w

NASA/TMm2001-211147

High Voltage TAL Performance

AIAA-2001-3777

David T. Jacobson, Robert S. Jankovsky, and Vincent K. Rawlin

Glenn Research Center, Cleveland, Ohio

David H. Manzella

University of Toledo, Toledo, Ohio

November 2001

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NASA / TMm2001-211147 AIAA-2001-3777

High Voltage TAL Performance

David T. Jacobson, Robert S. Jankovsky, and Vincent K. Rawlin

Glenn Research Center, Cleveland, Ohio

David H. Manzella

University of Toledo, Toledo, Ohio

Prepared for the

37th Joint Propulsion Conference and Exhibit

cosponsored by the AIAA, SAE, AIChE, and ASME

Salt Lake City, Utah, July 8-11, 2001

National Aeronautics and

Space Administration

Glenn Research Center

November 2001
NASA Center for Aerospace Information

7121 Standard Drive

Hanover, MD 21076

Available from

National Technical Information Service

5285 Port Royal Road

Springfield, VA 22100

Available electronically at httpi! / gltrs.grc.nasa.gov / GLTRS
High Voltage TAL Performance

David T. Jacobson, Robert S. Jankovsky, and Vincent K. Rawlin

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

David H. Manzella

University of Toledo

Toledo, Ohio 43606

Abstract

The performance of a two-stage, anode layer Hall thruster was evaluated. Experiments were conducted in

single and two-stage configurations, h_ single-stage configuration, the thruster was operated with

discharge voltages ranging from 300 to 1700 Volts. Discharge specific impulses ranged from 1630 to

4140 seconds. Thruster investigations were conducted with input power ranging from 1 kW to 8. 7 kW,

corresponding to power throttling of nearly 9:1. An extensive two-stage performance map was generated.

Data taken with total voltage (sum of discharge and accelerating voltage) constant revealed a decrease in

thruster efficiency as the discharge voltage was increased. Anode specific impulse values were

comparable in the single and two-stage configurations showing no strong advantage for two-stage

operation.

Introduction

It is well known that the use of electric

propulsion can reduce the on-board propulsion

system mass, thereby decreasing spacecraft

launch mass or increasing payload capability.

Typically, different electric propulsion devices

satisfy different mission requirements based on

their inherent characteristics. For example,

gridded ion thrusters better satisfy interplanetary

mission requirements, where mission benefit is

derived through high specific impulse operation. _

Conversely, the relatively high thrust density of

Hail thrusters is well suited to lower specific

impulse maneuvers such as orbit raising where

reasonable trip times are required.-" Even greater

mission benefits may be realized by increasing

the upper limit of specific impulse attainable by

current Hall thrusters, which has traditionally

been limited to 1500-1700 seconds. _

In an attempt to extend the operational envelope

of state-of-the-art (SOA) Hall thrusters, NASA

Glenn Research Center (GRC) awarded two

contracts to develop a Hall thruster with the

following characteristics: power=2.3 kW,

thrust=100 mN, Isp=3200 seconds (s),

lifetime=8000 hours. A magnetic layer thruster

was developed under the contract with Atlantic

Research Corporation and delivered to NASA

for evaluation. The results of this investigation

are presented in a paper authored by Manzella. 3

Another Hall thruster of the anode layer type

(TAL) was developed under contract NAS3-

99171, with Boeing Rocketdyne. 4 The thruster

was designed and fabricated by Central Research

Institute of Machine Building (TsNIMASH),

Boeing's subcontractor. This thruster,

designated D-80, was evaluated at NASA GRC.

The objective of this work was to investigate the

operating characteristics of the D-80 in a high

discharge voltage regime compared to SOA Hall

thruster discharge voltages (300-500 Volts). The

performance of the device was measured in both

NASA/TM--2001-211147 1
the traditionalsingle-stage,and two-stage

configurations. The results of these

investigations arepresentedherein.

Apparatus

The thruster under consideration is a laboratory

model TAL designated D-80. The model

designation refers to the average diameter of the

discharge chamber in millimeters. The thruster

employs a segmented anode consisting of two

electrodes. This geometry enables operation in

single and two-stage configurations. Two-stage

thruster operation allows different electric

potentials to be applied between the two

electrodes, thereby allowing modification of the

electric field distribution. The discharge voltage

is applied between the first and second stage

anode electrodes and the accelerating voltage is

applied between the cathode and second stage

anode. In this configuration, ionization is

desired in the first stage region, followed by

acceleration of the ions in the second stage 5. For

single-stage operation, the first and second stage

electrodes are electrically connected, allowing a

single potential difference to be applied between

anode and cathode. The D-80 Hall thruster is

described in detail elsewhere. 6 A photograph

and mechanical schematic drawing of the D-80

thruster are provided as Figures 1 and 2,

respectively.

The hollow cathode used was manufactured by

Semicon and was similar in design to the NASA

plasma contactor design. The cathode was a

laboratory model unit operated at a nominal flow

rate of 0.4 mg/s throughout testing. The cathode

was mounted at a 45 ° angle with respect to the

thruster axis as shown in Figure 1. The cathode

orifice was located 0.03 m downstream of the

thruster exit plane and 0.025 m radially from the

outer pole piece:

Thrust was measured continuously on a NASA

GRC designed inverted pendulum thrust stand.

The thrust stand used has been described in

detail elsewhere. 7`s The stand employed a closed

loop inclination control circuit, which utilized a

pizioelectric element to minimize thermal drift.

Calibration was performed in-situ using three

0.01 kg masses applied along the thrust vector

over a pulley.

The power system utilized commercially

available power supplies. Separate supplies were

used to power the inner and outer magnets,

cathode heater, and keeper. The discharge

circuit consisted of two power supplies enabling

thruster operation in single or two-stage

configurations. For single-stage operation, a

switch was used to short the discharge power

supply, electrically connecting the two electrodes

together. In the two-stage configuration, the

discharge supply was located between the first

and second stage anode electrodes, and the

accelerating supply was located between cathode

and second stage anode. Simple output filters,

consisting of 10 and 100 IxF capacitors were

used. The capacitors were located across the

discharge and accelerating electrodes, and the

accelerating electrode and cathode, respectively.

Two 70 V Zener diodes were placed back-toback from cathode common to ground to clamp

the cathode floating potential. The cathode

floating potential was not more that 13 volts (V)

negative with respect to ground during testing.

A schematic drawing of the electrical

configuration is provided in Figure 3.

All testing was performed in NASA Glenn's

Vacuum Facility 6 (VF 6). VF 6 is an oil free

facility, which employs 12 cyropumps, each with

a liquid nitrogen shroud. At the highest xenon

mass flow rate of 8 mg/s, the indicated facility

pressure was 2.0 x 10 .4 Pa as measured on ion

gauges calibrated for air. The main chamber has

a 7.6 m diameter and length of 22 m. The test

hardware was located in a 3 m diameter belljar

connected to the main chamber. The belljar has

isolation capability allowing the access to the

hardware without venting the main chamber to

atmosphere. A photograph of the test apparatus

is provided in Figure 4.

