880:
905:
power function. Initially, methods for fitting the power function were often left ambiguous in publications due to variation in the possible calculations for average mass flux, making it difficult to compare findings. A now commonly-referenced study by
Karabeyoglu indicates that the easiest measurement, the port diameter average, also provides the most accurate results.
904:
Because of the lack of accurate prediction methods, each system should generally be tested in full configuration to accurately determine the regression rate before flight. Typically, data points for several identical grains tested under different flux conditions are fitted to the space-time averaged
887:
In fact, the process is even slightly more complicated because corners protruding into the combustion chamber will regress more quickly than their circular counterparts, since they are exposed to heat on both sides. To model the problem, Bath developed a technique of iteratively blurring pixels and
810:
Using non-circular port cross sections increases the area exposed to the oxidizer to be gasified, especially at the start of the burn. However, as the fuel continues to regress it will begin to round out the shape because regression generally occurs normal to the fuel’s surface, and corners tend to
754:
Many alternative equations for regression rate have been derived, usually constructed by reconsidering the assumptions made by
Marxman but using the same diffusion-limited calculation approach. A model published by Karabeyoglu, for example, provides a more accurate approach by considering variation
39:
or complex port designs that result in excess mass. Regression rate has also proven quite difficult to predict, with advanced models still providing significant error when applied at various scales and with differing fuels. Recent research has centered around the development of more accurate models
48:
In contrast to solid rocket motors, hybrids exhibit significant dependence on the size of the port and low dependence on chamber pressure under normal conditions. Because they are dominated by thermodynamic forces, models typically emerge via a heat transfer calculation. Marxman provided the first
779:
The simplest technique for increasing the regression rate is to use a different fuel. Solids with lower molecular masses tend to have lower viscosities, a quality which generally correlates with a decrease in the required energy for gasification. Taken to the extreme, a new phenomenon actually
787:
and
Orbital Technologies Corporation (ORBITEC) tested several cryogenic fuels in an effort to increase specific impulse. Using solidified pentane, they found regression rates vastly increased over traditional hybrid fuels. Several tests with paraffin also foreshadowed modern liquifying rocket
891:
Unfortunately, most models still require an empirical factor that depends on variations in fuel and oxidizer flow paths for different port geometries. In the case of the image blurring model, predictions of regression are also dependent on the settings used in the image processing program.
430:
814:
Some of the first attempts at complex geometries were wagon wheel designs developed by the United
Technology Center. Though they massively increase fuel flow, wagon wheels require that a significant portion of fuel is left behind, or the structure could break apart.
780:
emerges, where a melt layer at the surface of the fuel allows droplets to be entrained as oxidizer flows past. At the flux levels commonly seen in hybrid rocketry, this entrainment actually accounts for the largest portion of regression (dominating vaporization).
34:
being burned is important for the effectiveness of combustion in the engine, the regression rate plays a fundamental role in the design and firing of a hybrid engine. Unfortunately, hybrid fuel grains tend to have extremely slow regression, requiring very long
826:
concluded that regression rates generally increased by at least a factor of two, up to even a factor of four. In general, helical regression rate is modeled by several multiplicative adjustments to the skin friction coefficient and to the blowing coefficient.
888:
removing those that fall below a certain threshold of brightness. Using the image processing to generate a table of surface area outputs for a given volume, it can easily be implemented into a model for regression of the fuel grain over time.
440:
by effectively combining most of the terms into one coefficient that is assumed constant throughout the burn. It was typically simplified into a basic equation by considering the average regression over time for a test, fitting coefficients
839:
of fuel is usually given by the regression rate multiplied by the burn area. Depending on the complexity of the grain geometry, it can also be quite difficult to calculate. At its simplest form, a tube-shaped fuel grain has a burn area of
436:, the strong dependence on flux was a key finding. Unfortunately, many components of the equation are extremely difficult to determine, so most engineers focused on developing models based on testing, fitting the regression rate to a
895:
Models of burn area based on 2D cross sections lose another component of accuracy because they assume regression in the radial direction. For a helical grain, for example, the burn area predicted by Bath's model would be incorrect.
