Daniel M. Hauser and Frank D. Quinn

Glenn Research Center, Cleveland, Ohio

Simulation of a Cold Gas Thruster 

System and Test Data Correlation

NASA/TM—2012-217271

February 2012

AIAA–2011–5769
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Daniel M. Hauser and Frank D. Quinn

Glenn Research Center, Cleveland, Ohio

Simulation of a Cold Gas Thruster 

System and Test Data Correlation

NASA/TM—2012-217271

February 2012

AIAA–2011–5769

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Prepared for the

47th Joint Propulsion Conference and Exhibit

cosponsored by the AIAA, ASME, SAE, and ASEE

San Diego, California, July 31–August 3, 2011
Acknowledgments

The authors would like to thank Brian Reed of the NASA Glenn Research Center’s Propulsion Branch for providing access to the 

AA-1 system design and test data. The authors would also like to acknowledge Steve Grasl, Antony Skaff, Terry Hui and the rest 

of the staff at Sierra Lobo, Inc., of Milan, Ohio, who integrated and conducting the testing of the AA-1 developmental hardware. 

Available from

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subject to revision as analysis proceeds.
NASA/TM—2012-217271 1

Simulation of a Cold Gas Thruster System 

and Test Data Correlation

Daniel M. Hauser and Frank D. Quinn

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Abstract

During developmental testing of the Ascent Abort 1 (AA-1) cold gas thruster system, unexpected 

behavior was detected. Upon further review the design as it existed may not have met the requirements.

To determine the best approach for modifying the design, the system was modeled with a dynamic fluid 

analysis tool (EASY5). The system model consisted of the nitrogen storage tank, pressure regulator, 

thruster valve, nozzle, and the associated interconnecting line lengths. The regulator and thruster valves 

were modeled using a combination of the fluid and mechanical modules available in EASY5. The 

simulation results were then compared against actual system test data. The simulation results exhibited 

behaviors similar to the test results, such as the pressure regulators response to thruster firings. Potential 

design solutions were investigated using the analytical model parameters, including increasing the volume 

downstream of the regulator and increasing the orifice area. Both were shown to improve the regulator 

response.

1.0 Introduction and Background

The Ascent Abort 1 (AA-1) test vehicle was part of the Orion flight test program conceived of to 

verify the launch abort system (LAS). The AA-1 flight was to demonstrate the LAS performance during 

abort at maximum dynamic pressure. The AA-1 Reaction Control System (RCS) was to be used to 

provide roll control to the boilerplate Crew Module (CM) during descent, to determine the response of the 

main parachutes to torque. The AA-1 RCS was also to demonstrate a roll control algorithm to position the 

CM for landing and provide rate damping as needed. The AA-1 RCS was designed to use non-flight 

components with no heritage to the production vehicle. A developmental test was performed on the RCS 

system in February 2010. During the testing, the regulator experienced significant pressure undershoot

and overshoot when the thruster valve was cycled open and closed. Un-commanded closure of the thruster 

valve was detected and attributed to the pressure undershoot. The closing time of the thruster valve 

appeared to be pulse length dependent.

2.0 AA-1 Reaction Control System Developmental Test

A developmental test of the AA-1 RCS cold gas system was constructed to demonstrate performance 

of the design. A simplified schematic of the flight RCS system can be seen in Figure 1. The black lines 

indicate the hardware that was included in the developmental test. The test system consisted of four 

nitrogen propellant tanks pressurized to 3600 psig for a total of 400 lb of nitrogen. A regulator was used 

to reduce the pressure to 600 psig. Further downstream was a relief valve set at 900 psig, and the thruster 

valve with an attached nozzle, designed to generate 150 lb thrust at sea level. The thruster valve was a 

solenoid pilot operated valve. The piloted valve was configured in a manner that requires a differential 

pressure across the valve for it to stay open. The system was designed with the expectation that the 

thruster valve could be commanded open and closed for various pulse lengths. Not shown on the 

schematic is the tank isolation valve and instrumentation. Testing consisted of filling, nominal and

emergency blow down operations. 
NASA/TM—2012-217271 2

Figure 1.—AA-1 RCS Schematic. Black lines represent hardware included in developmental test.

