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midterms aamt 1-10 > aircraft structures and landing gears > Flashcards

aircraft structures and landing gears Flashcards

1
Q

airfoils that move rapidly through the air, create lift

A

wings

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2
Q

plane with one wing

A

monoplane

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3
Q

plane with two wings

A

biplane

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4
Q

plane with three wings

A

triplane

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5
Q

formula of aspect ratio

A

span/chord

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6
Q

span greater than chord

A

high aspect ratio

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7
Q

chord greater than span

A

low aspect ratio

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8
Q

measure of how long and slender the wing appears from below

A

aspect ratio

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9
Q

wings of an aircraft can be attached to the fuselage where?

A

top, mid-fuselage, or at the bottom

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10
Q

wings attached at the bottom of the fuselage

A

low wing

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11
Q

advantage/s of low wing

A
  • easy to refuel
  • better visibility above at the sides of aircrafts
  • better ground effect which increase lift and reduces drag when it’s nearer to the surface
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12
Q

disadvantage/s of low wing

A

low passenger visibility

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13
Q

attached at the mid portion of the fuselage

A

mid wing

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14
Q

used by military aircraft

A

mid wing

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15
Q

advantage/s of mid wing

A
  • better rolling
  • less interference drag
  • allow to carry weapons
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16
Q

disadvantage/s of midwing

A
  • occupies lot of useful fuselage volume
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17
Q

attached at the top of the fuselage

A

high wing

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18
Q

advantage/s of high wing

A
  • better visibility
  • lots of space for ground staff during maintenance
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19
Q

disadvantage/s of high wing

A

difficult to refuel

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20
Q

short, nearly vertical supports that are attached to the wings a great distance from the fuselage

A

jury struts

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21
Q

Strongest wing structure which attached directly to the fuselage and does not have any type of external stress bearing structure

A

full cantilever

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22
Q

Usually has one or two supporting wires or struts attached on each wing and fuselage.

A

semi cantilever

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23
Q

Typical of a biplane ( two wings placed one above the other ) with its struts and wires.

A

externally braced

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24
Q

may be straight or curved, or one edge may be straight and the other curved

A

trailing edge and leading edge

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25
Q

internal structure of wings are made up of

A

spars and stringers spanwise, and formers or bulkheads running chordwise (leading edge to trailing edge)

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26
Q

principal structural members of a wing

A

spars

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27
Q

support all distributed loads, as well as concentrated weights such as the fuselage, landing gear, and engines

A

spars

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28
Q

carries part of the loads imposed during flight

A

skin

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29
Q

transfers the stresses to the wing ribs

A

skin

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30
Q

in turn, transfer the loads to the wing spars

A

ribs

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31
Q

incorporates only one main spanwise or longitudinal member in its construction.

A

monospar

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32
Q

ribs or bulkheads supply the necessary contour or shape to the airfoil here

A

monospar

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33
Q

incorporates more than one main longitudinal member in its construction. To give the wing contour, ribs or bulkheads are often included.

A

multispar

34
Q

wing construction uses two main longitudinal members with connecting bulkheads to furnish additional strength and to give contour to the wing.

A

box beam

35
Q

two sections of a spar

A

top section and bottom section

36
Q

what consists of top section

A

cap riveted to the upper web plate

37
Q

what consists of lower section

A

single extrusion consisting of the lower cap and web plate.

38
Q

structural crosspieces that combine with spars and stringers to make up the framework of the wing.

A

ribs

39
Q

where do ribs extend from

A

wing leading edge to the rear spar or to the trailing edge of the wing.

40
Q

what does the ribs give to the wing

A

cambered shape and transmit the load from the skin and stringers to the spars.

41
Q

ribs are also used where

A

ailerons, elevators, rudders, and stabilizers

42
Q

designed to carry part of the flight and ground loads in combination with the spars and ribs.

A

wing skin

43
Q

may be made from a wide variety of
materials such as fabric, wood, or aluminum.

A

wing skin

44
Q

kind of skin that can provide skin of varied thickness

A

Chemically milled aluminum skin

45
Q

are streamlined enclosures used primarily to house the engine and its components.

A

nacelles

46
Q

other name for nacelles

A

pods

47
Q

They usually present a round or elliptical profile to the wind thus reducing aerodynamic drag.

A

nacelles

48
Q

rigid structure used to hold the heavy aircraft engine in its place and position under or over an aircraft’s wings.

