explorations systems development (esd) division overview
TRANSCRIPT
For NASA Internal Use – Predecisional
National Aeronautics and Space Administration
For NASA Internal Use – Predecisional
Explorations Systems Development
(ESD) Division Overview and Status
2014 ELV Payload Safety Workshop
Shandy McMillian
Office of Safety and Mission Assurance
Mission Support Division
December 2014
For NASA Internal Use – Predecisional
ESD Composition and Make-Up
• Successor to the Space Shuttle Program and the previous Constellation Program (CxP)
• Composed of 3 separate programs
‒ Ground Systems Development Office (GSDO) managed out of KSC
‒ Multi-Purpose Crewed Vehicle (MPCV)/Orion managed out of JSC
‒ Space Launch System (SLS) managed out of MSFC
• Cross-Program Integration managed by the Cross-Program Integration Team (CPIT) at NASA HQ
• Organizational structure is shown on the next slide
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For NASA Internal Use – Predecisional
SLS Overview
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• Heavy lift launch vehicle that will be capable of lifting humans, support systems, and payloads beyond Earth Orbit
• Intended to be an evolvable launch vehicle with increasing lift capacity from 70 metric tons (77 tons) to 130 metric tons (143 tons)
• Payload Fairing details are TBD (Exploration Upper Stage SRR Kick-off anticipated to occur in December 2014)
For NASA Internal Use – Predecisional
Comparison to Existing and Proposed Launch
Vehicles
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• SLS will be the largest launch vehicle built to date, as denoted in the comparison chart below
For NASA Internal Use – Predecisional
Orion-MPCV Overview
• Next generation multi-purpose crewed vehicle
• Will have the capability to carry from 2-4 persons for up to 21 days
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• Has the capability to evolve to support a six-person crew on an extended duration mission
• Comprised of 5 major elements (see functional description of each on the next slide)
• Launch Abort System (LAS)
• Crew Module (CM)
• Crew Module Adapter (CMA)
• European Service Module (ESM)
• Spacecraft Adapter (SA)
For NASA Internal Use – Predecisional
Orion-MPCV Overview (Continued)
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Crew Module (CM) Functions
The CM provides a habitable pressurized volume to
support crewmembers and cargo during all elements of
a given mission - from Launch Operations to Earth
Entry, Descent, Landing, and Recovery.
Service Module (SM) Functions
The SM, comprised of two subcomponents the Crew
Module Adapter (CMA) and the European Service
Module (ESM), provides services to the CM in the form
of propulsion, consumables storage, heat rejection and
power generation.
Orion Top Level Functions & Configuration
• The Orion Spacecraft will serve as the primary crew vehicle for NASA
Exploration Systems Development (ESD) missions in Low Earth Orbit
(LEO) and Beyond Earth Orbit (BEO). The vehicle will be capable of
conducting regular in-space operations in conjunction with payloads
delivered by the Space Launch System (SLS) Launch Vehicle for all
missions.
• Control Mass
– Gross Lift Off Mass (GLOM) 78,010 lbm
– Trans Lunar Insertion Mass 58,467 lbm
– Post Trans Lunar Insertion Mass 57,035 lbm
Launch Abort System (LAS) Functions
The LAS provides an abort capability to safely transport
the CM away from the launch vehicle stack in the event
of an emergency on the launch pad or during ascent.
