(XXXX_+00 0.00(XXX]E+O0 0.000O00E+00 0.000000E+00
0.I16939E+O4 0._+00 0.000000E+00 0.000(X]OE+O0 0.000000E+00 0.00000(2E+00
6 3 4 -0.146366E+03 0.0(XX](DE+00 0.0(X]OOOE+00 O.000000E+O0 0.000(300£+00 0.000000E+00
0.146366E+03 0.000000E+00 O.0(X]OOOE+O0 O.000000E+O0 0.000000E+O0 0.000000E+O0
7 4 5 -0.627136E-01 O.000000E+00 0.000000E+00 O.000000E+O0 0.00000(E+O0 O.0(XX]OOE+O0
0.627136E-01 0.0(XXX_E+00 O.00(XX_E+00 0.000000E+00 0.000000£+00 0.0(XXX)0E+O0
8 5 6 0.177002E-02 0.O(XX]0OE+00 0.0(XXX]OE+00 0.0(XXXX)E-r{]O 0.0(X)(XX_+00 0._+00
-0.177002E-02 0.000000E+00 O.000000E+00 0.000000E+O0 0.000000E+00 O.O0000(E+00
9 6 4 0.150008E+03 0.00(XX_E+00 O.00(XX]OE+00 O.O00(XX)E+00 0.[XXXXX_+O0 0.O00000E+00
-0.150008E+03 0.00(XX3OE+(]O 0.000000E+00 0.(XX]OOOE+00 0.000(XX)E+00 0.0(XXX_E+O0
I0 4 7 0.705240E+03 0.000000E+00 0._+00 0.000000E+00 0.00000(E+O0 O.O00000E+O0
-0.705240E+03 0.00(XXDE+00 0.000000E+00 0.000000E+O0 0.0(KXX]O£+00 0.000000£+00
II 5 7 0.452271E-01 0.000000E+00 0.0(XXXDE+00 O.[XXXX3OE+O0 0.(XXX)0OE+O0 O.O00000E+O0
-0.452271E-01 0.000000E+O0 0.[XXXX)0E+O0 0.0000(X)E+[]O 0.00(XXXE+O0 0.(XXXXXE+00
12 5 8 O.000000E+00 0.000000E+00 0.0000(X_+00 0.000000E+O0 0.00000(E+O0 0.000000£+00
0.000000E+00 0.000(XX_+00 0.000000E+O0 O.000000E+O0 0.000(XXE+O0 0.0(XXXXE+O0
13 6 8 -0.180786E+00 0._+00 O.000000E+O0 0.0(XXX]OE+00 O.000000E+O0 0.0(30000E+00
0.180786E+ 00 0.000000E+(20 0.000000£+00 0.0(XXXDE+O0 0.0(XX](X_+00 0.0(X)(XXE+00
14 6 9 -0.927916E+03 0.(XX](XX)E+00 0.000000E+O0 O.(XXX)00E+00 0.(XXXX)OE+O0 0.0(XXXX_+00
0.927916E+03 0.0(XXX]0E+00 0.000000E+O0 0.000000E+00 O.[XXXXXE+O0 0.00000CE+O0
15 6 7 -0.321364E+03 0.000000w+00 0.O00000E+O0 0.(XXXX]0E+O0 0.0[X)00(]E+00 0.000000E+00
0.321364E+03 0.(XXXXX_+O0 0.000000E+(D 0.000000E+O0 0.O00000E+00 0.000000E+00
16 7 8 0.424805E-01 O.000000E+00 0.0(XXX]OE+00 0.O00000E+O0 0.000000E+O0 O.(XXXXX3E+00
-0.424805E-01 0.O00000E+00 0.00(XX]OE+00 0.00000OE+O0 0.00000CE+O0 O.O00000E+O0
17 8 9 0.837402E-01 0.000000E+00 O.000000E+00 0.[XXXX_E+O0 0.0(XXXXE+O0 O.O0(X3OOE+O0
-0.837402E-01 O.0(X)000E+00 O.[XXXX3OE+O0 0.000000E+O0 O.00000(]E+O0 O.O00(DOE+O0
18 9 7 0.000000E+O0 O.O00000E+O0 0.000000E+00 0.O00000E+O0 O.000000E+O0 0.000000£+00
0.OCO000E+00 0. O00000E+O0 0.00CO00E+O0 O.O00000E+O0 0.000(X)OE+O0 O.OCO000E+O0
? i/ii_i
19 7 I0 0.463998E+03 0.000000E+00 O.000000E+00 0.000000E+O0 0.000000E+00 O.00000DE+O0
-0.463998E+03 0.000000E+00 0.000000E+00 0.O(XXXX)E+O0 0.O00000E+00 0.00000(_+O0
20 8 i0 0.463998E+03 O.000000E+00 0.000000E+00 0.000000E+00 0.000000E+O0 0.000000£4430
-0.46399_E+03 0.000000E+00 0.000000E+00 0.O00000E_O 0.000000E+O0 0.000000E+00
21 9 I0 -0.927967E+03 0.000000E+00 0.000000E+00 0.000000E+00 0.000000E+00 0.000000£400
0.927967£+03 0.000000E+00 O.000000E+00 O.O00000E+O0 0.O00000E+00 0.000000£+O0
[Table 9 on pa[_e 58 should read 1
2
Natural frequency parameter
i::!?!i•
= _ "¢pt/D
1
Mode D.z = 0.8_ N i"2R = 100.00 rad/sec,
-- 100.00 rad/sec _'/x = i"2Y = _ = 57.735 rad/sec
7 7
1 233.57 3.9286 146.36 2.4617
2 534.17 8.9845 494.34 8.3146
3 1268.30 21.3323 1248.60 21.0009
4 1562.00 26.2722 1543.26 25.9570
5 1784.80 30.0196 1768.80 29.7505
6 2912.50 48.9871 •2898.28 48.7479
- [
ITable 12 on page 66 should read I
Buckling load parameter
Mode Exact
STARS solution solution
1 7012.33 7010.42
ILine 6.1.2 on page 80 should read[
6.1.2 ISTMN, NLVN, GR
Format (215, El0.4)
2
The first seven lines of ASE input data on page 136 should read
AE}_ TEST M3DEL -ANTI_TR_C CASE -_ = 5
SET t_ FOR A_ S(XL_IDN.
