Academic Field

Industrial Engineering, Mechanical Engineering

Faculty Mentor Name

Christopher Kumar

Presentation Type

Poster Presentation

Abstract

The Cessna 172 Skyhawk is the world’s most popular single engine aircraft. It is considered to be the safest general aircraft while being remarkably agile and stable. Aircraft are predominantly thought of as dynamic vehicles although static analysis can be applied to determine accurate results. This paper demonstrates the use of theoretical static equilibrium concepts in understanding actual, experimental situations. A three dimensional (3D) mechanical model of a Cessna 172 Skyhawk was created to analyze the forces acting on the wing strut and fuselage during simulated flight. The forces were recorded by placing four load sensors on the members and hanging the entire model from the ceiling using two centroid points on the wings. The experiment model was constructed using a Pasco 3D structural kit and the tension and compression forces on the members were measured using load cells, and Pasco-Capstone software. The obtained results were validated theoretically using static equilibrium principles.

Keywords

Strut, Static Equilibrium, Lift Forces on Wing

Start Date

10-4-2015 11:15 AM

End Date

10-4-2015 12:00 PM

Location

SERC House of Fields

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Apr 10th, 11:15 AM Apr 10th, 12:00 PM

Static Force Analysis of a Wing Strut for the Cessna 172 Skyhawk

SERC House of Fields

The Cessna 172 Skyhawk is the world’s most popular single engine aircraft. It is considered to be the safest general aircraft while being remarkably agile and stable. Aircraft are predominantly thought of as dynamic vehicles although static analysis can be applied to determine accurate results. This paper demonstrates the use of theoretical static equilibrium concepts in understanding actual, experimental situations. A three dimensional (3D) mechanical model of a Cessna 172 Skyhawk was created to analyze the forces acting on the wing strut and fuselage during simulated flight. The forces were recorded by placing four load sensors on the members and hanging the entire model from the ceiling using two centroid points on the wings. The experiment model was constructed using a Pasco 3D structural kit and the tension and compression forces on the members were measured using load cells, and Pasco-Capstone software. The obtained results were validated theoretically using static equilibrium principles.