Dynamic Modeling and Modal Analysis of an Air-to-Air Missile

111 Pages·2012·4 MB·English

AD-A245 957
INAVAL rvUTGRADUATE SCHOOL
Monterey, California
DTIC
A ELECTE
FEB 1 41992 J
D M
THESIS
DYNAMIC MODELING AND MODAL ANALYSIS
OF AN AIR-TO-AIR MISSILE
by
Michael Allen Shutty
September, 1991
A Thesis Advisor: Edward M. Wu
Approved fur public release; distribution is unlimited
92-03668
s;(cid:127)z(cid:127) 41z,
Unclassified
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4 PERFORMING ORGANIZATION REPORT NUMBER(S) 5 MONITORING ORGANIZATION REPORT NUMPER(S)
1b
6a NAME OF PRREF ORMING ORGANiZTIN OFFICE SYMBOL 7a NAME OF MONITORING ORGANIZATION
Naval Postgraduate School (If applica ble) Naval PosItgraduate School
6c ADDRESS (City, State, and ZIP Code) 7b ADDRESS (City, State, and ZIP Code)
Monterey, UA 93943 50001 Mtontere-y. CA 9394356000
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_______________________________I,-,______t W{ 1`101-1 N'O,, I o ,k MtA-.0
11 TITLE (include Security Classification)
DYNAMIC MODE)1.1ING ANI) MOI)Al.ANAI.YS1I 01"AN AlI-.TO-AII{MISSILEý;
12 PERSONAL AU1iT OR(S) Nljehoel A.Sliutty
7
1 3a TYPE OF REPORT 13b ThIME COVERED 4DT OEF REPORT (year. month, day) 15 PAGE -COUNT
Mi.sser','I'hviiso Fromn 114p4ii1e JIII1
16 SUPPLEMENTARY NOTATION
IThe views e xpressed in this thesis tire those of the author aid do not reflect theCo lbc al policy or posi tionot t.if DeI)epartmflent of IDefeiist. or thle Ui S.
Governiniei.
17 COSA~tCODES 18 SUEBJECTTE RMS (continue on reverse it necessary 'ind identity by block number)
FI1I D GROUP SUBGROUP Vibration, modal analysis. finite element modeling, dylinaiie modeling, P 3, AIM 9
19 ABSTRACT (continue on reverse if necessary and identify by block number)
~iiiisiiii.
Th~e P'-3 Orion liatruil aiirplaiii has u nuied [or ii:aoiLrr air miissile sýYslIUi 101jis uUFgIVliIUstL cliiiiixal~i crahutn IL' kiug raligci III
response tsi this need, the Navktl Air lest Cetnter was tasked in 1989 toj conduit a 1) /AIM.9 (Side%i idudr integration programl. In support il this
prtigrani, a vibration test stand was established at NIPS, and a ground vibratioii characterizatzioi, was cuiidLiCtid to determine ifo! potential flutter
p roblIi ii exstoted. This Lesi. resýulted in the d eve ltIimi t of a two-degree (,I IreediiIorn iuped-mssndI 1ileCeruuui Idtrmiatilitli
niissile's resoniance rudes iii pitch With the reuent terminationoift he P-7A. the P-3 community is now looking to the P-3 Orion If Programt to
cairry it inuto the 21st century. Tl'l Orion 11 will must likely have a beefed tip wing structure. necessitating ain analysis Ofthibwinl, in conjunction
with the AIM-9tmissile. This iivestugation responids to that requiremeont by conicurrently developing a miathienatical model if the AIM- numissile
usi ng fitni te e lemen t techaniq ues to analytically determ inte its, niidalI pi arameters, a rid settinrg op a ruiodalI test system to qua ntify the paramnete rs of
A thib model bye), perinientally deterrni niiug Lte niissulesb natural freqtuencies. moude shapes, and t ra nsient respoinse- This folIly uiistrumiented te.iL
system aud associapted methotdologies COUItldten be thiebasis foe cuuiductliug a ci~nililete mo~dal testtif thei AIM 9 nuissile systemn,as wll as to
qucantulfy the v ib ration charac~teristi cs (it iothier cuaidid idte ni issi le synitems firtt he P-3 a nd its event ualI ucceswur.
