PROBLEM1. The figure shows a space quality hydrazine fuel tank designed by the Orbital Propulsion Center and manufactured from Ti6A14V STA (3.7164.7) titanium alloy material. (a) Since the length of the tank is 890 mm, calculate the radius r of the 176.5 liter tank. (b) Calculate the wall thickness t such that it will not be deformed at 36.9 Bar pressure and will not disintegrate at 49.2 Bar pressure. (c) Calculate the maximum absolute shear stress that will occur in the tank at operating conditions (MEOP). http://www.space-propulsion.com/spacecraft-propulsion/hydrazine-tanks/index.html Surface Tension Propellant Tank OST 33/0 Net Volume Range 176.5 Litres Hydrazine (N,H,) Spherical with a cylindrical Intersection 24.63 bar Propellants Geometrical Shape Maximum Expected Operating Pressure (MEOP) Proof Pressure (1.5 x MEOP) 36.95 bar Burst Pressure (2.0 x MEOP) 49.26 bar Interface Fixation 4 Suspension Trunnions Materials - Pressure Vessel TIGAIAV STA (3.7164.7) - Trunnions / Ports TIGAI4V (3.7164.1) - PMD TIGAIAV (3.7164.1) Tank Mass Range 13.5 kg Project Involvement Cosmo / SkyMed

PROBLEM1. The figure shows a space quality hydrazine fuel tank designed by the Orbital Propulsion Center and manufactured from Ti6A14V STA (3.7164.7) titanium alloy material. (a) Since the length of the tank is 890 mm, calculate the radius r of the 176.5 liter tank. (b) Calculate the wall thickness t such that it will not be deformed at 36.9 Bar pressure and will not disintegrate at 49.2 Bar pressure. (c) Calculate the maximum absolute shear stress that will occur in the tank at operating conditions (MEOP). http://www.space-propulsion.com/spacecraft-propulsion/hydrazine-tanks/index.html Surface Tension Propellant Tank OST 33/0 Net Volume Range 176.5 Litres Hydrazine (N,H,) Spherical with a cylindrical Intersection 24.63 bar Propellants Geometrical Shape Maximum Expected Operating Pressure (MEOP) Proof Pressure (1.5 x MEOP) 36.95 bar Burst Pressure (2.0 x MEOP) 49.26 bar Interface Fixation 4 Suspension Trunnions Materials - Pressure Vessel TIGAIAV STA (3.7164.7) - Trunnions / Ports TIGAI4V (3.7164.1) - PMD TIGAIAV (3.7164.1) Tank Mass Range 13.5 kg Project Involvement Cosmo / SkyMed

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

PROBLEM1. The figure shows a space quality hydrazine fuel tank designed by the Orbital
Propulsion Center and manufactured from TI6AI4V STA (3.7164.7) titanium alloy material.
(a) Since the length of the tank is 890 mm, calculate the radius r of the 176.5 liter tank.
(b) Calculate the wall thickness t such that it will not be deformed at 36.9 Bar pressure and will
not disintegrate at 49.2 Bar pressure.
(c) Calculate the maximum absolute shear stress that will occur in the tank at operating
conditions (MEOP).
http://www.space-propulsion.com/spacecraft-propulsion/hydrazine-tanks/index.html
Surface Tension Propellant Tank OST 33/0
Net Volume Range
176.5 Litres
Propellants
Hydrazine (N,H,)
Geometrical Shape
Spherical with a cylindrical Intersection
Maximum Expected Operating
Pressure (MEOP)
24.63 bar
Proof Pressure (1.5 x MEOP)
36.95 bar
Burst Pressure (2.0 x MEOP)
49.26 bar
Interface Fixation
4 Suspension Trunnions
Materials
- Pressure Vessel
TI6AI4V STA (3.7164.7)
- Trunnions / Ports
TI6A|4V (3.7164.1)
TI6A|4V (3.7164.1)
- PMD
Tank Mass Range
13.5 kg
Project Involvement
Cosmo / SkyMed

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