2006-2007 - Kennedy Space Center Technology Transfer Office

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Mitigating Problems in Measuring Hypergolic FuelsPropellant Loading/Servicing/StorageTo monitor hydrazine concentrations accurately and safely, hydrazine is convertedinto a stable derivative that will be monitored and correlated to the actual hydrazineconcentration. The hydrazine’s reactivity is harnessed to produce a chemical reactionthat will form a stable gas-phase derivative which will not react or decompose before itreaches the detector.Hydrazine, monomethylhydrazine, and unsymmetrical dimethylhydrazine belong to a class ofcompounds known as hypergolic fuels. These fuels self-ignite upon mixing with hypergolic oxidizer(dinitrogen tetroxide), without need of a spark or other ignition source. The resulting reactionproduces thrust with exceptionally high energy, making these compounds particularly useful asrocket propellants.Hydrazines are also highly toxic and corrosive. The combined properties of reactivity, corrosivity,and toxicity present the potential for a leak, a disastrous situation in a hypergol-loaded system.Consequently, leak detection is of the utmost importance in protecting equipment and personnel.Hydrazine vapor quantification presents many challenges in addition to the safety concerns.The reactivity of these compounds causes thermal and catalytic decomposition, which results insignificant losses. Further complications arise from the “sticky” nature of hydrazine. Moleculesadsorb irreversibly to virtually any surface they make contact with before detection, which resultsin instrument drift. These properties make it difficult to accurately quantify hydrazines. Currentanalytical methods seek to minimize these interactions.After an extensive literature search to determine appropriate chemical reactions, a method wasdevised to quantify hydrazines, without the limitations of monitoring hydrazines. In theseexperiments, we used the recently developed Desorption Electrospray Ionization (DESI) to ionizeat ambient pressure a stabilized hydrazine derivative formed on a surface. To form the stabilizedderivative, we exposed glass wool impregnated with a complexing reagent to hydrazine vapors atvarying concentrations. We then used DESI to analyze the surface derivative, providing an indirectavenue for quantifying hydrazines. This approach harnesses, rather than limits, the reactivity of thesehydrazines for more accurate quantification.Our work successfully identified and characterized a gas-phase hydrazine reaction that formed astabilized gas-phase hydrazine derivative which could be detected in place of the hydrazine. The workincluded using DESI to demonstrate the concept. The figure shows the results of the experiments.Work continues in investigating and characterizing the current chemical reaction and in examiningdifferent chemical reactions and monitoring techniques. These tasks will be geared toward improvingdetection limits and producing a working prototype.Contact: Dr. Timothy P. Griffin , NASA-KSC, (321) 867-6755Participating Organization: ASRC Aerospace (Cristina M. Berger)76 Fluid System Technologies
140000120000100000Signal8000060000400002000000 200 400 600 800 1000 1200 1400 1600 1800Concentration (ppb)DESI response to hydrazine derivative.KSC Technology Development and Application 2006-200777
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ForewordSuccessful technology devel
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ContentsSpaceport Structures and Ma
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Contents (continued)Process and Hum
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IntroductionJohn F. Kennedy Space C
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Constellation SystemsSurfaceSystems
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Spaceport Structures and MaterialsK
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20181614∆ E1210Modified Sensor Be
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Initial results of the EDEM model o
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Contacts: Dr. Carlos I. Calle ,NASA
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Close examination of the corrosions
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Adhesion at Failure (psi)2500200015
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Figure 1. After 500 hours of salt f
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Contacts: Dr. Paul E. Hintze , NASA
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Figure 2. Repairs to various types
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on top of the cuvette contains the
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Figure 2. A corrugated NiTi sheet e
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The PLTD can be used to (1) calibra
Page 39 and 40: SEM images of neat MWNT fibers: (a)
Page 41 and 42: Contacts: Trent M. Smith
Page 43 and 44: Figure 1. An isometric cutaway view
Page 45 and 46: Figure 2. Quartz sand flowing in th
Page 47 and 48: Figure 2. Top images show how the e
Page 49 and 50: Sand volume fraction contour at t =
Page 51 and 52: Integrated LWRD/RVC engineering bre
Page 53 and 54: Mean relative percentage change in
Page 55 and 56: We compared the model’s predictio
Page 57 and 58: Figure 2. Three-dimensional simulat
Page 59 and 60: Figure 3. Camera calibration model.
Page 61 and 62: The sketch in Figure 2 shows alaunc
Page 63: Figure 2. Signal generator (right)
Page 66 and 67: Hail Size Distribution MappingA 3-D
Page 68 and 69: Launch Pad 39 Hail Monitor Array Sy
Page 70 and 71: Autonomous Flight Safety System - P
Page 72 and 73: The Photogrammetry CubeSpaceport/Ra
Page 74 and 75: Bird Vision SystemThe Bird Vision s
Page 76 and 77: Automating Range Surveillance Throu
Page 78 and 79: Next-Generation Telemetry Workstati
Page 80 and 81: GPS Metric Tracking UnitAs Global P
Page 82 and 83: Space-Based RangeSpace-Based Range
Page 85 and 86: Fluid System TechnologiesKSC Techno
Page 87 and 88: 0.900.850.80Discharge Coefficient,
Page 89: Composite seals for performance eva
Page 93 and 94: Contacts: Dr. Barry J. Meneghelli ,
Page 95 and 96: 60555045Comparative k-value (mW/m-K
Page 97 and 98: a compatible spacecraft model where
Page 99 and 100: In an ongoing effort for improvemen
Page 101: Low-gravity probe prototype test.th
Page 104 and 105: Countermeasure for Radiation Protec
Page 106 and 107: Focused Metabolite Profiling for Di
Page 109 and 110: Process and Human FactorsEngineerin
Page 111 and 112: DON uses game technology to enable
Page 113 and 114: Type of mobile crane that impacted
Page 115 and 116: SALT proof-of-concept communication
Page 117 and 118: SSLM CAD model.Our design offers th
Page 119 and 120: Variables that can be integrated by
Page 121: Exploration Supply Chain Simulation
Page 124 and 125: Nanosensors for Evaluating Hazardou
Page 126 and 127: Sixty-four-Channel Inline Cable Tes
Page 128 and 129: Wireless Inclinometer Calibration S
Page 130 and 131: Generating Safety-Critical PLC Code
Page 132 and 133: Spacecraft Electrostatic Radiation
Page 134 and 135: Ion Beam Propulsion StudySpacecraft
Page 136 and 137: RT-MATRIX: Measuring Total Organic
Page 139 and 140: Appendix AKSC High-Priority Technol
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Risk Assessment ToolMission Data Fe
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Appendix BInnovative Partnership Pr
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system for the Government, using th
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tracking objects after launch, and
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2006-2007 - Kennedy Space Center Technology Transfer Office

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