An Update on SKYLON REACTION ENGINES LTD Alan Bond Managing Director & Chief Engineer Reaction Engines Ltd.
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An Update on SKYLON
R E A C T I O N E N G I N E S L T D
Alan Bond Managing Director & Chief Engineer
Reaction Engines Ltd.
R E A C T I O N E N G I N E S L T D
S K Y LO N O p e ra t i o n s
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S K Y LO N
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1990 The SKYLON spaceplane… the phoenix of HOTOL
1951 Skylon Sculpture Festival of Britain
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Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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S K Y LO N D 1
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Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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T h a l e s A l e n i a S p a c e S U S C o n c e p t D e s i g n
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Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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S K Y LO N & S U S M a x i m u m G e o s ta t i o n a r y Pe r fo r m a n c e
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SKYLON / SUS Mission
Maximum Mass of Satellite into
GTO (Tonnes)
Maximum Mass of Satellite into GEO
(With 320s SI apogee engine) (Tonnes)
300 km LEO deployment Reusable SUS, 7:1 resonance return transfer orbit (GTO)
5.58 (3.50)
185 km LEO deployment Reusable SUS, 9:1 resonance return transfer orbit
6.39 (4.0)
185 km deployment Expendable SUS, destructive re-entry
8.08 (5.07)
300 km LEO deployment Reusable SUS 5,900 km circular MEO EP satellite, 20 kW HE thruster, 157 day transit to GEO
N/A
(8.96 GTO equivalent)
5.61
Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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P r e f e r r e d S K Y L O N a n d C i v i l R u n w a y P o s i t i o n & O r i e n t a t i o n
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Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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S ta n d a r d G TO M i s s i o n ( 7 : 1 r e s o n a n c e )
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N 12
3
45
Perigee burn into GTO
Upper-stage LEO insertion and recovery
Skylon in 300km LEO, payload deployed1
Satellite serparates in GTOSatellite apogee burn into GEO
2345
Length = 83m Take-off Mass = 325 t Payload to LEO = 15 t Payload to GTO = 6.4 – 8t
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S K Y LO N / S U S Pe r fo r m a n c e i nto P l a n e ta r y Tra j e c to r i e s
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S A B R E E n g i n e
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T h e S A B R E E n g i n e
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Pre-Cooler
Turbine
Thrust Chambers
Bypass Duct
Air Intake
Compressor
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S A B R E / S K Y LO N D e v e l o p m e nt P r o g ra m m e
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P r e - c o o l e r P r o d u c t i o n
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P r e - c o o l e r Te s t i n g , B 9 C u l h a m S c i e n c e C e nt r e
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▪ Over 700 rig tests … over 300 engine pre-cooler tests ▪ -150°C cryogenic temperature ▪ Operation of pre-cooler & frost control system
▪ Steady state cryogenic cooling over a sustained period
▪ Thermo-mechanical & aerodynamic integrity
▪ Technical objectives of the ESA programme
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R E L E n g i n e Te c h n o l o g i e s
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Pre-cooler heat transfer augmentation 2009
Micro-channel high pressure Hx 2010
Silicon carbide high temperature Hx 2002
Air intake 2012
STILETTO staged combustion 2011
Contra-rotating turbine 2008
Advanced nozzles laboratory tests 2006
STERN E/D nozzle 2008
STRICT E/D nozzle 2010
Bell nozzle separation 2010
Air/hydrogen cooling 2010
LOX cooling 2010
STRIDENT nozzle 2012
Laboratory scale 1GW/m3 HX 1996
Wind tunnel Hx module 2002
First full scale pre-cooler module 2005
Pre-cooler frost control 2004
Complete pre-cooler 2012
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R E L Ve h i c l e Te c h n o l o g i e s
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Re-entry aerodynamics
CFRP truss structure
Ascent trajectory modelling
Mach 12 hypersonic shock tunnel
Avionics
Aeroshell TiSic truss structure
Subsonic wind tunnel
Mach 9 hypersonic wind tunnel
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S K Y LO N / S A B R E P r o g ra m m e
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S K Y LO N Sy s te m Re v i e w
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UK Space Agency independent review Sep 2010 • ESA providing technical support
• Almost 100 invitees attended two
day workshop
• Part of wider review including on site audit by ESA
Review Conclusions ‘no impediments or critical items have been identified for either the SKYLON vehicle or the SABRE engine that are a block to further developments’.
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P h a s e 3 S A B R E D e v e l o p m e nt
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SABRE
Phase 3
SKYLON
£10bn Programme
£6bn
£3.64bn
£0.36bn
• Phase 2 Phase 3 Phase 4
October 2023
3 ½ Years 9 ½ Years
October 2017
April 2014
January 2014
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U K G o v e r n m e nt G ra nt
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In July 2013 the UK government awarded REL £60M to develop the SABRE Engine
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Thank you
R E A C T I O N E N G I N E S L T D 10th Appleton Space Conference 21
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