MAE 3404-Flight Vehicle Dynamics – Engineering Assignment Help

Assignment Task


Flight Vehicle Dynamics

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Outcomes In this section, the learning objectives and outcomes of the lectures/presentations include the following:

  • will learn (present all) the non-linear dynamic equations for an aircraft in a set – i.e. translational, rotational, and Euler equations
  • will learn how to reduce the complexity of such dynamic equations with assumptions such as symmetrical vehicle and steady state flight conditions;
  • will learn how to introduce small perturbations and linearise the equations of motion for symmetric steady state flight condition;
  • will learn about the aerodynamic forces and moments derivatives
  • will learn how to decouple the equations of motion into symmetric and anti-symmetric sets – i.e. longitudinal and lateral equations;
  • learn about the aerodynamic force and moment components (and aerodynamic derivatives) in stability axes – also referred to as wind axes
  • introduce aerodynamic control inputs – i.e. elevator, aileron and rudder motion input, and thrust;
  • learn about the complete linearised equations and their transfer functions

Linearization of the Aircraft Equations of Motion
(1) Complete Nonlinear Equations
(2) Symmetrical Vehicle
(3) Steady State Flight Conditions
(4) Small Perturbations
(5) Perturbation Equations from Symmetric Steady State Flight condition
(6) Aerodynamic Force and Moment Derivatives
(7) Symmetric and Antisymmetric Sets of Equations
(8) Aerodynamic Force and Moment Components in Stability Axes
(9) Aerodynamic Derivatives in Terms of Stability Axes Equivalents
(10) Aerodynamic Control Inputs
(11) Complete Linearised Equations

Aerodynamic Derivatives in Terms of Stability Axes Equivalents
We will now rewrite the aerodynamic derivatives appearing in Equations (39) and (40) in terms of the derivatives indicated by Equation (54). We are first interested in Aerodynamic Forces.

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