on the SKYLON Reusable Spaceplane · DLR Film Cooling Test Facility at P8 Lampoldshausen nozzle...
Transcript of on the SKYLON Reusable Spaceplane · DLR Film Cooling Test Facility at P8 Lampoldshausen nozzle...
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Progress
on the
SKYLON Reusable Spaceplane
7th Appleton Space Conference
8 December 2011
Alan Bond Managing Director
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SKYLON C1
12 tonnes to LEO
10 tonnes to ISS
200m3 payload bay
4.6m diameter payload
Being revised to D1
Payload 15 tonnes to LEO
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Headquarters Design and Test
Facilities
Culham Science Centre
Sheet metalwork
& fabrication
Wantage Experimental production
Abingdon Precision engineering
Newbury
Company Structure (April 2011)
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Progress on SABRE
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Air Intake
Precooler
Compressor
Bypass Duct
Thrust Chambers
Turbine
SABRE-3 Engine
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The SABRE Engine Cycle
A helium loop provides the intermediate cycle.
In rocket mode LOX replaces the air fed to the combustion
chamber.
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Rotors 2 & 4
Rotors 1 & 3
Inlet Plenum & IGV Assembly
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Experimental Contra-rotating
Stator-less Turbine Installation
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STRICT Thrust Chamber
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E-D Nozzle Test Program (STERN)
(Joint program Uni. of Bristol and Airborne Engineering)
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STERN Thrust Chamber Firing
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Reaction Engines Testing
J-site at Westcott
Joint programme with
Airborne Engineering
Thrust stand for Low-NOx
and Strict Programmes
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Strict Engine Test Firing – June 2011
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Test LCT-T01-4 @ pc=70 bar 8kg/s LOX cooling
Test bench P8, Lampoldshausen Germany
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DLR Film Cooling Test Facility at P8 Lampoldshausen
nozzle
supply film injector
supply line GH2
measurement segment
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Precooler Geometry
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Matrix Production
The prototype pre-cooler will be made from over 16,000 thin-walled Inconel tubes.
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Reaction Engines’ Radley Road (Abingdon)
Facility
All incoming tubes are inspected and processed prior to module assembly.
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Pre-Cooler Construction
A production module
under construction
Header tube
installation
Header/matrix tube
brazed joints Vacuum brazing
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Precooler Modules
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Pre-Cooler Testing at Reaction Engines B9
Circulator
VIPER 535
Pre-Cooler
LN2 Reservoir
Helium Flow
T = 96 K
P = 150 Bar
Air Flow
T = ambient
T = 260 K
T = 130 K
LN2
Pre-Cooler By-Pass
Temperature
Control Bypass
Pre-Cooler Stop Valve
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Pre-Cooler Testing
The Pre-Cooler will be tested at REL’s B9 test site using a VIPER 522 jet engine.
REL’s B9 installation with VIPER and
‘dummy’ pre-cooler assembly.
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High Pressure Helium Loop at B9
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Progress on SKYLON
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SKYLON D1
D1 requirements are now established and validated.
Configuration revision proceeds: a fully trimmed solution has been found,
but it will require further study before it can be finalised.
External contributions to D1 design (expand available skill base):
- Aerodyanmic modelling
- Structure loads analysis
- Payload interface
- Avionics and electrical power
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SKYLON D1
Airframe Support Studies
Re-entry Modelling with DLR Braunschweig using TAU CFD code
Aeroshell Material with Lateral Logic and Pyromeral
Titanium Matrix Composite Struts with TISICS Ltd (TSB supported Research)
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Phase 3 Programme
The Phase 3 Objectives
(30 month Programme)
Raise engine technology to TRL 6 through
ground testing.
Complete the design of the SABRE4 to
manufacturing drawings.
Ensure that the vehicle requirements and
SABRE4 engine design are compatible.
Flight test the nacelle design (desirable).
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Nacelle Flight Test Vehicle
Length ≈ 9m
Span ≈ 3.5m
Mass ≈ 1000kg
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Phase 3 Cost Estimate
Total Engine Programme (with NTV) £220m
Which is comprised by:-
Airframe requirement studies £6
Preparation for Phase 4 £30m
Engine technology demonstration £30m
SABRE4 design £134m
NTV £20m
The engine is the long lead item but the vehicle system design must
begin soon in order to meet entry to service in 2021-2022
Phase 3 Programme
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SKYLON Review
UK Space Agency independent review
ESA providing technical support
Almost 100 invitees attended two day workshop
(Sept 2010)
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’.