astrophysics science division - luvoir engineering team update · 2018-11-27 · 4/29/2016 o1...

LUVOIR Engineering Team Update

27 November 2018

Agenda

• Study Schedule

• Architecture Status• LUVOIR-A

• LUVOIR-B

• Update on Study Deliverables

• Issues

27 November 2018 2STDT Face-to-Face Meeting

Study Schedule

27 November 2018 3

Deliverable Due Date Completed Completed On

M1Comments on Study Requirements and

Deliverables4/29/2016

O1 Initial Technology Gap Assessment 6/30/2016

O2 Update Technology Gap Assessments 6/30/2017

M4 Interim Report to NASA HQ 3/30/2018 3/26/2018

O3 Update Technology Gap Assessments 6/30/2018No longer required as of

4/19/2018

M6Draft Final Report due to Large Mission Concept

Independent Assessment Team (LCIT*)2/28/2019

M6’ First meeting of LCIT with STDT’s 3/2019

M6’’ Second meeting of LCIT with STDT’s 5/2019

M6’’’ LCIT final report to NASA HQ 6/2019

M7 STDT Final Report due to NASA HQ 6/2019

M8 HQ Submits final report to Decadal 7/2019

*LCIT process, charter, and schedule is still tentative and may change.STDT Face-to-Face Meeting

The LUVOIR Architectures

27 November 2018 STDT Face-to-Face Meeting 4

Architecture Diagram


LUVOIRMission



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Mission

Segment



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Mission

Segment

Element



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Optical

Telescope

Assembly

(OTA)

Extreme

Coronagraph

for Living Planetary

Systems (ECLIPS)

High

Definition

Imager

(HDI)

LUVOIR

Ultraviolet

Multi-Object

Spectrograph

(LUMOS)

Pollux

Payload

Articulation

System

(PAS)

Bus Sunshade

Mission

Segment

Element

Sub-systems



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Optical

Telescope

Assembly

(OTA)

Extreme

Coronagraph


Systems (ECLIPS)

High

Definition

Imager

(HDI)

LUVOIR

Ultraviolet

Multi-Object

Spectrograph

(LUMOS)

Pollux

Payload

Articulation

System

(PAS)

Bus Sunshade

Mission

Segment

Element

Sub-systems

Assemblies

Primary

Mirror

PMSAs PMBSS BSF

Secondary

Mirror

Aft-Optics

System

OTA

Avionics

SMA SMSS

TMA FSM AOSS

MEB PDU LMEB

TMSHarness



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Optical

Telescope

Assembly

(OTA)

Extreme

Coronagraph


Systems (ECLIPS)

High

Definition

Imager

(HDI)

LUVOIR

Ultraviolet

Multi-Object

Spectrograph

(LUMOS)

Pollux

Payload

Articulation

System

(PAS)

Bus Sunshade

Mission

Segment

Element

Sub-systems

Assemblies

Primary

Mirror

PMSAs PMBSS BSF

Secondary

Mirror

Aft-Optics

System

OTA

Avionics

SMA SMSS

TMA FSM AOSS

MEB PDU LMEB

VIPPS

2-axis

Gimbal

1-axis

Gimbal

Articulating

ArmTMSHarness



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Optical

Telescope

Assembly

(OTA)

Extreme

Coronagraph


Systems (ECLIPS)

High

Definition

Imager

(HDI)

LUVOIR

Ultraviolet

Multi-Object

Spectrograph

(LUMOS)

Pollux

Payload

Articulation

System

(PAS)

Bus Sunshade

Mission

Segment

Element

Sub-systems

Assemblies

Primary

Mirror

PMSAs PMBSS BSF

Secondary

Mirror

Aft-Optics

System

OTA

Avionics

SMA SMSS

TMA FSM AOSS

MEB PDU LMEB

VIPPS

2-axis

Gimbal

1-axis

Gimbal

Articulating

Arm

Structure TMS ACS C&DH Comm.

