Quiz 1
The quiz is concerned with Chapter 1 - aircraft structure introduction and Chapter 2- airframe structure. There will be 25 questions picked in random order. Remember, you have to finish in 20 minutes.
Now, let's go!
The aircraft structure must remain substantially intact after experiencing:
the design ultimate load times a 1.5 factor of safety
the design limit load plus the design ultimate load
the design limit load times a 1.5 factor of safety
A fail safe structure:
is changed before its predicted life is reached
has redundant strenghth which will tolerate a certain amount of structural damage
is secondary structure of no structual significance
A safe life structure:
is changed before its predicted life is reached
should not fail until a predicted number of fatigue cycles has been achieved
will only fail after a known number of operations of hours of use
Of the airframe stresses, ( ) is a force which tends to shorten a structure.
Which design philosophy is applied for the following spar?
fail safe
damage tolerant
safe life
During testing, when a ( ) is applied to the structure, it must not suffer any permanent deformation.
Proof Load
Design Limit Load
Design Ultimate Load
The metal showed in the picture below suffered from:
oxidation corrosion
stress corrosion
electrochemicalcorrosion
请选择你的学号和姓名：
181340104 陈家毅
181340107 陈扬
181340114 黎洺豪
181340115 李好
181340122 屈昊橙
181340125 唐世明
181340147 邹开杰
181340204 范书麟
181340224 刘渠
181340226 刘雨昂
181340227 吕英哲
181340306 果琪智
181340312 贾一帆
181340333 王泽涛
181340341 谢瑞
181340347 赵涌任
181340412 兰义堃
181340707 郭胜超
181340725 汪锴
181340801 包麓田
181340809 段正一
181340818 李润鸿
181340824 任纪星
181340838 邢海涛
181340903 晁培源
181340907 都业鹏
181340918 林正茂
181340934 徐伟航
181341416 刘肖冰
181341419 娄上
181341422 佘洋
181341423 沈彦玎
181341510 吉颉颃
181341532 孙茂杰
181341533 谭明星
181341537 温家勋
181341605 丁伟平
181341606 董一丁
181341611 蒋小强
181341629 吴穹径
In the diagram shown, what strain is being produced in the vertical pin?
The maximum load regulated in aircraft operation manual is:
desine limit load
design ultimate load
proof load
Safe life on an aircraft is based on:1.calendar time2.total flying hours3.landings4.pressure cycles
only 2
1 and 2 are correct
any combination of all of the statements are taken into consideration
Which component of the airplane produce most of the lift required for flight?
The fuselage is designed to be ( ) for most of the modern transport aircraft.
semi-monocoque structure
monocoque structure
non-cantilever structure
Wings are subject primarily to:
bending and twisting loads.
tention and shearing loads.
bending and tention loads.
Whats the name of the component labeled with ②?
Motion around vertical axis is called:
A damage tolerant structure:
has degree of structural strength redundancy spread over a large area
is replaced when it reaches its predicted life
need not be repaired until the aircraft undergoes deep maintenance
Control surface flutter is minimised by:
mass balance
aerodynamic balance
reducing load
Which fuselafe design is not tolerant to surface damage?
A monocoque structure
A rigid frame structure
A semi-monocoque structure
Flight deck forward windows are heated to improve:
vision in icing cinditions and impact resistance
vision in all climatic conditions
vision in icing conditions
Choose the correct statement.
DUL is equal to 1.5 ×DLL
DLLisequal to 1.75 × DUL
DLL is equal to 1.5 × DUL
When an aircraft is pressurised what stress(es) is the fuselafe subjected to?
Axial only
Longitudinal only
Both hoop and axial
Which component is used to store fuel tank?
The name of component labeled with C is: ____________
The name of the component labeled with A is: ____________
The name of the component labeled with E is: ____________
The name of the component labeled with F is: ____________
Longitudinal control is provided by :
