738:. One advantage of this system is that since the DPO could be used as backup of the main propulsion for orbit correction and de-orbit maneuvers, there was no need of adding a backup main propulsion (the DKD S5.35 in the previous system). But more importantly they could implement more extensive redundancy while keeping the mass of the system down. And by switching all the engines to the same propellant, all reserves could be consolidating reducing mass further. They also switched to a more efficient and storable propellant
1730:
792:(3.09 kN (690 lbf) versus 4.09 kN (920 lbf)), it improved efficiency with a specific impulse of 292 seconds (the S5.60 had 278s). Also, the switch to pressure fed cycle eliminated the use of turbopumps and its associated cost and reliability issues. And it also enabled the reduction in minimum burn time and engine transients since there was no turbine start up and shut down hysteresis.
24:
912:
spacecraft have an evolution of the KTDU-80. Now all 28 thrusters are the high thrust DPO-B, arranged in 14 pairs. Each propellant supply circuit handles 14 DPO-B, with each element of each thruster pair being fed by a different circuit. This provides full fault tolerance for thruster or propellant
508:
that enables it to rotate ±5° in pitch and yaw. It also has an electro mechanically actuated engine nozzle cover that takes 15 seconds to open and 25 seconds to close. All the propellant supply has redundant circuits. The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure
487:
The first and second DPO circuits are connected through electro-hydraulic actuated valves that enable the transfer of propellant between line in case of failure of one pressurization or propellant storage circuit. So the system has dual and redundant circuits at all its stages. The total propellant
459:
actuated valves that enable to share both circuits, to use a single one, or to use both systems independently. The Helium is stored initially at 34.32 MPa (4,978 psi) and is regulated to 1.75 MPa (254 psi), with a maximum pressure of 2.15 MPa (312 psi) and a minimum of
892:
experience brought some further changes. Experience had shown that during docking operations, only two DPO-B were available for abort operations. Thus, on
October 23, 2002 a project was formally started to add two additional DPO-B, which brought the total number of high thrust DPO engines to 16.
809:
monopropellant they used the same cycle and propellant as the 11D426 SKD. They also increase the thrust from the previous 98 N (22 lbf) to 137.2 N (30.8 lbf). This enabled the DPO-B to act as backup engine for the de-orbit maneuver, which eliminated the need for the backup
1209:
1044:
562:
810:
de-orbit engine (the DKD), further simplifying the system. For the low thrust attitude control system (DPO-M), they used the new 11D427. The number of engines was increased from 8 to 12, and thrust augmented from 14.7 N (3.3 lbf) to 24.5 N (5.5 lbf).
251:
of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The integrated system without the pressurization or tanks weighs 310 kg (680 lb); it is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).
821:. It was an evolutionary revision of the KTDU-426 system, rather and a revolutionary transition like the one done from the KTDU-35. The propellant supply subsystem switched to metallic diaphragms for the tank pressurization. The SKD main engine was changed to the new
468:
The propellant supply subsystem function is to guarantee the supply of propellant within the required operating parameters of the engines. It uses two tanks of fuel and two of oxidizer in two separate circuits. It is separated into three propellant feed circuits:
454:
The system has four spherical pressurizing gas tanks in two separated circuits. Each circuit connects two tanks, and has its individual pressure transducer, valves, pressure regulator and electrically actuated valves. The circuits are separated by two
854:
used on the KTDU-426. Since the DPO-B also act as the backup engine for the main SKD, they always have to keep a reserve of propellant in case of SKD failure that is dead weight. Thus a project to develop a more efficient version, the
825:. While slightly less powerful than the 11D426 with 2.95 kN (660 lbf), specific impulse increased to 302 s (2.96 km/s) and total burn time increased from 570 seconds to 890. The low thrust DPO-M initially used the
577:
have used 16 DPO-B thrusters. These can be used for docking and un-docking maneuvers, for attitude control and, in case of SKD main engine failure, for de-orbit burn. When used in that function, they are called DPO-BT
714:
to generate thrust. Having such dissimilar systems with different cycles, propellant, and feed systems added failure modes and required heavy backup equipment, like the backup de-orbit engine, the S5.35.