287:
762:
Similar concepts can be seen in an extension by
Whitmore, where the Prandtl number is approximated as 0.8 and the skin friction coefficient is recalculated to consider blowing and the flow development along the grain length.
822:
designs have been used to create a centripetal component of flow, reducing blowing and providing greater friction between the oxidizer and fuel in order to increase convection. Analysis at the
799:
and leaving the engine. Indeed, paraffin has a tendency to even slough off large fragments, greatly reduces combustion efficiency and potentially contributing to combustion instability.
556:
835:
The burn area refers to the surface exposed to the heat of the combustion chamber, and it is just as pivotal to the regression of the rocket as the regression rate itself, since the
752:
23:
is converted from a solid to a gas that is combusted. It encompasses the regression rate, the distance that the fuel surface recedes over a given time, as well as the burn area, the
228:
807:
Although it is much harder to predict, complex grain geometries offer another technique for increasing regression rate and burn area in order to greatly increase fuel flow.
1322:
T. R. Brown, M. C. Lydon, Testing of
Paraffin-Based Hybrid Rocket Fuel using Hydrogen Peroxide Oxidizer, AIAA Region Student Conference, Wichita, KS, USA, April 6–8, 2005
188:
122:
870:
251:
611:
678:
582:
282:
876:
or other geometric software to determine the surface area, particularly as the surface area regresses along the normals, often creating highly irregular geometry.
146:
1410:
Bath, Andrew, "Performance
Characterization of Complex Fuel Port Geometries for Hybrid Rocket Fuel Grains" (2012). All Graduate Theses and Dissertations. 1381.
958:
937:
698:
651:
631:
499:
479:
459:
95:
75:
653:. By averaging the regression out over the length of the fuel grain, the commonly used space-time average regression equation is created (also typically using
1495:
An
Investigation of Injectors for Use with High Vapor Pressure Propellants with Applications to Hybrid Rockets. BS Waxman. Stanford University, 2014.
1642:
1600:
1198:
425:{\displaystyle {\dot {r}}={\frac {0.036G}{\rho _{f}}}{({\frac {Gx}{\mu }})}^{-0.2}{({\frac {u_{e}}{u_{c}}}{\frac {\Delta h}{h_{v}}})}^{0.23}}
883:
Bath's regression algorithm begins with a cross section of the port, blurs it, then converts back to black and white based on a threshold.
49:
attempt at an a priori model of hybrid regression, basing the rate on a heat transfer equilibrium calculation and assuming unity for the
1299:
1684:
558:
Where G is the mass flux of propellant and x is the distance along the fuel grain. Though
Marxman's initial math indicates that
504:
703:
784:
879:
795:. Because of the large particle size, the entrained droplets may not be fully consumed before flowing out of the
254:
20:
1689:
1219:"Correlation of Hybrid Rocket Propellant Regression Measurements with Enthalpy-Balance Model Predictions"
873:
792:
1156:
Sutton, George P, and Oscar
Biblarz. Rocket Propulsion Elements. New York: John Wiley & Sons, 2001.
1333:
193:
1388:
1230:
836:
796:
1540:"Radiation Heating Effects on Oxidizer-to-Fuel Ratio of Additively Manufactured Hybrid Rocket Fuels"
1384:
Experimental Review of Methods for Performance Enhancement of Paraffin Fueled Hybrid Rocket Motors
1561:
1363:
823:
151:
36:
100:
1638:
1596:
1475:
1355:
1246:
1194:
843:
233:
31:
1630:
1621:
Doran, Eric; Dyer, Jonny; Lohner, Kevin; Dunn, Zach; Cantwell, Brian; Zilliac, Greg (2007),
1588:
1551:
1518:
1467:
1456:"Development of Scalable Space-Time Averaged Regression Rate Expressions for Hybrid Rockets"
1436:
1345:
1280:
1238:
1186:
1139:
1128:"Development of Scalable Space-Time Averaged Regression Rate Expressions for Hybrid Rockets"
811:
regress faster. Generally, this will cause the O/F ratio to shift away from stoichiometric.