NASA/TM--2001-211147 2
Results and Discussion

The D-80 thruster was operated in both single

and two-stage configurations over a wide range

of mass flow rates and discharge voltages. The

range was selected to define the possible

operating envelope and allow for a broad

comparison of single and two-stage data. In the

single-stage configuration, data were initially

collected for mass flow rates between 4 and 8

mg/s and discharge voltages between 300 and

900 V. This range was subsequently extended to

include discharge voltages up to 1700 V.

Thruster operation was investigated in the twostage configuration over discharge voltages from

300-1000 V and a fixed discharge voltage of 100

V for a range of mass flow rates from 4-8 mgls.

First, the single-stage data will be presented,

followed by the two-stage data, and finally the

results of the two configurations will be

compared.

Single-stage Operation

The D-80 single-stage operational envelope is

depicted in Figure 5. All single-stage data,

ranging from 300 V to 1600 V in 100 V

increments are presented. Measured thrust

ranged from a minimum value of 64 mN at 300

V and 3.3 A, to a maximum of 240 mN at 1700

V and 5.1 A. Thruster investigations were

conducted with input power ranging from 1 kW

to 8.7 kW, corresponding to power throttling of

nearly 9:1. Temperature measurements indicated

that operation above 4 kW potentially exceeded

the steady-state thermal capability of the thruster.

These data are provided in Table 1.

Thruster operation was stable over this power

range. The exception to this was at voltages

above 1000 V where periodic, short duration,

occurrences of current limited operation were

experienced. These events typically only

occurred during transient periods when the

discharge voltage or anode mass flow rate was

being adjusted. Slow and deliberate adjustment

mitigated this anomalous behavior.

The D-80 single-stage, anode specific impulse is

plotted versus discharge voltage for anode mass

flow rates ranging from 3 to 8 mg/s in Figure 6.

Anode specific impulse is defined as the specific

impulse calculated excluding the cathode flow.

The discontinuities in the 4, 5, 6 mg/s cases were

attributed to small differences in anode mass

flow- rate between data taken on different days,

and incomplete optimization of the inner and

outer magnet currents for every point. Initial test

data were taken at mass flow rates between 4-8

mg/s and discharge voltages from 300-900 V.

The stable operation of the thruster at these

elevated voltages suggested that higher discharge

voltages were obtainable; as a result, data were

subsequently obtained at discharge voltages

between 900 and 1700 V.

For these data the anode specific impulse ranged

from 1630 s at 300 V and 3.3 A to a maximum

of 4140 s at 1700 V and 5.1 A. In all cases, the

anode specific impulse increased nearly

monotonically with increasing flow rate and

voltage. The anode specific impulse increased

less rapidly with increasing discharge voltages

for voltages above 700 Volts. A curve fit to the

specific impulse data was nearly proportional to

square root of the discharge voltage as expected.

The 3 mg/s mass flow rate data does not exhibit

this trend. At voltages above 1100 V that anode

specific impulse decreased.

Anode efficiency is plotted versus discharge

voltage in Figure 7 for the same single-stage

data. For a given anode mass flow rate the

maximum efficiency corresponded to discharge

voltages ranging from 500-800 V. After this

point, the efficiency decreased with increasing

voltage. The anode efficiency data suggested

that a loss mechanism was enhanced at these

higher voltages. While sufficient data does not

exist to definitively identify this mechanism,

similar trends have been observed with the SPT

device operated at elevated voltages 3.

NASA/TM--2001-211147 3
Thesedataalso suggesthe thrusterwas

oversizedforoptimumperformanceat2.3kW.

Forexample, at2.3kWwithadischargevoltage

of 700V anda dischargecurrentof 3.2A the

thrustwas97mN. Thiscorresponds toananode

specificimpulseof2480sandaanodefficiency

of 53%,whichapproachesthedesiredtarget

thrustof 100mNalbeitat700sbelowthetarget

of3200s.Incontrast, at5.2kWwithadischarge

voltageof 800Voltsandadischargecurrentof

6.5Amperesthethrustwas224mN.Theanode

specificimpulseandefficiencyatthispointare

3320s and71%,respectively.In general,all

thesedatareflectedthistrend,i.e.thespecific

impulseandefficiencyincreasedfor a given

dischargevoltagewithincreasinganodemass

flow rate. It is howeveranticipatedthat

operationatthesehighpowerdensitieswould

haveanadverseeffectonthethermaloperating

regimeofthethrusterandthrusterlife.

Two-Stage Operation

D-80 thruster operation in the two-stage

configuration was also investigated extensively.

Tests were conducted over a range of mass flow

rates from 4-8 mg/s with discharge voltages from

0 to 200 V, and a constant accelerating voltage

of 600 V in an attempt to identify an optimal

discharge voltage at which to evaluate two-stage

performance. The results of these tests were

inconclusive, but a discharge voltage of 100 V

was selected for further testing based on

previously published test results. 9 Performance

was then evaluated for anode mass flow rates

between 4 and 8 mg/s, a constant discharge

voltage of 100 V, and accelerating voltages

between 300 and 1000 V. For these data the

measured thrust ranged from 74 mN to 278 mN

and the anode specific impulse ranged from 1890

s to 3610 s. In general, the highest efficiency

data points corresponded to the highest mass

flow rate and accelerating voltages as was seen

during single-stage operation. These data are

presented in Table 2.

Due to the inconclusive result of the discharge

voltage variation, a second approach for

investigating two-stage operation was

implemented. For these tests the thruster was

operated with a constant total voltage, that is the

sum of the discharge voltage and the accelerating

voltage was constant. In the case of a constant

total voltage of 800 V, for example, the thruster

would be operated with discharge voltage of 100

V and accelerating voltage of 700 V.

Subsequent points would then be taken at

discharge and accelerating voltages of 125 and

675 V respectively. A single-stage point was

also included in each constant voltage data

series. A comprehensive tabulation of these data

is presented in Table 3.

Data with constant total voltage of 800V are

presented in Figure 8. Anode efficiency and

thrust are plotted versus discharge voltage for

anode mass flow rates of 6 and 7 mg/s. In both

cases, the peak anode efficiency was measured

during single-stage operation, or where discharge

voltage was zero. As the discharge voltage was

increased, and the accelerating voltage

decreased, the efficiency decreased. The

measured thrust over these data sets remained

constant. However, as the discharge voltage was

increased, the total power increased. This caused

the drop in efficiency.

