CF188 Landing Gear Upgrade: Research on Design, Loads & Testing

This presentation delves into the study of the CF188 landing gear upgrade, chosen for its landing gear configuration that facilitates the achievement of study aims and objectives. The primary goal was to assess the effectiveness of proposed modifications to minimize mechanism assembly failure risks. The presentation reviews landing gear uses, analyzes fixed and retractable types, and explores wheel, tandem, and tricycle landing gear arrangements. It also addresses horizontal, vertical, and crush loads experienced during ground operations. Interviews with aircraft design practitioners and practical sessions were conducted, with testing carried out in three phases using a build-up approach. Data was collected using two landing gear configurations for comparison, highlighting the challenges in designing landing gear systems with minimum volume, weight, reduced life cycle costs, and high performance. The research involved reviewing numerous books and publications to gather relevant data.

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Slide 1
 The topic of study was ‘study of the CF188 landing gear upgrade’.
 The CF 188 aircraft which was under study was selected due to its landing gear
configuration which provided an opportunity to achieve all the aims and objectives of
the study.

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Slide 2
The main aim of the project was to The main aim of this thesis was to research the
effectiveness of the proposed modifications to the landing gear of the CF188 in order to
minimise the risk of planning Mechanism Assembly failure.
Objectives were also set to help in achieving the aim of the project.

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Slide 3
 Various uses of the landing gears were reviewed and analysed

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 The fixed landing gears means that the landing gears are attached to the airframe and
they always remain exposed to the slipstream during flight while Retractable landing
gear stow in wing compartment or fuselage when the aircraft is in flight

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There three basic arrangements of landing gears: Wheel type landing gear (convectional
gear), tandem landing gears and tricycle-type landing gear


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 In this arrangement the main gear are located at the forward centre of gravity .Due to
that the tail is forced to get support from the third wheel assembly.

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 The tail gear and the main gear are aligned longitudinally to the axis of the aircraft.

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 It is usually made up of the nose gear and the main gear. Tricycle-type of landing
gears are used on both small and large aircrafts

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 During the operations of the landing gears on the ground it is subjected to the
horizontal, vertical and crush loads

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Slide 10
 The vertical loads are due to the aircraft weight and to the normal acceleration during
the touch down which is generated by descent rate and the impact of the weight of the
air craft.
 The horizontal loads which are also referred to as the drag loads are usually generated
from the friction between the landing surface and the tire.
 The crush loads happens when the aircraft runs over a sharp object for example the
arresting cable.

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Slide 11

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Various practitioners who are involved in the design of the aircrafts were interviewed on
various issues which are related to the design of landing gears. Questions which were relating
to the topic of study were used during the interviews.

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Slide 13
 A practical session was carried out regarding the design of landing gears and various
components were tested

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Slide 14
 The testing process was carried out in three phases by use of the build up approach.

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Slide 15
 The Study of the CF188 Landing Gear Upgrade was selected as a topic of research
because the design of the landing gear is the most challenging phase in the design of
the aircrafts.

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 It is very important to reduce the landing gear development and design to meet all the
regulatory and safety requirements.

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 For the purpose of comparison,data was collected by use of two landing gear
configurations.

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 There were no differences noticed between the two landing gear configurations.

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 The need to design a landing gear system with the minimum volume, minimum
weight, reduced life cycle cost and high performance have posted many challenges to
the aircraft designers and other practitioners in that field

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Slide 20
 Many books and other publications were reviewed to obtain data.