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bounds. In the case of H-25, it might be necessary to accelerate the fly-back boosters to above 2 km/s (1.2 mi/s) to help the upper stage achieve its desired orbit. Consequently, two solutions were proposed to decelerate the boosters after separation. The first option was to actively decelerate them using 10 tonnes (11 short tons) of fuel and reduce the velocity by 300 m/s (980 ft/s). However, launch performance would drop below that of the Vega derivative. Another option is to use aerodynamic forces to decelerate. However, a
292:
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carrying 50 tonnes (55 short tons) of propellant. The payload fairing mount atop the orbiter would be 5.4 by 20.5 metres (18 ft Ă— 67 ft). For LEO missions, the launch vehicle would be 57.3 metres (188 ft) tall, with a gross lift-off mass of 739.4 tonnes (815.0 short tons). The payload to LEO would be 12,800 kilograms (28,200 lb), with an increase to 8,500 kilograms (18,700 lb) to GTO when using an expandable upper stage.
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would use a new
Vulcain 3 main engine, with increased vacuum thrust. When launched with a single booster, both stages would be operated in parallel, and be delivered to a 180 by 800 km (110 by 500 mi) orbit before separation. The remaining upper stage composite would weigh 7,360 kg (16,230 lb), with a 5,000 kg (11,000 lb) payload performance to SSO. When launching to
653:
3336:
633:(TSTO) launch vehicle variant of LFBB was planned to be implemented about 15 years after the addition of LFBBs to Ariane 5. However, only a preliminary analysis of TSTO was completed. The proposed configuration consisted of two boosters with retractable wings attached to the external fuel tank, and a reusable orbiter with fixed wings carrying payload on top of it. During
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45:
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521:. Depending on the method of deceleration, the payload to SSO is between 1,481 and 2,788 kg (3,265 and 6,146 lb). The third was a large cryogenic upper stage, called H-185, based on an alternative, yet-to-be-developed Ariane 5 main stage with 185 tonnes (204 short tons) of cryogenic fuel. Its payload to SSO is 5,000 kg (11,000 lb).
482:
445:. The cruise back to the airport requires about 3,650 kg (8,050 lb) of hydrogen fuel and takes over two hours to complete. An undercarriage is deployed and each booster lands autonomously. After separation, the boosters are not under threat of collision until they land due to small differences in their initial flight trajectories.
260:, undertook this objective, they failed to meet their goals. Supporting technologies needed for LFBB construction can be developed within 10 years, and additional launchers can be developed based on fly-back boosters to minimise costs and provide maintenance synergy across multiple classes of launch vehicles.
608:
When launched to a 200 km Ă— 600 km (120 mi Ă— 370 mi) Low Earth transfer orbit, the LFBBs would separate at an altitude of 51 km (32 mi), at a speed of 1.55 km/s (0.96 mi/s). To avoid simultaneous separation of all boosters, either a cross-feed to the
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The heaviest configuration uses a single booster with an asymmetrically mounted, large, expendable cryogenic stage designated H-185. It was proposed as a future variant of the Ariane 5 core stage (H158), eventually meant to phase out the main stage in a standard launch configuration with LFBB. H-185
533:
was proposed. Flight dynamics simulation revealed that a ballute with a cross-section of 45 m (480 sq ft) offered the best compromise between loads on the booster and deceleration by aerodynamic forces. In this configuration, a launch performance of up to 2,788 kg (6,146 lb)
251:
The advantages of reusable boosters include simplicity from using only one type of fuel, environmental friendliness, and lower reoccurring costs. Studies concluded that reusable fly-back boosters would be the most affordable and the least risky way for
European space launch systems to start becoming
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Two of the lighter configurations (the Zefiro 23 and the H-25) use upper stages mounted on top of the booster. Due to the lower weight, it might have been necessary to lower the amount of fuel in a booster to ensure that the separation velocity, the flight path, and the reentry do not exceed design
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The external tank, being a core of the system, would have a diameter of 5.4 metres (18 ft) and a height of 30.5 metres (100 ft), carrying 167.5 tonnes (184.6 short tons) of propellant. The attached orbiter would be 28.8 metres (94 ft) tall and 3.6 metres (12 ft) in diameter,
424:
A typical mission profile would begin with the ignition of a main stage and both boosters, followed by an acceleration to 2 km/s (1.2 mi/s) and then a separation at the altitude of 50 km (31 mi). As the main stage continues its flight into orbit, the boosters follow a
558:
The Super-Heavy Lift
Launcher (SHLL) would consist of a new cryogenic main stage, five liquid fly-back boosters, and a re-ignitable injection stage. This configuration was designed to provide increased capabilities for complex missions, including crewed explorations to the
421:. Finally, the fourth propulsion system would be based on solid rocket motors that separate the boosters from the core stage. An up-scaled version of the motors used in existing EAP boosters would be mounted in the attachment ring and inside the wing's main structure.