A

pylon

49
Q

incorporated to isolate the engine compartment from the rest of the aircraft.

A

firewall

50
Q

stainless steel or titanium bulkhead that contains a fire in the confines of the nacelle rather than letting it spread throughout the airframe.

A

firewall

51
Q

These are the structural assemblies to which the engine is fastened. They are usually constructed from chrome/molybdenum steel tubing in light
aircraft and forged chrome/nickel/ molybdenum assemblies in larger aircraft.

A

engine mounts

52
Q

detachable panels covering those areas into which access must be gained regularly, such as the engine and its accessories.

A

cowling

53
Q

It is designed to provide a smooth airflow over the nacelle and to protect the engine from damage.

A

cowling

54
Q

also known as the tail sect

A

empennage

55
Q

what does most empennage design consist of

A

tail cone, fixed aerodynamic surfaces or stabilizers, and movable aerodynamic surfaces.

56
Q

fixed surfaces on an empennage

A

horizontal stabilizer, vertical stabilizer

57
Q

moveable surfaces on an empennage

A

rudder, elevator

58
Q

two major groups of flight control surfaces

A

primary or main flight control surfaces and secondary or auxiliary flight control

59
Q

directional control of a fixed-wing aircraft takes place around what axes?

A

lateral, longitudinal, and vertical axes

60
Q

what are the primary flight control surfaces

A

ailerons, elevator, rudder

61
Q

are attached to the trailing edge of both wings and when moved, rotate the aircraft around the longitudinal axis.

A

ailerons

62
Q

is attached to the trailing edge of the horizontal stabilizer. When it is moved, it alters aircraft pitch, which is the attitude about the horizontal or lateral axis.

A

elevator

63
Q

hinged to the trailing edge of the vertical stabilizer. the aircraft rotates about the
vertical axis (yaw). shows the primary flight controls of a light aircraft and the movement they create relative to the three axes of flight.

A

rudder

64
Q

most common high-lift devices used on aircraft. These surfaces, which are attached to the trailing edge of the wing, increase both lift and induced drag for any given AOA.

A

flaps

65
Q

increases the angle of attack at which the wing will maintain its laminar airflow, resulting in the ability to fly the aircraft slower and still maintain control.

A

slats

66
Q

is a device found on the upper surface of many heavy and high-performance aircraft. It is stowed flush to the wing’s upper surface. When deployed, it rises up into the airstream and disrupts the laminar airflow of the wing, thus reducing

A

spoiler

67
Q

similar to flight spoilers in construction can also be found on the upper surface of the wings of heavy and high-performance

A

speed brakes

68
Q

force of the air against a control surface during the high speed of flight can make it difficult to move and hold that control surface in the deflected position.

A

tabs

69
Q

to maintain a uniform flight path and recover from the various upsetting forces. Also, to achieve the best performance, the aircraft must have the proper response to the movement of
the controls.

A

stability

70
Q

pilot action of moving the flight controls, providing the aerodynamic force that induces the aircraft to follow a desired flight path. When an aircraft is said to be controllable, it means that the aircraft responds easily and promptly to movement of the controls.

A

control

71
Q

when is an aircraft in a state of equilibrium?

A

when the sum of all the forces acting on the aircraft and all the moments is equal to zero

72
Q

Is the initial tendency of an aircraft to return to its original position when it’s disturbed.

A

static stability

73
Q

exists when the disturbed object tends to return to equilibrium.

A

positive static stability

74
Q

exists when the disturbed object tends to continue in the direction of disturbance.

A

negative static stability

75
Q

exists when the disturbed object has neither tendency, but remains in equilibrium in the direction of disturbance.

A

neutral static stability

76
Q

Is how the airplane responds over time to a disturbance.

A

dynamic stability

77
Q

deals with the resulting motion with time.

A

static stability

78
Q

motion about the aircraft’s longitudinal (fore and aft) axis is a lateral, or rolling, motion. The tendency to return to the original attitude from such motion is this.

A

lateral stability

79
Q

occurs when the angle of attack becomes so great that the laminar airflow separates from the surface of an airfoil, leaving an area of burbling that destroys the low-pressure area normally existing at the upper surface of a wing in flight.

A

stall

80
Q

how does the stall warning activate

A

wing is nearly stalled, the upward airflow moves the vane

midterms aamt 1-10 (3 decks)

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