788:
technology, with the Peregrine rocket among others leading the way for further development.
587:
872:
added to the area on both ends. However, a star-shaped fuel grain could require the use of
656:
561:
260:
1507:"Nytrox as "Drop-in" Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems"
756:
131:
1423:
Whitmore, Stephen A.; Walker, Sean D.; Merkley, Daniel P.; Sobbi, Mansour (2015-11-01).
1392:
1382:
1234:
943:
922:
791:
The alternative regression method does supply some other issues, mainly a reduction in
683:
636:
616:
484:
464:
444:
437:
80:
60:
50:
1678:
1565:
1506:
1367:
1332:
Piscitelli, F.; Saccone, G.; Gianvito, A.; Cosentino, G.; Mazzola, L. (2018-09-01).
1622:
1580:
54:
24:
1178:
1334:"Characterization and manufacturing of a paraffin wax as fuel for hybrid rockets"
432:
Though the model showed large errors when used to predict regression rate for an
1581:"Analytical and Experimental Comparisons of HTPB and ABS as Hybrid Rocket Fuels"
190:
for the velocity ratio between gas in the main stream and gas at the flame, and
1350:
1185:. Sacramento, California: American Institute of Aeronautics and Astronautics.
783:
The concept was originally discovered during a brief research period in which
766:
Both improved formulas appear to show a better relationship with tested data.
230:
for the ratio considering the enthalpy difference from flame to fuel surface (
1523:
1479:
1425:"High Regression Rate Hybrid Rocket Fuel Grains with Helical Port Structures"
1359:
1250:
1424:
1455:
1218:
1127:
1411:
1268:
1623:"Nitrous Oxide Hybrid Rocket Motor Fuel Regression Rate Characterization"
1634:
1592:
1190:
1300:"From Pedicures to the Peregrine Rocket, Paraffin Wax Proves Its Worth"
125:
1126:
Karabeyoglu, M. Arif; Cantwell, Brian J.; Zilliac, Greg (2007-07-01).
759:, and moving the flame sheet location to the stoichiometric location.
40:
coupled with research into techniques for increasing regression rate.
1556:
1454:
Karabeyoglu, M. Arif; Cantwell, Brian J.; Zilliac, Greg (July 2007).
1440:
1269:"Combustion of Liquefying Hybrid Propellants: Part 1, General Theory"
1471:
1242:
1143:
1539:
1284:
878:
819:
433:
1627:
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
1585:
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
1183:
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
1579:
Whitmore, Stephen; Peterson, Zachary; Eilers, Shannon (2011),
1267:
Karabeyoglu, M. A.; Altman, D.; Cantwell, B. J. (2002-05-01).
755:
in the Prandtl number, accounting for entrance effects in the
1665:
Advanced Hybrid Rocket Motor Propulsion Unit For CubeSats
1217:
Eilers, Shannon D.; Whitmore, Stephen A. (2008-09-01).
1629:, American Institute of Aeronautics and Astronautics,
1587:, American Institute of Aeronautics and Astronautics,
1179:"Hybrid Rocket Fuel Regression Rate Data and Modeling"
946:
925:
846:
706:
686:
680:, the flux of oxidizer, for the flux term instead of
659:
639:
619:
590:
564:
507:
487:
467:
447:
290:
263:
236:
196:
154:
134:
103:
83:
63:
633:
and usually shows less dependence than predicted on
57:. He eventually developed the below equation, using
19:refers to the process by which the fuel grain of a
952:
931:
864:
746:
692:
672:
645:
625:
605:
576:
550:
493:
473:
453:
424:
276:
245:
222:
182:
140:
116:
89:
69:
1177:Zilliac, Gregory; Karabeyoglu, M. (2006-07-09).
