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Int. J. Mech. Eng. & Rob. Res. 2014 Vuyyuru Murali Krishna
and P V Anil Kumar, 2014
ISSN 2278 0149 www.ijmerr.com
Vol. 3, No. 4, October, 2014
2014 IJMERR. All Rights Reserved
Research Paper
DESIGN OPTIMIZATION OF A MISSILE CONTROLCOMPONENT USED IN A
GUIDED MISSILE
Vuyyuru Murali Krishna1* and P V Anil Kumar2
*Corresponding Author: Vuyyuru Murali Krishna
[email protected]
This paper presents a finite element model for strength analysis
of a missiles missile controlcomponent under different conditions
like pitch, roll and Yaw. Characteristics of stress distributionand
high stress locations are determined according to the model. The
high random vibrationloads imparted on Missile control component by
the other hardware during launch create anadverse design
requirement that all hardware have a natural frequency greater than
that of theMissile control component, in order to avoid damage and
failure due to dynamic coupling.Maximizing natural frequency is
generally accomplished by creating as stiff and lightweight adesign
as possible. However, designing for the resultant high loads also
requires a high stiffenedstructure. These two opposing design
requirements drive an optimization between a lightweightand high
strength structure. This paper also presents a finite element
analysis for strengthanalysis of a missiles Missile control
component under random loading conditions. Static, ModalRSA and
Power spectrum density (PSD) analysis will be carried out to plot
graph of the PSDvalue versus frequency, where the PSD may be a
displacement PSD, velocity PSD, accelerationPSD, or force PSD.
Based on the results obtained, optimization of the control
component wasalso done in this project.Keywords: Missile control
component, FEA, Guided missile
1 M. Tech Student, Department of Mechanical Engineering, Krishna
Chaitanya Institute of Technology & Sciences, Markapur 523316,
Prakasam District, A.P., India.
2 Associate Professor, Department of Mechanical Engineering,
Krishna Chaitanya Institute of Technology & Sciences, Markapur
523 316, Prakasam District, A.P., India.
INTRODUCTION
Missile control component have been, andare arguably still, the
most efficient meansof controlling a missile and guiding it to
atarget. They can efficiently generate therequired manoeuvring
force by a direct actionnear the centre of gravity. Affecting all
of theseaerodynamically controlled configurations arethe sizing and
power requirements of the
control surfaces. In missiles the controlfunction is to ensure
stability of the missileand implement the guidance signals
receivedfrom external sources or generated onboard.The control,
after processing the guidancesignals, actuates the aerodynamic
surfaceson thrust vector to generate turn of the missilespeed and
direction as required.
The missile must sense and correct for
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Int. J. Mech. Eng. & Rob. Res. 2014 Vuyyuru Murali Krishna
and P V Anil Kumar, 2014
each degree of moment to maintain anaccurate and stable flight
path. This stableflight path is often called attitude and refersto
the position of the missile relative to aknown (horizontal or
vertical) plane. Thecontrol system contains various componentsused
to maintain a proper flight attitude.
Figure 1: Rotary Moments of aMissile: Pitch, Roll, and Yaw
The objective of my project is to performfinite element analysis
for strength analysisof a missiles control bay under
differentconditions like Pitch, Yaw and Roll moments.Analysis has
been carried out for Aluminiummaterial.
EXPERIMENTAL METHODOLOGY
This paper presents a finite element modelfor strength analysis
of a missiles Missilecontrol component under different
conditionslike pitch, roll and Yaw. The high randomvibration loads
imparted on Missile controlcomponent by the other hardware
duringlaunch create an adverse design requirementthat all hardware
have a natural frequencygreater than that of the Missile
controlcomponent, in order to avoid damage and
failure due to dynamic coupling. Static, Modaland Spectrum
analysis will be carried out onMissile control component.
The methodology followed in my projectis as follows:
Design of Missile control component isdone in NX-CAD.
Perform Static analysis to find max.Deflections and max. Stress
on Missilecontrol component for operating loadingconditions.
Perform Modal analysis to find naturalfrequencies on the
original model of theMissile control component.
Perform spectrum analysis to findmaximum deflections and stress
onMissile control component for dynamicloads.
Optimize the original model to minimizethe deflections and
stress distributionsat high stress locations are
determinedaccording to the model.
Design of modified Missile controlcomponent is done in
NX-CAD.
Perform Static analysis to find max.Deflections and max. Stress
onmodified Missile control component foroperating loading
conditions.
Perform Modal analysis to find naturalfrequencies on the
original model of themodified Missile control component.