271:
The thing that shocked me was that at the beginning, this reusable flyback booster was just a cylinder with engines and little wings, just a turbo fan in the back. And three years later these were complete
Airbuses in terms of size with four engines in each of
457:. The aim of the LFBB project at DLR was to reduce Ariane 5 operational costs and to develop future derivatives, including a reusable first stage of a small-to-medium launch vehicle, a super-heavy launch vehicle capable of lifting 67 tonnes (74 short tons) to
213:; English: Systems and Technologies for Space Transportation Applications) programme from 1999 to 2005, with additional studies continuing until 2009. The LFBB design was one of two projects within the ASTRA program, the other being
399:(GLOW) of each booster is 222.5 tonnes (245.3 short tons), with 54 tonnes (60 short tons) upon separation and 46.2 tonnes (50.9 short tons) dry mass. In comparison, the GLOW for EAP P241 is 273 tonnes (301 short tons).
192:
German
Aerospace Center studied Liquid Fly-back Boosters as a part of future launcher research programme from 1999 to 2004. After the cancellation of the project, publications at DLR continued until 2009.
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585:. The upper stage would be a derivative of the Ariane 5 ESC-B, with the size upped to 5.6 m Ă— 8.98 m (18.4 ft Ă— 29.5 ft), and strengthened to bear higher loads. The
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is 41 m (135 ft) long, with an outer tank diameter of 5.45 m (17.9 ft), specifically designed to match the existing Ariane 5 core stage and to reduce manufacturing costs. A
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The development of liquid fly-back boosters has the potential to enable three additional space transportation systems with an objective of increasing production and creating
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The new core stage would stand 28.65 m (94.0 ft) tall and have a diameter of 10 m (33 ft), feeding 600 tonnes (660 short tons) of
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to three
Vulcain 3 engines. The increased circumference of the main stage allows five LFBBs to be integrated with either retractable or
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could be used. The return flight of the boosters would require an estimated 3,250 kg (7,170 lb) of fuel, including a 30% reserve.
402:
The booster was designed to have four independent propulsion systems, the first of which – main rocket propulsion – would be based on three
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toward the target airfield. Gliding continues until they achieve an altitude that is optimal for engaging turbofan engines and entering
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Top view of RFS configurations: Vega and Ariane 5 derivatives (top), large cryogenic upper stage (bottom) with the LFBB shown in blue
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509:(SSO) would increase to 1,882 kg (4,149 lb), compared to the 1,450 kg (3,200 lb) of the Vega. The second was an
83:
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The LFBB was studied with the three upper stage composites, to attain a
Reusable First Stage (RFS) configuration. The first was a
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launch vehicle. Initially, LFBBs would be used only on Ariane 5. Over time, alternative configurations could phase out
339:
Evolution type-A (ECA) variant would increase from 10,500 kg (23,100 lb) to 12,300 kg (27,100 lb).