DIRECT SUI_ACE _IATICN.
EIGHT EIASTIC MEDES, PLUS FIVE ADDED RIGID BCOY-C(_'/IROLHJDES;
I_:VISED RIGID B[X)YYTRANSIATIONS, BOLL, YAW, PLUS AI_ AND RIDDER MODES.
M_CH NO.- 0.90 ALTIT, X)E: SEA LEVEL
1 17 3 i0 1 0 0 0 0 0
IThe k-type flutter input data on page 140-141 should read I
AERO TEST MODKL - ANTI_C CASE - IINTP - 1
K-FILrI'nSRSOLUI'I(AW
DII___T SLRFA(_ _QN
_ MODEL, BYPASS RIGID IK_DYbIDES IN G_NMASS
M_H NO. - 0.90 _21TtDE: SEA
////////////////////////////////////////////////////////////
1 12 3 28 1 0 0 0 0 0
1 1 0 0 0 0 0 0 0 0
1 0 0 0 0 0 0 0 0 0
0 0 0 0 0 0 0 99 0 0
1
38.89 0.90
.350 .745 .940 1.491 1.615 1.698 I.864
2.000 2.450 2.750 3.150 3.270 3.400 3.850
4.150 4.551 5.250 7.000 9.000 Ii.ii0 15.000
19.000 24.070 50.000 140.000 315.774 616.746 1200.000
Table 17 in chapter 7 on page 141 should read]
Table 17. AERO test model: An aeroelastic antisymmetric analysis using a direct interpolation
for AERO paneling.
k -SOLN p-k ASE
Mode Instability Velocity, Frequency, Velocity, Frequency, Velocity, Frequency,
number
keas tad/see keas rad/sec keas rad/sec
Fuselage fh-stbending F1 506.15 77.49 533.53 77.54 591.16 76.03
Wing first bending F2 615.75 72.26 620.85 73.02 579.69 80.09
Fin fu'st bending F3 -- -- 856.64 138.92 742.81 128.87
Analysis notes:
1) F - Flutter point
2) D - Divergence point
3) Math - 0.90
4) Altitude = Sea level
:iiii
. iil_i
_? • : iii_
,Figures 30 through 32 on page 142-144 should be as on the following pages[
:H i¸
ii;i
? i_i?'_
i:__•
4
-ij
_L •L
!i__ i
Velocity, V,keas
_,3/
L :)_ /_,4 _,2 _,5 2000
0) ' •
/_ _,
\
Damping, -1O0 \
g'
/J 7
/!:L
Figure 30. STARS ATM-k flutter analysis----damping (g'), frequency (_), velocity (v) plot,
antisymmetric case, using direct interpolation where g' = g x 200.
-ii
5
Velocity, V,keas
0 _LL ,_,1 2000
Damping, -100
g'
\,i
-200
X; /_ 6
A
5OO A 500
J
J
J
400 400
" L8 "--'---- _,8
0
"11 CD
300 ._
_300
(D I;L7-.
¢D.
O
_7_ -_
J 200 ,_,6__ 5_. .
2_4_
f_
100 J =,,,;L2,
_,1 ,3 J
:>L"
J
-200 -100 0
2000
Damping, g' "g' _<x i _. 0 1000
J V Velod_, V, keas
Figure 31. STARS ATM-pk flutter analysis----damping (g'), frequency (_), velocity (v) plot,
antisymmetric case, using direct interpolation where g' = g x 200.
6
i: ¸¸I¸ •
Velocity, V,keas
/ _2 "_ _, 2000
Damping, -100
g'
i_iii!ii_i
-20O
_500
J 5OO
J r-...
Jf j
J
J
400 J J
J 400
( J
J J
_6 '_8 J
o
"11 (D
=oo!°
300
_'7 _ o'_ _,8
-<
t...-
_,4
J
J J 200 J
LL
0 J "_ _4
J Z J w F
J
100 J J 100
Z
J _._2 -.J\
J J
_,3
-2oo -loo o -,_ X X
1000 200O
"< x >>-
Damping, g' -g'
"<.i V Velocity, V, keas
Figure 32. STARS ATM-ASE flutter analysis--damping (a), frequency (13),velocity (v) plot,
antisymmetric case, using direct interpolation.
_ '7