The concept that the ionization and acceleration

regions can be separated in the first and second

stage of the thruster during two-stage operation

seems to be contradicted by the constant

measured thrust. By maintaining as much as 200

V between the first and second stage electrodes

there is 200 V less for acceleration in the

external anode layer. Because the thrust was

unchanged the thrust producing ions were

necessarily created upstream of the first stage to

second stage gap and were subsequently

accelerated through this region. This further

suggests that for the conditions tested the

ionization efficiency was extremely good. This

conclusion is also supported by the fact that

NASAfI'M--2001-211147 4
thrustwasconstant for variouscombinationsof

discharge and accelerating voltage. That is, the

ions seem to be accelerated through the same

total voltage regardless of how it was distributed

within the channel. Interestingly, two-stage

operation with zero voltage between the first and

second stages operated with zero discharge

current. This suggests that even during singlestage operation very little of the discharge

current is being collected in the upstream part of

the anode. Additional experiments would need to

be conducted to definitively prove each of these

conclusions.

Additional tests with different anode mass flow

rates and different total voltages are presented in

Figure 9. Five cases are for constant total

voltage of 800 V and anode mass flow rates from

3-7 mg/s and two cases are for an anode mass

flow rate of 6 mg/s and constant total voltages of

600 and 1000 V. With the exception of the

constant total voltage of 800V, 4 mg/s case, the

trends exhibited by the 6 and 7 mg/s and 800 V

constant total voltage were repeated. That is the

anode efficiency decreased with increasing

discharge voltage. In the 4 mg/s case, the

efficiency begins to decrease with increasing

discharge voltage up to 25.0 V, then begins to

increase to a maximum at 100-125 V. This

suggests that some performance benefit may be

realized in the two-stage configuration at low

anode mass flow rates. Specifically, this case

represented the lowest flow rate, and as a result,

lowest channel density case considered. Under

these conditions the ionization efficiency may

have in fact been enhanced through the use of the

first stage anode as was originally expected.

Single and Two-Stage Comparison

In order to allow for a direct comparison of

single versus two-stage operation, the data

presented in Figure 10 were taken at various

constant input powers. In this figure, anode

specific impulse is plotted versus thrust for

power levels ranging from 2-7 kW. In the 6 and

7 kW cases, only two-stage data were available.

In the other cases, there is no appreciable

difference between the single and two-stage

points at a given power level and the points lie

approximately on the same line. This behavior is

indicative of similar performance characteristics

in the two separate operating configurations.

Lastly, anode specific impulse is compared at

equivalent voltages for mass flow rate cases of 5,

6 and 7 mg/s. These data are depicted in Figure

11. For the two-stage points, the voltage used on

the abscissa is the sum of the accelerating and

discharge voltages. The data are very similar at

all points regardless of flow rate or voltage. The

two-stage configuration anode specific impulse

exceeds that of the single-stage configuration for

all but two data points. The difference in

magnitude between the specific impulse values is

between 1 and 3% in all cases. This difference is

not statistically significant, and seems to indicate

that this thruster performs similarly in the single

and two-stage configurations.

Conclusions

The D-80 Hall thruster was operated in single

and two-stage configurations. In single-stage

configuration, specific impulse in excess of 4000

s and efficiency over 70% was demonstrated.

Stable operation was achieved at voltages over

1600 V. Thruster investigations were conducted

with input power ranging from 1 kW to 8.7 kW,

corresponding to power throttling of nearly 9:1.

A two-stage performance map was generated

using a discharge voltage of 100 V. Two-stage

thruster operation was conducted at power levels

ranging from 1.3 to 8.2 kW. Demonstrated

specific impulse ranged from 1900 to 3600 s

over this range. Additional testing was

conducted, holding the sum of the discharge and

accelerating voltage constant. It was apparent

that the single-stage performance was equivalent

to the performance in the two-stage

configuration with zero discharge voltage. Any

discharge voltage increase had a negative effect

NASA/TM--2001-211147 5
onefficiency,asthepowerconsumedinthefirst

stagecreatedinefficiencyin the thruster

operation.

The original target parameters were a power

level of 2.3 kW, thrust of 100 mN, and specific

impulse of 3200 s. While these parameters were

not demonstrated at a single point, the thruster

operated in a stable fashion and performed well

over an extremely wide envelope. Maximum

performance was demonstrated at a discharge

voltage of 800 V and discharge current of 6.5 A.

The anode specific impulse, thrust and efficiency

were 3320 s, 224 mN and 71%, respectively.

A cursory investigation revealed that the steady

state thermal limit of the thruster may be 4 kW.

While a portion of the operating points were

above this power level, improvements in the

thruster's design could potentially be employed

to circumvent this issue.

References

l° Oleson, S. R., "Mission Advantages of

Constant Power, Variable Isp Electrostatic

Thrusters," AIAA-2000-3413, July 2000.

2. Oleson, S,R., Sankovic, J.M., "Advanced

Hall Electric Propulsion for Future In-Space

Transportation," NASA TM-2001-210676.

3. Manzella, D.H., et al., "High Voltage SPT

Operation," AIAA-2001-3774, July 2001.

4. Yuen, J.L., Tverdokhlebov, S.O., Semenkin,

A.V., "Hall Thruster Development-Anode

Layer Thruster D-80," NAS3-99171 Final

Report, April 2000_

5. RocketdynefrsNIIMASH Teaml "Anode

Layer Thruster D-80 Operation Manual,"

Hall Thruster Development Contract No.

NAS3-99171, January 2000.

6. Butler, G.W., et al., "Multi-Mode, High

Specific Impulse Hall Thruster

Technology," AIAA-2000-3254, July 2000.

7. Haag, T.W., Manzella, D.M.,

"RHETT/EPDM Performance

Characterization," IEPC-97-107, August

1997.

8.

9°

Jacobson, D.T., Jankovsky, R.S., "Test

Results of a 200 W Class Hall Thruster,"

NASA TM- 1999-209449.

Tverdokhlebov, S., "Study of Double-Stage

Anode Layer Thruster Using Inert Gases,"

IEPC-93-232, September 1993.

