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;EN PROPULSION N95-13236 (NASA-TM-I08606) sPACE STATION FREEOOM PROPULSION ACTIVITIES 22 p unclas (NASA. Lewis Research Center) ..... RESISTOJET PROPULSION 1 " :-:-NASA Lewls'sResearc'h Center

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Space Station Freedom Propulsion Activities April 1990 Foreword David A. Spera, Editor 216/433-5541 SSF Systems Engineering and Integration Division NASA Lewis Research Center Space Station Freedom Propulsion Activities is a periodic publication that highlights technical progress and accomplishments of the NASA Lewis Research Center (LeRC) that support development of the SSF propulsion system. The objectives of these efforts are to: o Develop and characterize resistojet-thruster components and assemblies o Develop and characterize hydrogen-oxygen thruster components o Conduct system trade studies Research projects primarily characterize propulsion performance and life. Other tests include environmental impacts, such as exhaust gas profiles and electromagnetic interference. Technical activities highlighted are being conducted at LeRC within the Aerospace Technology and Space Station Freedom directorates. These activities include: - Derivation of design analysis models - Trade studies of design options - Propulsion system impact studies - Component testing for characterization and design verification This publication is intended for the information and use of organizations and personnel which share concern about Space Station Freedom propulsion. These include: o NASA Headquarters o The NASA field centers o Industry o The international community o Space Station Freedom working groups, particularly, - Propulsion System - Fluid Management Systems (FMS) - Environmental Control and Life Support Systems (ECLSS) - Natural and Induced External Environment This publication includes a bibliography of LeRC reports that document the development of propulsion systems for the Space Station Freedom. The work completed on Advanced Development Phase activities is summarized in the report Space Station Propulsion Technology (October 1987, NASA TM 100108). LeRC has also been involved in two system trade studies, documented as follows: Space Station Propulsion Analysis Study, (June 1984, AIAA 84-1326), and Space Station Propulsion Requirements Study, by Boeing Aerospace (August 1985, CR 174934).

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Space Station Freedom Propulsion Activities April 1990 V ii

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Space Station Freedom Propulsion Activities April 1990 Table of Contents Resistojet Life Tests ................ Rodger J. Slutz Test 5 Resistojet Heater Calibration Edward P. Braunscheidel Hydrogen-Oxygen Propulsion 7 Space Station Freedom Brian D. Reed Fundamental Studies of Low Reynolds Number Nozzle/Plume Flows ................ Lynnette M. Carney, Paul F. Penko, and Iain D. Boyd Technology 13 Basic Research in Arc-Jet Ilter Serbetci Bibliography of Applicable LeRC @_ PAGE BLANK NOT FILMED I IIII II Reports ...... 17 w ///

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Space Station Freedom Propulsion Activities April 1990 iv

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Space Station Freedom Propulsion Activities April 1990 Resistojet Life Tests Rodger J. Slutz 216/433-6299 SSF Systems Engineering and Integration Division NASA Lewis Research Center In the case of resistojet thrusters, mechanical failure may be due to thermal fatigue which is associated with 1. operational cycling, 2. creep, 3. grain growth/boundary weakening, or 4. a combination of these. Mechanisms two and three are associated with operating time at elevated temperatures. Resistojet components identified for potential mechanical failure are the heater (the most likely candidate) and heat exchanger/pressure vessel. Besides mechanical failure as described above, failure in the heater element could occur due to local melting or material property changes (e.g., electrical insulation breakdown). Finally, nozzle erosion may occur and would first affect thruster performance; later it could lead to mechanical failure. Test Objectives and Conditions The goal of these life tests is to expand the scope and accuracy of the database providing characteristics of multipropellant resistojet thrusters, and their prime components. Even though complete life requirements and other design criteria have not been established for Space Station Freedom resistojet thrusters, life test data will be useful in the preliminary design process. The test conditions for thruster life testing were derived from the contamination requirement for a 14-day quiescent period and the assumption that the resistojet system must exhaust all waste fluids generated onboard Space Station Freedom. It was assumed that four of the resistojet thrusters would operate simultaneously at 500 W each with a heater temperature of 1,200 ° C. This results in approximately three days (or less) of "on" time. IIII PligllDtt_ PAGE BLANK NOT FILMED

