MARYLAND. Rocket engine basics Survey of the technologies Propellant feed systems Propulsion systems design U N I V E R S I T Y O F
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1 Rocket engine basics Survey of the technologies Propellant feed systems Propulsion systems design 2004 David L. Akin - All rights reserved umd.edu
2 Overview of the Design Process Program Objectives 1 System Requirements Vehicle-level Estimation (based on a few parameters from prior art) Increasing complexity Increasing accuracy System-level Estimation (system parameters based on prior experience) Decreasing ability to comprehend the big picture System-level Design (based on disciplineoriented analysis)
3 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal
4 Thermal Rocket Exhaust Velocity Exhaust velocity is V e = 2" " #1 $T 0 M + - % 1# p ( e - ' & p * - 0 ), " #1 " / where M " average molecular weight of exhaust " # universal gas const.= Joules mole K " # ratio of specific heats $ 1.2
5 Ideal Thermal Rocket Exhaust Velocity Ideal exhaust velocity is V e = 2" " #1 $T 0 M This corresponds to an ideally expanded nozzle All thermal energy converted to kinetic energy of exhaust Only a function of temperature and molecular weight!
6 Thermal Rocket Performance Thrust is T = m V e + ( p e " p amb )A e Effective exhaust velocity T = m c " c = V e + p e # p amb Expansion ratio # A t = % " +1 A e $ 2 & ( ' 1 # " )1 p e % $ p 0 ( ) A e m 1 * &" " +1, ( ' " )1 1) # p e, %, $ p 0 + & ( ' " )1 " " I sp = c % $ ' # g 0 & - / / /.
7 Nozzle Design Pressure ratio p 0 /p e =100 (1470 psi-->14.7 psi) A e /A t =11.9 Pressure ratio p 0 /p e =1000 (1470 psi-->1.47 psi) A e /A t =71.6 Difference between sea level and ideal vacuum V e V # e = 1" p e V % e,ideal $ I sp,vacuum =455 sec --> I sp,sl =333 sec p 0 & ( ' ) "1 )
8 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Monopropellants Bipropellants Solids Hybrids Liquids Air-Breathing
9 Solid Rocket Motor From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
10 Solid Propellant Combusion Characteristics From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
11 Solid Grain Configurations From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
12 Short-Grain Solid Configurations From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
13 Advanced Grain Configurations From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
14 Liquid Rocket Engine UNIVERSITY OF
15 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Monopropellants Bipropellants Solids Hybrids Liquids Air-Breathing Pressure-Fed Pump-Fed
16 Liquid Propellant Feed Systems
17 Space Shuttle OMS Engine From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
18 Turbopump Fed Liquid Rocket Engine From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986 UNIVERSITY OF
19 Sample Pump-fed Engine Cycles From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
20 Gas Generator Cycle Engine From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
21 SSME Engine Cycle From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
22 Liquid Rocket Engine Cutaway From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986 UNIVERSITY OF
23 H-1 Engine Injector Plate UNIVERSITY OF
24 Injector Concepts From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
25 Solid Rocket Nozzle (Heat-Sink) From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
26 Ablative Nozzle Schematic From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
27 Active Chamber Cooling Schematic From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
28 Boundary Layer Cooling Approaches From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
29 Hybrid Rocket Schematic From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
30 Hybrid Rocket Combustion From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
31 Thrust Vector Control Approaches From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
32 Apollo Reaction Control System Thrusters
33 Space Shuttle Primary RCS Engine From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
34 Monopropellant Engine Design From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
35 Cold-gas Propellant Performance From G. P. Sutton, Rocket Propulsion Elements (5th ed.) John Wiley and Sons, 1986
36 Pressurization System Analysis P g0, V g P gf, V g Adiabatic Expansion of Pressurizing Gas p g,0 V g " = p g, f V g " + p l V l " Known quantities: P g,0 =Initial gas pressure P L, V L Initial P L, V L Final P g,f =Final gas pressure P L =Operating pressure of propellant tank(s) V L =Volume of propellant tank(s) Solve for gas volume V g
37 Boost Module Propellant Tanks UMd Exploration Initiative Gross mass 23,000 kg Inert mass 2300 kg Propellant mass 20,700 kg Mixture ratio N 2 O 4 /A50 = 1.8 (by mass) N 2 O 4 tank Mass = 13,310 kg Density = 1450 kg/m 3 Volume = m 3 --> r sphere =1.299 m Aerozine 50 tank Mass = 7390 kg Density = 900 kg/m 3 Volume = m 3 --> r sphere =1.252 m Space Systems Laboratory University of Maryland
38 Boost Module Main Propulsion UMd Exploration Initiative Total propellant volume V L = m 3 Assume engine pressure p 0 = 250 psi Tank pressure p L = 1.25*p 0 = 312 psi Final GHe pressure p g,f = 75 psi + p L = 388 psi Initial GHe pressure p g,0 = 4500 psi Conversion factor 1 psi = 6892 Pa Ratio of specific heats for He = 1.67 ( 4500 psi)v 1.67 g = ( 388 psi)v 1.67 g + ( 312 psi) m 3 V g = m 3 " He = p g,0 M Ideal gas: #T T=300 K --> r =49.7 kg/m 3 0 (300 psi = MPa) M He =185.1 kg Space Systems Laboratory University of Maryland ( ) 1.67
39 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Monopropellants Bipropellants Nuclear Electrical Beamed Solar Cold Gas Solids Hybrids Liquids Air-Breathing Pressure-Fed Pump-Fed
40 Nuclear Thermal Rockets Heat propellants by passing through nuclear reactor Isp limited by temperature limits on reactor elements (~900 sec for H2 propellant) Mass impacts of reactor, shielding High thrust system
41 VASIMR Engine Concept
42 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Ion MPD Monopropellants Bipropellants Nuclear Electrical Beamed Solar Cold Gas Solids Hybrids Liquids Air-Breathing Pressure-Fed Pump-Fed
43 Ion Propulsion Uses electrostatic forces to accelerate ions Injects electrons to keep beam neutral High Isp (~3000 sec) at low thrust (~10 N) Substantial mass penalty for electrical power generation
44 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Ion Solar Sail Monopropellants Bipropellants Nuclear Electrical MPD Beamed Laser Sail Microwave Sail Solar Cold Gas MagnetoPlasma Solids Hybrids Liquids Air-Breathing ED Tether Pressure-Fed Pump-Fed
45 Solar Sails Sunlight reflecting off sail produces momentum transfer T = 2m V = 2m c E = mc 2 " m = E c 2 " m = E t At 1 AU, P=1394 W/m 2 c=3x10 8 m/sec T=9x10-6 N/m 2 1 c 2 = P c 2
46 Propulsion Taxonomy Mass Expulsion Non-Mass Expulsion Thermal Non-Thermal Chemical Non-Chemical Ion Solar Sail Monopropellants Bipropellants Nuclear Electrical MPD Beamed Laser Sail Microwave Sail Solar Cold Gas MagnetoPlasma Solids Hybrids Liquids Air-Breathing ED Tether Pressure-Fed Pump-Fed
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