Goddard Space Flight Center HST Program · PDF fileAperture door Secondary ... Soft Capture...

Hubble Space Telescope Program

1101907_PMB_STUC.ppt

Goddard Space Flight Center

HST Program StatusPresentation to:

Space Telescope User’s Committee

Preston M. BurchProgram Manager

October 19, 2007



Goddard Space Flight Center Topics

● Program Update

● Observatory Health

● SM4 Preparations and Status




HST Program Status(Since April 13, 2007)

● HST SM4 launch date moved up one month to August 2008 (was September 10, 2008)

– Still manifested on OV-104 (Atlantis)– SM4 development work on schedule– We are now at L minus 10 months

● HQ Science Mission Directorate reviewed HSTP recommended SM4 manifest content and priorities, directed minor change (FGS)

● EVA Working Group developed new EVA timeline– EVA days 1 and 2 are swapped– NOBL 5 removed from timeline

● Recently conducted NBL 07.3 (6 EVA days of runs), SM4 Crew Familiarization #1, Safety TIM, POWG, Flight Techniques Panel Meeting, Sim #1 (Rendezvous/Capture), Sim #2 (Gyros & Batteries), Sim #3 (WFC3 & Batteries), Sim #4 (COS & ACS-R), and Center Directors’ Quarterly Review

● Conducting Mini-POP 08-1 to assess FY09 Budget submission to OMB guidelines for SM4 development and post-SM4 operations

● Completed recovery from safemode events:– Gyro #2 failure on August 31– NICMOS safemode on September 1



Goddard Space Flight Center Major Mission Integration Milestones

● Preliminary Avionics Review June 28, 2007 Complete

● Baseline in Flight Definition/Requirement Doc. (FDRD) June 29, 2007 Complete

● Final Bay IPT Aug 15, 2007 Complete

● Cargo Integration Review Dry (CIRD)-Run (IPT) Sept 12, 2007 Complete

● Cargo Integration Review (CIR) Oct 15-19, 2007

● Flight Planning/Stowage Review (FPSR) (IPT) Nov 14, 2007

● Flight Operations Review (FOR) Feb 25, 2008

● Crew Equipment Interface Test (CEIT) May 9, 2008

● Bench Review June 26, 2008

● Payload Readiness Review (PRR) June 28, 2008

● Flight Readiness Review (FRR) July 24, 2008

● Payload End-to-End Pad test Aug 1, 2008

● Launch Aug 7, 2008




HST Servicing Mission 4Planned Mission Manifest and Priorities

Manifest in Priority Order1. RSUs (Gyros)2. WFC33. COS4. Battery Modules5. FGS2RR6. STIS Repair7. ACS Repair8. NOBL 89. NOBL 510. NOBL 7

Note: SCM and Reboost are parallel activities that do not contend with other EVA tasks and, therefore, do not affect priorities



Goddard Space Flight Center SM4 Manifest Rationale

Restores unique functionality of STIS: Imaging spectroscopy at full angular resolution of HST, high-resolution UV spectroscopy from 115 to 320nm; resolving power as high as 200,000; high-time-resolution (128 µs) UV spectroscopy and imaging, very high S/N visible spectrophotometry

STIS Repair

Replaces FGS-2R which has degraded star selector encoder LED (predicted unusable in 2011); FGS-3 bearings predicted usable until 2017; operational work-arounds available if only two, or even one, FGS available

FGS2RR

Provides additional margin to science altitude floorReboost

Provides cooperative docking system for future spacecraft to increase probability of eventual de-orbit mission success

SCM

Prevents further degradation of MLI from impacting temps of equipment in Bay 7 and adjacent bays

NOBL 7

Provides cooling of SSRs and MATs that will allow relaxation of roll restrictions and high data volume; more options for operational management of equipment in Bay 5 than Bay 8

NOBL 5

Provides cooling of PSEA that will extend life and allow use of +V3 sunpoint; very limited options for operational management of equipment in Bay 8; pointing restrictions would seriously impact science scheduling

NOBL 8

Restores unique functionality of ACS CCDs: Unexcelled performance in visible-red, best-ever coronagraph on HST

ACS Repair

Current capacity (304 Ah) approximately 58% of nameplate capacity (528 Ah); batteries will be 20 years old at SM4 (5 year on-orbit spec.); present capacity trend is flat

