5. 522, Space Propulsic Prof. Manuel martinez-Sanchez ecture 7: Bipropellant Chemical Thrusters and Chemical Propulsion Systems Considerations (Valving, tanks, etc) Characteristics of some monopropellants( Reprinted from H Koelle, Handbook of Astronautical Engineering, McGraw-Hill, 1961.) Sity s Sensitivit Nitroglycerine 1.60 54964942244Yes Ethyl nitrate 1030394659224Yes Hydrazine 1.01 2050 3952230 Tetranitromethane 1.65 3446 3702180Yes Hydrogen peroxide 1.45 18393418165No Ethylene oxide 0.87 1760 3980189No 1.06 4265201Ye Catalyst Bed Propellant Decompositi Monopropellant concept. SPACECRAFT PROPULSION, by Ch D, Brown AlAA Education Series, 1996 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 1 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 1 of 12 16.522, Space Propulsion Prof. Manuel Martinez-Sanchez Lecture 7: Bipropellant Chemical Thrusters and Chemical Propulsion Systems Considerations (Valving, tanks, etc) Characteristics of some monopropellants (Reprinted from H. Koelle, Handbook of Astronautical Engineering, McGraw-Hill, 1961.) Flame Chemical Density temp, F D C* ,fps Isp,S Sensitivity Nitromethane 1.13 4002 5026 244 Yes Nitroglycerine 1.60 5496 4942 244 Yes Ethyl nitrate 1.10 3039 4659 224 Yes Hydrazine 1.01 2050 3952 230 No Tetronitromethane 1.65 3446 3702 180 Yes Hydrogen peroxide 1.45 1839 3418 165 No Ethylene oxide 0.87 1760 3980 189 No n-Propyl nitrate 1.06 2587 4265 201 Yes
Standoff Catalyst Bed Heater Propellant valve Thrust Chamber Typical monopropellant thruster.( Courtesy Hamilton Standard. Image adapted from SPACECRAFT PROPULSION, by Ch D. Brown AlAA Education Series, 1996 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 2 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 2 of 12
Weight(Ibs) 6 0 80 100 120140 Thrust(lbs) Monopropellant thruster weight Image adapted from SPACECRAFT PROPULSION, by Ch D Brown AIAA Education Series, 1996 Thruster we A least-square curve fit of the weight of nine different thruster/valve designs with thrust levels from 1 to 150 lb produces the following relation W=0.34567F053235 The figure above shows the correlation; the correlation coefficient is 0. 97. For low thrust levels, the thruster weight approaches the valve weight an effect that Equation(4.5)will not predict. Use 0. 4lb as a minimum thruster/valve weight for low thrust levels. Note that figure above is for a thruster with single valves 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 3 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 3 of 12 Thruster Weight A least-square curve fit of the weight of nine different thruster/valve designs with thrust levels from 1 to 150 lb produces the following relation: 0.55235 W F t = 0.34567 The figure above shows the correlation; the correlation coefficient is 0.97. For low thrust levels, the thruster weight approaches the valve weight, an effect that Equation (4.5) will not predict. Use 0.4lb as a minimum thruster/valve weight for low thrust levels. Note that figure above is for a thruster with single valves
