JNTUK B.Tech Flight Mechanics-II gives you detail information of Flight Mechanics-II R13 syllabus It will be help full to understand you complete curriculum of the year.
Course Objective
The main objective of the subject is to change its orientation relative to the passing air. A power-driven heavier than air aircraft, deriving its lift chiefly from aerodynamic reactions on surface which remain fixed under given conditions of flight. The actual linkages within the aircraft are discussed in aircraft flight control systems.
UNIT – I : Introduction: Degree of freedom of a system – Static and dynamic stability – Need for stability in an airplanes – Purpose of controls – Inherently and marginally stable airplanes. Equations Of Motion Equations of motion of a rigid body. Inertial forces and moments. Equations of motion of flight vehicles. Aerodynamic forces and moments. Decoupling of longitudinal and lateral-directional equations. Linearization of equations.
UNIT – II : Aerodynamic Stability Derivatives : Aerodynamic stability and control derivatives. Relation to geometry, flight configuration. Effects of power, compressibility and flexibility. Static Longitudinal Stability and Control – Control Fixed.
Stick Fixed: Basic equilibrium equation – Stability criterion – Contribution of wing and tail and elevator to pitching moments – Effect of fuselage and nacelles – Effects of center of gravity location – Power effects – Stabilizer setting and center of gravity location – Elevator power– Elevator to trim . Trim gradients. Control fixed static stability – Control fixed neutral point. Stability margins.
UNIT – III : Static Longitudinal Stability – Control Free : Effects of releasing the elevator. Hinge moment coefficients – Control forces to trim. Control free neutral point – Trim tabs. Aerodynamic balancing of control surfaces. Means of augmentation of control.
UNIT – IV : Maneuver Stability : Contribution of pitch damping to pitching moment of flight vehicle – Effect on trim and stability. Control deflections and control forces for trim in symmetric maneuvers and coordinated turns. Control deflection and force gradients. Control fixed and control free maneuver stability. Maneuver points. Maneuver margins.
UNIT – V : Static Lateral and Directional Stability and Control : Dihedral effect – Coupling between rolling and yawing moment – Adverse yaw – Aileron power – Aileron reversal. Weather cocking effects – Rudder power. Lateral and directional stability- definition. Control surface deflections in steady sideslips, rolls and turns one engine inoperative conditions – Rudder lock.
UNIT – VI : Dynamic stability and response to control. : Solutions to the stability quartic of the linearised equations of motion. The principal modes. Phugoid, Short Period Dutch Roll and Spiral modes – Further approximations. Restricted degrees of motion. Solutions. Response to controls. Auto rotation and spin.
TEXT BOOKS
- Houghton, E.L., and Carruthers, N.B., Aerodynamics for Engineering Students, Edward Arnold Publishers Ltd., London, 1989
- Mc.Cormic, B.W., Aerodynamics, Aeronautics & Flight Mechanics, John Wiley 1995
REFERENCE BOOKS
- Perkins C.D., & Hage, R.E., Airplane Performance, Stability and Control, Wiley Toppan 1974.
- Nelson, R.C., Flight Stability and Automatic Control, McGraw Hill 1989
Course Outcome
Upon completion of the course the students shall be able to:
- Change aero plane orientation relative to the passing air.
- Identify the power-driven heavier than air aircraft, deriving its lift chiefly from aerodynamic reactions on surface which remain fixed under given conditions of flight.
- Know the actual linkages within the aircraft are discussed in aircraft flight control systems
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