q

NASA/TM--2001-211147 6
Table h D-80 Single StageData

Discharge Discharge

Volts 1 Amps Power_W

809.7 2.3 1838

900. I 2.3 2043

998.8 2.2 2187

1100,4 2,3 2487

t200.0 2.1 2532

1299.3 2,1 2716

1400.7 2. I 2899

300.0 3.3 1C02

400.0 3.3 1328

500,0 3.3 1630

600.0 3.2 1944

700.0 3.2 2240

800.0 3.2 2536

900.0 3.1 2826

300.0 3.2 966

799.7 3.3 2607

900.4 3.2 2890

1000.5 3,1 3132

11(30.0 3.1 3454

1200.0 3.2 3804

1300.0 3.2 4108

1400.4 3.1 4369

1499.2 3.1 4633

1600.8 3.1 4898

300.6 4.4 1332

400,4 4.3 1730

500.6 4.3 2128

599.9 4.2 2490

699.9 4.1 2877

799.9 4.1 3256

900.7 4.0 3603

800, I 4.3 3400

901,4 4.2 3804

10(30.0 4.2 4180

1097.9 4.1 4545

1200.3 4.2 4981

1301.6 4.1 5311

1401.3 4.1 5675

1500.4 4.0 6047

1600.0 4.0 6464

300.2 5,4 1633

400.0 5.4 2140

500.0 5.2 2620

601.9 52 3124

700.1 5! 3606

800.9 5.1 4077

900.4 5.1 4565

800.3 5.4 4322

900.3 5.3 4790

1006.5 5.3 533d

1100.8 5.3 5779

1201.1 5.2 6282

1300.3 5.2 6723

1400.4 5.2 7282

1497.4 5.2 7801

1600.7 5.2 8292

1699,0 5,1 8733

301,6 6.6 1985

400.0 6.4 2556

500.0 6.3 3135

601.5 6.2 3705

701.4 6.1 4265

800.1 6.3 5057

300.7 7.8 235 I

400.2 7.7 3078

499.5 7.5 3721

600.2 7.3 4387

700.6 7.2 5009

Inner Magnet O_ter Ma._p_el

Volts l Amps Volts [ Amps

2.1 0.71 1,7 0.23

1.5 0.40 2.4 0.31

1.6 0,52 3.2 0,41

1.6 0.49 2.2 0,27

1.4 0.4,4 3.9 0.47

1,6 0.47 3.7 0.43

1.7 0.52 3.7 0.43

2.8 0.70 3.1 0.38

2.8 0.70 3.1 0.38

2.8 0.70 3. I 0,38

2.8 0.70 3.2 0.38

2.8 0.70 3.2 0.38

2.8 0.70 3.2 0.38

2.8 0,70 33 0.38

2.9 0.70 3.3 0.38

2.6 0.73 4.1 0.44

2.8 0.74 4.9 0.50

3.1 0.81 5.3 0.54

3.0 0.76 4.8 0.48

2.8 0.68 4.7 0.46

3.0 0.71 5.3 0.50

2,8 0.65 5.2 0.48

3.0 0.66 5.4 0.49

3.0 0_66 5.5 0.49

3.6 1,23 4.6 0.72

3.6 1,22 4.0 0.61

3.5 1.19 4.5 0.68

3.0 0,98 3 4 0,5 I

2.6 0,87 3.6 0.52

2A 0,78 3.3 0.47

2.6 0.83 3.9 0.54

4.5 0.94 5,6 0.49

4.2 0.86 6.0 0.51

4.3 0.86 6,0 0.51

4.1 0.81 7,1 0.60

4.0 0.77 7.0 0.59

4,4 0.82 7.1 0.59

4.5 0.82 7,1 0.58

4! 0.74 7.9 0.64

3,8 0.67 7.9 0,64

4.1 1.35 2.5 0.37

4.1 1.35 2.5 0.37

4.1 1.35 2,5 0.37

3.4 1.10 3.8 0.56

3.4 1.08 3.9 0.57

3,4 1,07 4.0 0.56

3.2 0.95 5.4 0.66

5.7 0.98 9.0 0.71

6.5 1.08 8.8 0.69

5.6 0.92 7.3 0.57

5.6 0.91 7,4 0,57

5.7 0.91 6.8 0.53

6.0 0.96 6.7 0.52

5.6 0.88 6.7 0.52

5.1 0.78 7,6 0.58

5.1 0,78 7.7 0.58

5.2 0.78 7,7 0.58

5.7 1.61 45 0.53

5,8 1.61 4,6 0.53

5.9 1.61 4,6 0.53

5.5 1.43 5, I 0.57

5.4 1.38 4.5 0.50

5.5 1.38 4.6 0.50

5.1 1.24 4.8 0.5 I

5.2 1.24 4,9 0.50

6.1 1.41 4.9 0.50

6,2 1.41 5,0 0,50

7,2 1.59 5,4 0.53

Total Flow Rates, mg/s

Power? W Cath I Anode

1840 0.4 3.0

2045 0.4 3.0

2190 0.4 3,0

2488 0.4 3.0

25.34 0.4 3.0

2718 0.4 3.0

2902 0,4 3,0

1005 0.4 4.0

1331 0.4 4,0

1633 0.4 4.0

1947 0.4 4.0

2243 0,4 4,0

2539 0,4 4.0

2829 0.4 4,0

969 0.4 4,0

2611 0.4 4.0

2895 0.4 4,0

3137 0.4 4.0

3459 0.4 4.0

3808 0.4 4,0

4113 0,4 4.0

4374 0,4 4.0

4637 0.4 4.0

4903 0.4 4.0

1339 0.4 4.9

1737 0.4 4.9

2135 0.4 4.9

2494 0.4 4.9

2881 0.4 4.9

3259 0.4 4.9

3607 0,4 4.9

3407 0,4 4.9

3811 0,4 4.9

4187 0.4 4.9

4553 0.4 4,9

4988 0.4 4.9

5318 0.4 4.9

5683 O.4 4.9

6055 0.4 4.9

6472 0.4 4.9

1639 0.4 5.9

2146 0.4 5,9

2626 0.4 5.9

3130 0.4 5.9

3611 0.4 5.9

4082 0.4 5,9

4572 0.4 5.9

4334 0.4 5.9

4803 0.4 5.9

5344 0.4 5.9

5789 0.4 5.9

6291 0.4 5.9

6732 0.4 5.9

7291 0.4 5.9

7810 0,4 5.9

8300 0.4 5.9

8741 0.4 5.9

1996 0.4 6.9

2568 0,4 6.9

3147 0.4 6.9

3716 0.4 6.9

4274 0.4 6.9

5066 0.4 6.9

2360 0.4 7.9

3086 0.4 7.9

3732 0.4 7.9

4399 0.4 7.9

5024 0.4 7.9

* Indicates value_ calculated with discharge power only and without cathode flow.