8:
909:Space-Time Averaged Regression Coefficients
613:, data typically ranges from 0.5 to 0.8 for
148:for viscosity of the main-stream gas flow,
907:
1555:
1522:
1349:
945:
924:
845:
738:
731:
726:
708:
707:
705:
685:
664:
658:
638:
618:
589:
563:
542:
532:
527:
509:
508:
506:
486:
466:
446:
416:
404:
390:
382:
372:
366:
362:
352:
333:
329:
320:
306:
292:
291:
289:
268:
262:
235:
213:
208:
203:
195:
174:
165:
159:
153:
133:
108:
102:
82:
62:
551:{\displaystyle {\dot {r}}=a{G}^{n}x^{m}}
27:that is being eroded at a given moment.
1412:https://digitalcommons.usu.edu/etd/1381
1118:
747:{\displaystyle {\dot {r}}=a{G_{o}}^{n}}
1538:Whitmore, S. A.; Merkley, S. (2019).
1491:
1489:
1406:
1404:
1402:
7:
1262:
1260:
1212:
1210:
1172:
1170:
1168:
1166:
1164:
1162:
77:for instantaneous local mass flux,
393:
237:
197:
14:
1223:Journal of Spacecraft and Rockets
253:) in comparison to the effective
1667:. Pennsylvania State University.
1505:Whitmore, Stephen (2020-04-12).
223:{\displaystyle \Delta h/{h_{v}}}
97:as distance along the port, rho
1544:Journal of Propulsion and Power
1460:Journal of Propulsion and Power
1429:Journal of Propulsion and Power
1381:Clay, Reed McRae (2019-01-01).
1273:Journal of Propulsion and Power
1132:Journal of Propulsion and Power
700:for flux of oxidizer and fuel).
412:
363:
348:
330:
1:
1338:Propulsion and Power Research
1298:Tabor, Abigail (2017-04-18).
17:Hybrid rocket fuel regression
501:based on regression testing.
183:{\displaystyle u_{e}/u_{c}}
1706:
1663:McKnight, Brendan (2015).
1351:10.1016/j.jppr.2018.07.007
1685:Hybrid-propellant rockets
117:{\displaystyle \rho _{f}}
1524:10.3390/aerospace7040043
865:{\displaystyle \pi *D*l}
246:{\displaystyle \Delta h}
30:Because the quantity of
21:hybrid-propellant rocket
770:Regression enhancements
1387:(Thesis). p. 37.
954:
933:
884:
866:
748:
694:
674:
647:
627:
607:
606:{\displaystyle m=-0.2}
578:
552:
495:
475:
455:
426:
278:
247:
224:
184:
142:
118:
91:
71:
955:
934:
882:
867:
793:combustion efficiency
749:
695:
675:
673:{\displaystyle G_{o}}
648:
628:
608:
579:
577:{\displaystyle n=0.8}
553:
496:
476:
456:
427:
279:
277:{\displaystyle h_{v}}
248:
225:
185:
143:
119:
92:
72:
944:
923:
844:
704:
684:
657:
637:
617:
588:
562:
505:
485:
465:
445:
288:
261:
255:heat of vaporization
234:
194:
152:
141:{\displaystyle \mu }
132:
101:
81:
61:
1635:10.2514/6.2007-5352
1593:10.2514/6.2011-5909
1393:2019MsT.........37C
1235:2008JSpRo..45.1010E
1191:10.2514/6.2006-4504
910:
37:combustion chambers
950:
929:
908:
900:Regression testing
885:
862:
824:University of Utah
744:
690:
670:
643:
623:
603:
574:
548:
491:
471:
451:
422:
274:
243:
220:
180:
138:
114:
87:
67:
1644:978-1-62410-011-6
1602:978-1-60086-949-5
1200:978-1-62410-038-3
1110:
1109:
953:{\displaystyle n}
932:{\displaystyle a}
716:
693:{\displaystyle G}
646:{\displaystyle x}
626:{\displaystyle n}
517:
494:{\displaystyle m}
474:{\displaystyle n}
454:{\displaystyle a}
410:
388:
346:
326:
300:
90:{\displaystyle x}
70:{\displaystyle G}
1697:
1669:
1668:
1660:
1654:
1653:
1652:
1651:
1618:
1612:
1611:
1610:
1609:
1576:
1570:
1569:
1559:
1557:10.2514/1.B37037
1535:
1529:
1528:
1526:
1502:
1496:
1493:
1484:
1483:
1451:
1445:
1444:
1441:10.2514/1.B35615
1435:(6): 1727–1738.