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Space Station Freedom Propulsion Activities The thruster was tested with nitrogen April I990 because nitrogen closely approximates the temperature profile through the thruster of the mixed gases from Space Station Freedom, and it is readily available at the facility. Carbon dioxide was also used for some tests, because it duplicates SSF pressure conditions. The thruster operated at a nominal heater temperature of 1,200 ° C for three days, followed by cooling (approximately 6 hours) to ambient temperature. After the thruster reached ambient, a new cycle was begun. Every 1,500 hours the thruster was rotated 180 ° to minimize gravitational effects. Test Results The resistojet thruster successfully met its design goals by completing 10,036 hours and 141 thermal cycles (from room temperature to 1,000 ° C) of operation with no noticeable degradation and with minimal maintenance. There are no plans to dissect the thruster (to examine grain structure, surface condition, etc.), and no further tests are planned at this time. Other results are as follows: Throat erosion was negligible. Throat diameter measurements were taken at intervals of approximately 1,500 hr using an optical comparator. The results are shown in Figure 1. No erosion was detected. Instead, there was a small but measurable reduction in diameter (approx. 1 mill in 8,000 hr), probably caused by a build-up of contaminates on the throat walls. Figure 1" Thruster Throat Diameter Change Rocketdyne Engineering Model #2 Throat Diameter (in.) 0.042 0.04151 [3 0.04! 0 0.0405 0.04 0.O885 Q O.O39 I I 0 2,000 4,000 I I I 6,000 8,000 t0,000 12,000 Operation Time at Temperature (hm) Vedlcal_ o 2 HottzocdalOtam_er -1.0n_8,0OOhm n

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Space Station Freedom Propulsion Activities April 1990 Specific impulse remained constant. The thruster was periodically removed from the life test chamber and placed on a calibrated test stand to measure thrust and mass flow rate. Specific impulse was then calculated from these data and the results are presented in Figure 2. Except for operation with room-temperature nitrogen, ISP stayed constant or increased slightly during the 10,000 hr of operation. Figure 2: Specific Impulse Variation Rocketdyne Engineering Model #2 Specific Impulse (sec) 16o 140 120 •" 0 M 100 80 V V ' 0 , --" ....... "O----O .... 6O --O.. 4O I I El------ I I I 0 2,000 4,000 6,000 8,000 10,000 12,000 Operation Time at Temperature (hrs) Nitrog(mat 1896degF Carbon Dioxide at 1896degF B Nitro_ q_,72de_ F Cleon Dioxicle = 72 d_ F AC power was required. The thruster was first operated on DC power, but it became impossible to maintain the required 500 W input to the heater. Diagnostic testing determined that insulation in the heater had become ineffective. The exact mechanism of this breakdown is not yet known. By changing to an AC power supply the insulation's effectiveness was restored, and maintaining 500 W of power to the heater was no longer a problem. 3

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Space Station Freedom Propulsion Activities April 1990 Concluding Remarks This thruster design, by surviving 10,000 hr of life testing with thermal cycling to temperatures of 1,000°C, demonstrated both its ruggedness and reliability under conditions representing Space Station Freedom service. Further research is recommended on the following effects: 1. Effect of higher temperatures on thruster performance and durability. 2. Effect of operation with contaminated 3. Effect of long-term operation with insulation in the heater circuit. BB 4 gases (like SSF waste gases). DC power on effectiveness of electrical

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Space Station Freedom Propulsion Activities April 1990 Resistojet Heater Calibration Test Edward P. Braunscheidel 216/433-6298 SSF Systems Engineering and Integration Division NASA Lewis Research Center A calibration test was performed on Rocketdyne Thruster No. 1, to establish heater temperature versus heater resistance, in support of the 10,000-hr endurance test conducted at LeRC. Significant improvements in calibration test conditions included operating at a good vacuum level of S x 10 .5 tort, compared to 5 x 10.2 torr during previous calibrations. The latter pressure level is high enough to support convective heat transfer which could adversely affect the results. The heater was instrumented with four thermocouples as shown in Figure 1. The test was run on direct current, over a temperature range from ambient to 1,100°C (2,012°F). Figure 1" Diagram of Resistojet Heater Showing Thermocouple Locations POWER J LEADS HEATER THERMOCOUPLES 5