EPS Propulsion

TMSHarness



LUVOIR

Ground

Segment

Observatory

Segment

Launch

Segment

Payload

Element

Spacecraft

Element

Optical

Telescope

Assembly

(OTA)

Extreme

Coronagraph


Systems (ECLIPS)

High

Definition

Imager

(HDI)

LUVOIR

Ultraviolet

Multi-Object

Spectrograph

(LUMOS)

Pollux

Payload

Articulation

System

(PAS)

Bus Sunshade

Mission

Segment

Element

Sub-systems

Assemblies

Primary

Mirror

PMSAs PMBSS BSF

Secondary

Mirror

Aft-Optics

System

OTA

Avionics

SMA SMSS

TMA FSM AOSS

MEB PDU LMEB

VIPPS

2-axis

Gimbal

1-axis

Gimbal

Articulating

Arm

Structure TMS ACS C&DH Comm.

EPS Propulsion

Deployable

Boom

Systems

Blanket

AssembliesTMSHarness

LUVOIR-A


LUVOIR-A Spacecraft Element


Control

Moment

Gyroscopes

(4x)

Sunshade

Deployment

Booms

(4x)

Electrical

Power

System Avionics

Comm.

Star

Trackers

(4x)

LUVOIR-A Spacecraft Element


Roll-out

Solar

Arrays

(2x)

High-gain

Antenna

System

Separation

Ring

LUVOIR-A Payload Element


Instrument

Radiators

(270 K, 170 K)

*no longer

deployed*

Instrument

Radiator

(100 K)

HDI

LUVOIR BSF Design Update


OLD NEW

LUVOIR-B


LUVOIR-B Spacecraft Element


Control

Moment

Gyroscopes

(4x)

Sunshade

Deployment

Booms

(4x)

Electrical

Power

System

Avionics

Comm.

Star

Trackers

(4x)

LUVOIR-B Spacecraft Element


Roll-out

Solar

Arrays

(2x)

High-gain

Antenna

System

Separation

Ring

Thrusters

LUVOIR-B Payload Element


Instrument

Radiators

(270 K, 170 K)

Instrument

Radiator

(100 K)

ECLIPS-A/B

• UV Channel:• Imager only

• 3 Apodizers, covering 4-40 λ/D

• Five 10% science bands between 200-525 nm

• VIS Channel:• Imager, R140 IFS

• 4 APLC Apodizers, covering 3.5 –64 λ/D

• 1 VVC Apodizer, covering 2-40 λ/D

• Nine 10% science bands between 515-1030 nm


ECLIPS-A/B

• NIR Channel:• R70 IFS

• R200 Point-source spectrograph

• No Imager

• 4 APLC Apodizers, covering 3.5-64 λ/D

• 1 VVC Apodizer, covering 2-64 λ/D

• Eight 10% science bands between 1.0-2.0 µm


HDI-A

• FOV

• UVIS: 3.20 x 1.93’

• NIR: 3.31 x 1.95’

• Resolution:

• UVIS: 3.4 mas/pix

• NIR: 6.9 mas/pix

• Focal Planes:

• UVIS: 1.6 Gpix

• NIR: 0.4 Gpix

• Bandpass:

• UVIS: 200 nm - ~1.0 µm

• NIR: ~800 nm – 2.5 µm


HDI-B

• FOV

• UVIS: 2.69 x 1.78’

• NIR: 2.71 x 1.79’

• Resolution:

• UVIS: 6.4 mas/pix

• NIR: 12.9 mas/pix

• Focal Planes:

• UVIS: 0.4 Gpix

• NIR: 0.1 Gpix

• Bandpass:

• UVIS: 200 nm - ~1.0 µm

• NIR: ~800 nm – 2.5 µm


LUMOS-B

• Two Channel Instrument• MOS/Imager

• FUV MOS: 100 – 200 nm

• NUV/VIS MOS: 200 nm – 1.0 µm

• FUV Imager: 100 – 200 nm

• High-resolution Point source spectrograph: 100-200 nm

• FOV:• 2 x 2’ covered by a single MSA tile

of 840 x 480 shutters


Mass Status – LUVOIR-A


Projected (MEL not

yet finished)

Projected (MEL not

yet finished)

Allocation [kg] Estimate [kg] Difference [kg] Allocation [kg] Estimate [kg] Difference [kg]

Payload OTA Primary Mirror Segment Assemblies (All) 5488.82 7306.08 -1817.26 6098.69 9040.30 -2941.61

Payload OTA PM Backplane Support Structure (PMBSS) 2884.73 2913.53 -28.80 3864.02 3896.02 -32.00