956:(DO) and the main propulsion (SKD and DKD) into a single system. The new arrangement enabled the use of the DPO as backup for de-orbit engine, and thus the DKD was eliminated. The SKD used the new
1545:
325:: It is the system that keeps all tanks and lines pressurized and guarantees the correct working pressure is maintained in the storage and the propulsion subsystems. Given the use of
247:
main engine. It generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 880 kPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a
986:
they switched models to the S5.142 for manufacturability reasons. Initially the 11D428A was used as the DPO-B. But has been changed to the 11D428A-16 to reduce dead weight. Since
627:). The DPO-M can only be used for attitude control. The S5.142 generates 25 N (5.6 lbf) of thrust with a chamber pressure of 0.8 MPa (120 psi) and achieves a
1837:
1832:
841:). Since the S5.142 lack a pressure transducer on its main combustion chamber, the avionics had to be modified. On the other hand, this change enabled the DPO-B to keep the
1103:
731:
476:
First DPO circuit: it supplies all high thrust thrusters (originally 14 DPO-B, later 16) and half of the low thrust thrusters (six DPO-M) through a line controlled by
1004:
version of the propulsion system has replaced all DPO-M with DPO-B, and now the pressurization and propellant feeds circuits are fully symmetrical with 14 DPO-B each.
1538:
1822:
829:, an uprated version of the 11D427 that increased thrust to 26.5 N (6.0 lbf). But due to manufacturability issues, those were later changed (by
1531:
901:
debuted a new arrangement of the DPO-B thrusters. But this is a spacecraft specific configuration and does not mean any changes to the KTDU-80 per se.
483:
Second DPO circuit: it supplies propellant to the other half (six DPO-M) of the low thrust thrusters, also through electro-hydraulic actuated valves.
473:
Main
Propulsion (SKD) circuit: it supplies the SKD (S5.80 main engine) through a series of pneumatically actuated valves through two redundant lines.
1146:
1274:
588:). The 11D428A-16 generates 129.16 N (29.04 lbf) of thrust with an inlet pressure of 1.76 MPa (255 psi) and achieves a
1842:
1827:
960:, that while it had less thrust, it had better specific impulse, and thus reducing overall mass. The same elements were used on the
319:): It is the main propulsion and includes all propellant pressurization and storage system. It is subdivided into three subsystems:
978:. For the tanks they switched to a metallic diaphragm for pressurization. The SKD main engine was changed to the more efficient
739:
685:
460:
1.37 MPa (199 psi), which is the minimum required pressure to activate the pneumatically actuated valves of the SKD.
388:): These are all the thrusters used to control the attitude and translation movements. It has two different sets of thrusters:
288:
229:
89:
1462:
1412:
1437:
260:
The KTDU-80 system integrates a dual string redundant propellant and pressurization system, a main propulsion system (the
953:
889:
657:
592:
of 291 s (2.85 km/s). It is rated for 500,000 ignitions with a total maximum burn duration of 2,000 seconds.
273:
221:
885:
marked the debut of the switch to 11D428A-16 for the crewed craft, which meant a saving of 30 kg (66 lb).
477:
335:: It which ensures propellant supply to the Orbital Maneuver Engines. Includes storage and propellant distribution.
450:
Supply of operating pressure for the actuation of the pneumatically activated valves of the main propulsion (SKD).
1669:
1514:
1234:
723:
1664:
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68:
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of 285 s (2.79 km/s). It is rated for 300,000 ignitions with a total firing time of 25,000 seconds.
949:
649:
265:
217:
404:): These are used for attitude, translation, docking and undocking maneuvers and as backup de-orbit engine.
689:
1781:
1584:
693:
302:
with a common supply of pressurized propellant. Mechanically, the KTDU-80 is separated in two sections:
1202:
1801:
1694:
1579:
1392:
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743:
329:
engines, this subsystem is critical and a failure could mean that the crew is kept stranded in space.