Perform spectrum analysis to findmaximum deflections and stress
onmodified Missile control component fordynamic loads.
3D MODELLING OF MISSILE
CONTROL COMPONENT
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Int. J. Mech. Eng. & Rob. Res. 2014 Vuyyuru Murali Krishna
and P V Anil Kumar, 2014
Figure 2: 3D Model of MissileControl Component
Static Analysis of Missile
Control Component
Material Properties:Material used for Missile Control
componentis Aluminium Alloy 24345:
Youngs Modulus: 70GPa Density: 2800kg/m3 Yield strength:
420Mpa
Condition: YawThe missile yaws, or turns left and right,
aboutthe vertical axis. Moments are applied at theCG of Missile
Control component along X-axis. Deflections and stresses are
plotted.
Boundary ConditionsAll Bolting locations are constrained in all
Dof.Moment is applied along X-axis at the CG ofthe Missile Control
component and is trans-ferred to the control bay lugs using
coupleequation.
Table 1: Max. Deflection andMax. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.059 89
From the above results it is observed thatthe Von Mises stress
(89MPa) is less thanthe yield strength of the material
(420MPa).Condition: RollThe missile rolls, or twists, about the
longitu-dinal axis. Moments are applied at the CG ofMissile Control
component along Y-axis.Deflections and stresses are plotted.
Table 2: Max. Deflection andMax. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.088 129
From the above results it is observed thatthe Von Mises stress
(129MPa) is less thanthe yield strength of the material
(420MPa).Condition: PitchMoments are applied at the CG of
MissileControl component along Z-axis. Deflectionsand stresses are
plotted.
From the above results it is observed thatthe Von Mises stress
(127MPa) is less thanthe yield strength of the material
(420MPa).
Hence according to the MaximumVonMises Stress Theory, the
Missile Control
Table 3: Max. Deflection andMax. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.072 127
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component design is safe for the aboveoperating loads.
Modal Analysis
From the above modal analysis results it isobserved that only 5
natural frequenciesexists in the operating range of 0-1000 Hz.
From the modal analysis, The total weightof the Control bay is
14.2 kg.
It is observed that the maximum massparticipation of 13Kgs
observed in X-dir for the frequency of 902Hz.
It is observed that the maximum massparticipation of 12Kgs
observed in Y-dir for the frequency of 666Hz.
It is observed that the maximum massparticipation of 12Kgs
observed in Z-dir for the frequency of 723Hz and 997.
RSA Spectrum AnalysisSpectrum analysis has been carried out
tocheck the structure behaviour for randomvibrations in the
frequency range of 0-1000Hz.
From the RSA analysis in X- dir.
Figure 3: VonMises Stress of Missile ControlComponent for RSA
Analysis in X-Dir
From the RSA analysis in Y- dir.
Figure 4: VonMises Stress of Missile ControlComponent for RSA
Analysis in Y-Dir
Figure 5: VonMises Stress of Missile ControlComponent for RSA
Analysis in Z-Dir
From the RSA analysis in Z- dir.
Table 4: Deflection and Stress of MissileControl Component for
RSA Analysis in
X ,Y and Z- Dir
S.No. Deflection Von Mises Stress(mm) (MP a)
1
X
0.38
Y
0.36
Z
0.42
X
423
Y
283
Z
346
From the above results VonMises stressof 423MPa, 283MPa and
346MPa for RSA
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Int. J. Mech. Eng. & Rob. Res. 2014 Vuyyuru Murali Krishna
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analysis in X, Y, and Z directions observedrespectively. The
yield strength of the materialused for Missile Control component
is420MPa.According to the VonMises StressTheory, the VonMises
stress of MissileControl component is higher than the yieldstrength
of the material. Hence the design ofMissile Control component is
not safe for theabove dynamic loading conditions.
Design modifications are required toreduce high stress values to
achieve highFOS model of Missile Control component.From the results
obtained in RSA analysis inX - Direction, high stress regions are
identifiedand modifications are made accordingly. Thehigh stress
values are observed at pocketand fixing locations. Design
modifications aremade on Missile Control component modelby
increasing surface area near pocketregions to distribute stress
uniformly andbolting locations are rearranged.
Static Analysis of Modified Missile
Control Component
Condition: YawThe missile yaws, or turns left and right,
aboutthe vertical axis. Moments are applied at theCG of Missile
Control component along X-axis. Deflections and stresses are
plotted.