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Eventually, the hardware grew too large and the LFBB project was scrapped, with one member of the French space agency (
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fly-back turbofan engines would be propelled with hydrogen to reduce fuel mass. Further, ten 2 kN (450 lb
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reusable. These fly-back boosters had the potential to reduce launch costs. However, when other projects, such as
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128:
441:. At this point, about 550 km (340 mi) from the launch point, the boosters would be flying over the
299:
The overall concept of the liquid boosters in the LFBB programme was to retain the Ariane 5's core and upper
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319:. These boosters would provide the main thrust during take-off. After separation, they would return to a
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In the reference design, each LFBB consists of three engines installed in a circular arrangement at the
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135:, providing main thrust during the countdown. Once separated, two winged boosters would perform an
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Additionally a family of derivative launch vehicles was proposed in order to take an advantage of
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217:. During development, scale models were constructed for testing various configurations in DLR's
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of approximately 21 m (69 ft) and an area of 115 m (1,240 sq ft). The
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593:. Payload would be enclosed in an 8 m Ă— 29.5 m (26 ft Ă— 97 ft)
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1023:"Experimental studies on a Liquid Fly-Back-Booster configuration (LFBB) in wind tunnels"
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331:) mode of operation would allow liquid fly-back boosters to continue operating from the
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2013:
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933:(Report). American Institute of Aeronautics and Astronautics, Inc. 2012. Archived from
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17:
240:. The preliminary mechanical design of other major elements was done by the companies
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in order to significantly reduce the high cost of space transportation and increase
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The German
Aerospace Center (DLR) studied potential future launch vehicles of the
27:
This article is about the DLR study for Ariane. For NASA Space
Shuttle LFBB, see
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2008:
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597:. The launch vehicle would have a total height of 69 m (226 ft) and a
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parachute was deemed too expensive and too complex. As a result, an alternative
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429:, reaching an altitude of 90–100 km (56–62 mi). After low-energy
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engines fueled by 168,500 kg (371,500 lb) of propellant. Second,
848:
Sippel, Martin; Manfletti, Chiara; Burkhardt, Holger (28 September 2005).
433:, the boosters reach denser layers of the atmosphere where they perform a
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542:, payload mass can be increased to over 10,000 kg (22,000 lb).
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637:(GTO) missions, an additional, expandable upper stage would be used.
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by adding the orbital altitude and inclination for the given payload.
53:
669: – Re-useable rocket booster proposed for Angara carrier rocket
481:
417:) thrusters placed on each side of the vehicle would be used by the
513:
derivative called H-25. It was based on an H10 upper stage with a
181:
capable of lifting nearly 70 tonnes (150,000 lb) to the orbit.
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1988:
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could be achieved, partly thanks to a higher separation velocity.
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95:
501:
third stage and an AVUM upper stage. With the LFBB replacing the
3208:
3183:
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1086:"DLR - Institut fĂĽr Raumfahrtsysteme - ASTRA LFBB configuration"
328:
295:
A line drawing of DLR's LFBB, showing top, front, and side views
278:
264:
245:
2376:
2033:
1780:
1519:
1156:
1114:
1059:"French Debris-mitigation Law Could Pose Issue for Arianespace"
625:
Top view of the TSTO configuration with the LFBB shown in blue
554:
Top view of the SHLL configuration with the LFBB shown in blue
343:
241:
38:
150:, further reducing launch costs. These derivatives include:
567:, as well as the launch of large solar-powered satellites.
850:"Long-term/strategic scenario for reusable booster stages"
143:, and land horizontally on the airport like an aeroplane.