Batteries

Superb point-source, low- and medium-resolution UV spectrographCOS

HST’s first UV-IR panchromatic wide-field camera and wide-field IR imager; discovery efficiencies 40x over ACS in UV/blue,15-20x over NICMOS in IR

WFC3

Replaces failed gyros #2, #3 & #5, anomalous gyro #6, high run time gyros #1 and #4RSUs




HST SM4 EVA TimelineFor HST Program Planning Development Only

Priority Task Times1. RSUs (3) 3:152. WFC3 3:053. COS 2:254. Battery Modules (2) 1:50 ea5. FGS 2 3:056. STIS Repair 3:157. ACS - part I 2:15

- part II 0:308. NOBL 8 0:509. NOBL 5 0:5010. NOBL 711. SCM 0:1512. Reboost



Goddard Space Flight CenterHST Servicing Mission 4

Shortened Mission Scenarios

RSUs (3), WFC3, COS, Batteries (2 modules), ACS Repair, STIS Repair, NOBLs (8, 5), SCM4.5**

RSUs (2+), WFC3, COS, Batteries (1 module), STIS Repair, NOBL 8,SCM(2)

RSUs (3), WFC3, COS, Batteries (2 modules), ACS Repair, STIS Repair, NOBL 8, FGS2, NOBL 5, SCM5

RSUs (3), WFC3, COS, Batteries (2 modules), STIS Repair, NOBLs (8, 5), SCM(2)

RSUs (3), WFC3, COS, Batteries (2 modules), ACS Repair, NOBL 8, FGS2, SCM(1)4*

RSUs (2+), WFC3, COS, Batteries (1 module), ACS Repair, NOBLs (8, 5), SCM(1)3*

RSUs (2+), WFC3, COS, Batteries (1 module), SCM2

RSUs (2 or more), WFC3, SCM1

ORU/ORI Change-OutEVA Days

* Choice between ACS and STIS repair in 3 and 4 EVA scenarios to be made NLT FOR** 4.5 EVA scenario may be required by OBSS focused inspection



Goddard Space Flight CenterShortened Mission Scenarios

EVAs R

emaining

Nominal PlanACS-R pt. 2, FGSCOS, NOBLs 8, 5

WFC3, 2nd BMA, NOBL 82 RSUs, WFC3, SCM1

Nominal PlanCOS, (ACS-R &

FGS or STIS-R & NOBL 5), NOBL 8

WFC3, COS, ACS-R, NOBL 8

2 RSUs, WFC3, COS, 1 BMA, SCM2

Nominal PlanWFC3, COS, (ACS-R & FGS or STIS-R & NOBL 5), 2nd BMA,

NOBL 8

2 RSUs, WFC3, COS, 1 BMA, (ACS-R &

NOBL 5 or STIS-R), NOBL 8, SCM

3

Nominal Plan3 RSUs, WFC3, COS,

2 BMAs, (ACS-R & FGS or STIS-R & NOBL 5),

NOBLs 8, SCM4

Nominal Plan5

4(3 RSUs, WFC3,

COS, 2 BMAs, ACS-R pt. 1, STIS-R, NOBL 8, SCM)

3(3 RSUs, WFC3, COS, 2 BMAs, ACS-R pt. 1,

SCM)

2(3 RSUs, WFC3, 2

BMAs, SCM)

1(3 RSUs, 1 BMA,

SCM)

0

Planned EVAs Completed




HST Spacecraft HealthHigh gain antenna

Aperture doorSecondary

mirror

Primary mirror

Equipment Section– Degraded MLI:

Install NOBLs on Bays 5, 7, 8 in SM4

Fine Guidance Sensors– FGS2R: degrading servo LED– FGS3: degrading bearings– Replace one FGS on SM4

Axial Scientific Instruments

– STIS, failed 8/04– STIS Repair on SM4– ACS CCD Imaging

failed 1/07– ACS Repair on SM4– Install COS on SM4

Rate Sensor Units– Gyros 2, 3, and 5 failed:

replace all 6 gyros on SM4

Solar Arrays

Batteries– Charge capacity trending downward;

replace all 6 batteries on SM4Radial Scientific Instrument

– Replace WFPC2 w/ WFC3 on SM4

Aft Shroud– Higher power

instruments causing warming



Goddard Space Flight Center Run Times of HST Gyros at 9/17/07



Goddard Space Flight Center SM4 Flight CrewScott

AltmanGreg

JohnsonMegan

McArthur

MikeMassimino

DrewFeustel

Mike Good

John Grunsfeld



Goddard Space Flight Center HST Servicing Mission 4 (SM4) Configuration

Cosmic Origins Spectrograph

Wide Field Camera 3

Fine Guidance Sensor

Rate Sensor Units

Batteries

Flight Support System

Super Lightweight Interchangeable

Carrier

Orbital Replacement Unit Carrier

Multi-use Logistic

Equipment Carrier

Soft Capture Mechanism

IMAX



Goddard Space Flight Center SM4 Flight Hardware Status

● Cosmic Origins Spectrograph (COS)– Completed EMI and VEST testing, metrology verification, SMGT, and ORUC and Hi Fi