Payload OTA Backplane Support Frame (BSF) 5311.41 3937.22 1374.19 7081.88 5275.58 1806.31

Payload OTA Secondary Mirror Assembly (SMA) 89.71 55.31 34.40 99.68 79.01 20.67

Payload OTA Secondar Mirror Support Stucture (SMSS) 279.09 266.80 12.29 398.70 381.15 17.56

Payload OTA Aft-Optics System (AOS) 348.86 188.45 160.41 498.38 269.21 229.17

Payload OTA Thermal Management System (TMS) 930.30 502.87 427.43 1329.00 718.39 610.61

Payload OTA Payload Power Distribution Unit (PPDU) 29.07 39.60 -10.53 41.53 56.57 -15.04

Payload OTA Payload Main Electronics Box (PMEB) 29.07 30.60 -1.53 41.53 43.71 -2.18

Payload OTA Laser Metrology Electronics Box (LMEB) 0.00 113.18 -113.18 0.00 161.69 -161.69

Payload OTA Harness 93.03 293.89 -200.86 132.90 419.85 -286.95

Payload PAS Vibration Isolation & Precision Pointing System (VIPPS) 186.06 75.08 110.98 265.80 107.26 158.54

Payload PAS Gimbal #1 139.55 46.17 93.38 199.35 65.95 133.40

Payload PAS Gimbal #2 0.00 45.00 -45.00 0.00 64.29 -64.29

Payload PAS Tower / Articulating Arm 232.58 41.01 191.57 332.25 58.58 273.67

Payload HDI High Definition Imager 662.84 663.85 -1.01 946.91 947.93 -1.02

Payload ECLIPS Extreme Coronagraph for Living Planetary Systems 751.22 675.44 75.78 1073.17 964.91 108.26

Payload LUMOS LUVOIR Multi-object Spectrograph 518.64 518.64 0.00 740.92 740.92 0.00

Payload Pollux Pollux 448.87 450.00 -1.13 641.24 642.90 -1.66

Payload Misc Miscellaneous Hardware 69.77 792.74 -722.97 99.68 1132.48 -1032.80

18493.62 18955.44 -461.82 23885.63 25066.68 -1181.05

Spacecraft Bus Structure 2814.16 1101.70 1712.46 4020.23 1573.86 2446.37

Spacecraft Bus Thermal Management System (TMS) 418.64 33.70 384.94 598.05 48.15 549.90

Spacecraft Bus Attitude Control System (ACS) 460.50 251.40 209.10 657.86 359.14 298.72

Spacecraft Bus Propulsion System 162.80 102.70 60.10 232.58 146.71 85.87

Spacecraft Bus Command & Data Handling (C&DH) 46.52 55.60 -9.08 66.45 79.43 -12.98

Spacecraft Bus Communications 69.77 68.54 1.23 99.68 97.91 1.77

Spacecraft Bus Electrical Power System (EPS) 616.32 703.63 -87.31 880.46 1005.19 -124.73

Spacecraft Bus Harness 189.90 88.15 101.75 271.28 125.93 145.35

Spacecraft Sunshade Deployable Boom Assemblies 346.52 384.50 -37.98 495.05 549.28 -54.23

Spacecraft Sunshade Blanket Assemblies 244.90 244.90 0.00 349.86 349.86 0.00

Spacecraft Misc Miscellaneous Hardware 116.29 108.71 7.58 166.13 155.30 10.83

Spacecraft Propellant Propellant 1501.77 2000.00 -498.23 1501.77 2000.00 -498.23

6988.09 5143.53 1844.56 9339.40 6490.76 2848.65

25481.71 24098.96 1382.75 33225.03 31557.43 1667.60

LV Capacity Need: 42076.57

SLS Block 2: 44300.00

LV Margin: 2223.43

Maximum Expected Value (MEV) Mass

Observatory Total:

Payload Totals:

Spacecraft Totals:

Current Best Estimate (CBE) MassAssemblySub-SystemElement

Mass Status – LUVOIR-B


Projected (MEL not

yet finished)

Projected (MEL not

yet finished)

Allocation [kg] Estimate [kg] Difference [kg] Allocation [kg] Estimate [kg] Difference [kg]