292:
233:
78:
990:, two additional DPO-B were added to double the thrust in case of an abort during docking maneuvers.
1744:
1569:
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681:
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of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds.
326:
281:
225:
1108:
784:
and can be stored for years in space. For the orbital correction engine (SKD), they developed the
1335:
1119:
1050:
842:
754:
209:
1106:(June 1999). "3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System)".
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1270:
704:
456:
509:
of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a
781:
628:
600:
589:
579:
530:
521:
The berthing and attitude control thruster subsystem is composed of two types of thrusters:
510:
411:
395:
379:
360:
342:
310:
248:
228:
from a common dual string redundant pressurized propellant system. The common propellant is
193:
128:
1518:
1131:
146:
1488:
1816:
1338:[The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com
898:
878:
870:
866:
862:
284:
1589:
1360:
488:
load can vary between 440 kg (970 lb) and 892 kg (1,967 lb).
369:): It is reaction and attitude control system. It is composed of two subsystems:
1523:
1466:
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975:
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1147:"Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now Khimmash)"
1786:
1709:
1382:
945:
874:
857:
557:
1174:
1791:
1257:
700:
996:: While as of June 2016 it is not known if it is still called KTDU-80, the
1177:[Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry]
1654:
1068:
1062:
997:
971:
905:
814:
118:
1237:[Small thrust jet engine from 0.5 kgf to 250 kgf] (in Russian).
772:
cycle for all rocket engines, and consolidated propellants on the UDMH/N
23:
1749:
1607:
1594:
1388:
1056:
1032:
1020:
941:
937:
850:
719:
645:
551:
213:
53:
1511:
1256:
Chertok, Boris (May 2009). "Chapter 18 — Birth of the
Soyuzes".
1242:
1714:
1647:
1634:
1026:
797:
785:
619:
541:
505:
441:
1175:"Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные"
1759:
1754:
1719:
1704:
1689:
1679:
1659:
1642:
1014:
979:
961:
897:
was the first spacecraft to fly with this new configuration. With
822:
789:
677:
669:
497:
204:) is the latest of a family of integrated propulsion system that
1699:
1674:
1574:
1300:
1266:
1053:- The family of spacecraft that are integrated with this system.
929:
757:
attitude control system, still uses catalytic decomposition of H
1527:
795:
For the new and improved high thrust RCS (DPO-B), known as the
436:
The
Pneumatic Pressurization System has three main functions:
28:
Soyuz TM-32 departing the ISS with its SKD nozzle cover closed
982:. Initially they used the improved 11D427M for DPO-M, but by
1029:- Latest reaction control system low thrust engine (DPO-M).
1259:
Rockets and People Vol. 3 — Hot Days of the Cold War
447:
Supply of operational pressure for propellant tank ullage.
1303:[The main engines produced by KBKhM] (in Russian)
817:
in 1986 saw a new revision of the propulsion system, the
648:) from its orientation system. The latter, integrated a
1071:- Soyuz version with a significantly different KTDU-80.
428:
Each subsystem is described in the following sections.
1023:- Reaction control system high thrust engine (DPO-B).
801:, they kept the use of 14 thrusters, but instead of H
504:). It is mounted on an electro mechanically actuated
1110:
Soyuz Crew
Operations Manual (SoyCOM) (ROP-19) Final
692:. The DPO and DO thrusters, on the other hand, were
366:ДПО, Подсистема двигателей причаливания и ориентации
200:Корректирующе-Тормозная Двигательная Установка, КТДУ
1774:
1737:
1559:
1197:
1195:
936:): This was the original version developed for the
881:it flew with a full set of 11D428A-16, and finally
420:): These are used exclusively for attitude control.
176:
168:
160:
155:
145:
137:
127:
116:
108:
103:
95:
74:
67:
59:
49:
41:
33:
1107:
1035:- Previous version of the Soyuz propulsion system.