1420:
1414:
1408:
1397:
1396:
1378:
1372:
1371:
1353:
1329:
1323:
1320:
1314:
1313:
1311:
1310:
1295:
1289:
1288:
1264:
1255:
1254:
1229:(5): 1010–1020.
1214:
1205:
1204:
1174:
1157:
1154:
1148:
1147:
1123:
959:
957:
956:
951:
938:
936:
935:
930:
911:
871:
869:
868:
863:
837:volume flow rate
803:Complex geometry
775:Liquifying fuels
753:
751:
750:
745:
743:
742:
737:
736:
735:
718:
717:
709:
699:
697:
696:
691:
679:
677:
676:
671:
669:
668:
652:
650:
649:
644:
632:
630:
629:
624:
612:
610:
609:
604:
583:
581:
580:
575:
557:
555:
554:
549:
547:
546:
537:
536:
531:
519:
518:
510:
500:
498:
497:
492:
480:
478:
477:
472:
460:
458:
457:
452:
431:
429:
428:
423:
421:
420:
415:
411:
409:
408:
399:
391:
389:
387:
386:
377:
376:
367:
360:
359:
351:
347:
342:
334:
327:
325:
324:
315:
307:
302:
301:
293:
283:
281:
280:
275:
273:
272:
252:
250:
249:
244:
229:
227:
226:
221:
219:
218:
217:
207:
189:
187:
186:
181:
179:
178:
169:
164:
163:
147:
145:
144:
139:
123:
121:
120:
115:
113:
112:
96:
94:
93:
88:
76:
74:
73:
68:
1705:
1704:
1700:
1699:
1698:
1696:
1695:
1694:
1675:
1674:
1673:
1672:
1662:
1661:
1657:
1649:
1647:
1645:
1620:
1619:
1615:
1607:
1605:
1603:
1578:
1577:
1573:
1537:
1536:
1532:
1504:
1503:
1499:
1494:
1487:
1472:10.2514/1.19226
1453:
1452:
1448:
1422:
1421:
1417:
1409:
1400:
1380:
1379:
1375:
1331:
1330:
1326:
1321:
1317:
1308:
1306:
1297:
1296:
1292:
1266:
1265:
1258:
1243:10.2514/1.33804
1216:
1215:
1208:
1201:
1176:
1175:
1160:
1155:
1151:
1144:10.2514/1.19226
1125:
1124:
1120:
1115:
942:
941:
921:
920:
902:
842:
841:
833:
818:More recently,
805:
777:
772:
757:Reynolds number
727:
725:
702:
701:
682:
681:
660:
655:
654:
635:
634:
615:
614:
586:
585:
560:
559:
538:
526:
503:
502:
483:
482:
463:
462:
443:
442:
400:
392:
378:
368:
361:
335:
328:
316:
308:
286:
285:
284:) for the fuel.
264:
259:
258:
232:
231:
209:
192:
191:
170:
155:
150:
149:
130:
129:
104:
99:
98:
79:
78:
59:
58:
46:
44:Regression rate
12:
11:
5:
1703:
1701:
1693:
1692:
1690:Rocket engines
1687:
1677:
1676:
1671:
1670:
1655:
1643:
1613:
1601:
1571:
1550:(4): 863–878.
1530:
1497:
1485:
1466:(4): 737–747.
1446:
1415:
1398:
1373:
1344:(3): 218–230.
1324:
1315:
1290:
1285:10.2514/2.5975
1279:(3): 610–620.