Cat float "l'nrust lsp lsp* Eft Eft*

Volta_.e_ V mN see ,,,,_

-8,8 72 2153 2440 0.41 0.47

-9,7 79 2370 2687 0,45 0.51

-10.1 81 2423 2747 0,44 0.50

-9,3 84 2503 2838 0,41 0.47

-9.9 81 2431 2756 0.38 0.43

-9.8 82 2464 2794 0,37 0.41

-8.9 78 2345 2659 0.31 0.35

-10.6 64 1483 1633 0,46 0.51

-10.8 74 1725 1899 0.47 052

-10.9 83 1933 2128 0.48 0.53

-10,3 90 2092 2304 0,47 0.52

- I 1.5 97 2254 2481 0.48 0.53

- 11.4 102 2384 2624 0.47 052

-11.4 107 2497 2748 0,46 0,51

-I 1.5 62 1449 1596 0.46 0.50

-9.7 107 2495 2745 0.50 0.56

-9.9 113 2628 2892 0.50 0,56

-10.2 117 2727 3001 0.50 0.55

-9.7 122 2840 3125 0.49 0,54

-9,5 t27 2948 3245 0.48 0,53

-9.3 129 3000 3301 0.46 0.51

-9.5 133 3081 3391 0.46 0.5 I

- 10.8 134 3120 3434 0.44 0,49

-t0,1 137 3192 3513 0.44 0.48

-9.8 85 1625 1756 0.5 t 0.55

-10.1 98 1873 2025 0.52 0,56

-t0.7 tt0 2092 2261 0.53 0,57

-9.9 120 2286 2471 0.54 0,58

-9.7 127 2428 2625 0.53 0.57

-9.5 135 2579 2788 0.52 0,57

-9.6 140 2670 2887 0.51 0.55

-10,7 t40 2670 2887 0.54 0,58

-10.5 t48 2824 3053 0.54 0.58

- 10.4 155 2949 3188 0.53 0.58

-10.0 161 3073 3323 0.53 0.58

-10.5 168 3198 3457 0.53 0.57

-10.7 173 3297 3565 0.53 0.57

-10.6 178 3400 3675 0.52 0.57

-11.0 183 M87 3770 0.52 0.56

-t0.6 186 3543 3831 0.50 0.54

-10.9 105 1692 1807 0,53 0.57

- 11.5 121 1960 2092 0.54 0.58

-I 1.5 t35 2185 2333 0,55 0.59

-12.0 150 2429 2593 0,57 0.61

-11,5 162 2609 2786 0.57 0.61

-10,4 169 2726 2910 0.55 0.59

-10.3 177 2849 3042 0.54 0.58

-10.9 181 2932 3130 0.60 0.64

-10,7 191 3082 3291 0.60 0.64

-10.4 199 3216 3434 0.59 0.63

-10.3 206 3335 3562 0.58 0.62

-10.0 212 M29 3661 0.57 0,61

-9.9 218 3519 3758 0.56 0.60

-9.8 224 3616 3861 0.54 0.58

-10.3 229 3700 3952 0.53 0.57

-10,8 235 3799 4057 0.53 0.56

240 3879 4142 0.52 0.56

-10.5 126 1759 1862 0.54 0,58

-11.8 145 2034 2152 0.56 0.60

-11,9 163 2287 2420 0,58 0.62

-I 1.6 179 2509 2655 0.59 0.63

-10.9 192 2682 2838 0.59 0.63

-10,6 213 2975 3148 0,61 0.65

-9.6 148 1831 1925 0.56 0,60

-10.1 173 2141 2251 0.59 0,62

-I1.1 [92 2372 2493 0.60 0.63

-11,0 210 2594 2726 0.61 0.64

-10.8 225 2780 2922 0.61 0.64

NASA/TM--2001-211147 7
Table 2:D-80 Two-Stage Constant Discharge Voltage Data

Disdmrge Accelerator Inner N_net Outer Magnet Total Flow Rates, m_/s Cat to

-Volt* I AmF_ Volts [ A._ps Volt* I An,I,_ Volts [Aml_" Power, W Cathode [ Anode Grd. V

100.7 3.7 300.0 3.2 3.1 0.71 4.9 0.50 1343

101.0 3.6 400.0 3.2 3.1 0.71 5.0 0.50 1658

100.6 3.3 500.0 3.0 3.2 0.71 6.5 0.65 1851

100.9 3.3 600.8 3.0 3.3 0.71 6.6 0.65 2161

101.2 3.3 700.8 3.0 3.3 0.71 6.6 0.65 2431

100.0 3.2 800.6 2.9 3.4 0.71 6.7 0.65 2679

100.6 3.2 900.4 2.9 3.4 0.71 5.9 0.58 2974

100.9 3.2__ 1000,7 2.9 3.5 0.71 5.2 0.50 .... 3267

99.5 4,8 300.0 4.2 3.9 0.77 5.4 0.50 1756

100.0 4.7 400.0 4.2 4.0 0.77 5.4 0,50 2145

100.3 4.7 500.0 4.2 4.0 0.77 5.4 0.50 2547

(00.5 4.1 600.0 4.1 4.0 0.77 5.0 0.46 2873

100.7 4.5 700.0 4.1 4.1 0.77 5.0 0.46 3300

100.9 4.4 800.2 4.0 4.1 0.77 5.0 0.46 3659

101.3 4.4 900.2 4.0 4.1 0.77 4.6 0.43 4040

101.5 4.4 1001.0 4.0 4.1 0.77 4.6 0.43 4413

t 00.2 6.3 300.2 5.5 4. I 0.74 5.1 0.46 2273

100.3 6.0 400.0 5.4 4.t 0.74 5.1 0.46 2749

100.5 6.0 500.2 5.4 4.1 0.74 5.1 0.46 3290

t00.8 5.9 600.1 5.2 4.7 0.84 5.0 0.45 3742

101.0 5.8 700.1 5.2 4.8 0.84 5.1 0.45 4215

101.0 5.8 800.0 5.1 4.8 0.84 5.1 0.45 4675

101.0 5.7 900.0 5.1 4.9 0.84 5.1 0.45 5152

101.6 5.4 1000.0 4.9 6.0 1.00 5.7 0.48 5440

100.4 7.7 300.1 6.6 6.1 1.00 5.7 0.48 277t

100.6 7.5 400.0 6.5 6.2 1.00 5.8 0.48 3378

100.7 7.4 500.0 6.4 6.2 1.00 5.8 0.48 3965

100.9 7.2 600.5 6.3 6.3 1.00 5.8 0.48 4540

101.0 7.1 700.7 6.3 6.4 1.00 5.1 0.41 5107

101.4 7.0 800.0 6.2 6.4 1.00 4.2 0.34 5703

101.6 7.0 900.0 6.2 6.4 0.09 4.2 0.34 6295

101.7 6.9 1000.0 6.2 6.5 0.90 4.2 .= Q.=3.4....... 6883

66.5 9.1 299.8 7.8 6.9 1.02 10.3 0.81 2960

71.2 9.0 400.0 7.7 7.0 t.03 10.4 0.81 3734

78.2 8.9 500.2 7.6 7.0 1.03 10.4 0.81 4520

100.0 8.7 600.4 7.6 6.6 0.96 7.6 0.59 5465

100.3 8.6 700.0 7.5 6.6 0.96 7.6 0.59 6141

100.6 8.5 800.0 7.4 6.7 0.06 7.6 0.59 6815

101.0 8.4 900.0 7.4 6.7 0.96 7.6 0.59 7499

101.2 8.3 1000.0 7.3 6.7 0.96 7_6. ...... 0,59 8168

*Indicates values calculated with di_harge power only and without cathode flow.