During the testing of nominal operations the system experienced a large drop and rise in regulator 

outlet pressure when the thruster valve was opened and closed. In some instances the thruster valve was 

also shown to close momentarily after the dip in pressure. Another finding was that the valve opening and 

closing times seemed to be dependent on the thruster valve pulse length. To illustrate the behavior two 

plots of the test data are presented in Figures 2 and 3. 

Figure 2 shows two short (400 ms) pulses followed by one longer pulse (2500 ms). The plots show

the regulator inlet and outlet pressure, the command signal to the thruster valve and thruster chamber 

pressure. Notice that the thruster valve response time for opening is consistent for the three pulses shown. 

However, the valve closure is nearly immediate for the long pulse whereas it is significantly longer for the 

two short pulses. Notice that when the regulator outlet overshoot reaches the 1000 psi level the relief 

valve opens and the pressure drops to near the set point. These characteristics are common throughout the 

data collected.

As the regulator inlet pressure decreased the response deteriorated further as shown in Figure 3. 

Shown is a 1500 ms commanded pulse followed by a series of 400 ms pulses separated by 100 ms. 

During the first pulse shown in Figure 3 the valve opens and closes with similar timing as the long pulses 

shown in Figure 2. However the valve momentarily closes immediately after opening as determined by 

the thruster chamber pressure. Also notice that the thruster valve does not respond to the short pulse 

commands until the third closing command. 
NASA/TM—2012-217271 3

Figure 2.—AA-1 Developmental Test Results. Typical behavior with short and long pulses

Figure 3.—AA-1 Developmental Test Results Examples of erratic behavior at lower supply pressures.
NASA/TM—2012-217271 4

Figure 4.—Overall system model.

3.0 Modeling Approach

In response to the unexpected results exhibited by the system during testing, a dynamic model of the 

system was created with the following goals:

• Determine the cause of the regulator pressure undershoot and overshoot

• Determine the cause of the thruster valve closing during the thruster valve firings

• Determine the cause of the irregular closing times of the thruster valve

• Determine the effectiveness of different design solutions to normalize operation.

The software tool used to model the system was MSC EASY5, a dynamic fluid/mechanical systems

modeler. The majority of the components used in the model were built using components in the Gas 

Dynamics Library (GD) of the EASY5 modeling tool. An overall view of the model can be seen below in 

Figure 4. The regulator and thruster valve were modeled using a mix of fluid and mechanical components 

as explained in the following sections. The regulator and thruster valve supply lines included a transient 

momentum pipe and a generic loss component to account for the losses associated with the bends and 

fittings. The thruster nozzle was modeled with a generic EASY5 nozzle component that calculates the 

mass flow rate based on the upstream pressure and temperature. 

3.1 Regulator Model

The regulator used in the AA-1 test is a direct acting regulator loaded with a fixed spring. The 

pressure in the sense volume, connected to the downstream pressure, acts against the spring to close the 

poppet against its seat as it approaches the set pressure. A schematic representation of the functional 

components in the regulator can be seen in Figure 5. The pressure forces acting on the poppet were 

assumed to be balanced and therefore cancelled each other out.

Previous regulator studies in the literature accounted for an additional flow force acting on the 

regulator poppet (Refs. 1, 2, and 3). The flow force accounts for the uneven pressure acting on the 

different areas of the poppet. The flow force is typically found by measuring the force at various inlet 

pressures and poppet positions during a test. Unfortunately, the regulator poppet geometry used in the two 

previous studies was different than the geometry of the poppet being used in this study. It was decided not 

to include a flow force in the model since its application would have been arbitrary and would have no 

basis for its determination. 
NASA/TM—2012-217271 5

Figure 5.—Regulator schematic.

Figure 6.—Regulator model.

The EASY5 model of the regulator can be seen in Figure 6. A single acting cylinder was used to 

model the variable volume of the sense chamber and the poppet position. The regulator flow resistance 

was modeled with the variable orifice component. The orifice area is based on the poppet position and 

determined using a look-up table. The volume and piston areas of the regulator were determined from 

drawings supplied by the regulator manufacturer. An orifice was used to model the complicated flow 

passage connecting the sense volume to the regulator outlet. Since the orifice area was not known, it was 

varied within the model until the undershoot and overshoot behavior approximated the test results

The regulator poppet force balance equation is shown below in the following equation.

