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1. Anna University Practical Examination Oct- 2019 AE6712 - AIRCRAFT DESIGN PROJECT-2 DESIGN AND OPTIMIZATION OF FIGHTER AIRCRAFT BATCH MEMBERS PARISUTHAM INSTITUTE OF TECHNOLOGY & SCIENCE DEPARTMENT OF AERONAUTICAL REG NO NAME 821316101002 KEERTHANA.C 821316101005 PREETHI.D PROJECT GUIDE H.O.D Mr M.F MOHAMED HUSSAIN M.E Mr.N.VAIRAMUTHU M.Tech AP/ (AERO) (AERO)

2. ABSTRACT This project based on designing of fighter aircraft with an optimum range .the aim of this project is to design and conceptualize fighter jet.in this project, concentrated on the structural design based on aircraft design project -1 parameters. in aircraft design project-1 basic required parameters has been taken based on aerodynamic characteristics. this report given a conclusion of v-n diagram, load estimation of wing, load estimation of fuselage, balancing and maneuvering loads on tail plane, rudder and aileron loads, design of some components of wing and fuselage, materials selection the adequate details have been collected to make our calculation easier and to make design more precision the details have been collected from various sources which are given in the bibliography

3. INTRODUCTION The purpose of ADP-II is to enhance the knowledge in continuation of the design project given in ADP–I. Also,. In the following pages we have carried out structural analysis of fuselage and wings and the appropriate materials have been chosen to give our aircraft adequate structural integrity. The determination the landing gear position, retraction and other accompanying systems and mechanisms have also been done. Thus, by imposing all the performance parameters in our ADP-I, structural analysis of our business jet is done in this project. The structural design of an airplane actually begins with the flight envelope or the V-n diagram, which clearly limits the maximum load factors that the airplane can withstand at any particular flight velocity. But, in normal practice the airplane might experience loads that are much higher than the design loads. The two major members that need to be considered for the structural design of an airplane are the wings and the fuselage. As far as the wing design is concerned, the most significant load is the bending load. So, the primary load bearing component in the wing structure is the spar (the front and the rear spars) whose cross section is an I- section. Apart from the spar to take the bending loads, suitable stringers need to be provided to take the shear loads acting on the wing.

4. REQUIRED DATA’S FROM ADP-1 An airplane is a hybrid of various aspects of airplane design viz., airplane dynamics, propulsion, structures, stability and control. The airplane emerges as a compromise of several conditions directed by the specifications for which it is being designed .. This aircraft design project-II is basically a continuation of aircraft design project-I . Mission specifications   Literature survey   Weight estimation   Engine selection   Airfoil selection   Landing gear selection   Drag estimation

5. RESULTS OFF THE WEIGHT ESTIMATION WEIGHTS UNIT(kg) UNIT (N) Empty weight 24805.1 243338.031 Weight fuel 10322.4 101262.744 Overall weight 11075288 108648575

6. V-n diagram and schrenks curve

7. PRELIMINARY DESIGN OF AN AIRCRAFT Span Length The wingspan of an aircraft is always measured in a straight line, from wingtip to wingtip, independently of wing shape or sweep. Chord Length In  aeronautics,  chord  refers to the imaginary straight line joining the leading and trailing edges of an  aerofoil . The chord length is the distance between the trailing edge and the point on the leading edge where the chord intersects the leading edge. Spars And Ribs In a fixed-wing aircraft, the  spar  is often the main structural member of the wing, running span wise at right angles (or thereabouts depending on wing sweep) to the fuselage.

8. Shear force and bending moment

9. WING LOAD DISTRIBUTION TRAPEZOIDAL LIFT DISTRIBUTION ELLIPTICAL LIFT DISTRIBUTION

10. DETAILED DESIGN OF AN AIRCRAFT WING The aircraft wings are the primary lift producing device for an aircraft. The aircraft wings are designed aerodynamically to generate lift force which is required in order for an aircraft to fly. The basic goal of the wing is to generate lift and minimize drag as far as possible. Wing Skin Wing Spares Wing ribs

11. shear force and bending moment The solution methods which follow Euler's beam bending theory (σ/y=M/I=E/R) use the bending moment values to determine the stresses developed at a particular section of the beam due to the combination of aerodynamic and structural loads in the transverse direction. considerable shear forces and bending moments on it. They are as follows: → Lift force (given by Schrenk's curve) → Self-weight of the wing

12. Calculating shear force and bending moment

13. PRELIMINARY DESIGN OF AN AIRCRAFT FUSELAGE Introduction The fuselage layout is important in the design process as the length of the airplane depends on this.The length and diameter of the fuselage are related to the seating arrangement. The Fuselage of a passenger airplane can be divided into four basic sections viz. nose, cockpit, payload compartment and tail fuselage. In this section, the fuselage design is carried out by choosing the parameters of these sections.