0.4 4.0 -7.8

0.4 4.0 -7.6

0.4 4.0 -7.6

0.4 4.0 -10.1

0.4 4.0 -10.3

0.4 4.0 -10.3

0.4 4.0 -9.9

0.4 4.0 -9.6

0.4 4.9 -9.4

0.4 4.9 -9.5

0.4 4.9 -9.5

0.4 4.9 -9.2

0.4 4.9 -9.2

0.4 4.9 -9.2

0.4 4.9 -9.0

0.4 4.9 -9.0

0.4 5.9 -8.6

0.4 5.9 -8.9

0.4 5.9 -9.1

0.4 5.9 -8.9

0.4 5.9 -8.8

0.4 5.9 -8.8

0.4 5.9 -8.8

0_4 5.9 -8.7

0.4 6.9 -9.2

0.4 6.9 -9.2

0.4 6.9 -9.2

0.4 6.9 -9.1

0.4 6.9 -9.0

0.4 6.9 -9.0

0.4 6.9 -9.0

0.4 6.9 -8.9

0.4 7.9 -9.4

0.4 7.9 -9.8

0.4 7.9 -9.8

0.4 7.9 -9.3

0.4 7.9 -9.2

0.4 7.9 -9.1

0.4 7.9 -9.1

0.4 7.9 -9.0

Thrust _p _p* Eft Eft*

mN sec sec

74 1717 1890 0.46 0.51

83 1944 2140 0.48 0.53

90 2098 2310 0.50 0.55

96 2241 2467 0.49 0.54

102 2367 2605 0.49 0.54

107 2483 2733 0.48 0.53

113 2630 2896 0.49 0.54

118 2739 3015 0.48 0.53

98 1874 2026 0.51 0.56

111 2124 2296 0.54 0.59

121 2310 2497 @54 0.58

128 2449 2648 0.54 0.58

136 2584 2794 0.52 0.56

141 2696 2015 0.51 0.55

t46 2793 3020 0.50 0.54

152 2896 3131 0.49 0.53

124 2009 2145 0.54 0.58

139 2250 2403 0.56 0.60

151 2433 2598 0.55 0.58

161 2592 2768 0.55 0.58

170 2738 2924 0.54 0.58

178 2874 3069 0.54 0.57

185 2993 3196 0.53 0.57

190 3070 3278 0.53 0.56

149 2079 2200 0.55 0.58

167 2343 2479 0.57 0.60

182 2547 2696 0.57 0.61

195 2725 2883 0.57 0.61

205 2869 3036 0.57 0.60

214 2995 3170 0.55 0.58

224 3127 3310 0.54 0.58

232 3241 3429 0.54 0.57

165 2033 2137 0.56 0.59

189 2336 2455 0.58 0.61

211 2603 2736 0.60 0.63

231 2858 3004 0.59 0.63

245 3029 3183 0.59 0.62

258 3184 3347 0.59 0.62

269 3322 3491 0.58 0.62

278 3430 3606 0.57 0.60

NASA/TM--2001-211147 8
Table 3:D-80 Two-Stage Constant Total Voltage Data

Discharge Accelerator Total V Inner Mag. Ouier Mag. Total Flow Rates, mg/s Cathode Thrust Isp lsp* Eft Eft*

Volts [ Amp Volts [ Amp Volts Volts [Amp Volts tAmp Power I W Cath. [ Anode to Grd. _v_ mN sec sec