928:
Progress in the Design of a
Reusable Launch Vehicle Stage
327:
for landing. This vertical take-off, horizontal landing (
843:
841:
839:
837:
835:
833:
831:
74:
829:
827:
825:
823:
821:
819:
817:
815:
813:
811:
207:
Ausgewählte Systeme und Technologien für Raumtransport
991:
RESPACE - Key Technologies for Reusable Space Systems
686: – 2010-12 US Air Force space propulsion project
714:
712:
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601:of 1,900 tonnes (2,100 short tons). The payload to
1030:American Institute of Aeronautics and Astronautics
2155:Space Applications and Telecommunications Centre
100:The LFBB model used in wind tunnel tests by the
29:Studied Space Shuttle variations and derivatives
792:[Reusable booster stages for Ariane 5]
269:
2165:Space Telescope European Coordinating Facility
790:"Wiederverwendbare Boosterstufen fĂĽr Ariane 5"
188:system operating a dedicated reusable orbiter.
2045:
1792:
1126:
224:(TMK; English: Trisonic measuring section at
8:
3388:Former proposed space launch system concepts
1032:. December 2003. p. 4,5. Archived from
796:(in German). Raumfahrt Concret. January 2009
589:was proofed to be sufficiently powerful for
605:would be 67,280 kg (148,330 lb).
2389:
2373:
2314:European Launcher Development Organisation
2068:
2052:
2038:
2030:
1799:
1785:
1777:
1527:
1516:
1164:
1153:
1133:
1119:
1111:
365:section, provide power for fly-back. The
84:Learn how and when to remove this message
1543:Chinese reusable experimental spacecraft
902:"Space Launcher Systems Analysis (SART)"
743:
741:
739:
737:
722:(in German). astronews.com. 4 April 2007
675: – SpaceX heavy-lift launch vehicle
290:
115:'s (DLR's) project concept to develop a
708:
2276:Space Situational Awareness Programme
71:, which greatly affects the capacity.
7:
3323:
2319:European Space Research Organisation
2135:Space Research and Technology Centre
720:"Sonnensegel und Satellitenkatapult"
3347:
2004:Liquid Fly-back Booster Derivatives
379:configuration was selected, with a
25:
517:and 25 tonnes (28 short tons) of
346:of the vehicle. Each engine is a
154:A reusable booster in a class of
131:. lrb would replace the existing
3383:Space launch vehicles of Germany
3346:
3334:
3322:
3311:
3310:
2140:ESA Centre for Earth Observation
964:"Liquid Fly-back Booster (LFBB)"
651:
546:Super-Heavy Lift Launcher (SHLL)
43:
3393:Cancelled space launch vehicles
880:10.1016/j.actaastro.2005.09.012
179:super-heavy-lift launch vehicle
3159:Columbus Man-Tended Free Flyer
313:Étages d’Accélération à Poudre
139:, go back autonomously to the
1:
635:geostationary transfer orbit
393:Royal Aircraft Establishment
222:Trisonische Messstrecke Köln
1677:Ya Guidao Gainian Feixingqi
866:(published 2006): 209–221.
230:Hyperschallwindkanal 2 Köln
3409:
3229:Mars sample return mission
3049:European Data Relay System
2729:Meteosat Second Generation
2642:James Webb Space Telescope
2504:Jupiter Icy Moons Explorer
2186:European Data Relay System
2160:Concurrent Design Facility
749:"ASTRA LFBB configuration"
129:environmental friendliness
26:
3302:
2852:Meteosat Third Generation
2711:Meteosat First Generation
2372:
2360:Planetary Science Archive
2145:European Astronaut Centre
2067:
1759:
1526:
1515:
1163:
1152:
2271:Living Planet Programme
2130:Space Operations Centre
1469:Reusable Booster System
1459:Liquid Fly-back Booster
1142:Reusable launch systems
950:German Aerospace Center
753:German Aerospace Center
684:Reusable Booster System
667:Baikal (rocket booster)
583:variable-geometry wings
419:reaction control system
311:(EAP P241, from French
236:wind canal at Cologne)
113:German Aerospace Center
109:Liquid Fly-back Booster
102:German Aerospace Center
18:Liquid Fly-back Booster
3378:Ariane (rocket family)
2582:Hubble Space Telescope
2150:Space Astronomy Centre
1672:Goodyear Meteor Junior
1206:(orbiter and boosters)
699:with technical details
626:
555:
486:
354:. An additional three
317:liquid rocket boosters
296:
284:
133:liquid rocket boosters
105:
3373:European Space Agency
2379:Projects and missions
2061:European Space Agency
1599:Space Shuttle orbiter
966:. DLR. Archived from
904:. DLR. Archived from
624:
553:
507:Sun-synchronous orbit
484:
359:air-breathing engines
309:solid rocket boosters
294:
117:liquid rocket booster
99:
2979:European Robotic Arm
2823:Sentinel-5 Precursor
1096:on 23 September 2015
1001:. p. 20,22,26.
