Control systems Flashcards

1
Q

Flight control

A

an aircraft is controlled if its movement can be matched to its demanded input

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2
Q

Stability

A

an aircraft can be described as stable if it exhibits a tendency to resume its original attitude after an upset that causes displacements or rotations, without the intervention of the pilot

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3
Q

Primary flight control

A

Control surfaces and devices that allow the pilot and/or the FMS to change the aircraft altitude

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4
Q

Secondary flight controls

A

Control surfaces and devices that allow the pilot and/or the FMS to control lift and drag

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5
Q

Name primary controls

A

Rudder Elevator Aileron

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6
Q

Name secondary flight controls

A

Flaps Slats Spoilers

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7
Q

Match primary control surfaces to the manoeuvre and rotational axis

A
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8
Q

Factors affecting lift

A
  • relative airflow velocity
  • planform area of lifting surface
  • air density
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9
Q

Ailerons

A
  • located on the trailing edge of the wing
  • used to turn the aircraft left/right
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10
Q

Why are the ailerons located on the trailing edge of the wing?

A

there is a greater moment at the trailing edge

therefore, more effective and greater control

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11
Q

Elevators

A
  • located below the rudder at the back of the aircraft
  • used to control the pitch of the aircraft
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12
Q

Rudder

A
  • located on the tail of the aircraft
  • used to keep the nose and tail pointing in the same direction
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13
Q

Canard/foreplane

A

small wings at the front of an aircraft

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14
Q

chord

A

length from the leading edge to the trailing edge

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15
Q

Name other control surfaces and the manoeuvre they control

A

Control surfaces

Manoeuvre

Tailerons

Roll and pitch

Canards(foreplanes)

Pitch or pitch and roll

Elerons

Roll and pitch(delta wing)

Spoilers

Assist in roll control

Flaperon

Pitch, roll and flap functionality

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16
Q

Identify ways to reduce lift and forward speed

A
  • flaps, nose flaps, slats
  • variable camber wing(NASA complex system to alter wing curvature)
  • Boundary layer control(bleed air from the engine to re-energise the boundary layer)
17
Q

Types of flaps

A
18
Q

Which variables are affected by flaps?

A

wing area

coefficient of lift

19
Q

Lift equation

A
20
Q

Aspect ratio

A

It is a measure of wing planform ‘slenderness’

ratio of span to chord

21
Q

Span

A

distance from one wingtip to the other wingtip

22
Q

Factors affecting the coefficient of lift

A
  • aerofoil shape
  • angle of attack
  • air viscosity
23
Q

Manual flight control system

A

double run cable system

combination of rods, levers and cables

24
Q

Advantages and disadvantages of manual flight control

A

Advantages

  • natural feedback
  • cheap
  • fewer failure modes than hydraulic powered
  • lightweight
  • easy to maintain
  • simple to set up

Disadvantages

  • motion fixed at the design stage
  • difficult to fly unstable aircraft
  • limited to pilot strength
  • more potential for mechanical failure
25
Q

Power sources for power-assisted or operated controls

A

centralised hydraulic system

electro-hydrostatic actuation

electro-mechanical actuation

26
Q

Feel unit

A

replicates the aerodynamic forces on the aircraft

27
Q

Control system design

A
  • range of movement
  • correct sense
  • freedom of movement
  • correct operation
  • safety
  • sensitivity
  • response
  • rigidity
28
Q

Benefits and limitation of a control system

A

Benefits

  • no limits placed on aircraft by pilot strength
  • reduced physical exertion on pilot
  • pilot doesn’t need to hold control input

Limits

  • added weight
  • potential of hydraulic leaks
  • no natural feedback
29
Q

Simple FBW system

A
30
Q

ACT based FBW system

A
31
Q

Benefits of ACT based FBW system

A
  • not affected by structural distortion
  • easy to install in aircraft
  • low maintenance
  • enhanced safety
  • low pilot workload
  • systems integration
32
Q

Simple power-operated control system using centralised hydraulic power

A