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Space Station Freedom Propulsion Activities Test Results April 1990 Figure 2 presents the results of the calibration test, compared to the reference calibration curve supplied by the manufacturer. At higher temperature levels, it is necessary to operate at somewhat higher resistances than those given by the manufacturer, in order to achieve a given heater temperature. Figure 2: Heater Calibration Curve for Rocketdyne Resistojet Thruster #1 Heater Temperature (deg C) 1.400 1,200 1.000 8OO 6OO 4OO 2OO 0 0.3 0.4 o.s o.s 0.7 o.8 0.9 Heater Resistance (Ohms) Referecme Calibration Updated Calibration from manufacturer - .... Future Work at LeRC O A multiple-heater life test was planned to be run in the same tank utilized for the calibration test. New turbomolecular pumps were installed, and vacuum levels on the order of 10 -6 torr were achieved. Cold-wall temperatures down to -30 ° C (-20 ° F), were demonstrated. Because of changes in program priorities, this tank is currently scheduled for other research. However, the capability of conducting heater life tests will be maintained for the near future. 6

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SpaceStationFreedomPropulsionActivities April1990 Space Station Freedom Hydrogen-Oxygen Propulsion Brian D. Reed 216/433-8111 Space Propulsion Technology Division NASA Lewis Research Center The objective of the Space Station Freedom GH2/GO 2 propulsion development program is to demonstrate durability and reliability of small gaseous H/O rockets. Primary technology goals are as follows: o Thrust operating range from 12.5 to 3J lbf, with a design thrust of 25 Ibf. o Mixture ratio (MR) operating range from 3.0 to 8.5, with a design MR of 8. o Specific impulse of at least 364 sec. o Cumulative operating life equivalent to 22.2 hr at 25-1bf thrust (2,000,000 Ibf-sec). Contracts were awarded to Aerojet and Bell to build two GH2/GO 2 thrusters with a design MR of 4. The second Aerojet thruster was re-designed for MR = 8, when the water-electrolysis propulsion system was baselined for SSF. A contract was also awarded to Rocketdyne to build two thrusters designed for MR = 8. Characterization testing of all these thrusters is continuing, in conjunction with other low-thrust propulsion research at LeRC. Life testing was put on hold when hydrazine was baselined for SSF. Tests of Rocketdyne Designs Testing has been performed on a series of Rocketdyne designs with coaxial injectors, in an effort to find a balance between good performance and sufficient cooling. Test results to date are summarized in Table 1. Table 1: Hydrogen-Oxygen Thruster Test Data Rocketdyne Designs for 25-1bfThrust at MR = 8 DesignNo. OxidizerInjector Fuel Film Temp. Margin Specific (Test Site) PostAngle Cooling 0at Ext.Wail (a) Impulse(b) Prototype Straight 40 % + 280 OF 360 sec (MSFC) 2 Slraight 40 % - 50 OF 354 sec (MSFC/LeRC) (est) 3 Canted 15 % + 200OF 345 sec (MSFC/LeRC) 4 Canted 7.5 % - 100°F 348 sec (LeRC) (esl) 5 Canted 15 % + 200°F 355 sec (LeRC) (preliminary) (a) RedlineTemperature= 1,100 OF (b) C_ = 364 sec II 7

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April 1990 Space Station Freedom Propulsion Activities I The prototype thruster, with straight injector posts and 40% fuel film cooling (FFC), operated with good cooling margin and essentially met the specific impulse goal. This design contained wires in the cooling channels for improved heat transfer. In Design No. 2, the wires were removed in an effort to improve performance. Injector post angle and FFC percent were the same as the prototype. However, wall temperatures hit the redline before reaching steady state at MR -- 8. Design No. 3, with its canted injector posts and 15% FFC, provided sufficient cooling but had lower performance than the first two designs. Reducing the FFC to 7.5% (Design No. 4) caused over-heating. Design No. 5 (the latest design generation) is another with a canted injector and 15% FFC, but it has an oxygen annulus similar to the prototype and is fabricated to tighter tolerances. Preliminary data indicate that this latest injector has somewhat higher performance than Design No. 3, while maintaining chamber temperatures below the redline. An integral exciter/igniter, used in the space shuttle main engine and baselined for Rocketdyne's flight-type thruster, was successfully demonstrated during these thruster tests. A J-2 exciter was used previously. Future Research The two Rocketdyne 15% FFC, canted injectors (Designs 3 and 4), will be shipped to JSC for testing in a water-electrolysis-system testbed. Testing of a Rocketdyne resonance igniter (developed with internal funding) is planned for June 1990 at LeRC. The resonance igniter is designed to dynamically heat hydrogen above the auto-ignition temperature of oxygen gas, eliminating the need for an electrical ignition system. The second Aerojet thruster is serving as a testbed article for low-thrust computational fluid dynamics (CFD) research. Characterization testing was performed during the summer of 1989 and the winter of 1989/90, and more testing is planned for the summer of 1990. In the summer and fall of 1990, 5-1bf and 25-1bf radiation-cooled thrusters will be tested at LeRC. These thrusters are fabricated from high-temperature, oxidationresistant materials that allow operation at internal wall temperatures up to 4,000 °F. The thermal margins provided by these advanced thrusters offer significantly improved performance and/or longer life, which could benefit the evolution of space station propulsion systems.

