explorations systems development (esd) division overview

For NASA Internal Use – Predecisional

National Aeronautics and Space Administration


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


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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ESD Organization

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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)


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


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)


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


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


GSDO Integrated SLS/Orion Concept of Operations

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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


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


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


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


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


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


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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Questions?

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