MONOPROPELLANT SYSTEMS Pressurant Propellant agm Capillary Bladder Collapsible Cylinder Zero-g propellant control devices Image adapted from SPACECRAFT PROPULSION, by Ch D. Brown AlAA Education Series, 1996 1)Capillary devices, which use surface tension forces to keep gas and liquid separated These are particularly useful for bipropellant systems like the space Shuttle and viking Orbiter because they are compatible with strong oxidizers 2)Diaphragms and bladders, which are physical separation devices made of elastomer or Teflon. These are used by Voyager, Mariner 71, and Magellan Elastomer types are not compatible with oxidizers. 3)Bellows, a metal separation device, used by Minuteman 4)Traps, a check valve protected compartment, used by transtage 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 4 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 4 of 12 1) Capillary devices, which use surface tension forces to keep gas and liquid separated. These are particularly useful for bipropellant systems like the space Shuttle and Viking Orbiter because they are compatible with strong oxidizers. 2) Diaphragms and bladders, which are physical separation devices made of elastomer or Teflon. These are used by Voyager, Mariner 71, and Magellan. Elastomer types are not compatible with oxidizers. 3) Bellows, a metal separation device, used by Minuteman. 4) Traps, a check valve protected compartment, used by Transtage
H Tank a Tank B N2H4 Valve 3A Valve 3B Filter園 Branch a Filter Branch B Valve TCV IB Line heaters TCV 2B Catalyst Bed leaters Thruster Pair Temperatur ① Normally open pical 12 Places Pressure normally Closed System functional schemati Image adapted from SPACECRAFT PROPULSION, by Ch D. Brown AlAA Education Series. 1996 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 5 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 5 of 12
Image adapted from: SPACECRAFT PROPULSION, by Ch D Brown AIAA Education Series, 1995 Flight monopropellant systems ariner Landsat Viking HEAO Venus elsat v IUS ellan Launch date Altitude control 3 Axis 3 Axis 3 Axis 3 Axis 3 Axis 3 Axis 3 Axis No, thrusters 4,3 12 ,4,4 12,4,8 Initial thrust, lb 50 10,600 1.1 0.2,5,1001.5 0.1,0.6,5 0.2,5,100 Pressurization Regulated Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Pressurant No prop tanks 1 2 1,2,or31 Initial pressure 350 270 psia Blowdown ratio .8 Repressurization 0 Ye Bladder Diaphragm Deceleration Diaphragm gm 5 rpm spin Capillary Control Tank shape SphericalSpherical Spherical Spherical Spherical Cenosphere Barrel Spherical Spherical Crossover Dry mass, Ib 26.7 56.2 78 Propellant mass 21.5 185 300 230 86.2 410 123/Tank2932 Features Slug starts Simplicity Throttlable 400,000 Electrother Removable cycle pulsing tanks Primary 26 Reference 16522, Lecture Prof. manuel ma Page 6 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 6 of 12 Image adapted from: SPACECRAFT PROPULSION, by Ch. D. Brown AIAA Education Series, 1995 Flight monopropellant systems Mariner 4 Landsat Viking HEAO Voyager Pioneer Venus Intelsat V IUS Magellan Launch date 1964 1972 1976 1977 1977 1978 1980 1982 1989 Altitude control 3 Axis 3 Axis 3 Axis 3 Axis 3 Axis Spin 3 Axis 3 Axis 3 Axis No. thrusters 1 3 4, 3 12 16, 4, 4 7 20 12 12, 4, 8 Initial thrust, lb 50 1.0 10,600 1.1 0.2, 5, 100 1.5 0.1, 0.6, 5 0.2, 5, 100 Pressurization Regulated Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Blowdown Pressurant N2 N2 N2 N2 N2 He N2 N2 He No. prop tanks 1 1 2 2 1 2 2 1,2, or 3 1 Initial pressure, psia 530 350 450 350 270 450 Blowdown ratio - 3.3 3.5 1.8 1.8 4 Repressurization - No No No No No Yes No Yes Propellant Control Bladder Diaphragm Deceleration Diaphragm Diaphragm 5 rpm spin Capillary Diaphragm Diaphragm Tank shape Spherical Spherical Spherical Spherical Spherical Conosphere Barrel Spherical Spherical Crossover - - - Yes - Yes Yes Yes No Dry mass, lb 26.7 56.2 78 135 Propellant mass 21.5 67 185 300 230 86.2 410 123/Tank 293.2 Features Slug starts Simplicity Throttlable 400,000 cycle pulsing Electrother mal thrusters Removable tanks Primary 23 24 25 30 16 27 28 26 29 Reference