989:GĂĽlhan, Ali (2008).
759:on 23 September 2015
477:Reusable first stage
427:ballistic trajectory
350:engine with reduced
281:launcher directorate
75:improve this article
34:Launch vehicle study
3304:Future missions in
2350:European Space Camp
2081:Guiana Space Centre
1570:Buran-class orbiter
1411:Energia II (Uragan)
1084:Lindemann, Sabine.
872:2006AcAau..58..209S
515:Vinci rocket engine
493:derivative, with a
397:gross lift-off mass
361:, installed in the
333:Guiana Space Centre
277:Christophe Bonnal,
164:heavy lift boosters
3154:Ceres Polar Lander
2989:Telecommunications
1308:Rocket Lab Neutron
940:on 10 January 2006
659:Spaceflight portal
631:two-stage-to-orbit
627:
617:Two-stage-to-orbit
556:
487:
463:two-stage-to-orbit
455:economies of scale
307:, and replace its
297:
186:two-stage-to-orbit
160:medium-lift launch
148:economies of scale
106:
3360:
3359:
3298:
3297:
2916:
2915:
2698:Earth observation
2528:Comet Interceptor
2519:Rosalind Franklin
2491:Trace Gas Orbiter
2442:Planetary science
2368:
2367:
2281:Science Programme
2027:
2026:
1774:
1773:
1755:
1754:
1751:
1750:
1638:Orel (spacecraft)
1511:
1510:
1507:
1506:
1319:Starship (SpaceX)
1008:978-3-540-77819-6
855:Acta Astronautica
591:orbital insertion
505:, the payload to
467:Arianespace Soyuz
461:, and a reusable
431:atmospheric entry
391:profile from the
303:, along with the
137:atmospheric entry
94:
93:
86:
62:does not include
56:article contains
16:(Redirected from
3400:
3350:
3349:
3338:
3326:
3325:
3314:
3313:
3290:Schiaparelli EDM
3149:Calathus Mission
2973:Georges Lemaître
2931:ISS contribution
2390:
2374:
2069:
2054:
2047:
2040:
2031:
1801:
1794:
1787:
1778:
1621:Boeing Starliner
1528:
1517:
1324:Stoke Space Nova
1273:8R (first stage)
1270:6X (first stage)
1165:
1154:
1135:
1128:
1121:
1112:
1106:
1105:
1103:
1101:
1092:. Archived from
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953:
947:
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924:
918:
917:
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913:
908:on 30 March 2014
898:
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891:
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795:
786:
769:
768:
766:
764:
755:. Archived from
745:
732:
731:
729:
727:
716:
661:
656:
655:
654:
497:second stage, a
395:(RAE 2822). The
315:) with reusable
305:payload fairings
282:
89:
82:
78:
64:orbital altitude
47:
39:
21:
3408:
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3399:
3398:
3397:
3363:
3362:
3361:
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3125:
3106:LISA Pathfinder
3063:
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2984:
2967:Albert Einstein
2955:Johannes Kepler
2912:
2693:
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2096:Launch vehicles
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1039:on 10 June 2015
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735:
725:
723:
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710:
706:
693:
657:
652:
650:
647:
619:
609:main stage, or
579:
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540:Low Earth orbit
479:
459:Low Earth orbit
451:
416:
387:was based on a
352:expansion ratio
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232:(H2K; English:
