Lander Phase Hybrid Propulsion System Propellant Tank Sizing

Lander Phase: Hybrid Propulsion System Propellant Tank Sizing and Pressure Analysis Thermodynamic analysis on Hydrogen peroxide Tanks Week 5 Presentation Thursday, Feb 12, 2009 1 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Propellant Tank Sizing and Pressure Analysis Tank Sizing: Lander. Wet Propellant mass 158. 62 kg Propellant Tank Volume 0. 115 m 3 Operating Chamber Pressure 1. 73 MPa Manufacturing Material Aluminum Yield Strength Wall Thickness Tank inert mass Al – 7075 T 6 500 MPa 0. 6 mm 1. 6 kg Pressure-Fed System: Pressure of the Tank = 2. 59 MPa Further Analysis: Mass and Volume of the pressurized tank 2 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Preliminary Thermodynamic Analysis: Thermal Blanket Insulation Assumptions: Tank operating Temperature = 283 K (50 F) Surrounding Temperature = 2. 73 K ΔT = 280. 3 K Space Blanket Properties: k (thermal conductivity) = 0. 044 W/m. K thickness = 200 mm mass ~ 2 kg Heat dissipation ~ 35 W 3 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Backup Slides: Pressure-Fed System § For smaller Tank volumes: Pchamber = 1. 73 MPa ∆Pdynamic = ½�� v 2 ~ 0. 02 MPa ∆Pfeed (Upper bound) ~ 0. 05 MPa ∆Pcool ~ 0. 15 pc = 0. 26 MPa ∆Pinjector ~ 0. 3 pc = 0. 519 MPa Ptank ~ 2. 58 MPa 4 Source: Humble, R. W. , Henry, G. N. , & Larson, W. J. (1995). Space Propulsion and Design. : Mc. Graw-Hill Companies, Inc. AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Backup Slides: Tank sizing 5 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Backup Slides: Tank sizing Continued … Spherical pressure Vessel Where: § P is the internal pressure § t is the wall thickness § d is the inside diameter of the cylinder. § σ is the hoop stress. 6 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Backup Slides: Tank Sizing Continued … 7 AAE 450 Spring 2009 Saad Tanvir Propulsion Group

Backup Slides: Thermodynamic Analysis Q: Rate of Heat transfer [W] A: Area of Cross section of the tank [m 2] k: Thermal Conductivity [W/m. K] ΔT: Temperature Difference [K] t: Thickness of the blanket [m] For Tank (Aluminum) A = 1. 14 m 2 t = 0. 001 m ΔT = 280. 3 K k = 235 W/m. K 8 ~70 MW AAE 450 Spring 2009 Saad Tanvir & Brad Appel Propulsion Group