Mechanical Simulator fit checks

– Aluminum grating performance issue investigation concluded

● Wide Field Camera 3 (WFC3)– Thermal Vac Test #2 completed

• UVIS-2 and IR-1 detectors are in WFC3

• IR channel thermal instability problem resolved

– Glinting problem identified on UVIS-2 during T/V #2

– Stopped UVIS-1 ATP to address glinting• Removed outer (vacuum) housing to install baffle

– IR-3 detector received at Goddard September 28• IR-4 completing ATP

– Replacement engineering and flight calibration lamps received and are in testing• Calibration system to be removed and modified after EMI testing

– IR channel throughput performance degradation resolved



Goddard Space Flight Center SM4 Flight Hardware Status (cont’d)

● New Batteries at Goddard in cold storage– Recent test of flight spare battery shows no sign of degradation

– New battery procurement at Eagle-Picher terminated

● Gyros (aka Rate Sensor Units (RSUs); 1 RSU = 2 gyros)– RSUs 1005, 1006, and 1007 at GSFC

– RSU 1004 in development; to be delivered December 2007

● Fine Guidance Sensor (FGS)– Delivered to Goddard

● New Outer Blanket Layers (NOBLs 5, 7, and 8)– Modifications in work

● Space Telescope Imaging Spectrograph (STIS) Repair– Development work on track



Goddard Space Flight CenterOverall WFC CEB/LVPS-Replacement

Implementation

New WFC CEB Module is inserted into and clamps to CEB box

New LVPS module clamps to handrail standoff

Cable conducts power and signals between WFC CEB and LVPS

Cable conducts power between ACS input harness and LVPS




Teledyne(ASIC/ Design & Fab)

J&T (CEB-R PWA/ Design, Fab,

Assy, Test)

Ball (CEB-R Chassis/ Mech. Design and Fab)

Ball (LVPS-R/ Box Level)

GSFC(441/FSW)

GSFC(441/FSW)

GSFC (442/I&T)

Key Products Responsibilities



Goddard Space Flight Center Key Demonstrations Provide Design Validation

● At PDR (June 20-21), we demonstrated a CEB Breadboard that performed all CCD clocking and video processing functions using the SIDECAR ASIC

– Checks CEB-R to WFC CCD interface– A revised version of this breadboard implements the exact flight design to

enable detailed performance testing without a full CEB-R

● At CDR (October 3-4), we demonstrated the Pre-EM hardware that implements all the FPGA and ASIC functions that are seen by the ACS MEB

– Checks the CEB-R to MEB interface– Being used for early FSW development and testing

● HRC Backpowering Tests demonstrated ability to restore HRC imaging by backpowering the HRC CEB through the flight power harnesses

– Two tests performed with HRC 2 Flight Spare Detector– Detector noise showed no significant differences from nominal performance– On-orbit success with HRC remains dependent on condition of on-orbit

hardware (possible collateral damage from failures)




-- Backup Charts --




HST Observatory StatusStatus as of 9/4/07 Last changed 9/4/07

Color Code

● Tailor attitude and equipment usage as needed● Consider conditional limitations on operations in

order to retain flexibility● Install Bays 8 and 5 NOBLs on SM4

● MLI degradation assumed to be continuing; may accelerate during coming Solar Min

● Slow warming of aft shroud and equipment bays

● Operations has realized a 38% decrease in SSAT cycles [2044 (7/05-7/06) vs. 3281 (7/03-7/04)]

● 1st year of MAT power cycling LEI yielded a 24.7% reduction [7599 (2/06-2/07 vs. 10089 (2/05-2/06)]

● No performance liens● On/off cycles for the Multi-access & S Band

Single-access transmitters are accumulating

Communications

● ExcellentData Mgmt System

● Two-Gyro Science Mode ops began 8/29/05● FGS-2R acceleration limit K-factor lowered to

ameliorate loss of performance. Effectivenessdecreases with servo-loop gain loss; remainingmargin uncertain. Periodic tests show thatperformance is slowly worsening