 

Nomenclature

P = pressure

Subscripts

u = upstream

s = sensing volume

d = downstream 

Flow

Pd

Pu

PS

Valve Seat

Sense 

Orifice Flow

Pd

Poppet

Sense 

Volume
NASA/TM—2012-217271 6

p p s s p s,p s d xp m ⋅

x = F − K ⋅ x + F − f − f ⋅ 

Where xp̈ , xṗ , xp is the regulator poppet acceleration, velocity, and position respectively, mp is the poppet 

mass, Fs is the force acting on the sensing area due to the pressure in the sensing volume. Ks and Fs,p are 

the spring rate and spring preload, fs and fd are the static and dynamic friction coefficients. 

The static friction and dynamic friction coefficients were varied in the simulation model and were not 

shown to have a significant effect on the response as most of the damping is a result of the pneumatic 

process occurring in the regulator (Ref. 2).

3.2 Thruster Valve Model

The normally closed thruster valve uses upstream pressure in the sensing volume in conjunction with 

a spring to hold the poppet closed. The closing force on the poppet is opposed by main valve inlet and 

outlet pressures acting on the poppet. A small direct acting solenoid valve controls a path between the 

sensing volume and the valve outlet. Similarly a path between the valve inlet and the sensing volume is 

controlled by a fixed “sense” orifice. When the solenoid valve is initially opened the gas leaves the sense 

volume reducing the closing force sufficiently for the valve to open. When the solenoid valve is closed, 

the pressure in the sense volume increases closing the poppet. A schematic of the thruster valve can be 

seen in Figure 7. 

The EASY5 model of the thruster valve can be seen in Figure 8. Similar to the regulator the poppet 

was modeled by a single acting cylinder with a spring. In this case, the spring acts to extend piston. Gain 

factors representing the poppet area acted upon were applied to the inlet and outlet pressures with the 

resulting forces being summed and applied to the cylinder. 

The main valve was modeled using a variable area orifice where the effective flow area was 

determined using the poppet position and a look-up table. Flow into and out of the valve was modeled by 

orifices. The solenoid orifice area was provided by a time dependent lookup table to simulate operating 

sequences. The sensing volume and pressure areas were determined from drawings supplied by the 

thruster valve vender.

Figure 7.—Thruster valve schematic.

Nomenclature

A = area

P = pressure

Subscripts

u = upstream

s = sensing volume

d = downstream 

(Chamber Pressure)

Flow

Au

Ad

S

Pd

Pu

AS PS

Valve Seat

Sense 

Orifice

Pilot Solenoid 

Valve

Poppet

 
NASA/TM—2012-217271 7

Figure 8.—Thruster valve model. 

The upstream and downstream pressure forces were included in the force acting on the poppet. The 

poppet acceleration can then be calculated through the following equation after accounting for the static 

and dynamic friction as well as the inertia or poppet mass. 

p

d u s s p s,p s d p

p m

F F F K x F f f x

x   + − − ⋅ + − − ⋅ =

Where Fd, Fu, and Fs are the pressure forces acting on the downstream, upstream and sense pressure areas,

xp̈, xṗ , xp are the valve poppet acceleration, velocity, and position respectively, mp is the poppet mass, Ks

and Fs,p are the spring rate and spring preload fs and fd are the static and dynamic friction coefficients.

4.0 Simulation Results

Simulations were run in EASY5 with short segments of thruster firing profiles conducted during 

testing. The thruster valve was commanded open (2.0 sec) and closed (3.57 sec) in the simulation by 

adjusting the pilot valve orifice area via the time based look-up table. A comparison of the simulated 

regulator outlet pressure with the test data can be seen in Figure 9. The simulation is of a “long” thruster 

firing of 1.6 sec. The regulator outlet pressure experiences a large undershoot when the thruster valve is 

opened. Similar behavior is seen as the thruster valve is commanded closed, the downstream pressure 

overshoots to a pressure close to or above the relief valve set pressure. It should be noted that the relief 
NASA/TM—2012-217271 8

valve is not part of the model. The measured steady state pressure at the high flow rate is less than the 

steady state pressure in the simulation. One explanation for this difference is due to the flow force not 

being included in the model. As discussed previously in Section 3.0 the flow force can become significant 

and lower or raise the regulator steady state outlet pressure. 