228:) and in their
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3005:
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2961:Edoardo Amaldi
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1204:Space Shuttle
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1117:
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1095:
1091:
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1080:
1077:
1064:
1063:Aviation Week
1060:
1054:
1051:
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1024:
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629:The reusable
623:
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439:cruise flight
436:
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411:Eurojet EJ200
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325:French Guiana
322:
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286:
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268:
267:) remarking:
266:
261:
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254:Space Shuttle
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111:(LFBB) was a
110:
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41:
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3339:
3328:
3315:
3305:
3214:Lunar Lander
3132:and proposed
3117:
2904:
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2850:
2842:
2834:
2685:
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2534:
2526:
2518:
2509:
2490:
2467:Mars Express
2429:
2307:Predecessors
2286:Horizon 2000
1763:* indicates
1627:Dream Chaser
1593:SpaceShipTwo
1587:SpaceShipOne
1442:
1181:Falcon Heavy
1100:30 September
1098:. Retrieved
1094:the original
1089:
1079:
1067:. Retrieved
1065:. 5 May 2014
1062:
1053:
1043:21 September
1041:. Retrieved
1034:the original
1017:
990:
984:
972:. Retrieved
968:the original
958:
948:– via
942:. Retrieved
935:the original
922:
910:. Retrieved
906:the original
896:
859:
853:
798:. Retrieved
763:30 September
761:. Retrieved
757:the original
724:. Retrieved
673:Falcon Heavy
639:
628:
607:
587:Vinci engine
569:
557:
536:
523:
488:
452:
435:banking turn
423:
401:
341:
312:
298:
270:
262:
250:
238:wind tunnels
229:
221:
206:
200:
191:
145:
108:
107:
80:
73:Please help
61:
36:
3352:WikiProject
3224:MarcoPolo-R
3174:Don Quijote
3144:Ariane 5 ME
3108:(2015–2017)
3038:Galileo FOC
3032:Galileo IOV
3004:(1989–1993)
2943:Jules Verne
2924:spaceflight
2755:(2009–2013)
2743:(2003–2007)
2741:Double Star
2737:(2002–2012)
2725:(1995–2011)
2719:(1991–2000)
2713:(1977–1997)
2626:(2009–2013)
2620:(2009–2013)
2596:(1995–1998)
2578:(1989–1993)
2572:(1983–1986)
2566:(1978–1996)
2560:(1975–1982)
2498:BepiColombo
2485:(2005–2014)
2479:(2004–2016)
2463:(2003–2006)
2457:(1997–2005)
2451:(1985–1992)
2420:(2000–2024)
2408:(1990–2009)
2402:(1977–1987)
2335:Arianespace
2009:BAC Mustard
1974:Capricornio
1966:Ariane 5 ME
1935:Black Arrow
1847:Ariane Next
1720:Silver Dart
1652:upper stage
1581:Gemini SC-2
1538:Boeing X-37
1499:VentureStar
1431:Hyperbola-2
1358:Kankoh-maru
1291:Orbex Prime
1260:Hyperbola-3
1239:Ariane Next
1218:* (booster)
1212:* (booster)
1187:New Shepard
944:9 September
912:9 September
449:Derivatives
287:Description
258:VentureStar