Table 5: Max. Deflection and
Max. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.05 80
From the above results it is observed thatthe Von Mises stress
(80MPa) is less thanthe yield strength of the material
(420MPa).Hence according to the Maximum VonMises
Stress Theory, the Modified Missile Controlcomponent design is
safe for the aboveoperating loads.
Condition: RollThe missile rolls, or twists, about
thelongitudinal axis. Moments are applied at theCG of Missile
Control component along Y-axis. Deflections and stresses are
plotted.
Table 6: Max. Deflection and
Max. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.05 101
From the above results it is observed thatthe Von Mises stress
(101MPa) is less thanthe yield strength of the material
(420MPa).Hence according to the Maximum VonMisesStress Theory, the
Modified Missile Controlcomponent design is safe for the above
op-erating loads.
Condition: PitchMoments are applied at the CG of control
bayalong Z-axis. Deflections and stresses areplotted.
From the above results it is observed thatthe Von Mises stress
(95MPa) is less thanthe yield strength of the material
(420MPa).Hence according to the Maximum VonMisesStress Theory, the
Modified Missile Controlcomponent design is safe for the above
op-erating loads.
Table 7: Max. Deflection and
Max. Von Mises Stress
S.No. Deflection Von Mises Stress(mm) (MP a)
1 0.067 95
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Modal Analysis
From the above modal analysis results it isobserved that only 4
natural frequencies ex-ists in the frequency range of 0-1000
Hz.From the modal analysis,The total weight of the Modified Missile
Con-trol component is 14 kg
It is observed that the maximum massparticipation of 11Kgs
observed in X-dir for the frequency of 987Hz.
It is observed that the maximum massparticipation of 10Kgs
observed in Y-dir for the frequency of 703Hz.
It is observed that the maximum massparticipation of 10Kgs
observed in Z-dir for the frequency of 757Hz.
RSA SpectrumFrom the RSA analysis in X - Dir.
Figure 6: VonMises Stress of Modified MissileControl component
for RSA in X-Dir
From the RSA analysis in Y - Dir.
Figure 7: VonMises Stress of Modified MissileControl component
for RSA in Y-Dir
From the RSA analysis in Z - Dir.
Figure 8: VonMises Stress of Modified MissileControl component
for RSA in Z-Dir
Table 8: Deflection and Stress ofModified Missile Control
Componentfor RSA Analysis in X ,Y and Z- Dir
S.No. Deflection Vonmises Stress(mm) (MP a)
1
X
0.42
Y
0.32
Z
0.43
X
363
Y
238
Z
259
From the above results observed 362MPa,238MPa and 259 MPa
VonMises stress ofRSA analysis in X, Y, and Z directions
withrespectively. The yield strength of the material
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Int. J. Mech. Eng. & Rob. Res. 2014 Vuyyuru Murali Krishna
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used for Modified Missile Control componentis 420MPa.According
to the VonMises StressTheory, the VonMises stress of
ModifiedMissile Control component is less than theyield strength of
the material.
Hence the design of Modified MissileControl component is safe
for the dynamicloading conditions.
PSD SpectrumFrom the PSD analysis in X-Dir.
Figure 9: VonMises Stress of Modified MissileControl component
for PSD in X-Dir
From the PSD analysis in Y - Dir.
Figure 10: VonMises Stress of ModifiedMissile Control component
for PSD in Y-Dir
From the PSD analysis in Z - Dir.
Figure 11: VonMises Stress of ModifiedMissile Control component
for PSD in Z-Dir
From the PSD results the maximum 3sigma stress of 69MPa, 66MPa
and 63MPaare observed in X,Y and Z directionsrespectively and are
less than the yieldstrength of material used for Modified
MissileControl component. Hence the design ofmodified Missile
Control component is safefor the random vibrations.
CONCLUSION
In the present project, the Missile Controlcomponent has been
studied for structuralbehaviour and optimised for safe
structure.
The Missile Control component wasstudied for 2 different
cases:
Static loads Dynamic loads
Table 9: Deflection and Stress ofModified Missile Control
Componentfor PSD Analysis in X ,Y and Z- Dir
S.No. Deflection Vonmises Stress(mm) (MP a)
1
X
0.075
Y
0.09
Z
0.105
X
69
Y
66
Z
63
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From the above analysis it is concludedthat the modified Missile
Control componenthas stresses and deflections within the
designlimits of the material used. The deflectionsand stresses
obtained in the dynamicanalysis are also under the design limits
ofthe material used.
Therefore it concluded that the ModifiedMissile Control
component is safe under thestatic and dynamic loading
conditions.
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