357:Berthing/Attitude Control Thruster Subsystem (DPO)
861:was started in 1993. During a series of flights (
664:. The KTDU-35 had a main orbit correction engine
1354:
1352:
970:: Developed between 1968 and 1974 years for the
848:The high thrust DPO-B system initially kept the
845:away from the reentry capsule after separation.
1361:"Propulsion system for the Soyuz MS spacecraft"
1229:
1227:
1203:"Bipropellant Low Thrust Rocket Engine 11D428A"
1329:
1327:
1325:
1323:
1321:
1319:
1317:
1169:
1167:
974:, it is still used with slight changes on the
780:combination, which gives superior density and
1539:
1336:"Le système de propulsion du vaisseau Soyouz"
1065:- Soyuz version that inaugurated the KTDU-80.
604:
583:
534:
415:
399:
383:
376:The Berthing/Attitude Control Thrusters (DPO)
364:
346:
314:
197:
8:
768:For this version of the KTDU, they used the
765:, but that is a completely separate system.
555:, later version use the improved efficiency
348:ББ, Сближающе-корректирующий двигатель (СКД)
16:
1838:Rocket engines using the pressure-fed cycle
1465:. Encyclopedia Astronautica. Archived from
1440:. Encyclopedia Astronautica. Archived from
1415:. Encyclopedia Astronautica. Archived from
1294:
1292:
644:had a separated orbital correction system (
1833:Rocket engines using hypergolic propellant
1546:
1532:
1524:
1098:
1096:
1094:
1092:
1090:
1088:
1086:
1084:
877:flew with a partial set of 11D428A-16. By
753:, which improved performance further. The
613:, and KTDU-80 initially used the improved
496:Its main propulsion unit, uses the single
372:The redundant propellant supply subsystem.
22:
1041:- Developer and manufacturer of the KTDU.
921:This engine has had two main variations:
517:Berthing/Attitude Control Thrusters (DPO)
948:. It integrated into the KTDU unit, the
385:ДПО, Двигатели причаливания и ориентации
1080:
1059:- Soyuz version that used the KTDU-426.
672:and a backup orbital correction engine
1512:KB KhIMMASH Official Page (in Russian)
1127:
1117:
15:
734:an integrated propulsion system, the
561:. All versions have been supplied by
7:
1301:"Основные двигатели разработки КБХМ"
1047:- Developer of the DPO-M 11D428A-16.
788:. That while less powerful than the
565:. Since the original KTDU-426 until
243:and the main propulsion unit is the
1265:. Vol. 3 (NASA SP-2006-4110).
280:). All the propulsion elements are
1823:Rocket engines of the Soviet Union
1384:The New, Improved Soyuz Spacecraft
539:): The original KTDU-426 used the
14:
216:. It integrates main propulsion,
1728:
1017:- Main propulsion engine (SKD).
432:Pneumatic Pressurization System
323:Pneumatic Pressurization System
617:but later versions changed to
569:the KTDU used 14 DPO-B. Since
549:). KTDU-80 initially used the
1:
1554:Spacecraft engines and motors
1235:"ЖРДМТ от 0,5 кгс до 250 кгс"
392:High thrust thrusters (DPO-B)
339:Orbital Maneuver Engine (SKD)
1181:(in Russian). pp. 75–81
722:(first flight during 1979),
545:(manufacturer's designation
408:Low thrust thrusters (DPO-M)
1359:Zak, Anatoly (2016-07-08).
1149:. B14643.de. Archived from
944:of the previous generation
890:International Space Station
1859:
1843:KB KhimMash rocket engines
478:electro-hydraulic actuated
1726:
1381:Rob Navias (2016-07-08).
964:space station propulsion.
605:
584:
535:
440:Storage of high pressure
416:
400:
384:
365:
347:
315:
198:
181:
21:
1828:Rocket engines of Russia
1299:Ponomarenko, Alexander.
813:The introduction of the
333:Propellant Supply System
208:has implemented for the
1738:Solid propellant motors
1491:. Jonathan Space Report
1391:). Space Station Live.