1256:
1206:
1199:
1158:
1149:
1138:(4): 737–747.
1117:
1116:
1114:
1111:
1108:
1107:
1105:
1102:
1099:
1096:
1092:
1091:
1089:
1086:
1083:
1080:
1076:
1075:
1073:
1070:
1067:
1064:
1060:
1059:
1057:
1054:
1051:
1048:
1044:
1043:
1041:
1038:
1035:
1032:
1028:
1027:
1025:
1022:
1019:
1016:
1012:
1011:
1009:
1006:
1003:
1000:
996:
995:
993:
990:
987:
984:
980:
979:
977:
974:
971:
968:
964:
963:
960:
949:
939:
928:
918:
915:
901:
898:
861:
858:
855:
852:
849:
832:
829:
804:
801:
776:
773:
771:
768:
741:
734:
730:
724:
721:
715:
712:
689:
667:
663:
642:
622:
602:
599:
596:
593:
573:
570:
567:
545:
541:
535:
530:
525:
522:
516:
513:
490:
470:
450:
438:power function
419:
414:
407:
403:
398:
395:
385:
381:
375:
371:
365:
358:
355:
350:
345:
341:
338:
332:
323:
319:
314:
311:
305:
299:
296:
271:
267:
242:
239:
216:
212:
206:
202:
199:
177:
173:
168:
162:
158:
137:
111:
107:
86:
66:
45:
42:
13:
10:
9:
6:
4:
3:
2:
1702:
1691:
1688:
1686:
1683:
1682:
1680:
1666:
1659:
1656:
1646:
1640:
1636:
1632:
1628:
1624:
1617:
1614:
1604:
1598:
1594:
1590:
1586:
1582:
1575:
1572:
1567:
1563:
1558:
1553:
1549:
1545:
1541:
1534:
1531:
1525:
1520:
1516:
1512:
1508:
1501:
1498:
1492:
1490:
1486:
1481:
1477:
1473:
1469:
1465:
1461:
1457:
1450:
1447:
1442:
1438:
1434:
1430:
1426:
1419:
1416:
1413:
1407:
1405:
1403:
1399:
1394:
1390:
1386:
1385:
1377:
1374:
1369:
1365:
1361:
1357:
1352:
1347:
1343:
1339:
1335:
1328:
1325:
1319:
1316:
1305:
1301:
1294:
1291:
1286:
1282:
1278:
1274:
1270:
1263:
1261:
1257:
1252:
1248:
1244:
1240:
1236:
1232:
1228:
1224:
1220:
1213:
1211:
1207:
1202:
1196:
1192:
1188:
1184:
1180:
1173:
1171:
1169:
1167:
1165:
1163:
1159:
1153:
1150:
1145:
1141:
1137:
1133:
1129:
1122:
1119:
1112:
1106:
1103:
1100:
1097:
1094:
1093:
1090:
1087:
1084:
1081:
1078:
1077:
1074:
1071:
1068:
1065:
1062:
1061:
1058:
1055:
1052:
1049:
1046:
1045:
1042:
1039:
1036:
1033:
1030:
1029:
1026:
1023:
1020:
1017:
1014:
1013:
1010:
1007:
1004:
1001:
998:
997:
994:
991:
988:
985:
982:
981:
978:
975:
972:
969:
966:
965:
961:
947:
940:
926:
919:
916:
913:
912:
906:
899:
897:
893:
889:
881:
877:
875:
859:
856:
853:
850:
847:
838:
830:
828:
825:
821:
816:
812:
808:
802:
800:
798:
794:
789:
786:
781:
774:
769:
767:
764:
760:
758:
739:
732:
728:
722:
719:
713:
710:
687:
665:
661:
640:
620:
600:
597:
594:
591:
571:
568:
565:
543:
539:
533:
528:
523:
520:
514:
511:
488:
468:
448:
439:
435:
417:
405:
401:
396:
383:
379:
373:
369:
356:
353:
343:
339:
336:
321:
317:
312:
309:
303:
297:
294:
269:
265:
256:
240:
214:
210:
204:
200:
175:
171:
166:
160:
156:
135:
128:of the fuel,
127:
109:
105:
84:
64:
56:
55:Lewis numbers
52:
43:
41:
38:
33:
28:
26:
22:
18:
1664:
1658:
1648:, retrieved
1626:
1616:
1606:, retrieved
1584:
1574:
1547:
1543:
1533:
1514:
1510:
1500:
1463:
1459:
1449:
1432:
1428:
1418:
1383:
1376:
1341:
1337:
1327:
1318:
1307:. Retrieved
1303:
1293:
1276:
1272:
1226:
1222:
1182:
1152:
1135:
1131:
1121:
903:
894:
890:
886:
834:
817:
813:
809:
806:
790:
782:
778:
765:
761:
434:annular port
47:
29:
25:surface area
16:
15:
1679:Categories
1650:2022-04-07
1608:2022-04-07
1309:2022-04-06
1113:References
1566:189961306
1517:(4): 43.
