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(12) Patent Application Publication (10) Pub. No.: US 2009/0133788 A1 Mungas Et Al

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(12) Patent Application Publication (10) Pub. No.: US 2009/0133788 A1 Mungas Et Al US 200901.33788A1 (19) United States (12) Patent Application Publication (10) Pub. No.: US 2009/0133788 A1 Mungas et al. (43) Pub. Date: May 28, 2009 (54) NITROUS OXIDE FUEL BLEND Related U.S. Application Data MONOPROPELLANTS (60) Provisional application No. 60/986,991, filed on Nov. 9, 2007. (75) Inventors: Gregory Mungas, Arcadia, CA Publication Classification (US); David J. Fisher, Denver, CO (US); Christopher Mungas, (51) Int. Cl. Plymouth, CA (US); Benjamin C06B 47/04 (2006.01) Carryer, Denver, CO (US) (52) U.S. Cl. .......................................................... 149/74 (57) ABSTRACT Correspondence Address: Compositions and methods herein provide monopropellants HENSLEY KIM & HOLZER, LLC comprising nitrous oxide mixed with organic fuels in particu 1660 LINCOLN STREET, SUITE 3000 lar proportions creating stable, storable, monopropellants DENVER, CO 80264 (US) which demonstrate high ISP performance. Due to physical properties of the nitrous molecule, fuel/nitrous blends dem (73) Assignee: Firestar Engineering, LLC, onstrate high degrees of miscibility as well as excellent Broomfield, CO (US) chemical stability. While the monopropellants are particu larly well Suited for use as propulsion propellants, they also lend themselves well to power generation in demanding situ (21) Appl. No.: 12/268,266 ations where some specific cycle creates useable work and for providing gas pressure and/or heat for inflating deployable (22) Filed: Nov. 10, 2008 materials. Isp (NOFB3X at 100 psia Chamber Pressure) vs OF (To=298 K) ----------arrarilla-rule 2001 F --vacuum Eq v 2001 Ed T-ch T-th EQUBRUM { % - 4% 9%. 8. sash;94 -ko's -8%xxxx was wi:8%. g. gzge 8% is es: 8 as: 8 Patent Application Publication May 28, 2009 Sheet 1 of 17 US 2009/0133788A1 isp (NOFB3X at 100 psia Chamber Pressure) vs OF (To=298 K) --vacuum F -e-2001 F --vacuum Eq.- 2001 Ed T-ch T-th ------- 3500 350 d ... 3.3.xv, www. - 3OOO " EQUBRUM -- 2500 a resis is uses - or- so so, e - e, , is a se - 330 - Ex entally Observed 2001. 2OOO Yeero -ierit." : intois's - vacuum:- - - g"." Equivalent spis r. %. 320 - are KX8: 8x8, 9%y tw: , p:% x8% arz Wee Rw8 was 888: 888 8 888. 8: 48 %. Mix %. 8%8. &. 1500 FROZEN AT THROAT FIGURE 1 Patent Application Publication US 2009/O133788A1 Patent Application Publication May 28, 2009 Sheet 3 of 17 US 2009/0133788A1 METRIC N.H. NTOIMMH NOFB34, NOFB37 Propulsion Type Monopropellant Bipropellant Monopropellant Specific impulse (sP) 230 - 240 S 288 - 326 s >300 s - 345 s) - --- ----- --- -- Minimum impulse bit - 15OS 1) ISP >{ 300s) -------- - - - - - - - - - - - ----------------------------- - - - performance SSP 2) 50-600x less impulse per valve opening -- ----- withlower density propellant ----- Specific Energy Density s f (Propellant) 390 Whi/kg 2049 Whi/kg 1360 - 1520 Wh/kg Pressurized Total 56-0.65 --- ------- internal Tank Volume (including He { -0.75 p; (C) Specific Gravity pressurant) -------- .0 (G) -75 Density impulse (wsp) 1.52 NSCC {2,4} N'Sicc 1.7 Nsico (0) 31°C - 3.2} N's/CC (O) -75°C Adiabatic Flame Temp. ; - 1200°K -27OOK 3OOO-345O K Storage Pressure " . 