950:reaction control system
650:reaction control system
1489:"5.2: Russian engines"
1782:Spacecraft propulsion
837:(manufacturer's name
623:(manufacturer's name
609:): KTDU-426 used the
492:Main Propulsion (SKD)
1802:Liquid apogee engine
1487:McDowell, Jonathan.
1363:. Russian Space Web
1114:. pp. 122–129.
224:in a single system
18:
1517:2016-03-20 at the
1051:Soyuz (spacecraft)
994:KTDU-80 (Soyuz MS)
940:that replaced the
699:rockets that used
69:Liquid-fuel engine
1810:
1809:
1797:Apogee kick motor
1334:Pillet, Nicolas.
1276:978-0-16-081733-5
1245:on 23 April 2013.
1145:Brügge, Norbert.
913:circuit failure.
703:decomposition of
680:. These two were
464:Propellant Supply
186:
185:
34:Country of origin
1850:
1775:Related articles
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1153:on 2015-06-02
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899:Soyuz TMA-11M
896:
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886:
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880:
879:Progress M-39
876:
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682:gas generator
679:
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640:The original
635:
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500:main engine (
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63:In production
62:
58:
55:
52:
48:
44:
40:
36:
32:
25:
20:
1626:
1493:. Retrieved
1482:
1471:. Retrieved
1467:the original
1457:
1446:. Retrieved
1442:the original
1432:
1421:. Retrieved
1417:the original
1407:
1396:. Retrieved
1383:
1376:
1365:. Retrieved
1340:. Retrieved
1305:. Retrieved
1280:. Retrieved
1258:
1251:
1243:the original
1214:. Retrieved
1183:. Retrieved
1155:. Retrieved
1151:the original
1140:
1109:
993:
967:
957:
933:
925:
920:
903:
887:
856:
849:
847:
838:
834:
826:
818:
812:
796:
794:
770:pressure fed
767:
735:
717:
697:pressure fed
673:
665:
661:
653:
639:
624:
618:
614:
610:
596:
556:
550:
546:
540:
526:
520:
501:
495:
486:
467:
453:
435:
427:
407:
391:
375:
356:
338:
332:
327:pressure fed
322:
306:
282:pressure fed
277:
276:system (the
269:
261:
259:
244:
226:pressure fed
199:
189:
187:
147:Gimbal range
99:Pressure fed
42:Manufacturer
1561:Liquid fuel
1239:KB KhIMMASH
1104:RKK Energia
1039:KB KhIMMASH
1002:Progress-MS
988:Soyuz TMA-5
984:Soyuz TM-23
976:Soyuz-TMA-M
952:(DPO), the
910:Progress-MS
895:Soyuz TMA-5
883:Soyuz TM-28
831:Soyuz TM-23
575:Soyuz-TMA-M
571:Soyuz TMA-5
567:Soyuz TMA-4
256:Description
206:KB KhIMMASH
104:Performance
50:Predecessor
45:KB KhIMMASH
1817:Categories
1787:Spacecraft
1710:SuperDraco
1495:2015-07-25
1473:2015-07-25
1448:2015-07-25
1423:2015-07-25
1398:2016-07-09
1367:2016-07-09
1342:2015-07-14
1307:2015-07-25
1282:2015-07-15
1185:2015-07-25
1157:2015-06-02
1076:References
875:Progress-M
858:11D428A-16
558:11D428A-16
212:since the
156:Dimensions
75:Propellant
1792:Satellite
1767:SpaB-140C
1463:"KTDU-80"
1413:"KDU-426"
1130:ignored (
1120:cite book
833:) to the
701:catalytic
272:) and an
138:Burn time
1655:KTDU-425
1515:Archived
1438:"KRD-79"
1393:NASA JSC
1069:Soyuz-MS
1063:Soyuz-TM
1009:See also
998:Soyuz-MS
972:Soyuz-TM
926:KTDU-426
917:Versions
906:Soyuz-MS
904:The new
815:Soyuz-TM
736:KTDU-426
718:For the
656:and the
573:and all
547:RDMT-135
287:burning
169:Diameter
119:pressure
117:Chamber
1764:SpaB-65
1750:Star 48
1745:Star 37
1627:KTDU-80
1608:KTDU-35
1595:KDU-414
1563:engines
1389:YouTube
1210:NIIMash
1057:Soyuz-T
1045:NIIMash
1033:KTDU-35
1021:11D428A
968:KTDU-80
942:KTDU-35
938:Soyuz-T
851:11D428A
827:11D427M
819:KTDU-80
720:Soyuz-T
652:called
646:KTDU-35
636:History
615:11D427M
601:Russian
580:Russian
563:NIIMash
552:11D428A
531:Russian
480:valves.