A plot of the simulation thruster chamber pressure (Pd) is shown against the measured chamber 

pressure during tests in Figure 10. The chamber pressure increases after the valve is opened but then 

decreases tracking the regulator outlet pressure. The thruster pressure drops momentarily to 14.7 psia 

indicating that the valve closes. The valve is commanded closed at 3.57 sec and closes within 40 ms. The 

measured steady state pressure at the high flow rate is less than the simulated pressure because the model 

was tuned to approximate both the undershoot and overshoot sacrificing the steady state accuracy. 

A plot of the poppet positions of both the regulator and the thruster valve relative to each other is can 

be seen in Figure 11. Notice that the thruster valve opens and closes before the regulator poppet starts to 

move. This suggest that the response time of the regulator needs to be improved or the gas stored 

downstream of the regulator needs to be increased enough to allow the regulator extra time to react before 

the thruster valve closes. A plot of the thruster valve inlet, outlet and sense pressures can be seen in 

Figure 12. Note that at two points in time the flow reverses through the pilot valve, as determined by the 

downstream pressure being higher than the sense pressure. This occurs when the thruster valve first 

opens, at the 2.1 and 2.27 sec on the timeline. 

Figure 9.—Regulator outlet pressure, test versus simulation. 

200

300

400

500

600

700

800

900

1000

1100

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Regulator Outlet Pressure (PSIA)

Time, (seconds)

Measured Test Data

Simulation Results

Regulator overshoots after 

thruster valve is closed

Regulator outlet pressure droops

after thruster valve is opened
NASA/TM—2012-217271 9

Figure 10.—Thruster chamber pressure, test versus simulation. 

Figure 11.—Regulator and valve poppet position during thruster firings.

Figure 12.—Valve inlet, outlet, and sensing pressure during thruster firings.

0

100

200

300

400

500

600

700

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Thruster Pressure (PSIA)

Time, (seconds)

Measured Test Data

Simulation Results

Valve closes due to regulator

pressure droop

0

0.004

0.008

0.012

0.016

0.02

0

0.04

0.08

0.12

0.16

0.2

2 2.05 2.1 2.15 2.2 2.25 2.3 2.35 2.4

Regulator Position (inches)

Thruster Position (inches)

Time, (seconds)

Thruster Valve Position

Regulator Position

0

100

200

300

400

500

600

700

800

2 2.05 2.1 2.15 2.2 2.25 2.3 2.35 2.4

Pressure (PSIA)

Time, (seconds)

Thruster Valve Inlet(Pu)

Thruster Valve Outlet(Pd)

Thruster Valve Sensing Volume(Ps)
NASA/TM—2012-217271 10

5.0 Proposed Design Solutions

Two potential design solutions to reduce the regulator undershoot/overshoot and resulting thruster 

valve closing were investigated with the EASY5 system model. One was increasing the volume 

downstream of the regulator perhaps by adding an accumulator. Another approach was to decrease the 

flow resistance between the regulator sense volume and regulator outlet. These design solutions were 

easily investigated using the EASY5 model by increasing the node volume downstream of the regulator 

and increasing the diameter of the orifice used to model the flow resistance into the sense volume of the 

regulator.

The system volume downstream of the regulator was varied in the simulation to see what impact it had 

on the pressure undershoot/overshoot, and resulting thruster valve performance. The as tested volume of 

110 in3 was run along with volumes of 1000, 2000, and 5000 in3

. A plot showing the regulator outlet 

pressure and thruster valve outlet pressure for the various downstream volumes can be seen in Figures 13

and 14 respectively. As volume increased the regulator outlet undershoot and overshoot pressure also 

decreased resulting in increasing acceptable thruster pulses. The practical limitations into how much 

volume can be added to the system due to weight and volume constraints were not determined.

