COBRA Main Engine Proj - NASA · SMV/SOV International STAS 3B Results ... • Engine Operation &...
Transcript of COBRA Main Engine Proj - NASA · SMV/SOV International STAS 3B Results ... • Engine Operation &...
COBRA Main Engine ProjNAS8-01108
AIAA/IAF Symposiumon Future RLV's
12 April 2002
Jim SnoddySteve Sides
P&W-Aerojet Propulsion Associates
(A Joint Venture)
https://ntrs.nasa.gov/search.jsp?R=20020085154 2018-06-10T23:42:00+00:00Z
COBRA MAIN ENGINE PROJECT TEAM NAS8-01108/01083PRATT & WHITNEY- AEROJET PROPULSION ASSOCIATES Generation RLV
IEngineSystemsManager
KathyKynard/UP30
(256)544-7439721-26-22
NASAProjectManagerlCOTR721.26-20
JimSnoddr/UP30
(256)5444972Cell 256)651-3700
ResidentOffice t
@WestPalmBeach
BillPoweWUP30
(561)796-6132Cell(561)236-1560
LeadSystemEngineer /
TomByrd/UP30 1(256)544-7147
I
AssistantProjectManager
RandyForsythe/UP30
(256)544-2456
ProjectOfficeSupport
I °
L_ManagementSupportAssistance
AmyrebeccaShockley/Inlinity
(256)544.4997
m
mmm mm am aim i l
PowerheadManager I
EricTepool/UP30
(256)544-3196721-26.23
Contractor Project ManagerRick Bachtel/Pratt
(561) 796-9O67a
AJ_istant Project ManagerSteve Sides/Pratt(561) 796-2611
|Deputy Preject Manager
Dick Johnaon/Aerojet(916) 355-4622
|Chief Engineer
Tom Kmiec/Pratt(561)796.4059
IDeputy Chief Engineer ]
Scott Sieger/Aerojet I(916) 355-3353
I
] Pratt Regional Manager IHuntsville/Vie Giuliano
(256) 721-2422
I....._ IAerojet Director Space Propulsion
ThrustChamberAssemblyManager[ [ Huntsville/Carla Bossard
MikeShadoan/UP30 [ [ (256)837-3982
(256)544-5276 |
721-26.24 I
12 April 02 2
ROADMAP - NRA 8-27 THROUGH NRA 8-30.A.N_n_RFYON_n Generation RLV
SSME StudiesXLR129
RL10 FamilyTitian Propulsion
ALS/NLSDC-X, DC-XA
SSME-AT
X-33 ActivityIHPRPT
EELVSMV/SOV
InternationalSTAS 3B Results
2010
Operational.,2GRLV -"
r
NRA 8-27 Vehicle PrimesBoeing
Lockheed Martin
Kelly AerospaceOrbital Sciences
Space AccessAndrews Space
2005-2010
2GRLV
FSD Program
Initial
2GRLV Engine Options
DBFRSC
DBFFSC
SBFRSC
SBORSC
SPLTEX
SBFRGG
Phase II
2003-2005
ContinuedRisk Reduction
Prototype Engine TestFSD SRR
ContractNAS8-00168
Phase I
2001.2003
NRA 8-30
Cycle I Base &Option
NRA 8-30 'Cycle 1'Candidates
SBFRSC
SBORSC
SPLTEX
NR/_8-3oContract
NAS8-011 O8
NRA 8-30 'Cycle 1'
SBFRSC -COBRA
SPLTEX-RLX
DBFRSC - Dual Burner Fuel Rich Staged Combustion (H2/O2)
DBFFSC - Dual Burner Full Flow Staged Combustion (H2/O2)
SBFRSC - Single Burner Fuel Rich Staged Combustion (H2/O2)
SBORSC - Single Burner Oxidizer Rich Stage Combustion (RP/O2)
SPLTEX - Split Expander (H2/O2)
SBFRGG - Single Burner Fuel Rich Gas Generator (H2/O2)
12 April 02 3
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COBRA PROTO-TYPE ENGINE APPROACHENABLES MISSION SUCCESS Generation RLV
• Requirements
- Propulsion Systems Requirement Document (PSRD) Traceable to the SynthesizedArchitecture Requirements (SAR) and both are Full Scale Development (FSD)
Requirements
• COBRA Engine Requirements Traceable to PSRD
- COBRA Engine System Proceeding to Configuration Control
,, SRR Conducted
,, PDR Conducted
,, Powerhead Test in Option II
,, CDR end of Option II
• Design and Development Approach
- COBRA Engine System Integrates Risk Reduction Technologies with Engine Cycle
- COBRA Engine System Design Fidelity Enables
• Engine System Relevant Environments Characterization
• Risk Reduction Technology Demonstration in a Relevant Environment
• Engine Reliability Demonstration to Allow Traceability to FSD
• Engine Operation & Maintenance Demonstration to Allow Traceability to FSD
• Engine Manufacturing Demonstration
• Engine Performance Verification at Thrust Level Representative for a Wide Scale
12 April 02
Design Process & Control are FSD Applicable (e.g., EEE Parts, Fracture Control, Ops
Concept) 5
COBRA PROVIDES QUICK, LOW COST DEMO OFCYCLF AN_D TECHNOLOGIES °°-"°°_
Program PDR(_Milestones
800K
" COBRA
ine W/,=
40K
Cycle II and Phase
12 April 02 6
COBRA CYCLE I RISK REDUCTION SUPPORTSTECHNOLOGY NEEDS FOR 2GRLV °--"°°_
Co-Optimized Booster for Reusable Applications
2nd Gen RLV Focus