215:Phoenix RLV
197:Development
119:capable of
68:inclination
3367:Categories
3239:Phootprint
3219:Marco Polo
3060:Technology
2890:MetOp-SG-B
2882:MetOp-SG-A
2858:Sentinel-4
2829:ADM-Aeolus
2809:Sentinel-3
2791:Sentinel-2
2777:Sentinel-1
2705:Copernicus
2600:XMM-Newton
2418:Cluster II
2224:Copernicus
2195:Programmes
2123:Facilities
2073:Spaceports
1872:North Star
1765:suborbital
1521:Spacecraft
1484:Tianjiao-1
1479:Sea Dragon
1402:(boosters)
1335:Tianlong-3
1266:Long March
1146:spacecraft
1090:www.dlr.de
704:References
611:throttling
527:hypersonic
234:Hypersonic
219:supersonic
205:under the
3280:CryoSat-1
3254:STE-QUEST
3189:Eddington
3179:e.Deorbit
3130:Cancelled
3002:Olympus-1
2844:EarthCARE
2765:CryoSat-2
2614:(2006–13)
2590:(1992–93)
2576:Hipparcos
2550:cosmology
1961:Aldebaran
1954:Cancelled
1807:European
1730:X-30 NASP
1692:Cancelled
1660:Proposals
1646:(capsule)
1640:(capsule)
1634:(capsule)
1623:(capsule)
1577:(capsule)
1441:Hopper /
1416:Falcon 1e
1351:Proposals
1343:(engines)
1285:New Glenn
888:0094-5765
697:ASTR LFBB
503:P80 stage
495:Zefiro 23
389:transonic
337:Cryogenic
321:spaceport
3341:Wikinews
3317:Category
2937:Columbus
2861:) (2024)
2671:ARRAKIHS
2624:Herschel
2606:INTEGRAL
2536:EnVision
2489:ExoMars
2345:EUMETSAT
2236:Columbus
2229:Sentinel
2109:Ariane 6
2104:Ariane 5
1970:Ariane M
1887:Spectrum
1862:Haas 2CA
1852:Bloostar
1826:Ariane 6
1767:vehicles
1650:Starship
1632:Mengzhou
1554:Shenlong
1549:Dragon 2
1421:Falcon 5
1377:Canceled
1329:Terran R
1297:Pallas-1
1254:Electron
1244:CALLISTO
1175:Falcon 9
864:Elsevier
645:See also
511:Ariane 4
499:Zefiro 9
404:gimbaled
385:aerofoil
381:wingspan
371:low-wing
367:fuselage
356:turbofan
275:—
125:Ariane 1
3329:Commons
3306:italics
3275:Cluster
3259:THESEUS
3244:SOLARIS
3119:PROBA-3
3112:OPS-SAT
3094:PROBA-V
3088:PROBA-2
3076:PROBA-1
3026:HYLAS-1
3020:GIOVE-B
3014:GIOVE-A
3008:Artemis
2836:Biomass
2735:Envisat
2674:(2030s)
2473:Rosetta
2461:SMART-1
2455:Huygens
2406:Ulysses
2386:Science
2261:ExoMars
2251:GALILEO
2241:CryoSat
2202:Artemis
2181:ESTRACK
2086:Esrange
1999:Liberty
1940:Diamant
1896:Retired
1877:RFA One
1867:Miura 5
1857:Haas 2b
1809:orbital
1715:Mustard
1563:Retired
1545:(CSSHQ)
1443:Phoenix
1384:Adeline
1279:Miura 5
1197:Retired
995:Cologne
868:Bibcode
595:fairing
563:and to
531:ballute
407:Vulcain
348:Vulcain
226:Cologne
58:payload
3285:GEOS 1
3268:Failed
3234:ODINUS
3204:Hopper
3199:Hermes
3194:EXPERT
3122:(2024)
3102:(2015)
3084:(2007)
3072:(1998)
2998:(1978)
2996:GEOS 2
2981:(2021)
2975:(2014)
2969:(2013)
2963:(2012)
2957:(2011)
2949:Cupola
2945:(2008)
2909:(2027)
2901:(2025)
2893:(2025)
2885:(2025)
2877:(2025)
2869:(2025)
2866:ALTIUS
2847:(2024)
2839:(2024)
2690:(2035)
2682:(2035)
2679:Athena
2666:(2029)
2658:(2026)
2648:Euclid
2636:CHEOPS
2618:Planck
2588:Eureca
2570:EXOSAT
2539:(2031)
2531:(2029)
2523:(2028)
2514:(2024)
2506:(2023)
2477:Philae
2449:Giotto
2434:(2031)
2400:ISEE-2
2214:Aurora
1984:Hopper
1945:Europa
1903:Ariane
1882:Skylon
1819:Active
1704:Kliper
1667:Avatar
1575:Dragon
1531:Active
1489:Spiral
1436:HOPE-X
1400:Ares V
1394:Ares I
1389:Angara
1363:SASSTO
1341:Vulcan
1314:Skylon
1303:RLV-TD
1249:CORONA
1210:Petrel
1168:Active
1069:9 June
1005:
974:9 June
952:(DLR).