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Space Station Freedom Propulsion Activities April 1990 Fundamental Studies of Low Reynolds Number Nozzle and Plume Flows Lynnette M. Carney 216/433-2409 Paul F. Penko 216/433-2404 Space Propulsion Technology Division NASA Lewis Research Center and lain D. Boyd Eloret Institute NASA Ames Research Center Work is progressing in this cooperative program between the Lewis and Ames Research Centers, which has the following objectives: o To determine the validity of analyses of rarefied flow and identify possible deficiencies in applying continuum methods to such flows. o To verify with experimental data the prediction of plume flowfields from small thrusters in space. o To identify possible plume effects on satellite surfaces, such as contamination, disturbance torques, and heat loading. Thruster Configuration The initial case for both analysis and experiment is a conical nozzle with a throat diameter of 0.318 cm and an area ratio of 100. The working gas is CO 2 at a stagnation pressure of 7,700 Pa (N/m 2) and a temperature of 1,000 K, which gives a Reynold's Number (based on throat diameter) of about 1,000. The flow for this case is quite viscous and hence requires analysis by the Navier-Stokes equations in the continuum regime. The flow, however, attains considerable rarefaction at the nozzle exit where the continuum assumption becomes questionable. Two Analytical Methods The approach of this study is to analyze the flow with both a Navier-Stokes code and a code based on a direct simulation Monte Carlo (DSMC) scheme. With the DSMC method, all physical phenomena are modelled on the molecular level, including (as the Monte Carlo name implies) a statistical analysis of molecular collisions and trajectories.

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Space Station Freedom Propulsion Activities April 1990 The continuum analysis has been conducted at LeRC with the VNAP (Viscous Nozzle Analysis Program). Plans are to use an alternate program for a more accurate Navier- Stokes solution. The DSMC analysis is being performed at ARC, using the Ames/Stanford Particle Kinetic (ASPK) code. Results from the continuum analyses are used as starting or boundary conditions for the DSMC analyses. Analytical Results Results from each of the numerical schemes are illustrated in Figure 1, which shows contours of constant Mach Number. Although the DSMC computation needs to be refined, the results do compare reasonably well (at least qualitatively) with those from the continuum analysis [1]. Deviations do occur at the nozzle lip (as expected), because of the degree of rarefaction of the gas at that point in the flow, and because of the somewhat artificial boundary condition that is applied to the flow in the continuum analysis in the subsonic region at the exit near the nozzle wall. Figure 1' Calculated Velocities Inside Nozzle UnesofConstantMachNumber Radial Distance from Centerline (cm) o.51"511VNAP __lC°ntinuumAnalysis o- i 0 0.5 ! 1.5 2 2.5 3 3.5 4 Axial Distance from Throat (cm) lO

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SpaceStationFreedomPropulsionActivities April1990 Test Verification To complement the theoretical analyses, experimental data have been taken recently in the large vacuum tank (Tank 5) of the Electric Propulsion Laboratory at LeRC. These data consist of pitot pressure measurements taken near the exit plane of the nozzle. A typical pitot scan is shown by the data points in Figure 2. As an initial comparison, calculated pitot pressure distributions are shown for the exit plane (see Fig. 1), according to the two analytical models discussed earlier. Comparison between computed and experimental results are within reason, although there were slightly different conditions of axial location, total pressure, and temperature between experiment and analysis. The computer codes will be rerun to match experimental conditions. Figure 2: Experimental and Analytical Pressures Distributions Across the Nozzle Exit Plane Pitot Pressure (Ton) 4 mmm u qlmm_ O _'_O O 0 0 0.5 0 Nozzle Lip 1 1.5 2 Radial Distance from Nozzle Centedine (cm) VNAP Analysis DSMC Analysis Exped(nental mmmmm _ m 0 A thorough pitot-pressure survey will be taken to identify flow direction in the nearfield plume where pressure measurements are valid. Measurements of mass deposition with a quartz microbalance will also be taken in the plume farfield to determine the nature of plume expansion. These measurements will be used to validate computed results of the plume from the molecular model. J. Boyd, I. D.; Penko, P. F.; and Carney, L. M.: Efficient Monte Carlo Simulation of Rarefied Flow in Small Nozzles. AIAA Paper 90-1693, June 1990. 11