Spacecraft Adapter (SA) Functions
• Provide structural connection to the launch vehicle
from ground operations through orbital injection
• Provide protection for SM components from
atmospheric loads and heating during first stage flight
For NASA Internal Use – Predecisional
Ground Systems Development Office (GSDO)
Overview
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• GSDO manages two complementary development and
modernization efforts
– Exploration Ground Systems (EGS)
– 21st Century Space Launch Complex (21CSLC)
• EGS development focuses on SLS and Orion (see next
slide for details)
– Ground systems and operations to prepare, assemble, test,
launch and recover Exploration elements
– Flexible approach to accommodate evolution of SLS and
future exploration elements
– Builds on investments made during Apollo, Shuttle, and
Constellation
• 21CSLC Initiative supports multi-use
– Investments to repair, upgrade and modernize infrastructure
– Intended to support multiple commercial and government
users
For NASA Internal Use – Predecisional
Current Mission Design Overview
• Current mission design set is comprised of two additional test flights, Exploration Flight Test-1 (EFT-1) (see next slide) and Ascent Abort-2 (AA-2), and two tactical missions, Exploration Mission-1 (EM-1) and EM-2
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• Programs have additional sizing requirements to enable accomplishment other possible future missions‒ Extensibility requirements are assessed at each milestone and are intended to
preserve the ability of the programs to accomplish future design reference missions
• Intent is to meet all Human Rating requirements to achieve full human rating certification for EM-2 in accordance with the requirements of NPR 8705.2B, NASA Human Rating Requirements For Space Systems
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Exploration Flight Test-1 (EFT-1) Mission Profile
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• Planned Launch Readiness Date – 12/4/2014 @ 7:05 EST
• 7th Launch of a Delta-IV Heavy Rocket and 28th launch of a Delta IV‒ Heaviest Delta IV Heavy Rocket to date
• Primary payload is the Orion Test Module coupled with a Service Module structure and fairing and topped by an inert Launch Abort System (LAS)
– Test Module is heavily sensored to allow for gathering of testing data
– Future EM and Service Module will be modified, if necessary, based on the results of the EFT-1 flight and will also incorporate the following changes:
• Modifications to the Parachute Assembly System (TBR) and TPS design (TBR)
• Addition of pressure control, Environmental Control and Life Support, and Air Revitalization Systems, along with Crew System Equipment
• European Service Module (ESA) Service Module equipped with active radiators, Shuttle-derived OMS-E Engine, and Solar Arrays
• Addition of an active LAS
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Exploration Flight Test-1 (EFT-1) Mission Profile
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Objectives and Mission Notes:• Successfully launch and deliver EFT-1 into the planned orbit• Demonstrate critical separation events during ascent and deorbit• Demonstrate Thermal Protection System (TPS) performance during high
energy return• Demonstrate descent, landing and recovery.• Successful data recording, analysis, and delivery of flight test data to
NASA in accordance with the EFT-1 Data Analysis Plan
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EM-1: Uncrewed Distant Retrograde Orbit
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Objectives and Mission Notes: • Demonstrate spacecraft systems performance prior to crewed flight• Demonstrate high speed entry (~11 km/s) and TPS performance prior to crewed
flight• Landing off the coast of California
SLS Configuration:• 5-seg SRBs and 4 RS-25D• Interim Cryogenic Propulsion Stage• 22x975 nmi (40.7x1806 km) insertion
orbit• 28.5 – 35 deg inclination parking orbit
2) Perigee Raise Maneuver (PRM)ICPS - 100x975 nmi(185x1806 km)
1) Launch
3) Trans-LunarInjection (TLI)ICPS
12) Entry &Landing
11) CM/SM SepEI-20 min
Total Mission Duration: 25-26 days
4) Outbound Trajectory Correction (OTC) burns
5) Outbound Powered Flyby (OPF) burn
Outbound: 7 days
8) Distant Retrograde orbitDeparture (DRD) burn
6) Distant Retrograde orbitInsertion (DRI) burn
7) Distant Retrograde Orbit ~37,797 nmi (~70,000 km)
DRO: 6 days
10) Return Trajectory Correction (RTC) burns
9) Return Powered Flyby (RPF) burn
Return: 12 days
For NASA Internal Use – Predecisional14
EM-2: Crewed (High) Lunar Orbit
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SLS Configuration:• 5-seg SRBs and 4 RS-25D• 22x975 nmi (40.7x1806 km) insertion orbit• 28.5 – 35 deg inclination parking orbit
1) Launch 2) Perigee Raise Maneuver (PRM)ICPS - 100x975 nmi(185x1806 km)
3) Trans-LunarInjection (TLI)ICPS
9) Entry &Landing
8) CM/SM SepEI-20 min
Total Mission Duration: 10-14 days
Objective and Mission Notes: • Demonstrate crewed (up to 4) flight beyond LEO• Demonstrate baseline Orion vehicle• TLI places Orion on a lunar flyby free-return trajectory
4b) Outbound Trajectory Correction (OTC) burns
Outbound: 3-6 days
5) Lunar OrbitInsertion (LOI)
4a) Outbound Trajectory Adjust (OTA)Orion
High Lunar Orbit (HLO) for 3 days54x5400 nmi (100x10,000 km)
6) Trans-EarthInjection (TEI)
Return: 3-6 days
7) Return Trajectory Correction (RTC) burns
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ESD Path to EM-1, EM-2
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FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20 FY21
Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1
ESD EM-1 / EM-2 Integrated Schedule
Element
HEO / ESD
GSDO
Veh. Integ. / Launch
Mobile Launcher
VAB
Pad B
Offline Proc.
