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:. Asteroseismology
:. Dark Matter Galaxies
:. EPR
:. Gravitophotons
:. Hybrid Rocket Engine
:. Pulse-Ram Induction

:. Sections:
:. Disclaimer
:. Purpose
:. Theory
:. References

:. Components:
:. Combustion Chamber
:. CDN Nozzle
:. Gasoline Tank
:. Injector System
:. Internal Structure
:. Launch Control
:. Pressure Manifold
:. Pressure Tank
:. Propellants
:. Solid Fuel and Ignition
:. T-stoff Tanks
:. --

:. Data:
:. CFD CDN01
:. FEA Combustion Chamber
:. FEA F-02
:. FEA F-03
:. FEA F-04
:. FEA F-05
:. FEA F-06
:. FEA F-07
:. FEA T-stoff Flange
:. Pressure Tank Test

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Stress analysis of the combustion chamber

1. Materials
2. Load & Restraint Information
3. Study Property
4. Stress Results
5. Strain Results
6. Displacement Results
7. Deformation Results
8. Design Check Results
9. Appendix

1. Materials:

No. Part Name Material Mass Volume

1

combustion chamber

[SW]AISI 1020

3.56961 lb

12.5071 in^3

2. Load & Restraint Information:

Restraint
Restraint-1 <combustion chamber> on 1 Edge(s), 5 Face(s) fixed.



Load
Pressure-1 <combustion chamber> on 2 Face(s) with Pressure 70 psi along direction normal to selected face Sequential Loading
Force-1 <combustion chamber> on 2 Edge(s) apply force -45 lb normal to reference plane with respect to selected reference Face< 1 > using uniform distribution Sequential Loading
Temperature-2 <combustion chamber> on 5 Face(s) with temperature 110 Celsius  


3. Study Property:

Mesh Information
Mesh Type: Solid mesh
Mesher Used: Standard
Automatic Transition: Off
Smooth Surface: On
Jacobian Check: 4 Points
Element Size: 0.13351 in
Tolerance: 0.0066754 in
Quality: High
Number of elements: 37937
Number of nodes: 74869


Solver Information
Quality: High
Solver Type: FFEPlus
Option: Include Thermal Effects
Thermal Option: Input Temperature
Thermal Option: Reference Temperature at zero strain: 25 Celsius

Combustion chamber-combustion chamber-Stress-Plot1
JPEG


4. Stress Results:

Name Type Min Location Max Location

Plot1

VON: von Mises stress
267.386 psi
Node: 57626
(10.4672 in,
12.4579 in,
7.24506 in)
49444.1 psi
Node: 43716
(12.8308 in,
9.32781 in,
5.79605 in)


Combustion chamber-combustion chamber-Stress-Plot1
JPEG

Combustion chamber-combustion chamber-Stress-Plot2
JPEG

5. Strain Results:

Name Type Min Location Max Location
Plot1
ESTRN: Equivalent strain
1.12172e-005
Element: 2291
(13.9059 in,
10.9181 in,
7.13456 in)
0.00122873
Element: 15258
(11.388 in,
10.3562 in
-0.794549 in


Combustion chamber-combustion chamber-Strain-Plot1
JPEG

Combustion chamber-combustion chamber-Strain-Plot2
JPEG

6. Displacement Results:

Name Type Min Location Max Location

Plot1

URES: Resultant displacement
0 m
Node: 2499
(9.69908 in,
10.5129 in,
7.12006 in)
7.56836e-005 m
Node: 5485
(11.7865 in,
10.9583 in,
-2 in)


Combustion chamber-combustion chamber-Displacement-Plot1
JPEG

Combustion chamber-combustion chamber-Displacement-Plot2
JPEG

7. Deformation Results:

Plot No. Scale Factor
1
313.67


Combustion chamber-combustion chamber-Deformation-Plot1
JPEG

8. Design Check Results:
Combustion chamber-combustion chamber-Design Check-Plot1
JPEG

Combustion chamber-combustion chamber-Design Check-Plot2
JPEG


9. Appendix:
Material Name:
[SW]ANSI 1020
Description:
--
Material Source:
Used SolidWorks Material
Material Library Name:
SolidWorks Material
Material Model Type:
Linear Elastic Isotropic


Property Name Value Units Value Type

Elastic modulus

2e+011

N/m^2

Constant
Poisson's ratio
0.29
NA
Constant
Shear modulus
7.7e+010
N/m^2
Constant
Mass density
7900
kg/m^3
Constant
Tensile strength
4.2051e+008
N/m^2
Constant
Yield strength
3.5157e+008
N/m^2
Constant
Thermal expansion coefficient
1.5e-005
Kelvin
Constant
Thermal conductivity
47
W/(m.K)
Constant
Specific heat
420
J/(kg.K)
Constant