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Space Station Freedom Propulsion Activities April 1990 Basic Research in Arc-Jet Technology liter Serbetci NRC Research Fellow 216/433-2427 Space Propulsion Technology Division NASA Lewis Research Center Arc-jets, like resistojets, convert electrical energy into kinetic energy to produce thrust. In an arc-jet, however, electric current is run directly through the ionized propellant between a cathode and an anode (nozzle) to increase its enthalpy, unlike a resistojet which employs a heat exchange mechanism such as a heating element. Direct Wheat injection" results in a higher specific impulse, Isp, in arc-jets compared to resistojets. This additional Isp comes with some penalties, however. A considerable amount of electrical energy is spent to ionize the propellant and stays trapped in the "frozen flow mode". Also, the initial ionization requires a power conditioning unit with high-speed current regulation and high-voltage ignition capabilities, both of which translate into extra mass. Background Arc-jet research dates back to late ]gS0's and early 60's. Most of this work ceased during the 70's because of on-board power limitations and electrode erosion problems. With the advent of solar arrays which can produce more than 30 kW and the prospect of on-board nuclear power, arc-jets came back onto the low-thrust propulsion scene in the 80's. Using strong swirl-stabilization, electrode erosion rates were lowered to a reasonable level. Smaller and more effective power conditioning units have been built. With these advances the goal of long-term operation appears feasible, and arc-jets have become strong candidates for satellite station-keeping missions. Now that certain basic problems have been solved, we face the following questions as we are developing the next generation of arc-jets: o Within an arc-jet, how does the plasma behave in the outer and colder flow? How thick is the arc diameter? How does it attach to the anode? How hot does it get? o How does clogging of the nozzle throat (by the arc) affect overall performance? o What are the nozzle geometry and flow-field effects on electrical field strength and also on heat transfer rates? o Is there an optimum swirl rate? PRIBOII)N_ PAGE BLANK NOT FILMED I IIII

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Space Station Freedom Propulsion Activities April 1990 Optical Diagnostics In order to answer the first two types of questions, one is compelled to resort to optical diagnostic techniques which can range from the old Schlieren method to the more-recent Wollaston Diffractiometer (WD) and spectroscopic measurements. The WD technique [1] is especially useful for visualizing isodensity lines in flow fields with the steep thermal gradients characteristic of arc-jets. Recently, a rectangular, transparent arc-jet and a Wollaston Diffractiometer have been built at LeRC for optical diagnostic studies (Fig. 1_). This facility enables one to observe the inside of the nozzle in addition to the nozzle plume. The arc-jet currently under test employs a multi-expansion nozzle to create high values for the local mass flux, and three different swirl injectors, to study the effect of vortex strength on arc-jet performance. Figure 1: The Wollaston He-Ne Laser (2 MW) Pin Hole + Spacial Filter t Arc Jet with ,,, Diffractiometer Facility . Transparent Nozzle- _ _ Colhmatin_ Lens / ! ::: ! I----"ILL' "- - t +--:'=''-" I l I "' \ .... Vacuum Tank | /o,'rox / ,=,v .0.04 Torr) \ ',:: / <z:D> De-Collimating Lens tie $l I ,.. Polarizer 1 Wollaston Prism Polarizer 2 ---Interference Filter I,; = ',1 Camera 14