Command, Ctrl, Comm & RangeOperations - LV Process.
- SC Process.
- Operations
- Landing & Recov.
Orion
EM1 (Uncrewed)
STA
EM2 (Crewed)
12/5
C-SRR
4/2
C-SDR APMC EFT-1
12/4
1/13
Design-to Sync Kickoff
8/21
Build-to Sync12/1 9/30
AA-212/15/19
EM-2 Crewed8/15/21
11/30
MCR
8/30
SRR/SDR
3/20
PDR
10/15
CDR
11/15
ESM CDR
11/3
OPI w/C3R SAR/ORR
12/1
OPI w/C3R ORD
3/21
ML-VAB w/C3R SAR/ORR4/17/17 ML-VAB w/C3R ORD
7/30
ML-PAD w/C3R SAR/ORR
10/27
ML-PAD w/C3R ORD
5/9
ML Struct Sys.Mod Start
3/31
ML StructMods Comp.
5/1
Umb.Inst.St.
7/11
Umb. InstallComplete
9/14
GSE Install Complete
Program Reserve
12/31
VAB Door
3/5
HB3 Demo Complete
3/3
VAB Platform Const. Start
4/1
V&V 4/25
Veh. Access Platform Comp.
9/15
10/3
Pad Infrastruct Const Start
1/2
Flame Trench Start
2/1
V&V
5/31
Flame Trench Comp
11/17
9/21
ML/VAB V&V
12/19 3/22
ML/PAD V&V
2/11
MPPF FacilityConstruct St.
10/30
LVO Element Readiness Date
7/18
MPPF Fac. Const. Cmplt.
9/6
MPPF ORD
11/1
Basic C&C
6/28
SCCS 1.0 9/19
SCCS2.0/2.1 Val.Complete
8/17
SCCS 3.0
10/18
SCCS 4.0
EM-1 SRM Aft Seg.,Exit Cone 3/2
5/22 SRM Fwd & Center Segments
6/26 FWD Assy
7/14 Em-1 Core 8/14 LVSA 8/16 MSA
10/13
EM-2 SRM AftSegment, FWD Assy
2/9
EM-2 Core
3/2
EM-1 CM/SM Need 7/21 ICPS
10/13
EM-2 CM/SM
3/2
EM-1 Ops11/9
xfer to Pad12/15
10/13EM-2 Ops
7/1
xfer to Pad8/16
EM-1 Recover
CSM Del.
