Structural considerations for aircraft payload modification-P-3H zero fuel weight increase.

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by  Culpepper, Steven Drew.;Wu, Edward M.

NAVAL POSTGRADUATE SCHOOL
Monterey
California
,
THESIS
C9Z.575
Structural Considerations for Aircraft
Payload Modification-
P-3C Zero Fuel Weight Increase
by
Steven D. Culpepper
March 199i
Wu
Thesis Advisor: Edward M.
Approved for public release; distribution is unlimited.
T253981

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b Declassification/Downgrading Schedule Approved for public release; distribution is unlimited.
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»Javal Postgraduate School (IfApplicable) 67 Naval Postgraduate School
c Address (city, state, andZIPcode) 7b Address (city, state, andZIPcode)
Monterey, CA 93943-5000 Monterey, CA 93943-5000
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Program ElementNumber | ProjectNo | TaskNo | WorkUnitAccessionNo
STRUCTURAL CONSIDERATIONS FOR AIRCRAFT PAYLOAD
1 Tide(IncludeSecurityClassification)
MODIFICATION- P-3H ZERO FUEL WEIGHT INCREASE
2 Personal Author(s) Steven D. Culpepper,LT USN
3a Type of Report 13b TimeCovered 14 Date ofReport (year, monlh.day) 15 Page Count
Master's Thesis From To March 1991 77
6 SupplementaryNotation The views expressed in this thesis are those ofthe author and do not reflect the official
ic-licy orposition ofthe Department ofDefense or the U.S. Government.
Cosati Codes 18 Subject Terms (continue on reverse ifnecessary and identify by block number)
Aircraft structures. Center section wing box, Euler-Bemoulli, Finite Element model. Structural analysis
9 Abstract (continue on reverse ifnecessary and identify by block number
TheNavy isconsidering the feasibility ofincreasing thepatrol aircraftP-3C zero fuel weightenablingavionics and payload
rowth. This analysis examines the consequences to the structural requirements of the center section wing box. Two solutions to the
tructures fieldequations are investigated: asimplified hand solution forpreliminary feasibility calculationsanda more precise
olution for design analysis. Together, thesolutions providea necessary check for the results. The simplified solution employs the
luler-Bernoulli assumption which generates asetofintegrals expressed in termsoftheassumed displacements. These integrals, when
ombined with simplified geometric shapes and symmetry, ultimatelyproduce adecoupled matrix solution. The precise solution uses
PC based finite element method which simultaneously solves the fieldequations forbasic elements tobe linked togetherwith the
ppropriate boundary conditions. Forthecurrent 135,000poundgross weight lg loadcondition, the internal stresses calculated by
miteelementare in accord with thoseby simplified handcalculation. Extensions from this modeling will generatedesign criterion
3rthe target95,000poundzero fuel weightaircraftaswell as alternate flightor taxi conditions.
Distribution/Availability of Abstract 21 Abstract Security Classification
X unclassified/unlimited same as report DTICusen Unclassified
2a Name of Responsible Individual 22b Telephone(IncludeAreacode) 22c Office Symbol
'.dward M. Wu [phone] 67
DFORM 1473. 84 MAR 83 APR editionmaybe used until exhausted security classification of this page
All other editions are obsolete Unclassified
Approved for public release; distribution is unlimited.
Structural Considerations For Aircraft Payload Modification-
P-3H Zero Fuel Weight Increase.
by
Steven Drew Culpepper
Lieutenant, United States Navy
B.S., United States Naval Academy, 1983
Submitted in partial fulfillment of the requirements for the degrc >f
MASTER OF SCIENCE IN AERONAUTICAL ENGINEERING
from the
NAVAL POSTGRADUATE SCHOOL
March 1991
ABSTRACT
The Navy is considering the feasibility of increasing the patrol aircraft
P-3C zero fuel weight enabling avionics and payload growth. This analysis
examines the consequences to the structural requirements of the center
section wing box. Two solutions to the structures field equations are
investigated: a simplified hand solution for preliminary feasibility
calculations and a more precise solution for design analysis. Together, the
solutions provide a necessary check for the results. The simplified solution
employs the Euler-Bernoulli assumption which generates a set of integrals
expressed in terms of the assumed displacements. These integrals, when
combined with simplified geometric shapes and symmetry, ultimately
produce a decoupled matrix solution. The precise solution uses a PC based
finite element method which simultaneously solves the field equations for
basic elements to be linked together with the appropriate boundary
conditions. For the current 135,000 pound gross weight lg load condition,
the internal stresses calculated by finite element are in accord with those by
simplified hand calculation. Extensions from this modeling will generate
design criterion for the target 95,000 pound zero fuel weight aircraft as
well as alternate flight or taxi conditions.
in
TABLE OF CONTENTS
INTRODUCTION
I. 1
PROBLEM DEFINITION 4
II.
BOUNDARY CONDITIONS
A. 4
FUSELAGE LOADS
B. 4
WING LOADS
C. 5
GROUND TAXI LOADS
D. 6
CONTROL SURFACE LOADS
E. 7
III. GENERAL SOLUTION TO P-3C 8
SOLUTION USING EULER-BERNOULLI ASSUMPTION
A. 8
1. Summary of Field Equations 10
HAND CALCULATION
IV. 21
WING MODELING
A. 21
FUSELAGE MODELING
B. 24
V. FINITE ELEMENT METHOD 30
PROCEDURES
A. 31
1. Geometric Definition 31
2. Boundary Conditions 31
3. Model One 32
ALTERNATIVE SOLUTIONS (PROBLEM EXTENSION)
VI. 35
A. BENEFITS OF THE DUAL APPROACH 35
1. Configuration Change 35
a. Example 1 36
2. Changing Material Properties 36
Example 2 37
a.
RESULTS
VII. 38
IV