Reference no: EM132581118 , Length: 3000 Words

314AAE Aerospace Technology Stability and Control Assignment - School of Engineering - Emirates Aviation University, UAE

As a team member working in an aviation company you have been told to conduct a research on fundamentals of mechanics of flight. You need to provide a professional report, maximum 20 pages, regarding stability of a conventional aircraft, effect of components on the aircraft stability and stability equations.

Tasks 1 -

Describe the motion of aircraft using standard terminology, static and dynamic stability, and control of an aircraft.

Define the following terms:

- Aircraft three body axes

- Aerodynamic forces and moments about three axes; and their convention positive direction

- Positive angle of attack and positive angle of sideslip

What is the static and dynamic stability of an airplane? Discuss in details the longitudinal, lateral and directional stabilities.

Describe the static margin and briefly explain the effect of the static margin on aircraft stability and control.

Describe the spiral mode and dutch-roll mode.

Describe Explain how sweep angle and dihedral angle help aircraft stability.

Short answer questions (use one word for the answer):

- How will the longitudinal stability change, with increase in tail size?

- How will the static longitudinal stability change, with increase in elevator size?

- What determines the longitudinal stability of an airplane?

a) Relationship of thrust to weight and drag

b) Location of CG with respect to the neutral point

c) Location of CG with respect to the manueuvering point

d) None of the above

For static longitudinal stability minimum condition that must be satisfied is:

a) C_mα < 0

b) C_mα < 0, C_m0 > 0

c) C_mα > 0, C_m0 > 0

d) C_mα < 0, C_m0 < 0

For static directional stability minimum condition that must be satisfied is:

a) C_nβ < 0

b) C_nβ > 0

c) C_nβ > 0, Cl_β > 0

d) C_nβ > 0, Cl_β < 0

Task 2 -

Describe and compare control systems of various aircraft

Distinguish between stability and controllability. Explain longitudinal control, roll control and yaw control of an airplane from an equilibrium point.

Identify the various control surfaces associated with the

(a) Tail (i.e. Yaw damper) and

(b) Wing

Which impact on aircraft stability and control?