Airdale
Member
- Joined
- Dec 31, 2002
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Hello All,
I have some questions about compressive loading on phenolic tubing, and if it will survive without having to reinforce the phenolic tubing with either fiberglass or carbon fiber.
Known qualities are: phenolic tubes can withstand a compressive loading of 1000 psi based on this web sites research https://www.rocketmaterials.com/data/tubes/ before failing.
My rocket design has the following properties a 5.5-inch diameter Red Arrow hobbies phenolic airframe. The cross sectional area of a 5.5-inch tube is 23.75 inches. If I did my math right?
Maximum velocity of the proposed design is 2453.42 feet per second. Based on Greg Deputy Excel spreadsheet on compressive loading of airframes diameters. And selecting a 5.5-inch diameter airframe, and based on a flight of 2453.42 feet per second the spreadsheet indicated a compressive load of 1176.97 lbs. force at sea level. Which needs to be converted to psi to make all things equal (and not apples & oranges) right?
To do this I need to do take the frontal area of my rocket and divide by the force, that gives me psi (lbs force per square inch). Right?
So if I take the 1176.97 lbs and divide it by 23.75 inches in area. Force I should get 49.55 psi. Is this correct or did I mess it up completely?
I have some questions about compressive loading on phenolic tubing, and if it will survive without having to reinforce the phenolic tubing with either fiberglass or carbon fiber.
Known qualities are: phenolic tubes can withstand a compressive loading of 1000 psi based on this web sites research https://www.rocketmaterials.com/data/tubes/ before failing.
My rocket design has the following properties a 5.5-inch diameter Red Arrow hobbies phenolic airframe. The cross sectional area of a 5.5-inch tube is 23.75 inches. If I did my math right?
Maximum velocity of the proposed design is 2453.42 feet per second. Based on Greg Deputy Excel spreadsheet on compressive loading of airframes diameters. And selecting a 5.5-inch diameter airframe, and based on a flight of 2453.42 feet per second the spreadsheet indicated a compressive load of 1176.97 lbs. force at sea level. Which needs to be converted to psi to make all things equal (and not apples & oranges) right?
To do this I need to do take the frontal area of my rocket and divide by the force, that gives me psi (lbs force per square inch). Right?
So if I take the 1176.97 lbs and divide it by 23.75 inches in area. Force I should get 49.55 psi. Is this correct or did I mess it up completely?