14. Cabin diameter Using the number of seats abreast,seatwidth,aisle width the internal diameter of the cabin is calculated as: dfinternal = 22 × 1 + 19 × 6 = 136 in = 3.4 m According to standards prescribed by the structural thickness in inches is given by : t = 0.02 dfinternal + 1 = 0.02 × 136 + 1 = 3.72 in = 0.093 m Therefore, the external diameter of the fuselage is obtained as : 3.4+0.093 × 2 = 3.59 m.

15. Total fuselage length Nose length = 1 m Cockpit length = 2.5 m Cabin length = 21.25 m Rear length = 8.25 m Total = 33 m

16. DETAILED DESIGN OF AN AIRCRAFT FUSELAGE Bending Stress And Shear Flow Calculations  Let consider fuselage is simply supported beam Reaction Force Calculation : Rb =8422048.746N Ra=1246411.254N Shear Force Calculation : Fa =Ra=1246411.254   Fc=1246411.254N-78480N =1167931.254N   Fd =1167931.254N-58.36KN = 1109071.254 Bending Moment Calculation : Ma=0 Mh =10065483.82N

17. Design of bulkheads and longerons There are two general types of fuselage construction welded  steel  truss  and   monocoque designs. The welded steel truss was used in smaller Navy aircraft, and it is still being used in some helicopters Primary bending loads are taken by the longerons , which usually extend across several points of support. The longerons are supplemented by other longitudinal members known as stringers. Stringers are more numerous and lightweight than longerons . The vertical structural members are referred to as bulkheads ,    frames , and    formers . The heavier vertical members  are  located  at  intervals  to  allow  for concentrated loads.

18. Analysis of bulkhead and longerons

19. DESIGN OF A CONTROL SURFACES Development of an effective set of flight control surfaces was a critical advance in the development of aircraft. Early efforts at  fixed-wing aircraft  design succeeded in generating sufficient lift to get the aircraft off the ground. Ailerons Ailerons  are mounted on the trailing edge of each wing near the wingtips and move in opposite directions. When the pilot moves the  stick  left, or turns the wheel counter-clockwise, the left aileron goes up and the right aileron goes down . Elevator The   elevator  is a moveable part of the  horizontal stabilizer , hinged to the back of the fixed part of the horizontal tail. The elevators move up and down together. When the pilot pulls the stick backward, the elevators go up Rudder The  rudder is typically mounted on the trailing edge of the vertical stabilizer, part of the empennage. When the pilot pushes the left pedal, the rudder deflects left. Pushing the right pedal causes the rudder to deflect right

20. Control Surfaces Sele / Sh = 0.22 Srud = 5.8 m2 bflap = 23.7 m

21. WING ROOT ATTACHMENT Wing Root Fairings Wing root fairings have substantially improved low-speed and high-load flying characteristics. The design process and results are described in Finding Hidden Drag . Then this increases drag and reduces lift, particularly for large payloads or high angles of attack.

22. DESIGN OF A LANDING GEAR The calculation of landing gear loads for gyroplanes has never been documented. My following article is based on my calculations of landing gear loads for fixed wing aircraft and the Code of Federal Regulations (CRF)

23. Conclusion The requirements for the design of fighter aircraft are immense.We have continued our work form ADP-I and we have successfully managed totweak our design further. The structural analysis of the aircraft members carried outhas yielded acceptable results. The flight envelope of our aircraft was also defined and was found again to bewithin acceptable limits. To increase the lifespan of our aircraft, we have gone in for a composite material structure, as they have the distinct advantage of not failingeasily under the action of high stress and temperatures, thereby making our structurestrong and efficient.