120
[)IS1RIBUTION/AVAILABILI .Y OJ ABS TRACT 21 ABSTRACT SECURITY CLASSiI iCAT ION
El 'INLLA SS11IW Ai,.litiM i, Ii O. AMMi HPiti O R] 3t i Is icas
22a NAME Of RESPONSIBLE INDIVIDUAL 22b TELEPHONE (!nclude Area code) i2c OFFICE SYMBOL
P'rofessor Edward M. Wu ______ __ 408) 646 3459 7 AA/Wu
DD FORM 1473,84 MAR 83 APH edition riuuy be used Until exhiitstedl SLCUFIIJYCLASSIFICATINON 1TISPG
All other editionb airc obsolete U nclassified
MR,
Approved for public release; distribution is unlimited.
Dynamic Modeling and Modal Analysis
of an Air-to-Air Missile
by
Michael Allen Shutty
B.S., Pennsylvania State University, 1983
Submitted in partial fulfillment
of the requirements for the degree of
MASTER OF SCIENCE IN AERONAUTICAL ENGINEERING
from the
NAVAL POSTGRADUATE SCHOOL
September 1991
Author: A
Michael A. Shutty -
Approved by- .___,
Edw d M. Wu, The::is Advisor
./ /
Gerald -. Lindsey, Secon
Daniel J. Coiliiir', Chairman -
Department of Aeronautics and Astronautics
iii
ABSTRACT
The P-3 Orion patrol airplane has a netd for an air-to-air missile system for defense
against enemy aircraft on its long-range missions. In response to this need, the Naval Air
Test Centcr was tasked in 1989 to condvct a P-3/AIM-9 (Sidewinder) integration program.
In support of this program, a vibration test stand was established at NPS, and a ground
vibration characterization was conducted to determine if a potential flutter problem existed.
This test resulted in the development of a twc degree-of-freedom lumped-mass model and
experimental determination of the missile's iesonance modes in pitch. With the recent
termination of the P-7A, the P-3 community is now looking at the Orion II program to
carry it into the 21st century- The Orion II will most likely have a beefed-up wing
structure, necessitating an analysis of this wing in conjunction with the AIM-9 missile.
This investigation responds to that requirement by concurrently developing a mathematical
W
model of the AIM-9 missile using finite element methods to analytically determine its
modal parameters, and setting up a modal test system to quantify the parameters of this
model by experimentally determining the missile's natural frequencies, mode shapes and
transient response. This fully instrumented test system and associated methodologies
could then be the basis for condu(cid:127) ting a comprehensive modal test of the AIM-9 missile
system, as well as to quantify the vibration characteristics of other candidate missile
systems for the P-3 and its eventual successor.
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TAPLE OF CONTENTS
I. INTRODUCTION .................. ................... 1
A. BACKGROUND ............... .................. I
B. MISSILE MODELING TECHNIQUES ......... .......... 5
C. IMPORTANT DEFINITIONS ............ ............. 6
II. ANALYTICAL MODELING .............. ............... 9
A. FINITE ELEMENT METHOD BACKGROUND ...... ....... 9
B. MSC/PAL2 FINITE ELEMENT ANALYSIS SOFTWARE . . 11
1. Introduction ........... ................ 11
2. Basic Program Operation ..... .......... 12
a. File ............. .................. 12
b. Edit ............... .................. 13
c. Analysis ........... ................ 14
d. Graphics ........... ................ 16
e. Composite Capabilities ... ......... 17
f. Advanced Capabilities ... ......... 17
3. MSC/PAL2 Analysis Procedure ... ........ 18
4. MSC/PAL2 Limitations ....... ............ 20
C. MSC-PAL2 SIDEWINDER MISST LE ANALYTICAL MODEL 22
1. Model Geometry ........... ............... 22
2. Determination of Modal Parameters ..... 26
3. Modification of Modal Parameters ...... 29
iv
Ill. EXPERIMENTAL MODAL ANALYSIS ............ 3Z
A . GEINERAI . . . . . . . . . . . . . . . . . . . . . 32
B. PREVIOUS WORK ACCOMPLISHED ......... .......... 35
1. Test Setup .......... ................. 35
2. Previous Results ........ .............. 36
C. MODAL TEST SETUP CONSIDERATIONS .......... 38
1. Transducer Selection .......... ............ 38
2. Transducer Mounting ....... ............ 40
3. Transducer Calibration .... ........... 41
4. Excitation Techniques ...... ........... 41
a. Shaker Excitation ..... ........... 41
b. Impulse (Impact) Excitation ...... 43
5.. Specifying the Number of Degrees-of-Freedom 44
D. SIDEWINDER MISSILE MODAL 2T.ALYSIS TEST SETUP 45
1. Test Structure .......... ............... 45