Payload OTA Primary Mirror Segment Assemblies (All) 1518.00 2483.25 -965.25 1897.49 3121.86 -1224.37

Payload OTA PM Backplane Support Structure (PMBSS) 898.44 958.04 -59.60 1203.52 1288.87 -85.35

Payload OTA Backplane Support Frame (BSF) 2257.63 2001.31 256.32 3010.18 2675.02 335.16

Payload OTA Secondary Mirror Assembly (SMA) 31.56 48.24 -16.68 39.45 60.76 -21.31

Payload OTA Secondar Mirror Support Stucture (SMSS) 374.85 340.49 34.36 535.50 486.41 49.09

Payload OTA Aft-Optics System (AOS) 110.25 158.98 -48.73 157.50 227.11 -69.61

Payload OTA Thermal Management System (TMS) 264.60 365.38 -100.78 378.00 521.97 -143.97

Payload OTA Payload Power Distribution Unit (PPDU) 28.88 39.60 -10.72 41.25 56.57 -15.32

Payload OTA Payload Main Electronics Box (PMEB) 28.88 30.60 -1.72 41.25 43.71 -2.46

Payload OTA Laser Metrology Electronics Box (LMEB) 0.00 59.10 -59.10 0.00 84.43 -84.43

Payload OTA Harness 83.94 104.41 -20.47 119.91 149.16 -29.25

Payload PAS Vibration Isolation & Precision Pointing System (VIPPS) 183.75 75.08 108.67 262.50 107.26 155.24

Payload PAS Gimbal #1 139.13 46.17 92.96 198.75 65.95 132.80

Payload PAS Gimbal #2 0.00 45.00 -45.00 0.00 64.29 -64.29

Payload PAS Tower / Articulating Arm 73.50 5.09 68.42 105.00 7.26 97.74

Payload HDI High Definition Imager 455.00 462.17 -7.17 650.00 660.24 -10.24

Payload ECLIPS Extreme Coronagraph for Living Planetary Systems 751.22 751.22 0.00 1073.17 1073.17 0.00

Payload LUMOS LUVOIR Multi-object Spectrograph 518.64 518.64 0.00 740.92 740.92 0.00

Payload Misc Miscellaneous Hardware 52.50 338.04 -285.54 75.00 482.91 -407.91

7770.77 8830.78 -1060.01 10529.39 11917.86 -1388.47

Spacecraft Bus Structure 889.35 889.35 0.00 1270.50 1270.50 0.00

Spacecraft Bus Thermal Management System (TMS) 94.50 33.70 60.80 135.00 48.14 86.86

Spacecraft Bus Attitude Control System (ACS) 103.95 251.40 -147.45 148.50 359.14 -210.64

Spacecraft Bus Propulsion System 51.45 102.70 -51.25 73.50 146.71 -73.21

Spacecraft Bus Command & Data Handling (C&DH) 42.00 55.60 -13.60 60.00 79.43 -19.43

Spacecraft Bus Communications 44.63 68.54 -23.91 63.75 97.91 -34.16

Spacecraft Bus Electrical Power System (EPS) 139.13 703.63 -564.50 198.75 1005.19 -806.44

Spacecraft Bus Harness 58.80 88.15 -29.35 84.00 125.93 -41.93

Spacecraft Sunshade Deployable Boom Assemblies 342.00 384.50 -42.50 488.57 549.28 -60.71

Spacecraft Sunshade Blanket Assemblies 185.00 244.90 -59.90 264.29 349.86 -85.57

Spacecraft Misc Miscellaneous Hardware 52.50 52.50 0.00 75.00 75.00 0.00

Spacecraft Propellant Propellant 540.00 986.10 -446.10 540.00 540.00 0.00

2543.31 3861.07 -1317.76 3401.86 4647.09 -1245.23

10314.08 12691.85 -2377.77 13931.25 16564.95 -2633.70

LV Capacity Need: 22086.60

SLS Block 1B: 37000.00

LV Margin: 14913.40

Current Best Estimate (CBE) Mass Maximum Expected Value (MEV) Mass

Payload Totals:

Spacecraft Totals:

Total:

Element Sub-System Assembly

Update On Study Deliverables


Internal Cost Estimates

• All forms submitted to Goddard’s Resource Analysis Office (RAO) on 11/16

• RAO performs parametric cost modeling using high-level cost-estimation relationships (CERs)