Image adapted from: SPACECRAFT PROPULSION, by Ch D Brown AIAA Education Series, 1995 Spacecraft bipropellant systems Transtage Mars global Shuttle rcs First launch 1964 1975 Galileo IntelsatⅥI 1996 No, thrusters 13 13 Thrust, Ib 25,45 300 25,870 2.25,90 5,110 1,134 Engine cooling Ablative Beryllium Radiation cooled Radiation Radiation Radiation and insulated Fuel 50/50 mix of MMH MMH Hydrazine hydrazine and UDMH Oxidizer Nitrogen Nitrogen Nitrogen Nitrogen tetroxide tetroxide tetroxide tetroxide tetroxide tetroxide Mixture ratio 1.6 1.6 Propellant control Teflon Capillary vane Capillary screens Centrifugal Centrifugal Capillary vane apnraams devices 10(rpm) Propellant tanks Titanium equal Titanium equal Titanium equal Four equal Eight equal volume, Three equal volume barrel volum titanium, spherica olume spherical titanium titanium Pressurization Regulated Regulated Regulated Requlated helium Regulated nitrogen helium helium helium Vapor mIXing Series soft seat Single soft Single check valves Pyro-valves prevention seat check check valves seat check valves leak design Dry mass, Ib 442 Propellants, Ib 3137 5100to5990 36 Primary reference 32 34 features Early design Beryllium cooling Large size Spinner, flushing Spinner, Dual-mode multiuse burns redundant half-system operati 16522, Lecture Prof. manuel ma Page 7 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 7 of 12 Image adapted from: SPACECRAFT PROPULSION, by Ch. D. Brown AIAA Education Series, 1995 Spacecraft bipropellant systems Transtage RCS Viking Orbiter Shuttle RCS Galileo Intelsat VI Mars Global Surveyor First launch 1964 1975 1981 1989 1989 1996 No. thrusters 8 1 (ACS by cold gas) 44 13 8 13 Thrust, lb 25,45 300 25,870 2.25,90 5,110 1,134 Engine cooling Ablative Beryllium Radiation cooled and insulated Radiation Radiation Radiation Fuel 50/50 mix of hydrazine and UDMH MMH MMH MMH MMH Hydrazine Oxidizer Nitrogen tetroxide Nitrogen tetroxide Nitrogen tetroxide Nitrogen tetroxide Nitrogen tetroxide Nitrogen tetroxide Mixture ratio 1.60 1.50 1.6 1.6 Propellant control Teflon diaphragms Capillary vane devices Capillary screens Centrifugal 10(rpm) Centrifugal Capillary vane Propellant tanks Titanium equal volume spherical Titanium equal volume barrel Titanium equal volume, spherical Four equal volume, titanium, spherical Eight equal volume, titanium, spherical Three equal volume, titanium, barrel Pressurization Regulated nitrogen Regulated helium Regulated helium Regulated helium Regulated helium Vapor mixing prevention Single, soft seat check valves Series soft seat check valves Single soft seat check valves, low leak design Single check valves Pyro-valves Dry mass, lb 55 442 139 Propellants, lb 120 3137 2040 5100 to 5990 836 Primary reference 32 33 34 features Early design Beryllium cooling Large size, multiuse Spinner, flushing burns Spinner, redundant half-system Dual-mode operation
D Fill and Drain valve O Normally Open pyrovalve D)I Check valve 囚 Latch valy LAMI Solenoid valve Pressure Transducer INTEL SAT V propulsion sy stem (from Ref. 34. P, 4) SOVCECRATT PROFLLSNON b Ch D RoaN ALAA ECtm Sanes. 19)6 16522, Lecture Prof. manuel ma Page 8 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 8 of 12