412:Russian
396:Russian
380:Russian
361:Russian
343:Russian
311:Russian
214:Soyuz-T
194:Russian
190:KTDU-80
177:Used in
123:880 kPa
112:2.95 kN
54:KTDU-35
17:KTDU-80
1715:TR-201
1648:S5.142
1635:11D428
1631:11D426
1602:S5.114
1273:
1212:. 2009
1027:S5.142
958:11D426
934:11D426
932:Index
839:DST-25
835:S5.142
798:11D428
786:11D426
732:TsKBEM
724:Isayev
676:, the
668:, the
625:DST-25
620:S5.142
611:11D427
585:ДПО-Бт
542:11D428
506:gimbal
264:), an
161:Length
109:Thrust
60:Status
37:Russia
1760:FG-36
1755:FG-15
1720:XLR81
1705:S5.92
1690:RS-25
1684:11D58
1680:RD-58
1660:LEROS
1643:S5.80
1639:S5.79
1621:S5-66
1618:S5-60
1615:S5.53
1612:S5-35
1599:S5.19
1590:Draco
1585:Curie
1570:17D61
1263:(PDF)
1216:5 May
1206:(PDF)
1179:(PDF)
1015:S5.80
980:S5.80
962:S5.79
946:Soyuz
823:S5.80
790:S5.60
728:OKB-2
690:AK27I
678:S5.35
670:S5.60
642:Soyuz
606:ДПО-М
597:DPO-M
536:ДПО-Б
527:DPO-B
498:S5.80
457:squib
417:ДПО-М
401:ДПО-Б
278:DPO-M
270:DPO-B
268:(the
245:S5.80
210:Soyuz
182:Soyuz
141:890 s
133:302 s
96:Cycle
1700:S5.4
1695:S400
1675:R-4D
1670:LMDE
1665:LMAE
1580:BT-4
1575:AJ10
1271:ISBN
1267:NASA
1218:2023
1132:help
1000:and
930:GRAU
908:and
888:The
871:M-38
869:and
867:M-37
863:M-36
742:and
740:UDMH
688:and
686:UDMH
444:gas.
291:and
289:UDMH
232:and
230:UDMH
220:and
188:The
172:2.1m
164:1.2m
90:UDMH
843:PAO
726:'s
674:DKD
666:SKD
654:DPO
502:SKD
266:RCS
262:SKD
218:RCS
1819::
1351:^
1316:^
1291:^
1226:^
1208:.
1194:^
1166:^
1124::
1122:}}
1118:{{
1083:^
873:)
865:,
662:DO
603::
582::
533::
442:He
414::
398::
382::
363::
351:):
345::
313::
196::
88:/
1547:e
1540:t
1533:v
1498:.
1476:.
1451:.
1426:.
1401:.
1387:(
1370:.
1345:.
1310:.
1285:.
1220:.
1188:.
1160:.
1134:)
928:(
807:2
805:O
803:2
778:4
776:O
774:2
763:2
761:O
759:2
750:4
748:O
746:2
744:N
711:2
709:O
707:2
705:H
599:(
578:(
529:(
410:(
394:(
378:(
359:(
341:(
309:(
299:4
297:O
295:2
293:N
240:4
238:O
236:2
234:N
192:(
151:5
85:4
83:O
81:2
79:N
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
