static and fatigue simulation of aircraf
DESCRIPTION
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STATIC AND FATIGUE SIMULATION OF AIRCRAFT LANDING GEAR M.VIJAYAN 1, JENITH N BARNABAS 2, K.HARIRAM 3
Department of Mechanical Engineering, Udaya School of Engineering, Vellomodi-629204, Kanya kumari, Tamilnadu, INDIA1, 2, 3
Tel : + 91978886149991 ,+ 9180565656562,+9194434950933 .
[email protected]@gmail.com2
ABSTRACT: The main objective of this project is to analyse the aircraft landing gear with different material .All the parts of landing gear designed by Pro-E Software but Static and fatigue simulation done by Solid works Soft ware.Current we are landing gear material is Alloy Steel .In this fatigue simulation, the damage percentage and life of axle is 0.0178961 and 5587.82 cycles respectively .Instead of this material is introducing carbon steel on that part .After static and fatigue simulation completed , the result value of damage percentage and life of axle is higher than previous material. . .Key words: (Landing Gear , Alloy Steel , Cast Caron Steel , Fatigue)
1.INTRODUCTION
Another aircraft major component that is needed to
be designed is landing gear (undercarriage). The
landing gear is the structure that supports an
aircraft on the ground and allows it to taxi, take-off,
and land. In fact, landing gear design tends to have
several interferences with the aircraft structural
design. In this book, the structural design aspects of
landing gear are not addressed; but, those design
parameters which strongly impact the aircraft
configuration design and aircraft aerodynamics will
be discussed.
1.Wheel hub
2.Lower Link
3.Upper Link
4.Axle
5.Piston
The landing gear usually includes wheels, but some
aircraft are equipped with skis for snow or float for
water. In the case of a vertical take-off and landing
aircraft such as a helicopter, wheels may be
replaced with skids. illustrates landing gear primary
parameters. The descriptions of primary parameters
are as follows. Landing gear height is the distance
between the lowest point of the landing gear (i.e.
bottom of the tire) and the attachment point to the
aircraft. Since, landing gear may be attached to the
fuselage or to the wing; the term height has
different meaning. Furthermore, the landing gear
height is a function of shock absorber and the
landing gear deflection. The height is usually
measured when the aircraft is on the ground; it has
maximum take-off weight; and landing gear has the
maximum deflection (i.e. lowest height).
LANDING GEAR CONFIGURATION:
The first job of an aircraft designer in the landing
gear design process is to select the landing gear
configuration. Landing gear functions may be
performed through the application of various
landing gear types and configurations. Landing
gear design requirements are parts of the aircraft
general design requirements including cost, aircraft
performance, aircraft stability, aircraft control,
maintainability and operational considerations. In
general, there are ten configurations for a landing
gear as follows:
1. Single main
2. Bicycle
3. Tail-gear
4. Tricycle or nose-gear
2
5. Quadricycle
6. Multi-bogey
Transport aircraft McDonnell Douglas MD-88 with
tricycle landing gear:
3. Bomber aircraft B-52 Stratofortress with
quadricycle landing gear is using parachute during
a landing operation
4. Transport aircraft Boeing 747 with multi-bogey
landing gear:
The features and the technical descriptions of each
landing gear configuration will be presented in this
section. The landing gear configuration selection
process includes setting up a table of features that
can be compared in a numerical fashion. It needs to
be clarified that for simplicity the term “gear” or
“wheel” is sometimes employed for a single strut
and whatever that is connected to it which
comprises such items as tire, wheel, shock
absorber, actuators, and brake assembly. Hence,
when the term “nose-gear” is used, it refers to a
landing gear configuration; while when the term
“nose gear” is employed, it refers to a gear that is
attached under the fuselage nose. In general, most
general aviation, transport and fighter aircraft
employ tricycle landing gear, while some heavy
weight transport (cargo) aircraft use quadricycle or
multi-bogy landing gear. Nowadays, the tail-gear is
seldom used by some GA aircraft, but it was
employed in the first 50 years of aviation history by
majority of aircraft.
MODELLING:
Pro-E Model of Aircraft landing Gear Parts:
3
1.Wheel Hub:
2.PISTON:
3.STRUT:
4.AXLE:
4.UPPER LINK:
5.LOWER LINK:
4
ASSEMBLE OF PARTS:
CONVERT PRO-E ASSEMBLE MODEL INTO
IGES FORMAT:
After all the parts assembled in Pro-E,
save that model into IGES format shown below:
Assemble model →Click file → Save as → Click
save as type → Select IGES(*igs.) → Ok.
IMPORTING PRO-E ASSEMBLE MODEL INTO
SOLIDWORKS:
When the solid works window open, the
following steps are involved for importing the
assemble model,
Open Solid works 2015 (icon) → Click open →
Click open type
→ Select IGES(*igs) → Select assemble model →
Click Open.