** 801.7 2.4 802,0 1.6 0,57 2,5 0,40 1910 0.4

5.2 1.5 795.6 2.2 800.8 3,0 0,53 4.4 0.40 1778 0,4

9.9 2.0 790,5 2.2 800.4 2,9 0.52 4,5 0,40 1786 0,4

25,6 2.3 775.9 2.2 801,5 3,3 0.59 4.5 0.40 1776 0.4

50,1 2.4 750.5 2.3 800.6 2,8 0.50 5,1 0.45 1814 0.4

75,3 2.4 725. I 2.2 800.4 2.7 0.49 6.4 0.57 1780 0,4

100.3 2.4 700.1 2.2 800.4 2,3 0.43 7,3 0.66 1770 0.4

125.2 2.5 675.6 2.2 800.8 2.3 0.44 7,2 0,65 1807 0.4

150,0 2,5 650.1 2.2 800.1 2,3 0.44 7.9 0.72 1809 0.4

200,0 2.7 600.0 2.3 800.0 2,9 0,55 7,4 0.67 1891 0.4

** 800.2 3.4 800.2 3,0 0,81 3.3 _37 2716 0.4 4.1

0.2 0, l 800, I 3.4 800.3 3. I 0,81 3.3 0.36 2708 0,4 4. I

5.0 1,8 795.0 3,6 800.0 2.3 0,61 3.5 0.38 2850 0,4 4,1

10.1 3.0 790,3 3,5 800.4 2.4 0.61 3.6 0.38 2831 0.4 4,1

15.0 3,5 786,0 3.7 801.0 2.0 0.51 3.4 0.35 2931 0.4 4. I

25.0 3,6 774,4 3.6 799.4 1.9 0,45 4.4 0,45 2896 0,4 4. I

50. I 3,6 750.4 3,5 8130.5 2.0 0.48 5.2 0.51 2790 0,4 4. I

75. I 3.8 725.3 3,5 800.4 2.2 0,50 4.7 0,45 2858 0.4 4.1

100,2 3.8 700,3 3.5 800.5 2,6 0,58 4.5 0.43 2817 0,4 4.1

125,3 3.9 675,3 3.5 800.6 2.7 0,58 4,5 0.42 2859 0,4 4.1

150.1 4.0 650,9 3.5 801,0 2.8 0,58 4,5 0,42 2906 0,4 4.1

175,3 4.1 624.9 3.5 800,2 3.2 0,66 5,3 4,85 2913 0.4 4.1

3.0

3.0

3.0

3.0

3.0

3.0

3.0

3,0

3.0

3.0

200.6 4.1 600,4 3.4 801,0 3,6 0.72 6.6 0.60 2860 : 0.4 .... 4A

** 801.1 4.4 801,0 2.3 0.81 4.2 0.65 3529 0,4 4.9

0.3 0.2 801.0 4.4 801.3 2.3 0.81 4.3 0.64 3505 0,4 4.9

5.0 2.3 795.2 4.4 800.2 2.0 0£8 4,2 0.60 3522 0.4 4,9

10.1 4,0 790.6 4.4 800,7 2.4 0.78 3.2 0.43 3514 0.4 4.9

15. I 4.4 786.0 4.4 80I. l 2,4 0.78 4,0 0.52 3497 0.4 4,9

25,3 4.5 775.6 4,4 800.9 2,4 0.72 3,9 0.48 3507 0.4 4.9

50,2 4,6 750.5 4.3 800.7 2.1 0.63 5,1 0,60 3494 0.4 4.9

75.0 4.8 725.6 4.3 800.6 2.4 0,67 5.6 0,64 3511 0.4 4.9

100.7 4.9 700.0 4,3 800,7 2,8 0,75 6,9 0,77 3538 0.4 4,9

125,4 5,0 675.4 4,4 800.8 3.1 0,81 5,7 0,61 3575 0.4 4.9

150,0 5.1 650.6 4.4 800,6 3.4 0,84 4,7 0,49 3604 0.4 4.9

175.2 5,2 625,6 4,4 800,8 3.8 0,91 5.6 0.57 3636 0.4 4.9

200. I 5,3 600.2 4.4 800.3 3.6 0.82 5.7 0.57 368,1 0,4 4.9

** 800,8 5,4 800,8 5.5 I, 12 7.3 0.77 4360 0,4 5.9

5,1 3,1 795.2 5.6 800.3 4.2 0.86 6.7 0.69 4461 0.4 5.9

10.2 5,4 790.5 5,6 800.7 3.5 0.71 5.5 0,56 4496 0.4 5.9

25.4 5,8 775,7 5.5 801.1 3.4 0.68 6.7 0,66 4421 0.4 5.9

50,3 6.0 750.6 5.5 800.9 3.8 0.75 6.6 0,64 4407 0.4 5.9

75.2 6.2 725.1 5.5 800.3 3.9 0.75 7.2 0.70 4444 0.4 5.9

100.6 6.3 700.5 5.5 801.1 4.6 0,87 9.1 0.86 4462 0.4 5.9

125,3 6.3 675.1 5.5 800.4 4.8 0.91 6.8 0,63 4509 0,4 5.9

150 6.42 650 5.5 800.0 4.9 0,89 7.5 0.682 4547 0,4 5.9

175.3 6.55 624,6 5.52 799.9 5,0 0.889 7.6 0.681 4606 0,4 5.9

200,1 6.61 599. t 5.52 799,2 4,7 0.821 8.9 0.779 4640 0.4 5.9

** 800.4 6.5 800,4 5.2 1,30 8,6 0,91 5185 0,4 6.9

0.5 0.3 800,3 6.5 800,8 5.0 1.19 8.8 0.90 5216 0.4 6.9

2.2 1.0 799,1 6.6 801,3 7.5 1,21 8,1 0.67 5291:2 0,4 6.9

2.9 2.0 796.8 6.7 799.7 6.6 1.04 8.8 0,71 5357 0.4 6.9

4,3 3.2 706,8 6.7 801,1 6.3 0.99 9.0 0.72 5397 0.4 6,9

5.6 4.0 794.1 6.8 799.7 6.5 0.99 8,4 0.67 5410 0.4 6,9

7.5 5.3 793.0 6.8 800.5 6.7 0.86 8.6 0.67 5436 0.4 6.9

9.9 5.9 790.7 6.8 800,6 6,0 0.89 8.8 0.68 5447 0.4 6,9

16.0 7.0 78.4.8 6.8 800.8 5.9 0.86 8,9 0.68 54.44 0.4 6.9

25,0 7.3 775.4 6.7 800.4 6,0 0.87 9.2 0.71 5419 0.4 6.9

50.0 7.5 750.4 6,7 800,4 5,4 0.91 9,3 0.70 5422 0.4 6.9

75.1 7,7 725.3 6,7 800,4 6,5 0.91 8,9 0.67 5476 0.4 6.9

100.2 7,8 700.1 6.8 800.3 6,5 0.90 I 1.1 0.84 5530 0.4 6.9

125.1 7,9 675.0 6.8 800.1 6,6 0.90 10.7 0.80 5582 0.4 6,9

150,2 8,0 650.5 6.8 800.7 6. I 0.82 10,9 0.81 5620 0.4 6.9

175.1 8,0 625.3 6,7 800.4 6.6 0.89 13.4 1.00 5619 0.4 6.9

200.5 8,1 600.4 6.8 800.9 7.0 0,92 I 1.7 0.86 5715 0.4 6.9

-9.6

-10,8

-10.8

-11.2

-I 1.2

-12.2

-12.7

-12,8

-13,0

-12,6

-9.2

-4.3

-8.6

-8.7

-8.3

-8.6

-9.5

-9.2

-9.4

-9,3

-9.1

-9,4

-I 1,0

-10,0

-9.9

-9.9

-9.2

-9.3

-9.3

-9,9

-10.2

-]0,7

-10,3

-9.8

-10,1

-10,2

-8,9

-9.6

-9.4

-9.9

-I0,0

-lO.l

-10.8

-I0.0

-10. i

-10.1

-10,4

-10.3

-10,4

-9,0

-9,0

-8,8

-8.6

-8.7

-8,6

-8,7

-8,8

-8.8

-8.8

-9.2

-9.2

-9.3

-9.9

-9,4

78 2348 2661 0.47 0,54

76 2275 2579 0.48 0,54

76 2276 2580 0.47 0.54

77 2310 2619 0,40 0.56

77 2306 2614 0,48 0.54

76 2266 2569 0.47 0.54

75 2243 2542 0.47 0.53

75 2261 2563 0.46 0.53

75 2245 2546 0.46 0,52

76 2287 2592 0.45 0,51

I10 2514 2762 0.50 0.55

II1 2532 2782 0.51 0.56

112 2558 2810 0,49 0,54

112 2558 2810 0.50 0,55

114 2588 2843 0.49 0,54

113 2574 2828 0.49 0.54

113 2579 283,4 0.51 0.56

116 2648 2908 0.53 0.58

116 2648 2908 0.54 0,59

117 2661 2923 0.53 0.59

117 2657 2919 0.52 0.57

115 2627 2885 0.51 0.57

114 2591 284,6 0.50 0.56

146 2779 3004 0.56 0.61

145 2761 2985 0.56 0.61

145 2760 2984 0.56 0.60

143 2728 2949 0.54 0,59

142 2719 2939 0.54 0,59

143 2726 2947 0.54 0,59

143 2726 2947 0.55 0.59

t43 2739 2960 0,55 0,59

t44 2756 2979 0,55 0,60

145 2775 2999 0.55 0,60

145 2775 2999 0,55 0.59

146 2781 3006 0.55 0,59

146 2789 3014 0.54 0.59

185 2995 3197 0.62 0,67

183 2958 3158 0.60 0.64

183 2949 3149 0,59 0,63

180 2911 3108 0.58 0,62

181 2923 3121 0,59 0,63

181 2930 3128 0.59 0.63

183 2964 3165 0,60 0,64

184 2975 3176 0.60 0.64

185 2981 3182 0,59 0.63

184 2978 3180 0,58 0,63

184 2968 3169 0,58 0.62

224 3137 3320 0.67 0.71

224 3133 3315 0.66 0.70

224 3133 3316 0.65 0,69

226 3158 3342 0.65 0.69

226 3157 3341 0.65 0,69

225 3153 3337 0.64 0,68

225 314.4 3327 0.64 0.68

225 3149 3332 0.64 0,68

225 3142 3325 0.64 0.67

224 3133 3315 0.64 0,67

223 3119 3301 0.63 0.67

224 3135 3318 0.63 0.67

225 3150 3333 0.63 0.67

226 3162 3346 0.63 0.67

225 3t50 3334 0.62 0.66

225 3154 3338 0.62 0.66

226 3168 3353 062 0.65

*Indicates values calculated with discharge power only and without cathode flow.

