P18102: RIT Launch Initiative Hybrid Rocket
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Table of Contents

Structures Overview

Mass Allocation

Component Breakdown

Combustion Chamber

Updates for 2/22/18

Stress in Top Chamber Bulkhead

Stress in Top Chamber Bulkhead

Deflections in Top Chamber Bulkhead

Deflections in Top Chamber Bulkhead

Bolt Calcs (formulae from Roark's Stress & Strain)

Bolt Stresses

Force F = Chamber x-section * chamber pressure / # bolts

Bolt (effective axial) Area At = 0.7854(D-0.9743/n)^2 = 0.7854(0.25-0.9743/28)^2 = 0.03637in^2

Bolt (effective shear) Area As = pi*n*Le*Ds*(1/(2n)+0.57735(Ds,min - En,max))

Mcmaster ¼-20 cap screws: 150 KSI

Bolt Axial Failure

Inner Ring (10 bolts) (150000psi)/((830PSI*pi*(2.5in/2)^2)/(0.031in^2*10)) --> FOS = 11.4

Outer Ring (20 bolts) (150000psi)/((500PSI*pi*(5.0in/2)^2)/(0.031in^2*20)) --> FOS = 9.47

Bolt Tear-Out

Inner Ring (10 bolts) (40000psi)/((830PSI*pi*(2.5in/2)^2)/(0.34818in^2*10)) --> FOS = 34.2

Outer Ring (20 bolts) (40000psi)/((500PSI*pi*(5.0in/2)^2)/(0.34818in^2*20)) --> FOS = 28.3

Vessel Calcs (formulae from Roark's Stress & Strain)

Sigma_axial = pr/2t = (500PSI * 2.5in)/(2*0.25in) = 2.5 ksi (16 margin)

Sigma_hoop = pr/t = (500PSI * 2.5in)/(0.25in) = 5.0 ksi (8 margin)

Structures Action Items

Thus far, only a feasibility study has been completed on the combustion chamber to determine how difficult it would be to operate at an internal pressure of 500 psi. The following presentation shows this this pressure is very feasible.

Combustion Chamber Feasibility Analysis

A more in-depth analysis will need to be completed once a more finalized geometry is completed. Additionally, combined loadings and temperature considerations will be included into the analysis to ensure that our metallic factor of safety of 2 is met.

A quick hoop-stress calculator can be found here. The last tab shows some temperature considerations on stress and the resulting factor of safeties.

Chamber Selection

Prior to our Preliminary Detailed Design Review, we finalized our decision to make the combustion chamber of aluminum. This was primarily due to mass and cost concerns. Strength should not be an issue unless the hot gasses find a path to the casing. A huge goal of our testing will be to ensure that the casing is not heating up from lack of insulation or gaps between insulative components.

The two primary choices for combustion chamber material at this point are:

The grade is to be finalized based on availability and cost from chosen supplier. We are aiming for the following dimensions:

Estimated Mass

As mentioned prior, the potential max temperature of the combustion chamber is an area of concern at this time. According to some hand calculations, we will be able to maintain a FoS of 2 up to:

These hand-calcs are documented here.