300-400 psia (separate pressurant) 100-1000 psia (self-pressurizing) 1) -0.015%-1.6% (G1-100 psia unburned Unusable Tanked respectively 1%-5% ------------------------ - ------------------------- Propellant Residuals O J AO 2) Last -5-20% of Propellant Load measureable wif gas pressure transducer Freezing Point 2 oC MMH: - 11°C <-77°C (insensitive to cycling) Auto Ignition of...An 400°C inside 316 Stainless Steel tube) Temperature Minimum Surface) -- Material incompatibilities not fully tested --- Auto ignition 270°C (on 650°C (after detonations on 316). May likely Temperature Maximum glass) be higher on inert surfaces. impact Sensitivity Unable to cause ignition with mechanical impact (5.5 m drop test to date) SS316 causes a minor catalytic reduction in Material Incompatibility Reacts violently with many metals, auto ignition temp. Entire trade space not fully metal oxides and porous matcrials explored yet. Exhaust Products - for Astrobiology NH3 is issue N2, CO, H2O, H., CO2 Investigations -------...W. Human DH limit 50 ppm 20 ppm (Immediately dangerous (Low Vapor (LOW Vapor Asphyxiant. Not OSHA-regulated. to life and health) Pressure) Pressure) Rapidly volatilizes into air Corrosive, Burning sensation. High doses may cause asphyxiation, low Cough, Headache. Nausea. doses may cause narcotic effects i.e. inhalation Shortness of breath. Sore throat. dizziness, headache, nausea and loss of --- Convulsions. COOrdination Ski Corrosive. MAYBE ABSORBED Rapid propellant discharge can cause Cold - | Redness. Skin burns. Pain. --- burns. Eves Corrosive. Redness. Pain. Severe High pressure discharge to eyes may cause --- cy deep burns. " | damage. - - - - - - - ingestion Cogy gettps Engestion is not considered a likely route of exposure given high volatility - F GRE 3 Patent Application Publication May 28, 2009 Sheet 5 of 17 US 2009/O133788A1 NOFB37 VARATION NULLAGE GAS PHASE FTIR SPECTRA FROM -77C TO ROOMTEMPERATURE AND 114 TANK DRAWDOWN 4800 4700 4600 4500 4400 4300 WAVENUMBERS (cm-1) FIG.5A Patent Application Publication May 28, 2009 Sheet 6 of 17 US 2009/O133788A1 NOFB3x DRAWDOWN OVERVIEW EQUILIBRIUMISPI (POINTS REPRESENTAVERAGES OF TRIALS) FROZEN THROAT ISP 327292 KEYNUMBERSALONGSIDE POINTS REPRESENT 2- - - - 331/295 8.5 1.) INITIALLIQUID PHASE OF MEASUREMENT 802) INITIALULLAGEVOLUMEGASPHASE OF MEASUREMENT - 333,298 3) POST-DRAWDOWNGASPHASE OF MEASUREMENT 2ND ORDERBEST FITCALIBRATIONCURVE 334,301 70 (BASED ON2POINTSPER OF FOR NOFB 335/303 33,34,35,3637,3839) R2 = 9833. 6.5 - - - - - - - - - - - - - - -/42- - - - - - - 335.306 335/308 5 334/310 333/312 331/314 - - O NOFB35 - - - - - - - - 327/315 A NOFB37 - - - - - - - - - - - - - - - - - - - - - - 324/314 3.0 323,309 0.040 0.042 0.044 0.046 0.048 0.050 0.052 0.054 0.056 0.058 0.060 ABSORBANCE PEAKG 4430.50 cm-1 FIG5B Patent Application Publication May 28, 2009 Sheet 7 of 17 US 2009/O133788A1 Cf VSAelAt FOR NOFB3 BLEND OF = 5 -O-EQUILIBRIUM--FROZENAT COMBUSTOR-a-FROZEN AT THROAT 1H:e. Patent Application Publication May 28, 2009 Sheet 8 of 17 US 2009/O133788A1 NOFB34THERMALDECOMP FLOW - BLOCK TEMP - GASTEMP - SYSTEMPRESSURE 560 AUTOIGNITION 555 370 C 550 545 540 535 530 