**Indicates single stage point taken with anode electrodes electrically connected.

NASA/TM--2001-211147 9
Figure1: Laboratory model D-80 Hall thruster.

6 8 I 2 3

/

/

Figure 2: Mechanical Schematic Drawing of D-80 Hall thruster.

Legend:

1.

2.

3.

4.

.

6.

7.

8.

9.

First Stage anode

Second Stage Anode

Inner coil with magnetic pole

Outer coils (4) connected

series

Outer pole pieces

Flange

Guard rings

Insulators

Screen

in

NASA/TM--2001-211147 10
++,,',_ - .!...,...!._f.+_++i ............

[ T

\

Figure 3: Electrical schematic drawing.

Figure 4:D-80 Hall thruster and test apparatus in NASA's Vacuum Facility 6.

NASA/TM--2001-211147 11
250

230

2!0

190

170

150

130

I10

90.

70

50

0

#

oov

y_/ +4oov

-+-900 V

_ 1000_

...... I100V

-Q_ 1200V

.... _ 1300 V

....!400v

1500 V

_ 1600 "v

1000 2000 3000 4000 5000 6000 7000

Discharge Power (W)

Figure 5: Single stage thrust versus discharge power.

_000 9000

4500

4000

_" 3500

E 3ooo

m 2500

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2000

1500

1000

0 200

• ! "A A

m I_ A

I A

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t [ _ 4 mg/s

I "s reeds

[• 6 mg/s

[* 7 mg/s

[ • 8 mg/s

400 600 800 I000 I200 1400 1600 1800

Discharge Voltage(V) .

Figure 6: Single stage specific impulse versus discharge voltage.

NASA/TM--2001-211147 12
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0.40

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200 400 600 800 1000 1200

Discharge Voltage (V) .

Figure 7: Single stage efficiency versus discharge voltage.

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[ _ 4 mg/s

] • 5 mg/s

I • 6 mg/s

] _ 7 mg/s

1400 1600 1800

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0.70

0.69

0.68

0.67

0.66

0.65

0.64

0.63

0.62

0.61

..... • .... m ....... -- - --- •

• • ...... • ......... •

o ..... * . .... 41. • •

0 50 100 150 200

Discharge Voltage (V) .

Figure 8: Two-stage anode efficiency and thrust versus discharge voltage for constant total

voltage of 800 V

250

230

210

190

170

150

130 _

110

90

70

50

NASA/TM--2001-211147 13
¢9

<

0.75 F o 3 mg/s, Vtot=800 V

/

-_+-4 m_s, Vtot=800 V

5 mg/s, Vtot=800 V

_^ I _ 6 m_s, Vtot=800 V

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[i_ 7 mg/s, tot=8OOV

| ___. _ -q-.- 6 mg/s, Vtot=600 V

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0.6O k_M __

_ . _

0.55

0.50 |

0 50 100 150 200

Discharge Voltage (V) .

Figure 9: Two stage anode efficiency versus discharge voltage for total constant voltage cases.

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c, 5 kW-2 Stage

n 6 kW-2 Stage

7 kW-2 Stage

50 100 150 200 250

Thrust, (raN) .

Figure 10: Single and two-stage specific impulse versus thrust for 2-7 kW power levels.

300

NASA/TM--2001-211147 14
v

Figure 11:

3500

3300

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l-Stage, 7 mffs

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a 2-Stage, 6 mg/s

2-Stage, 7 mg/s

200 400 600 800 1000 1200

Total Volts (V) .

Comparison of single and two stage anode specific impulse for flow rates 5-7 mg/s.

?

NASA/TM--2001-211147 15
REPORT DOCUMENTATION PAGE FormApproved

OMB No. 0704-0188

Publicrepodingburdenforthiscollectionof informationisestimatedto average1 hourperresponse,includingthe timeforreviewingInstructions, searchingexistingdatasources,

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1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE

November 2001

4. TITLE AND SUBTITLE

High Voltage TAL Performance

,6. AUTHOR(S)

David T. Jacobson, Robert S. Jankovsky,

Vincent K. Rawlin, and David H. Manzella

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

John H. Glenn Research Center at Lewis Field

Cleveland, Ohio 44135- 3191

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

Washington, DC 20546-0001

3. REPORT TYPE AND DATES COVERED

Technical Memorandum

5. FUNDING NUMBERS

WU-755-B4-05-00

8. PERFORMING ORGANIZATION

REPORT NUMBER

E-12999

10. SPONSORING/MONITORING

AGENCY REPORT NUMBER

NASA TM--2001-211147

AIAA-2001-3777

11. SUPPLEMENTARY NOTES

Prepared for the 37th Joint Propulsion Conference and Exhibit cosponsored by the AIAA, SAE, AIChE, and ASME,

Salt Lake City, Utah, July 8-11, 2001. David T. Jacobson, Robert S. Jankovsky, and Vincent K. Rawlin, NASA Glenn

Research Center; and David H. Manzella, University of Toledo, 2801 W. Bancroft Street, Toledo, Ohio 43606-3328.

Responsible person, David T. Jacobson, organization code 5430, 216--433-3691.

12a. DISTRIBUTION/AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE

Unclassified - Unlimited

Subject Category: 20 Distribution: Nonstandard

Available electronically at ht _tp://gltrs.m-c.nasa.gov/GLTRS

This publication is available from the NASA Center for AeroSpace Information, 301-621---0390.

13. ABSTRACT (Maximum200 words)

The performance of a two-stage, anode layer Hall thruster was evaluated. Experiments were conducted in single and

two-stage configurations. In single-stage configuration, the thruster was operated with discharge voltages ranging from

300 to 1700 V. Discharge specific impulses ranged from 1630 to 4140 sec. Thruster investigations were conducted with

input power ranging from I to 8.7 kW, corresponding to power throttling of nearly 9:1. An extensive two-stage performance map was generated. Data taken with total voltage (sum of discharge and accelerating voltage) constant revealed a

decrease in thruster efficiency as the discharge voltage was increased. Anode specific impulse values were comparable in

the single and two-stage configurations showing no strong advantage for two-stage operation.

14. SUBJECT TERMS

Hall thruster

17. SECURITY CLASSIFICATION

OF REPORT

Unclassified

NSN 7540-01-280-5500

18. SECURITY CLASSIFICATION

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Unclassified

19. SECURITY CLASSIFICATION

OF ABSTRACT

Unclassified

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Standard Form 298 (Rev. 2-89)

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