• Relate system quantities such as mass, volume, schedule, data rate, pointing accuracy, etc. to cost

• Relatively agnostic to actual hardware implementation

• Forms submitted:

• 2 Mission-level forms (A, B)

• 2 OTA forms (A, B, include Payload Articulation Systems)

• 2 HDI forms (A, B)

• 2 ECLIPS forms (A, B)

• 2 LUMOS forms (A, B)

• 1 Pollux form (A)

• 2 Spacecraft Bus forms (A, B)

• 2 Sunshade forms (A, B)



• Began submitting Master Equipment Lists (MELs) to Goddard’s Cost Estimating, Modeling, and Analysis (CEMA) group

• CEMA also uses parametric cost modeling, but at the lower hardware level

• They’ll use analogous hardware and CERs to cost, for example, each mirror in HDI individually, rather than the instrument as a whole

• Use models and historical data to estimate development, integration, and personnel costs associated with each piece of hardware



• Both groups will provide estimated costs for WBS elements 05 and 06 (Payload and Spacecraft), and wrap factors for elements 01-04 and 07-11 to determine total mission cost

• Both groups will provide a point-design cost for each architecture, as well as an S-curve with confidence-levels indicated

• That is, each group will do a limited cost-risk analysis

• Should have all RAO results, and most (but not all) CEMA results back for CML4 deadline


System LUVOIR-A LUVOIR-B

OTA (including Payload

Articulation System)

Under Review by

Engineering TeamSubmitted

HDI Submitted Submitted

ECLIPSUnder Review by

Engineering TeamIn Progress

LUMOS Not Started In Progress

Spacecraft (includes Bus

and Sunshade)

Under Review by

Engineering TeamIn Progress

MEL Status


MEL Example


Issues


Vector Vortex Coronagraph

• Recently became aware of a limitation of vector vortex coronagraphs

• Currently baselined as primary coronagraph for LUVOIR-B

• Still gathering information on the topic, so final impact / criticality is not yet known

• Want to give STDT a heads-up



• Issue: Current limitations in liquid crystal mask fabrication require the use of circular polarizers to reduce contrast leakage

• Impact: As currently implemented, a VVC would require a 50% throughput reduction in the coronagraph, reducing exoplanet yields accordingly



• Mitigation: Four options…1. Retain current operational assumption of no

polarizers in beam path with vortex coronagraph• Throughput and yields remain unaffected

• Take a TRL-hit that requires additional development of either liquid crystal masks, or scalar vortex masks

2. Retain current operational assumption of no polarizers in beam path with APLC coronagraph• Throughput and TRL remains unaffected

• Exoplanet yield is reduced



• Mitigation: Four options…(cont.)3. Adopt single polarization operation with a vector

vortex coronagraph• TRL remains the same

• Throughput is reduced by 50%, affecting exoplanet yields

4. Adopt single polarization operation, convert UV channel into a second VIS channel that operates simultaneously in other polarization• Throughput and TRL remains the same

• Exoplanet yields improve slightly

• Loss of UV exoplanet science (200-350 nm)

• Note: this is current HabEx baseline. Drop the “red” channel and convert to second “blue” channel to run two polarizations simultaneously



• Summary:

• *It’s unclear what the actual TRL hit would be. HabEx team claims the existing VVC

technology is TRL 5. LUVOIR has claimed both VVC and APLC are TRL 3.

• HabEx team believes dual polarization liquid crystal masks and scalar vortex

masks are TRL 2.

• Hope to discuss this on Thursday at our joint meeting.


OptionSingle vs. Dual

Polarization

Primary

Coronagraph

Type

Coronagraph

TRL

(currently 3*)

ExoEarth

Candidate

Yield

Coronagraph

Channels

1 Dual

Vortex

(vector or

scalar)

~2 28 UV, VIS, NIR

2 Dual APLC 3* ~16 UV, VIS, NIR

3 Single Vector Vortex 3* 21 UV, VIS, NIR

4 Single Vector Vortex 3* 29 VIS, VIS, NIR

Questions?


astrophysics science division - luvoir engineering team update · 2018-11-27 · 4/29/2016 o1...

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