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SpaceStationFreedomPropulsionActivities April1990 Multi-Zone Expansion Nozzles Recent studies [2] show that the nozzle geometry is one important determinant factor in arc-jet performance. It has been formulated that the electric field strength, E, is a strong function of the nozzle mass flux, pu. This functional relationship can be expressed in a simplified way as E = k (pu). Here k is not a constant but a function of plasma temperature and acceleration. Thus, new nozzle designs which yield higher local mass fluxes should increase electric field strength and, therefore, the Ohmic heating of the propellant. One such design is a multi-zone expansion nozzle which theoretically would result in higher electric field strength than a conventional converging-diverging nozzle, as depicted in Figure 2. Figure 2: Electric Field Strength Distribution in Two Types of Arc Jet Nozzles Electric Field Strength Ratio 1.2 1 0.8 .--'.. Conventional -- ' _ _ _ "\ 0.6 _nverNgionzg_Diverging 0.4 _nverging-Diverging \ Throat 0.2 0 / Multi-Zone Expansion Nozzle _ - Exit 0 0.2 0.4 0.6 0.8 1 1.2 Axial Distance from Inlet/Nozzle Length Swirl Stabilization Vortices induced by the swirl action diminish the axial pressure gradient inside the nozzle, which is the main driving force for the propellant. There may be an optimum swirl rate which reduces electrode erosion and at the same time results in a reasonable axial pressure gradient. By employing different injectors of various vortex strengths in the LeRC arc-jet facility, such an optimum swirl rate could be determined experimentally. . Serbetci, I., and Nagamatsu, H.T.: Nature of Convection Stabilized DC Arcs in Dual- Flow Nozzle Geometry, Pt. II - Optical Diagnostics and Theory. IEEE Trans. on Plasma Sci., v. 18, no. 1, lg8g, pg. gl - 114. 2. Ioc. cit.: Part I - The Cold Flow Field and DC Arc Characteristics. II I II 15

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Bibliography of Applicable LeRC Reports • Sovey, J. and Whalen, M.: Resistojet Performance Characteristics for Space Station Application, LeRC PIR Number 60; March 1984 • Donovan R.M.; Sovey, J.S.; and Hannum, N.B.: Space Station Propulsion Analysis Study; AIAA-84-1326; AIAA/SAE/ASME 20th Joint Propulsion Conference, TM-83715 • Whalen, M.V.; Grisnik, S.P.; Experiments of Facilities, Cincinnati, Ohio; June 1984; NASA and Sovey, J.S.; Compatibility Materials and Propellants for Electrothermal Thrusters, NASA TM-86956, April 1985 , Klemetson, R.W.; Garrison, Evaluation of Oxygen Hydrogen P.W.; and Hannum, N.P.: An Propulsion Systems for the Space Station; AIAA-85-1156; AIAA/SAE/ASME/ASEE 21st Joint Propulsion Conference, Monterey, California; July, 1985; NASA TM-87059 • Jones, R.E.: Space Station Propulsion: The Advanced Development Program at Lewis; 21st Joint Propulsion Conference AIAA/SAE/ASME, Monterey, California; July, 1985; NASA TM-86999 • Wilkinson, C.L. and Brennan, S.M.: Space Station Propulsion Requirements Study; NASA CR-174934; August 1985 • Whalen, M.V. and Grisnik, S.P.: Compatibility of Grain Stabilized Platinum with Candidate Propellants for Resistojets; AIAA-85-2014; AIAA/JSASS/DGLR 18th International Electric Propulsion Conference, Alexandria, Virginia; September 30 - October 2, 1985; NASA TM-86956 • Penko, P.F.; Staiger, P.J.; and Bur, M.J.: An Analysis of Low- Thrust, Resistojet Reboost for the Space Station; AIAA-85- 2042; AIAA/JSASS/DGLR 18th International Electric Propulsion Conference, Alexandria, Virginia; September 30 - October 2, 1985 , Hoffman, D.J.: Space Station Environment Contamination Resulting form Resistojet Exhaust Plumes; LeRC PIR Number 125; January, 1986 I0. Sovey, J.S.; Hardy, T.L.; and Englehart, M.: A Bibliography of Electrothermal Thruster Technology, 1984; NASA TM-86998; March 1986 II. Palaszewski, B.: Free-Flyer Advanced Propulsion; Jet Propulsion Laboratory, Pasadena, California; prepared for NASA Lewis Research Center; JPL D-3257; 17 May 1986 P_ PAC_ BLANK NOT FN.,.MEID