1511:Aerospace
1480:0748-4658
1368:139475007
1360:2212-540X
1251:0022-4650
857:∗
851:∗
848:π
831:Burn area
714:˙
598:−
515:˙
394:Δ
354:−
344:μ
318:ρ
298:˙
238:Δ
198:Δ
136:μ
106:ρ
973:0.03043
1389:Bibcode
1231:Bibcode
1085:0.1876
1069:0.0255
1053:0.0211
1021:0.0128
989:0.0234
962:Source
820:helical
126:density
51:Prandtl
1641:
1599:
1564:
1478:
1366:
1358:
1249:
1197:
1101:0.038
1088:0.347
1072:0.679
1056:0.615
1037:0.166
1024:0.524
1008:0.498
1005:0.042
992:0.620
976:0.681
797:nozzle
1562:S2CID
1364:S2CID
1082:HTPB
1066:HTPB
1050:PMMA
1040:0.46
1002:HDPE
986:HDPE
970:HTPB
917:Fuel
310:0.036
1639:ISBN
1597:ISBN
1476:ISSN
1356:ISSN
1304:NASA
1247:ISSN
1195:ISBN
1104:0.5
1098:ABS
1095:N2O
1079:N2O
1063:N2O
1047:GOX
1034:ABS
1031:GOX
1018:ABS
1015:GOX
999:GOX
983:LOX
967:LOX
785:AFRL
584:and
481:and
418:0.23
124:for
53:and
32:fuel
1631:doi
1589:doi
1552:doi
1519:doi
1468:doi
1437:doi
1346:doi
1281:doi
1239:doi
1187:doi
1140:doi
914:Ox
874:CAD
601:0.2
572:0.8
357:0.2
1681::
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1625:,
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1509:.
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1464:23
1462:.
1458:.
1433:31
1431:.
1427:.
1401:^
1362:.
1354:.
1340:.
1336:.
1302:.
1277:18
1275:.
1271:.
1259:^
1245:.
1237:.
1227:45
1225:.
1221:.
1209:^
1193:.
1181:.
1161:^
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1134:.
1130:.
461:,
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1591::
1568:.
1554::
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1521::
1515:7
1482:.
1470::
1443:.
1439::
1395:.
1391::
1370:.
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1342:7
1312:.
1287:.
1283::
1253:.
1241::
1233::
1203:.
1189::
1146:.
1142::
948:n
927:a
860:l
854:D
740:n
733:o
729:G
723:a
720:=
711:r
688:G
666:o
662:G
641:x
621:n
595:=
592:m
569:=
566:n
544:m
540:x
534:n
529:G
524:a
521:=
512:r
489:m
469:n
449:a
413:)
406:v
402:h
397:h
384:c
380:u
374:e
370:u
364:(
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331:(
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304:=
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241:h
215:v
211:h
205:/
201:h
176:c
172:u
167:/
161:e
157:u
110:f
85:x
65:G
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