The effect of changing the regulator sense orifice was accomplished by varying the modeled orifice 

diameter. The sense orifice resistance was varied by changing the orifice diameter from the original 

0.0052 in. to values of 0.008, 0.01 and 0.02 in. Figures 15 and 16 show the regulator outlet pressure and 

thruster valve outlet pressure for the various orifice diameters used in the simulation. 

As the orifice diameter increased the regulator response time decreased. The faster response time and 

corresponding reduction in regulator pressure undershoot resulted in satisfactory thrust impulses. The 

increased volume approach effectively delayed the rate at which the pressure dropped allowing regulator 

to recover before the drop in pressure adversely impacted the thruster valve performance. The larger 

orifice did nothing to change the rate of pressure drop, but did allow the regulator to respond quickly 

enough to provide satisfactory thruster performance. 

Figure 13.—Regulator outlet pressure.

200

300

400

500

600

700

800

900

1000

1100

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Regulator Outlet Pressure (PSIA)

Time (seconds)

110 cubic inch

1000 cubic inch

2000 cubic inch

5000 cubic inch
NASA/TM—2012-217271 11

Figure 14.—Thruster valve outlet pressure.

Figure 15.—Regulator outlet pressure.

0

100

200

300

400

500

600

700

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Thruster Pressure (PSIA)

Time (seconds)

110 cubic inch

1000 cubic inch

2000 cubic inch

5000 cubic inch

200

300

400

500

600

700

800

900

1000

1100

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Regulator Outlet Pressure (PSIA)

Time (seconds)

0.0052 inch diameter

0.008 inch diameter

0.01 inch diameter

0.02 inch diameter
NASA/TM—2012-217271 12

Figure 16.—Thruster valve outlet pressure.

6.0 Conclusion

The value of system level developmental testing is illustrated by this investigation of the test results. 

Models generated using EASY5 provide insight to the component interaction and system level 

performance. The simulation of the cold gas thruster system compared well with the test data. The

fluid/mechanical model of the thruster valve contained enough fidelity to predict the momentarily closing 

of the valve as a result of the regulator pressure undershoot. The regulator pressure undershoot was 

determined to be the primary cause of the momentarily closing of the thruster valve. The simulation 

provided an ideal tool for investigating design modifications for improved performance. The simulation 

predicted that increasing the regulator downstream volume and/or decreasing the regulator sense flow 

restriction would reduce the regulator outlet pressure undershoot enough to prevent the momentarily 

closing of the thruster valve. 

References

1. Dustin, M.O., “Analog Computer Study of Design Parameter Effects on the Stability of a DirectActing Gas Pressure Regulator,” NASA TN D-6267, 1971.

2. Nabi, A., Wacholder, E., Dayan, J., “Dynamic Model for a Dome-Loaded Pressure Regulator,” Trans. 

ASME, 122, 2000, p.290.

3. Andersen B. W., “The Analysis and Design of Pneumatic System,” John Wiley and Sons, Inc, 1967. 

0

100

200

300

400

500

600

700

2 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4

Thruster Pressure (PSIA)

Time (seconds)

0.0052 inch diameter

0.008 inch diameter

0.01 inch diameter

0.02 inch diameter

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Simulation of a Cold Gas Thruster System and Test Data Correlation 

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Hauser, Daniel, M.; Quinn, Frank, D. 

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13. SUPPLEMENTARY NOTES

14. ABSTRACT

During developmental testing of the Ascent Abort 1 (AA-1) cold gas thruster system, unexpected behavior was detected. Upon further 

review the design as it existed may not have met the requirements. To determine the best approach for modifying the design, the system was 

modeled with a dynamic fluid analysis tool (EASY5). The system model consisted of the nitrogen storage tank, pressure regulator, thruster 

valve, nozzle, and the associated interconnecting line lengths. The regulator and thruster valves were modeled using a combination of the 

fluid and mechanical modules available in EASY5. The simulation results were then compared against actual system test data. The

simulation results exhibited behaviors similar to the test results, such as the pressure regulators response to thruster firings. Potential design 

solutions were investigated using the analytical model parameters, including increasing the volume downstream of the regulator and 

increasing the orifice area. Both were shown to improve the regulator response.

15. SUBJECT TERMS

Regulator; Valve; Simulation; Cold gas propulsion system 

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