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1. Morren, W.E.; Whalen, M.V.; and Sovey, J.S.: Performance and Endurance Tests of a Multipropellant Resistojet for Space Station Auxiliary Propulsion; AIAA-86-1435; AIAA/ASME/SAE/ASEE 22nd Joint Propulsion Conference, Huntsville, Alabama; June 16- 18, 1986; NASA TM-87278 13. Pugmire, T.K.; Cann, G.L.; 10,000-hour Life Multipropellant Application; AIAA-86-1403; Hechert, B.; and Sovey, J.S.: A Engine for Space Station AIAA-86-1435; AIAA/ASME/SAE/ASEE 22nd Joint Propulsion Conference, Huntsville, Alabama, June 16- 18, 1986 14. Senneff, J.M. and Richter, Thruster for Space Station; G.P.: A Long-Life 50 LBf H2/O 2 AIAA-86-1404; AIAA/ASME/SA_/A_EE 22nd Joint Propulsion Conference, Huntsville, Alabama, June 16- 18, 1986 15. Robinson, P.J. and Rosenthal, S.E.: A Proven 25-LB_ H2/O 2 Thruster for Space Station Auxiliary Propulsion; AIAA-86-1_60T AIAA/ASME/SAE/ASEE 22nd Joint Propulsion Conference, Huntsville, Alabama, June 16-18, 1986 16. Richter, G.P. and Price, H.G.: Proven, Long-Life Hydrogen Oxygen Thrust Chambers for Space Station Propulsion; NASA TM-88822; 1986 JANNAF Propulsion Meeting, New Orleans, Louisiana, August 26-28, 1986 17. Senneff, J.M.: Space Station Auxiliary Thrust Chamber Technology; NASA CR-179552; Bell Aerospace Textron; Bell Report Number 8911-950001; August 1986 18. Page, R.J.; Stoner, W.A.; and Barker, L: A Design Study of Hydrazine and Biowaste Resistojets; The R.J. Page Company, Santa Ana, California; Contract NAS3-23863; September 1986; NASA CR-199510 19. Bader, C.H.; Potential Propellant Storage and Feed Systems for Space Station Resistojet Propulsion Options; Sverdrup Technology, Inc; Contract NAS3-24105; January 1987; NASA CR- 179457 20. Jones, Robert E.: High and Low-Thrust Propulsion Systems for the Space Station; NASA TM-88877; AIAA-87-0398; AIAA 25th Aerospace Sciences Meeting, Reno, Nevada; January 12-15, 1987; NASA TM-88877 21. Zana, Lynnette M.; Hoffman, David J.; Breyley, Loranell R.; and Serafini, John S.; An Analytical and Experimental Investigation of Resistojet Plumes; NASA TM-88852; AIAA-87-0399; AIAA 25th Aerospace Science Meeting, Reno, Nevada; January 12-15, 1987; NASA TM-88852 18

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1. Heckert, B.J.: Space Station Interface Definition Study; Rocketdyne Division; Rockwell Park, California; (Contract CR-179581 Resistojet System Requirements and Report Number RI/RD87-109; International Corporation, Canoga NAS3-24658); February 1987, NASA 23. Peterson, T.T.: Space Station Fluid Inventories of the Integrated Waste Fluid and Integrated Water Systems; LeRC PIR Number 191; March 1987 24. Hoffman, D.J.: Resistojet Analysis; Master of Science University; May 1987 25. Penko, P.F.; Manzella, D.H.; Plume and Induced Environment Thesis; Case Wester Reserve DeWitt, K.J.; Keith, T.J.: Effect of Ambient Pressure on the Performance of a Resistojet; AIAA- 87-0991; AIAA/DGLR/JSASS 19th Conference, Colorado Springs, TM-89854 International Electric Propulsion Colorado; May 11-13, 1987; NASA 26. Morren, W.E. and Sovey, J.S.: 2000-Hour Endurance Test of a Laboratory Model Multipropellant Resistojet; AIAA-87-0093; AIAA/DGLR/JSASS 19th International Electric Propulsion Conference, Colorado Springs, TM-89854 Colorado; May 11-13, 1987; NASA 27. Gruber, R.P.: Resistojet Control and Power for High Frequency AC Buses; AIAA-87-0094; AIAA/DGLR/JSASS 19th International Electric Propulsion Conference, 11-13, 1987; NASA TM-89860 Colorado Springs, Colorado; May 28. Tacina, R.R.: Conceptual Design and Integration of a Space Station Resistojet Propulsion Assembly; AIAA-87-1860; AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference, San Diego, California; June 29 - July 2, 1987; NASA TM-89847 29. Beryley, L.R.; Hoffman, D.J.; Zana, L.M.; and Serafini, J.S.: Effect of Nozzle Geometry on the Resistojet Exhaust Plume; AIAA-87-2121; AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference, San Diego, California; June 29 -July 2, 1987 30. Morren, W.E.; Hay, S.S.; Engineering Model Resistojet AIAA/SAE/ASME/ASEE 23rd Joint Sovey, J.S.; and Haag, T.W.: Characterization; AIAA-87-2120; Propulsion Conference, San Diego, California; June 29 - July 2, 1987 31. Jones, R.E.; Meng, Phillip James S.; and Tacina, Robert Technology; International International Astronautical Kingdom; October 10-17, 1987; 19 R.; Schneider, Steven J.; Sovey, R.: Space Station Propulsion Astronautical Federation 38th Conference, Brighton, United NASA TM-100108

