MECH5675M - Vehicle Systems - Modelio Software - Engineering Assignment Help

Assignment Task

Part 1
For this task, you can use the Modelio software to draw SysML diagram:
Modelio (https://www.modelio.org/) : this is a freeware and can be installed on both Mac and Windows computers. You can also use any drawing software such as the drawing tools in MS-Word and MS-PowerPoint.

a) Draw the block definition diagram (bdd) for the aileron actuation system implemented in HydraulicSim.slx given in Computer Session 5. [10 Marks]

b) Draw the internal block diagram (ibd) for the aileron controller implemented in HydraulicSim.slx. [10 Marks]

c) Draw the activity diagram (act) for the operation of a fuel jettison system for an aircraft. The jettison system requirements are given as:
The flight crew shall be able to jettison excess fuel in an emergency situation in order that the aircraft may land under the maximum landing weight.
The flight crew shall be able to jettison down to a preselected fuel quantity.
The flight crew shall be given indications that fuel jettison is underway.
The flight crew shall be given indications that fuel jettison is completed.

Part 2
Simplified aircraft stability model
Conventional aircraft pitch stability is achieved when the balance of moments around the pitch axis is equal to zero. Check pages 6 and 7 for relevant diagrams and nomenclature drawings.

• The simplified aircraft model is using a rectangular wing and rectangular tail.
• The wing is installed with an incident angle of 2° i.e. in level flight conditions the wing is at αw = 2° in the positive pitch direction.
• The lift generate by a lifting surface applied at the aerodynamic centre (a.c.) is given as L = C1 ρU2S = QC S where C is the coefficient of lift as a function of angle of attack α , ρ is L the air density, U is the air speed, S is the 2D surface area, Q is the dynamic pressure. Use S.I. units.
• The moment generated by a lifting surface w around point b is given as Mb,w = Lwdab where Lw is the lift generated at point a and dab is the distance between point a and b.
• Pitch up is the positive pitch direction. A positive pitching moment is in the direction that would move the nose up.
• Assume the main contributors to the pitching moment are the Wing Lift and the Tail lift and all other contributors are negligible.
• Assume the downwash effect is negligible at the tail.
• Assume the aircraft is flying in a free stream at its constant cruise speed. i.e. not accelerating or decelerating.

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