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Aircraft Systems 1 > Chapter 1 - Airframe Structure > Flashcards

Chapter 1 - Airframe Structure Flashcards

1
Q

What factors are considered in the design of an aircraft?

A 
Stress
Strain
Stiffness or rigidity
Design Limit Load (DLL)
Temperature
Corrosion
Natural/Environmental Hazards - Lightning, bird strikes, hail, saline environments, erosive atmospheres (e.g. sand), pollutants, etc
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2
Q

What is stress?

A

Load per unit area of cross-section

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3
Q

What is strain?

A

Deformation caused by stress

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4
Q

What is stiffness (or rigidity)?

A

Ratio of stress over strain

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5
Q

What is the Design Load Limit (DLL)?

A

Maximum load the designer would expect and airframe to experience in service

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6
Q

What two sources of heating need to be considered when taking temperature in account during aircraft design?

A

Local heating - Structures near engines, heat exchangers, hot gas ducts, etc

Kinetic heating - High ambient temp, surface of airframe at high speeds due to friction

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7
Q

What are the two key types of corrosion that must be considered during aircraft design?

A

Chemical corrosion

Stress corrosion

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8
Q

What are the ideal properties of materials used in aircraft construction?

A

High strength and stiffness

Lightness

Low cost

Ease of construction and production

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9
Q

Name some materials commonly used in aircraft construction?

A

Aluminium alloys

Titanium alloys (fire resistant + light and strong)

Magnesium alloys (light but rare due to flammability)

Steel

Carbon Fibre Composites (CFCs)

Glass Reinforced Plastic (GRP) - Radomes

Wood

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10
Q

What is the primary consideration when designing a fuselage?

A

The load it has to carry, this governs its shape.

Aerodynamic features are secondary to the necessity to accommodate payload.

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11
Q

What are the 3 common types of fuselage structure?

A

Truss

Monocoque

Semi-monocoque

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12
Q

What does a truss structure consist of?

A

Longerons

Vertical Web Members

Diagonal Web Members

Stringers

Bulkheads

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13
Q

What does a monocoque structure consist of?

A

Bulkhead

Stressed skin to support load

Frames

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14
Q

What does a semi-monocoque structure consist of?

A

Bulkhead

Stressed skin attached to sub structures

Frames

Stringers

Note - Can have longerons running the length of it as well, see diagrams in section 5-1-2 of manual and memorise

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15
Q

Note - See manual for the roles of the different parts making up the fuselage.

A

Is this information required for the exam?

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16
Q

What makes up a typical wing structure?

A

Front Spar

Rear Spar

Ribs

Stringers

Skin

Note - Memorise diagram in section 5-1-3 of the course manual

17
Q

What parts of the wing structure carry wing loading forces?

A

Spars, stringers, ribs and skin (all)

18
Q

What are the 3 typical wing configurations used in aircraft design?

A

High wing
Mid wing
Low wing

19
Q

Why might a high wing be used?

A

Enables ease of loading for cargo aircraft + gets the wing spar out of the way for greater internal stowage

20
Q

Why might a mid wing be used?

A

Presents a smaller radar signature, used on “stealth” aircraft

21
Q

Why might a low wing be used?

A

Shorter undercarriage, crash protection

22
Q

What design features can be used to make an aircraft efficient in both subsonic and supersonic flight?

A

Variable sweep wings
Moderate sweep - Thin wings with high light devices (flaps and slats)
Anhedral wing - Unstable
Dihedral wing - Stable

23
Q

What does the empennage consist of?

A

Fixed surfaces - Fin and Tailplane

Moveable surfaces - Elevator, Rudder and Trim Tabs

Ground Adjustable surfaces - Fixed Tab

24
Q

What is the primary purpose of the empennage?

A

Provides stability and control for the aircraft about the normal and lateral axis.

25
Q

What is the role of the tailplane?

A

Provided longitudinal stability about the lateral axis.

26
Q

Name four common tailplane configurations.

A

All flying tailplane

Taileron

Tailless

V Tail

27
Q

Explain what an all flying taiplane is/why it is used?

A

An all flying tailplane means the entire tailplane’s AoA can be adjusted by trim actuators to compensate for the increased nose down trim forced at higher speeds and any changes in the CoG due to payload and fuel distribution, with MINIMAL increase in trim drag.

I.e. great control over wide trimming range for cargo/fuel distribution and is far more fuel efficient than greatly trimming the control surface itself (less drag).

28
Q

How does a taileron work/what advantage does it offer?

A

Each side can be actuated separately to the other or together, provides the ability to act as either an aileron or an elevator, providing control in both pitch and roll.

29
Q

How does control work in a tailless aircraft?

A

Control power is provided by trailing edge elevators or elevons.

Wing trailing edge flaps cannot be used.

Consequences are the ineffectiveness of trailing edge controls at high supersonic speeds.

30
Q

How does a V tail work?

A

Two fins, each performing the functions of both a rudder and elevator.

31
Q

What is the purpose of a canard?

A

A canard reduces trim drag at high speeds.

Up-load will be required on the canard for trim.

32
Q

What are the main features influencing the fuselage design for a combat aircraft?

A

Powerplant installation

Fuel and undercarriage stowage and weapon carriage

Low frontal area with a smooth build-up of cross-section area over the forebody, canopy and wings, followed by a gradual decrease over the afterbod

Stealth technology (both radar and IR)

33
Q

What are the main features influencing the fuselage design for a transport aircraft?

A

Cabin length

Cabin width (i.e. usable floor area)

Freight volume

Passenger and freight distribution to maintain the correct CG

34
Q

What are the primary flying controls?

A

Rudder

Elevators

Ailerons

35
Q

What are the secondary flying controls?

A

Spoilers

Flaps

Slats

36
Q

Describe wing loading?

A

Forces arising on the wing due to the aircraft’s manoeuvre and the payload.

Aircraft Systems 1 (6 decks)

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