2. Test Equipment .......... ............... 46
E. MODAL-PC SOFTWARE BACKGROUND ... ......... 50
1. Introduction .......... ................ 50
2. Major Features .............. ............... 50
F. EMODAL-PC MODAL TESTING FUNDAMENTALS ... ..... 51
1. Test Procedures. ............. .............. 51
2. Modal Testing vs. Operating Deflection Shape
Test ................ .................... 52
a. Modal Testing ....... ............. 52
b. Operating Deflection Shape Test .... 52
3. Curvefitting .......... ................ 53
v
a. Coincident/Quadrature (Co/Quad) Fit 53
b. Circle Fit ........ ............... 54
c. Rational Fraction Polynomial Fit . . .. 54
G. EMODAL-PC TEST PROCEDURE ..... ........... 55
1. Configuring the General Set-up ......... .. 55
2. Geometry ............ .................. 57
3. Data Acquisition ........ .............. 58
4. Extract and Animate Shapes ... ......... 61
5. Store Project ......... . .............. 63
6. Recall Project ........ ............... 64
7. Prepare Reports ......... .............. 64
IV. CONCLUSIONS ............... ................... 66
A. ANALYTICAL MODELING ........ .............. 66
B. EXPERIMENTAL MODELING ...... ............. 67
C. COMBINED TESTING AND ANALYSIS ... ......... 68
V. RECOMMENDATIONS ............ .................. 69
A. ANALYTICAL MODELING ........ .............. 69
B. EXPERIMENTAL MODELING ...... ............. 70
C. COMBINED TESTING AND ANALYSIS ... ......... 70
APPENDIX A ................. ...................... 72
APPENDIX B ........................................... 82
vi
APPENDIX C . . . . . . . . . . . . . . . . . . . .. . 90
APPE(cid:127) DIX 0L) . . . . . . . . . . . . . . . . . . . . . . 93
LIST OF REFPERENCES............................................98
BIBLIOGRAPHiY .............. ..................... 100
INITIAL DISt mRIBUTION LIST ..... .............. 101
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LIST OF FIGURES
Figure 1 Siduwindul Missile ............ ............. 2
Figure 2 AIM-9 Missile System.... .......... ............ 3
Figure 3 Modeling Techniques ............ ............. 6
Figure 4 I'AL2 Program Exccution ..... ........... 13
F igure 5 MSC/PAL2 Suggested Oider of Analysis . . . . 2]
rigure 6 MSC/PAL2 AIM-9 Geometry Model .......... 23
Figure 7 Combined Testing and Analysis .......... 33
Figure 8 Missile Modes for Oingle-Rail AIM-9 ..... 37
Figure 9 Spring - Mass Model .......... ............. 36
Figure 10 Typical Shaker Setup .... ............ .. 43
Figure 11 AIM-9 Missile Modal Analysis Block Diagram 47
Figure 12 AIM-9 Missile Modal Analysis Test. Setup . 48
Figure 13 EMODAL-PC lest Procedure ........ .......... 56
Figure 14 AIM-9 Missile Model Mode 1 Response . . . . 84
Figure 15 AIM-9 Missile Model Mode 2 Response . . . . 85
Figure 16 AIM-9 Missile Model Mode 3 Response . . . . 86
Figure 17 AIM-9 Missile Model Mode 4 Response . . . . 87
Figure 18 AIM-9 Missile Model Mode 5 Response . . . . 88
Figure 19 AIM-9 Missile Model Mode 6 Response . . . . 89
viii
ACKNOWLEDGUMENT
1 would like to expiess my gratitude and appreciation to
thu following people, whose support and confidence in my
abilities helped me make it through these last fifteen months.
First, I would like to thank Professor Ed Wu, my thesis
advisoi, foi his guidance, patience and always optimistic
outlook on life. It. has been a privelege working with you,
and an even greater pleasure knowing you.
Secondly, I would liko to thank and acknowledge the
support and advice I received from Mr. Ken Ranger of the
MacNeal Schwendler Corporation, without whose help I might not
have been able to get as far on the AIM-9 model as I did.
Next, I would like to thank Mi.. Tim Twigg fLion the Naval
Air Tcst Center, who not only got me the missiles in the first
place, but also obtained much-needed information about the
missiles on the spur of the moment.
My deepest gratitude goes to my wife Maureen, and our two
children, Michael and Meagan. I can probably never make up
for all. those times when I coulan't go where you wanted to go,
or do what you wanted to do, but please believe it was for a
good cause. You may never realize how important your constant
I
Jove, understanding and encouragement have been to me, not to
mention the help with the typing. Thanks Lor being there when
I needed you.
ix
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