886:
800:9 June
726:9 June
679:RETALT
377:canard
374:V-tail
301:stages
54:rocket
3249:SPICA
3044:EGNOS
2906:FORUM
2898:SMILE
2771:Swarm
2747:MetOp
2723:ERS-2
2717:ERS-1
2663:ARIEL
2655:PLATO
2612:CoRoT
2558:Cos-B
2521:rover
2431:Vigil
2355:GEWEX
2298:Pride
2256:ELIPS
2246:EGNOS
2014:OTRAG
1989:HOTOL
1683:SUSIE
1644:Orion
1474:Roton
1449:HOTOL
1426:Nexus
1037:(PDF)
1026:(PDF)
938:(PDF)
931:(PDF)
862:(4).
794:(PDF)
272:them.
211:ASTRA
166:like
156:small
121:reuse
104:(DLR)
52:This
3209:LOFT
3184:EChO
3164:CSTS
3139:AIDA
3082:YES2
2874:FLEX
2759:SMOS
2753:GOCE
2687:LISA
2630:Gaia
2511:Hera
2412:SOHO
2266:FLPP
2114:Vega
2019:SOAR
1979:Haas
1831:Vega
1736:X-33
1725:SOAR
1709:Lynx
1604:X-15
1464:MAKS
1233:Amur
1216:Skua
1144:and
1102:2015
1071:2015
1045:2015
1003:ISBN
976:2015
946:2014
914:2014
884:ISSN
802:2015
765:2015
728:2015
599:mass
565:Mars
561:Moon
491:Vega
471:Vega
469:and
363:nose
329:VTHL
279:CNES
265:CNES
246:NASA
244:and
170:and
168:Vega
162:and
123:for
3100:IXV
3070:ARD
2922:ISS
2594:ISO
2564:IUE
2219:ATV
2207:ESM
1699:H-2
1494:V-2
1454:K-1
876:doi
603:LEO
572:LOX
344:aft
323:in
256:or
242:ESA
172:SLS
66:or
3369::
2817:3B
2815:/
2813:3A
2811:/
2803:2C
2801:/
2799:2B
2797:/
2795:2A
2793:/
2785:1B
2783:/
2781:1A
2779:/
1088:.
1061:.
1028:.
997::
993:.
882:.
874:.
860:58
858:.
852:.
810:^
773:^
751:.
736:^
711:^
576:LH
473:.
248:.
184:A
177:A
2855:(
2475:/
2053:e
2046:t
2039:v
1928:5
1923:4
1918:3
1913:2
1908:1
1800:e
1793:t
1786:v
1744:*
1738:*
1732:*
1711:*
1679:*
1606:*
1595:*
1589:*
1583:*
1189:*
1134:e
1127:t
1120:v
1104:.
1073:.
1047:.
1011:.
978:.
916:.
890:.
878::
870::
804:.
767:.
730:.
578:2
574:/
415:f
209:(
174:.
158:,
87:)
81:(
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20:)
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