Additional Reading for system Design Redondo Beach, CA: TRW Space Electronics Group. July 1-3, 1996. pp. 1-10Ctae Mayer, N. L.AIAA 96-2869, Advanced X-ray Astrophysics Facility -Imaging(A) I)Propulsion Subsystem "32 AIAA/ASME/SAE/ASEE Joint Propulsion Confere 16.522, Space P pessan Lecture 7 Prof. Manuel martinez Page 9 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 9 of 12 Additional Reading for System Design: Mayer, N. L. “AIAA 96-2869, Advanced X-ray Astrophysics Facility – Imaging (AXAFI) Propulsion Subsystem.” 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Redondo Beach, CA: TRW Space & Electronics Group. July 1-3, 1996. pp. 1-10
Some Examples of small Solid Propellant rockets for In-space propulsion The sTAR 13B incorporates the lightweight case developed for the staR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor. The motor case has been stretched 2. 2 inches to provide for increased propellant loading the motor has been used to adjust orbit inclination of a satellite from a delta launch MOTOR PERFORMANCE (70 F Vacuum) Burn Time/Action Time, sec 148/161 Ignition Delay Time, sec 0.02 Burn Time Average Chamber Pressure, psia 823 Action Time Average Chamber Pressure, psia 787 Maximum Chamber Pressure, psia 935 Total Impulse, Ibf-sec 26,040 Propellant: Specific Impulse, Ibf-sec/Ibm 286.6 Effective Specific Impulse, Ibf-sec/Ibm Burn Time Average Thrust, Ibf 1708 Action Time Average thrust, ibf 1577 Maximum thrust ibf 2160 SPIN CAPABILITY, rpm WEIGHTS Ibm Total Loaded 90.9 Case assembly 5.64 Nozzle assembl 3.72 Igniter Assembly 0.68 nternal insulation 2.34 Liner 0.14 Miscellaneous 0.28 Total Inert(excluding igniter propellant 12.80 Burnout Propellant Mass Fraction 0.87 TEMPERATURE LIMITS Operation 40to+110°F Storage 40to+110°F Material 6A1-4V Titanium Minimum Ultimate Strength, psi 165,000 Minimum Yield Strength, psi Hydrostatic Test Pressure, psi 1330 Yield Pressure, psI Hydrostatic Test Pressure/Maximum Pressure 16.522, Space Propulsion Lecture 7 Prof. Manuel martinez-Sanchez Page 10 of 12
16.522, Space Propulsion Lecture 7 Prof. Manuel Martinez-Sanchez Page 10 of 12 Some Examples of Small Solid Propellant Rockets for In-space Propulsion The STAR 13B incorporates the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor. The motor case has been stretched 2.2 inches to provide for increased propellant loading. The motor has been used to adjust orbit inclination of a satellite from a Delta launch. MOTOR PERFORMANCE (70 ° F Vacuum) Burn Time/Action Time, sec 14.8/16.1 Ignition Delay Time, sec 0.02 Burn Time Average Chamber Pressure, psia 823 Action Time Average Chamber Pressure, psia 787 Maximum Chamber Pressure, psia 935 Total Impulse, lbf-sec 26,040 Propellant: Specific Impulse, lbf-sec/lbm 286.6 Effective Specific Impulse, lbf-sec/lbm 285.7 Burn Time Average Thrust, lbf 1708 Action Time Average Thrust, lbf 1577 Maximum Thrust, lbf 2160 SPIN CAPABILITY, rpm 120 WEIGHTS, lbm Total Loaded 103.7 Propellant 90.9 Case Assembly 5.64 Nozzle Assembly 3.72 Igniter Assembly 0.68 Internal Insulation 2.34 Liner 0.14 Miscellaneous 0.28 Total Inert (excluding igniter propellant) 12.80 Burnout 12.30 Propellant Mass Fraction 0.87 TEMPERATURE LIMITS Operation 40 to +110°F Storage 40 to +110°F CASE Material 6Al-4V Titanium Minimum Ultimate Strength, psi 165,000 Minimum Yield Strength, psi 152,000 Hydrostatic Test Pressure, psi 1330 Yield Pressure, psi 1394 Hydrostatic Test Pressure/Maximum Pressure 1.05