525 520 O 2 4 6 8 10 12 14 TIME(S) FIG.7A Patent Application Publication May 28, 2009 Sheet 9 of 17 US 2009/O133788A1 NOFB35 SS316 CAPILLARYTUBETHERMAL DECOMPTESTS 0 NODECOMPOSITION THERMALDECOMPOSITION 500 450 G 400 350 s 300 250 200 o 150 NOTE: HYDRAZINE THERMALDETONATION 35 100. LIMIT IS 270°C ON ACID-CLEANED 50 QUARTZAND 24°C ONOXIDZED IRON O O 100 200 300 400 500 600 GAS PRESSURE (psia) FG.7B Patent Application Publication May 28, 2009 Sheet 10 of 17 US 2009/0133788A1 NOFB34 HEAT OF WAPORIZATION VS. TEMP -NOFB34 - N2O - - - - - - it - ENTHALPY OF RAISING 20% OF FUELTO 300°C (BIPROP. REGEN. COOLING) -75 -50 -25 O 25 50 TEMPERATURE (C) FIG.8A Patent Application Publication May 28, 2009 Sheet 11 of 17 US 2009/0133788A1 NOFB34 TEMPERATURE (T), DENSITY (p), AND QUALITY(x) VS. THROTTLED PRESSURE 1.0 25 0.9 15 S, 0.70.8 Po,2. (TnCo-260) = 26OK is5 a 0.6 -15 Ais 05 25 5. 0.4 -35 5 0.3 -45 x(t-oo- -55 0.0' ' 2 (0.-200a, 2 (TOF R -75-65 800 700 600 500 400 300 200 100 O THROTTLED PRESSURE, P2 (psia) FIG.8B Patent Application Publication May 28, 2009 Sheet 12 of 17 US 2009/0133788A1 N2O Max Gap vs. Pressure at Paschen Curve Minimum (418 W) E. eart; 0.0010 (f) f ( ). N s ( ----- 0.0001 -------- -...------------- 1-------- --------------, O 200 400 600 800 O Pressure (psia) FGRE 9 Patent Application Publication May 28, 2009 Sheet 13 of 17 US 2009/0133788A1 NCFE Filter Vedia Quenching Distance as a Function of Loaded NOFB line Density aircra-a-a-iwar---ir------...-kect----e-r--------- reluro i: -, -334. Fai CE 1 a NOF835 Fail : - - - - - r - . 'worn iv. 'wr m r - - - C se t is sak s t s See . e - k : w . i w ok w . w A w.w is 8 br w - - w is 4 r a w w w A w w a y i t 5 N o 2. o E. No.2 : role------------------- -------- -o-, -vi (5 O O.5 C2 NCFB loaded line tensity (gicc) FBG RE 10 Patent Application Publication May 28, 2009 Sheet 14 of 17 US 2009/O133788A1 (MW88-)HEGWWHO1SnHHINZZEdÅ1010\dd Patent Application Publication May 28, 2009 Sheet 15 of 17 US 2009/0133788A1 8/13/06 ENGINE RUN 1 O 0.5 1 15 2 2.5 3 3.5 TIME (S) FIG. 12 Patent Application Publication May 28, 2009 Sheet 16 of 17 US 2009/0133788A1 DRYMASS (MINUSTANKS) TO TOTALMASS VS. AV 0.6 320S NOFBOBS 7%. TANKAGE O 5 300S NOFBOBS 0.3 13%. TANKAGE ES 0.2 N2H4 0.1 7%. TANKAGE S 0.0 O O 1000 2000 3000 4000 5000 6000 7000 8000 AV (m/s) FIG.13 Patent Application Publication May 28, 2009 Sheet 17 of 17 US 2009/0133788A1 Table 5. Summary of NOFB deployable Wing Spar Specs are - in Tubular deployable rigidizable Cross |- section centered on 4 chord. m Max Wehicle Weight 1100 kg 10,791 N Combined Tapered Wing Area 40 m --- - ----- Root chord 2.4 m --------------------- - - Tip chord 1.0 m (0.4x root) ------------- individual wingspan 12m Max composite tensie stress 13.3 ksi mulu Spar internal gas pressure 100 psia -- run. Deployed Spar Density 12 g/cc Total Spar Plass (2 Wings) 47 kg NOFB thermal gas mass for High energy density. kg deploying both wings | Low Energy Density, 3 kg --- Figure 4 US 2009/O 133788 A1 May 28, 2009 NITROUS OXDE FUEL BLEND energy. However, the hot (>1500° C.), highly oxidizing reac MONOPROPELLANTS tion products make catalyst bed and reaction chamber design challenging. CROSS-REFERENCE TO RELATED 0006.
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