9/308/13
EM-2 Recover8/17
6/18
PTR 2
11/17
PTR 3
7/27
MPCVSynch
5/15
ESMPDR
8/28
DeltaPDR
8/1
CDR(UR)
3/15
EM2 CDR (UR)
DDT&E
1/25
DAC1POD
B/L ERB
4/16
DAC1 POD KO
11/19
DAC2POD
Procurement6/10
DAC2 Close
5/1 CM5/25
Comp. Qual
11/30
11/30
AI&T
6/15
DAC1 POD(EM2)
12/1
12/1
EM1 SAR (UR)
6/18
DAC2Synch
10/27
Mate
1/1 Vehicle on dock at KSC
10/1 SM
10/1 Inert LAS
1/8
4/1
12/1Procurment/Fab
12/1CM Primary Struct. 7/1
11/30
Procurement
SM5/1
CM12/1
CM/SM AI&T2/1
Comp Qual
8/1
5/1PQ
2/1 HITL
M4/1 7/1
Veh on dockat KSC
9-10-2014
Status as of 7-31-2014
Launch Readiness Window
Integrated Ops
For NASA Internal Use – Predecisional
ESD Path to EM-1, EM-2
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FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20 FY21
Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1
ESD EM-1 / EM-2 Integrated Schedule
Element
SLS
Booster
Core Stage
Engines
- RS-25 Adaptation
- RS-25 Testing
- Engine Controller
SPIE
- MPCV Stage Adapter
- Launch Vehicle/Stage Adapter (LVSA)
- Interim Cryogenic Propulsion Stage (ICPS)
3/11
MCR
7/19
ASM
3/30
SRR/SDR
5/17
Brd reconvene
7/31
PDR Brd
7/22
CDR Brd
10/3
DCR Brd
9/14
DM-3
8/28
BRR PDR
4/2 8/6
CDRBrd
12/18
QM-1
12/3
QM-2
8/29
DCR Brd
3/2
Aft Skirt/SRM Aft Seg/Aft Exit Cone
5/22
SRM Fwd/Ctr Segs.
6/15
Fwd Assy
10/1
EM-2 H/WAft Skirt
2/8
Fwd Assy
10/17
ATP
6/15
SRR/SDR
12/21
PDR
8/1STAs Mfg/Assy/Instr.
7/1
CDR Brd
12/153/15Struct tests
10/3
DCR Brd
12/19
7/14
EM-1 H/W
2/9
EM-2 H/W
2/24Core Stage 1 MFG/Assy/Integration
9/25
B-2 Test Stand Const. Cmplt Activation
8/15
Available to ship to SSC
9/1 2/24Green Run
7/7
J-2X TestingStart
12/7
UCA
8/16
ContractDefinitization 11/25
RS-25 Eng Deliv(4/4R) Flt #1 [L-21M] 3/4
RS-25 Eng DelivFlt #2 (L-18M)
4/25
PPSC
Eng #1 Assy
12/15
IPSC
Production
7/15
FPSC
Eng #2 Assy
7/21 9/30
5/2
Cntrl SDR/CoDR
10/24
Cntrl PDR
4/30
Cntrl CDR
4/2
SRR
10/16
SDR
6/27
PDR
4/30
CDR Brd
8/15
DCR Brd
10/1
Design
12/21
Mfg
2/15
Design Cmplt
6/26
Fit Chk
1/31
EFT-1
8/16
EM-1
4/30
EM-2
10/1
MSFC Design
9/16
MSFC DesignComplete
STA mfg
2/3
Start Design by Prime Cont
7/15
STA TestStart
7/15
STA TestComp
8/1
IssueJFOC
12/3
Start Design@ Prime
Production
10/31
ContractDefinitization
7/21
EM-1 HW
1/15
EM-2 H/W
9-10-2014
Status as of 7-31-2014
For NASA Internal Use – Predecisional
General Notes on ELV Payload Safety
• Payload safety process for primary (e.g., Europa-Clipper) and secondary payloads (e.g., cubesats) flying on SLS is still in the formulation process
• Expect decision on process to occur after the upcoming ESD Design-to-Sync review early next year
• Payloads will need to comply with SLS-Spacecraft ICD requirements (TBR), as well as all ground processing requirements at KSC (e.g., KNPR 8715.3)
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