Stroke of a shock absorber is defined as _______

lift required at takeoff

length of crank shaft of engine

piston distance travelled inside engine

required deflection of the shock absorbing system

Correct Answer : required deflection of the shock absorbing system

Explanation : Stroke of absorber can be defined as the required deflection of the shock absorbing system. Stroke of the shock absorber depends upon number of factors such as shock absorbing material etc. Lift required at takeoff will be more than its weight.

Recently Updated in Aircraft Design Questions

Hydraulic system affect conceptual design based on ______

lift required at tail

space for control surface

hydraulic pump space requirements

secondary control surface

Correct Answer : Option (C) : hydraulic pump space requirements

Explanation : A typical hydraulic system will affect conceptual design based on space requirements for pumps typically. Control surface are located at the wing or at tail section. Lift required at tail will be affected by which type of airfoil is used.

Following diagram represents _______

fuel tank location

simplified hydraulic system

pneumatic subsystem

wing loading diagram

Correct Answer : Option (B) : simplified hydraulic system

Explaination : A typical hydraulic system is shown. A simplified hydraulic system can be observed in the diagram. As shown in the diagram a simplified hydraulic system includes actuators, feed lines etc. Fuel tank can be located in fuselage, in wing or in tail.

A typical electrical system may include _____

only generator

only transformers

drag polar system

generators, transformers, cables, etc

Correct Answer : Option (D) : generators, transformers, cables, etc

Explanation : A typical electrical system consists of generators, transformers, cables etc. It is used to provide electrical energy. Drag polar is graphical representation of drag. It is used to show relationship between drag and lift.