• Crew and vehicle safety
• Reliability• Operability• Maintainability• Low payload cost
Ill=,,._
2nd Gen RLV _p_
Architectures SupportedDerived shuttle
• Evolved shuttle• TSTO
Cycle I Risk Reduction
• Systems engineering• EHMS architecture/safety sensor)
• Full-scale 600K preburner• Full-scale 600K main case
• 40K main injector• 40K main chamber• 40K LOX-cooled nozzle section
• LOX and fuel boost pumps
• High pressure turbopumps• Smart valves
• Full-scale nozzle fabrication
• Main LOX valve development
• Lightweight material development• Integrated powerhead testing• Main combustion chamber
• Preburner LOX valve
12 April 02 7
COBRA FEATURES GROUNDED FROMNRA 8-27 STUDY Generation RLV
COBRA Safety
Single prebumer cycle
COBBA ReUsabtii_/0Pera_ili_ _ COBRA Risk Reduction Activities
Powerduct main case
for lightest weightand fewest hot gas
joints
Mature SSME-AT
)umps increase
safety and reduce risk
Main injectorreduces touch labor
and has no partswhich can come loose
Long life Liner
Milled channel
regenerativelycooled nozzle -70:1
adopted from SSME
nozzle upgrade
12 April 02 8
ACHIEVING ENGINE SAFETY
Design for Safety• Single fuel rich preburner• Fail safe powerduct• External heat exchanger• Cool turbine temperatures
Technologies for Safety• Advanced engine health monitoring• Channel wall nozzle• Combustion Device liners pmo_w
N_,=m=
Maturity for Safety• Early hardware testing• Demonstrated technologies• Mature turbomachinery (ATD)
Generation RLV
12 April 02 9
RLX CYCLE I RISK R DUCTION SUPPORTST_CHNOLOGY N_=FDS FOR 2GRLV o..o_,,oo_v
Rocket, Liquid, Expander (RLX) - Split Expander (SPL TEX) Cycle
2nd Gen RLV
• Crew and vehicle safety
• Reliability• Low payload cost• Maintainability
2nd Gen RLV
Architectures Supported
• Orbiter
• TSTO (upper stage)
Cycle I Risk Reduction
• Heat transferenhancementdemonstration
12 April 02 10
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NRA 8-30 TECHNOLOGIES ARE ENABLING TO
2GRLV SAFETY GOALS °'°-"°°_v
Benefit of COBRA Safety Risk Reduction Technologies
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Component technologies System technologies
12 April 02 12
NRA 8-30 CYCLE I TECHNOLOGY ROADMAP Generation RLV
1.4.7 Propulsion1,4,7.1 Project Management1.4.7.2 PropuLsion Systems Eng1.4.7.3 Cobra Engine
1.4.7.3.1.1 Prototype & Risk reduction1.4.7.3.1,1.1 Combustion Devices
1.4.7,3.1.1.1.1 Prebumer1.4.7.3.1.1.1.1.1 Subscale1.4.7.3,1,1.1.1.2 Proto
1.4.7.3.1.1.1.2 Powerball
1.4.7.3.1,1.1.3 Injector1.4.7.3.1.1.1.1.3.1 Unlelement1.4.7.3.1,1.1.1.3.2 SubQcale1.4.7.3.1.1.1.1.3.3 Prototype
1,4,7,3.1.1.1.4 Combustion Chamber1.4.7.3.1.1,1.4.1 Subakcale1.4.7.3,1.1.1.4.2 Prototype1.4.7,3.1.1.1.4.3 Fabrication
1.4.7.3.1.1.1.5 Nozzle1.4.7,3.1,1.1.5.1 Sul:_cale1.4.7,3.1.1.1.5.2 Fabrication1..4.7,3.1.1.1.5.3 Prototype
1.4.7.3,1.1.2 Turbomaehinery1,4.7.3.1.1.2.1 ATD Modification
LOXLH2
1.4.7.3.1.2.2.2 Boost Pumps
1,4.7.3.1.1.2.2,1 LOXComponentPrcto
1.4.7.3.1.1.2.2.2 LH2ComponentProto
1.4.7 3.1.1.3 Controls14.7.3.1.1.3.2 Controller1.4.7.3.1.1.3.3 Actuators
1.4.7.3.1 1,3.4 Valves
1,4,7.3.1.1.4 Externals1,4.7.3.1.1,4,2 Plumbing
1.4.7.3,1.1.5 EHMSProtoComponent
1.4,7.3.1.1.6 Light Weight Matedal Dev1.4.7.3.1.1.6.2 Plumbing & Valves1.4.7.3.1.1.6.3 Chamber Structural Jacket
1,4.7.3.1.1,7 Engine/Subsystem Test1.4.7.3.1.1.7.1 Powerhead Test
1.4.7.3.1.3 MCC Heat Transfer for RLX1.4.7.3.1.3.1 Lab. Dev,1.4.7.3.1.3.2 Subscale Dev/Test1.4.7.3.1.3.3 Full Scale Day
_1_ End of Base End of Option
i ....
U :Ill _
L ; .........._1 _ ........................................
16 Technology Needs
i Proto engine
Subscale
12 April 02 13
COBRA PROGRAMAligns Risk Reduction Data with FSD decisions-Uses Building Block Approa
I
Program milestonesATP RRR11
,I_SRR
Design
RR and comp test
Prototype engine development
Advanced development leadingto FSD
Flight qualification
Certification testing
Life extension engine testing
Technology readiness levels
Proto1
protodesignATP
II I
PDR _:SD CD_ lOG
_F i.ISp Decis_n
FSD ATp
Proto CDR
PH test
RLX MCC HTst
FETT1
1st'
Cert
I
e
12 April 02 14