SIMULATION RESULTS
1.ALLOY STEEL
MATERIAL PROPERTIES:
LOADS AND FIXTURES:
Properties
Name: Alloy Steel
Model type: Linear Elastic
Isotropic
Default failure
criterion:
Max von Misses Stress
Yield strength: 620.422 N/mm^2
Tensile strength: 723.826 N/mm^2
Elastic modulus: 210000 N/mm^2
Poisson's ratio: 0.28
Mass density: 7700 g/cm^3
Shear modulus: 79000 N/mm^2
Thermal expansion
coefficient:
1.3e-005 /Kelvin
Fixture name Fixture Image Fixture Details
Fixed
Entities: 4 faces Type: Fixed
Geometry
Load name Load Image Load Details
Load
Entities: 1 face Force Valu s:
-289395 N
Gravity
Reference: Plane 2 Values: -9.81 Units: SI
5
STUDY RESULTS:
FATIGUE SIMULATION:
Type Min Max
von Misses Stress
0.000184536 N/mm^2 (MPa)
Node: 10069
863.427 N/mm^2 (MPa)
Node: 21740
Type Min Max
Resultant Displacement
0 mm
Node: 19871
0.431681 mm
Node: 6712
Type Min Max
Damage plot 0.01247 Node: 1 0.0178961 Node: 21781
Type Min Max
Life plot 5587.82 cycle Node: 21781
8019.25 cycle
Node: 1
6
2.CAST CARBON STEEL
MATERIAL PROPERTIES:
STUDY RESULTS:
Type Min Max
von Misses Stress
1.2739e-006 N/mm^2 (MPa)
Node: 4411
227.215 N/mm^2 (MPa)
Node: 21781
FATIGUE SIMULATION:
STUDY RESULTS:
Type Min Max
Damage percentage
0.01247
Node: 1
0.0176355
Node: 21781
PROPERTIES
Name: Alloy Steel (SS)
Upper link lower link ,piston strut ,wheel hub
Model type: Linear Elastic Isotropic
Default failure criterion:
Max von Misses Stress
Yield strength: 620.422 N/mm^2
Tensile strength: 723.826 N/mm^2
Elastic modulus: 210000 N/mm^2
Poisson's ratio: 0.28
Mass density: 7700 g/cm^3
Shear modulus: 79000 N/mm^2
Thermal expansion coefficient:
1.3e-005 /Kelvin
Name: Cast Carbon Steel (axle)
Model type: Linear Elastic Isotropic
Default failure criterion:
Max von Misses Stress
Yield strength: 248.168 N/mm^2
Tensile strength: 482.549 N/mm^2
Elastic modulus: 200000 N/mm^2
Poisson's ratio: 0.32
Mass density: 7800 g/cm^3
Shear modulus: 76000 N/mm^2
Thermal expansion coefficient:
1.2e-005 /Kelvin
7
CONCLUSION:
Aircraft landing gear modeled and simulated by
Pro-E and Solid works Software respectively
.Simulate landing gear with alloy steel material and
obtained stress, displacement, strain results from
solid works static simulation. Simulate landing gear
with alloy steel material and obtained damage
percentage and life results from solid works fatigue
simulation .Simulate landing gear with cast carbon
steel material and obtained stress, displacement,
strain results from solid works static simulation.
Simulate landing gear with cast carbon steel
material and obtained damage percentage and life
results from solid works fatigue simulation. Then
compare all results with each material and choose
favorable material for landing gear axle part.Finally
cast carbon material is suitable material for aircraft
landing gear as per its results.
REFERENCES:
1. Norman S. Currey, Aircraft Landing Gear
Design: Principles and Practices, AIAA, 1988
2. Roskam J., Roskam’s Airplanes War Stories,
DAR Corp., 2006
3. FAR Part 23.473, Federal Aviation
Administration
4. Russell C. Hibbeler, Engineering Mechanics:
Statics, 12th Edition, Prentice Hall, 2009
5. Budynas R. G. and Nisbett J. K., Shigley's
Mechanical Engineering Design, McGraw-Hill, 9th
Edition, 2011
6. Aircraft Tire Data, The Goodyear Tire & Rubber
Company
7. Aircraft Tire Data, Bridgestone Corporation
8. Paul Jackson, et al., Jane’s all the world’s
aircraft, Jane’s Information Group, several years
9. Green W. L., Aircraft Hydraulic Systems: An
Introduction to the Analysis of Systems and
Components, Wiley, 1986
10. Robert L. Norton, Design of Machinery: An
Introduction to the Synthesis and Analysis of
Mechanisms and Machines, McGraw-Hill, 2008
11. Arthur G. Erdman, George N. Sandor, Sridhar
Kota, Mechanism Design: Analysis and Synthesis,
4th Edition, Prentice Hall, 2001
12. Anon, MIL-F-1797C, Flying qualities of
piloted airplanes, Air force flight dynamic
laboratory, WPAFB, Dayton, OH, 1990
Type Min
Max
Life 5670.37 cycles
Node: 21781
8019.25 cycles
Node: 1