frame design
Frame construction is used throughout the aerospace industry in the creation of welded steel-tube fuselages, piston-engine motor mounts, ribs, and landing gear. In this activity a frame assembly was designed for a motor mount structure for a Lycoming O-300 to be installed in a light aircraft. The original part is shown below:
From this point, research was conducted to find the strongest material to support the engine. The result was carbon steel and the following constrains were followed
1. The large plate represents the aircraft firewall
2. The structure will support one Lycoming O-300 engine weighing 250 pounds.
3. The structure will be loaded with negative 3G and positive 6G as a substitute for exaggerated engine weight
4. The structural members must be 1.5 in ANSI pipe
5. Frame members must be trimmed/extended to frame and mitered as necessary
6. Only six fixed constraints may exist and only at points that connect the frame members an the firewall
From there, the critical points and location and magnitude of mass were calculated:
1. The large plate represents the aircraft firewall
2. The structure will support one Lycoming O-300 engine weighing 250 pounds.
3. The structure will be loaded with negative 3G and positive 6G as a substitute for exaggerated engine weight
4. The structural members must be 1.5 in ANSI pipe
5. Frame members must be trimmed/extended to frame and mitered as necessary
6. Only six fixed constraints may exist and only at points that connect the frame members an the firewall
From there, the critical points and location and magnitude of mass were calculated:
The frame was final designed on Autodesk inventor and was used with extra-strong, 1.5 in. ANSI carbon steel piping. Part efore testing shown below:
The frame design was then tested. Results are below: The first image represents negative 3G testing, the second positive 6G
Frame analysis
This design is the best design possible due to its strength. It shows the least amount of stress, and on the outermost two connection points there is no stress whatsoever. This design show minimal stress due to tension and compression. nad is made of the strongest materials available, extra-strong carbon steel.
conclusion
1. The critical area did not differ in the analysis compared to design. This is due to the strategically placed fixed constraints, which strengthened all areas of the structure including the red high-stress area.
2. There are many more loading conditions an aircraft designer needs to include as constraints, such as air resistance, extra weight, and maneuverability.
2. There are many more loading conditions an aircraft designer needs to include as constraints, such as air resistance, extra weight, and maneuverability.