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1. Louviere, A.J.; Jones, R.E.; Water-Propellant Resistojets International Astronautical Morren, W.E.; and Sovey J.S.: for Man-Tended Platforms; Federation 38th International Astronautical Conference, Brighton, United Kingdom; October I0- 17, 1987; NASA TM-100110 33. Whalan, M.V. and Nathal, M.V.: Compatibility of Dispersion- Strengthened Platinum with Technical Paper 2765; October Resistojet Propellants; NASA 1987 34. Finden, L.E.: Space Station Resistojet System Requirements and Interface Definition Study; NASA CR-180832; November 1987 35. Meng, P.R.; Schneider, S.J.; Morgan, C.J.: A Life Test of a 22- Newton (5-LBf) Hydrazine Rocket; 1987 JANNAF Propulsion Conference, SEn Diego, California; December 15-17, 1987; NASA TM-I00232 36. Jones, R.E.: Space Station Propulsion; 1987 JANNAF Propulsion Conference; San Diego, California, 1987; NASA TM-100216 37. Bader, C.: Component Data Base for Space Station Resistojet Auxiliary Propulsion; NASA CR-180834; January 1988 38. Briehl, D.: Magnetic Emissions Engineering Model Resistojet; Testing of the Space Station February 1988; NASA TM-I00788 39. Shephard, C.B.; McKevitt, F.X.; Finden, L.E.: Multipropellant Resistojet Design Manual; March 1988 40. Morren, W.E. and Stone, J.R.: Resistojet; AIAA-88-3288; Propulsion Conference, Boston, TM-I00927 Development of a Liquid-Fed Water AIAA/ASME/SAE/ASEE 24th Joint Massachusetts; July 1988; NASA 41. Carney, L.M. and Bailey, A.B.: Experimental Evaluation of Resistojet Thruster Plume Shields; IEPC-88-091; DGRL/AIAA/JSASS 20th International Electric Partenkrichen, West Germany; Propulsion Conference, Garmish- October 1988; NASA TM-I01363 42. Gruber, R.P.: DC Power Control for a Liquid-Fed Resistojet; IEPC-88-04; DGRL/AIAA/JSASS 20th International Electric Propulsion Conference, Garmish-Partenkrichen, West Germany; October 1988; NASA TM-101326 43. Shephard, C.B.; McKevitt, F.X.; Finden, L.E.: Multipropellant Resistojet, Final Report; NASA CR-182199; October 1988 44. Riley, B.R. and Scheller: Kinetic Theory Model for the Flow of a Simple Gas from a Two-Dimensional Nozzle; 16th International Symposium on Rarefied Gas Dynamic Proceedings; December 1988 20

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1. Braunscheidel, Edward P.: Performance Characterization and Transient Investigation of Multipropellant Resistojets; AIAA- 89-2837; AIAA/ASME/SAE/ASEE Monterey, CA; July 10-12, 1989 46. Manzella, D.M. and Carney, Fed Water Resistojet Plume; 25th Joint Propulsion Conference, L.M.: Investigation of a Liquid- AIAA-89-2840; AIAA/ASME/SAE/ASEE 25th Joint Propulsion Conference, Moneterey, CA; July 10-12, 1989; NASA TM 102310 47. Serbetci, I., and Nagamatsu, H. T.: Nature of Convection Stabilized DC Arcs in Dual-Flow Nozzle Geometry; Part I - The Cold Flow Field and DC Arc Characteristics; Part II - Optical Diagnostics and Theory. IEEE i, 1989, pg. 91-114. Trans. on Plasma Sci., v. 18, no. 48. Boyd, I. D.; Penko, P. F.; and Carney, L. M.: Efficient Monte Carlo Simulation of Rarefied 90-1693, June 1990. Flow in Small Nozzles. AIAA Paper 21

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Space Station Freedom Propulsion Activities ! 22 April I990