JNTU
JNTU B.Tech III FLIGHT MECHANICS II Previous Question Paper (May - 2018 - R13)
Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5 Units. Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c as sub questions.
Part A
Describe the importance of controlled flight.
Answer
Controlled flight is essential for an aircraft to maintain a desired trajectory, attitude, and speed despite external disturbances like gusts. It ensures safety by allowing the pilot or flight control system to maneuver the vehicle, perform take-offs and landings, and prevent loss of control during flight.
Discuss the longitudinal static stability of canard aircraft.
Answer
A canard configuration places the horizontal stabilizer forward of the main wing. For longitudinal static stability, the center of gravity must be located forward of the neutral point of the combined wing-canard system. Unlike conventional aircraft where the tail provides a downward force, the canard typically provides an upward lift, requiring the main wing to be positioned further aft to maintain balance and stability.
Explain the importance of aerodynamic derivatives.
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State the stability derivatives due to rolling rate.
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Describe stick free neutral point.
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Write a short note on hinge moment coefficients.
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State the assumptions made in the small perturbation theory.
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Describe the motion of the flight vehicle.
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Explain the forces acting on the aircraft during spin.
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Write a short note on damping ratio.
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Part B
Explain the contribution of wing to the static longitudinal stability of the aircraft.
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Illustrate the static margin of the aircraft.
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Formulate an expression for the elevator angle to trim the airplane.
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Discuss the contribution of tail on the longitudinal static stability of the aircraft.
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Explain the stability derivatives due to pitching velocity.
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Discuss the effect of aspect ratio on Cmβ.
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Describe the significance of control derivatives in the stability and control of the aircraft.
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Develop an expression for Cmq due to canard surface.
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Illustrate different types of aerodynamic and mass balancing of aircraft control surfaces.
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Discuss the functions of tabs used in aircraft control systems.
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Explain the lateral and directional stability of the aircraft.
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Describe the role of rudder in cross wind landings and asymmetric power condition.
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Illustrate the body and inertial axis system of the aircraft.
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Starting from the Y force equation, use small disturbance theory to determine the linearized force equation.
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Discuss why product of inertia are usually zero for an airplane configuration.
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Describe the small disturbance theory.
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Calculate the natural frequency, damping ratio, damped frequency and time constant for the Short period oscillations. The characteristic equation for the short period oscillation is λ2 + 4.58λ + 21.6 = 0.
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Write a short note on the spiral divergence of the aircraft.
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Describe the lateral-Directional equations of motion of the aircraft.
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Write a short note on the two degrees of freedom approximations.
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