Problem Statement:
The Torrance office of Moog Aircraft Group is primarily involved with designing, manufacturing, and testing of various flight control actuation components for both commercial and military application. These components include the various slats, flaps, gearboxes, and actuators of the entire wing. Moog conducts their tests in aircraft attitude, meaning the exact shaft angle configuration that the system would be in the wing. Because the wing design is unique to each airplane, Moog experiences the physical limitations of each wing design and is forced to build a new test stand for each new wing, which is very expensive.
Project Overview:
The objective of this Capstone Project is to design a test stand that is capable of supporting and testing a number of different actuators. General guidelines for shaft angle and size are based off of the Airbus A350 -1000 High Lift System, but the stand must also be able to be used for future designs. The stand must support the use of both electrical and hydraulic power with the capability to make simple interface changes for unique products. It must also provide a means for load control and be durable enough to last for multiple actuator test cycles. The goal was to minimize both material and labor costs by reusing materials and avoiding the design process for production of a new test stand for each actuator.
Design Objectives
1. Universal Fit
3. Cost
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DESIGN ALTERNATIVES
Lift & Tilt
X & Y: Physical Movement of the Tables Z: Hydraulic Lift Table Angular: Hydraulic Tilt Table |
Stack & Hinge
X & Y Motion: Physical Movement of the Tables Z Motion: Hydraulic Lift Table / Stacking Metal Bars Angular Motion: Hinge with Locking Feature |
Power Screw Design
X & Y: Green Sliding Rails Z: Light Blue Power Screw Angular: Red Universal Joint |