Removable Stressed Skin Fuselage Panelling
Removable Stressed Skin Fuselage Panelling
(OP)
Hi folks,
I'm currently undertaking a fuselage design project for a UAV. My question relates to something I read in this textbook, link to paragraph: Unmanned Aircraft Systems: UAVS Design, Development and Deployment by Reg Austin (http://bit.ly/zMaMaK).
I am looking at potential design solutions for incorporating stressed skin panelling, but that is almost completely removable around the fuselage. So far I see three solutions, using removable high tensile rubber seals around the panels, using a blended fit for the fuselage structure, or just having removable side panels with the top and bottom surfaces being placed under stress.
Discuss? Cheers,
Bradley
PS: Picture of solutions
http: //imageupl oad.org/en /file/1993 60/dsc-005 8.jpg.html
I'm currently undertaking a fuselage design project for a UAV. My question relates to something I read in this textbook, link to paragraph: Unmanned Aircraft Systems: UAVS Design, Development and Deployment by Reg Austin (http://bit.ly/zMaMaK).
I am looking at potential design solutions for incorporating stressed skin panelling, but that is almost completely removable around the fuselage. So far I see three solutions, using removable high tensile rubber seals around the panels, using a blended fit for the fuselage structure, or just having removable side panels with the top and bottom surfaces being placed under stress.
Discuss? Cheers,
Bradley
PS: Picture of solutions
http:





RE: Removable Stressed Skin Fuselage Panelling
Do you have any other requirements that might drive the solution such as low observability (stealth)? Or is it mainly aerodynamic considerations?
The page in that book you link to is blocked for me, though the proceeding page talks about needing mostly removable skin for access requirements - is this your main driver?
I'm not sure I follow the reasoning for your rubber seals per your attached sketch. The other option you show can sometimes be achieve by jogling/dimpling the skin, rather than machining thickness away.
(Just a warning, student posts for help on assignments are discouraged/banned as detailed in the links in my signature. However, leeway tends to be given for interesting topics of discussion etc. that doesn't get specific enough to be considered cheating.)
What is Engineering anyway: FAQ1088-1484: In layman terms, what is "engineering"?
RE: Removable Stressed Skin Fuselage Panelling
To clarify, this is a project based completely in my spare time, with the question more related to future projects.
Thanks for your response, it is solely structural considerations, just trying to prompt a discussion on what methods can be used to make stressed skin panels removable, as opposed to a modular UAV design or a truss structure.
Hope this helps to focus on what I am getting at.
Thanks
RE: Removable Stressed Skin Fuselage Panelling
Cheers
Greg Locock
New here? Try reading these, they might help FAQ731-376: Eng-Tips.com Forum Policies http://eng-tips.com/market.cfm?
RE: Removable Stressed Skin Fuselage Panelling
For removable panels you'd also need to worry about fasteners getting lost which may drive you to captive fasteners for frequently removed panels. However, these impose their own constraints.
I have to admit most of my relevant experience is on nominally single flight equipment not true aerostructures, hopefully someone with more directly relevant experience will feel like imparting some knowledge to both of us.
What is Engineering anyway: FAQ1088-1484: In layman terms, what is "engineering"?
RE: Removable Stressed Skin Fuselage Panelling
Cheers
Greg Locock
New here? Try reading these, they might help FAQ731-376: Eng-Tips.com Forum Policies http://eng-tips.com/market.cfm?
RE: Removable Stressed Skin Fuselage Panelling
I would think if this is your goal, the added supportive structure & parts count, ie nutplates & threaded fasteners, is going to make this thing to heavy to fly.
RE: Removable Stressed Skin Fuselage Panelling
I'll be pursuing a reinforced shell for my semi monocoque fuselage, with top and bottom surfaces in stress, trapezoidal cross section and consequently with the side panels removable. Been scanning CAP 722/CS-25(Closest spec!) and looks like a viable solution.
Any closing thoughts please let me know, but otherwise, cheers for the input folks
RE: Removable Stressed Skin Fuselage Panelling
Kenat has aero background. Just not on repetitive-use structures. Mine was similar, and my suggestion would have been to use a primacord charge to seperate the skin...but that is a single-use solution too.
RE: Removable Stressed Skin Fuselage Panelling