● FGS-3 use reduced to preserve bearings● Hybrid HST 486/FGE acquisition mode being

developed

● Gyros 1, 6 operating well; Gyro 4 in reserve, and should be used with primary heaters off

● Gyro 2 failed 8/31/07● FSW compensation of Gyro 6’s bias

instability is being recalibrated● FGS-1R Excellent● FGS-2R Degraded (Anomalous A-Servo

LED suspected)● FGS-3 Degraded (Bearing performance

sub-par; higher torques required)

● Software taper charge continues● 2006 capacity testing completed 8/25/06● 2 additional amps of array output shorted

on 8/31/07

● Batteries are aging ● System-level battery charge capacity

increased ~ 6 Ahr from 2004 to 2006● SA3 performing very well (~77 of 80 strings)

● Highly competitive Cycle 15 and Cycle 16 Science Programs will maintain a 1st rate science program with the remaining SIs

● ACS SBC science resumed February 20● NICMOS recovered 9/4 from 9/1 safing

● WFPC2 Excellent● ACS Redundant electronics failed 1/27/07

SM4 recovery of WFC/HRC pending● NICMOS Excellent● STIS Failed 8/3/04, SM4 repair pending

Changes in Status/Accomplishments/Life-Extension MeasuresSummarySubsystem

G

G

G

G

G

GScience Instruments

Electrical Power System

Pointing Control System

Thermal Performance




NOTES:

ORBITAL REPLACEMENT UNITS (ORU's) (TO GSFC I&T)

GROUND SYSTEMS

FLIGHT SYSTEMS

OPS & GND SYSTEMS DEVELOPMENT

PROGRAM MILESTONES

J A S OMILESTONES

1

2

3

4

11

13

14

GODDARD SPACE FLIGHT CENTER

APPVL RESP

BASELINE AS OF

LAST SCHED CHG

STATUS AS OF

HUBBLE SPACE TELESCOPE SM4 MASTER SCHEDULEP. BURCH

FLIGHT INSTRUMENTSCOSMIC ORIGINS SPECTROGRAPH (COS)

SPACE SUPPORT EQUIPMENT (SSE)

LAUNCH

SHUTTLE

PROJECT

0 - 1

1 2

MISSION MANAGEMENT/EVA VERIF.

J3 4 F

2006A M JM

7

8

6

5

- HST 486 FLT SW

- CTL CTR SYS

- OPS SYS DEV

9

SR-3.1

- NSSC-1 FLT SW

SYSTEM TESTING & TRAINING

12

EVA SYSTEMS & CREW TRAINING

MISSION H/W INTEG & TEST @ GSFC

KSC PRE LAUNCH/LAUNCH OPS

2.7 486/R1

JN D F

START SMGTs

ALIVENESS FUNC TEST

START JSC TESTING

09/30/07

PIP/ BL

ICD/ BL

QUEEN V5

J AA M JM

2007

COMPL SMGTs

S O N

WIDE-FIELD CAMERA 3 (WFC3)

FORCIR

486/R2

8.6

10/04/07

CRITICAL PATH

CDR/TRR

5.4.2 5.4.3

8.4

BATTs

2008JD F J AA M JM S

SR-2.1SR-3.2

ARCHIVE 1.0

5.4.4

9.0

O N

KSC FRR

SMOV

SHIP TO KSC

GSFC FRR

GND SYS FREEZE

S/W FREEZE

S/W FREEZE

DELIV TO KSC COMPL

COMPL ETEs

SHIP TO KSC

SHIP TO KSC

LAUNCH OPS

2/09

EVA VERIF COMPLETE

8.5

FGSRSU 1005

5.4.5

LAUNCH

10

DEL TO SYS I&T

RSU 1006

COS ACOUSTIC

RAAS/HOMS DELV

PRE ENV'T FUNC

MULE ACSTCSLIC STRENGTH TESTHP PALLET TO GSFC

GND SYS FREEZE

ACOUSTIC TEST

EMI/ EMC#1

T/V CALIB TEST#2

IR2@ GSFC

2.8 486/R4

RSU 1007

CREW ASSIGN

CF#1 CF#2 CF#3 CF#4 CF#5

JISsGSFC SIMS

FUNC TEST

T/VAC COMPL

PIP SUBMIT

NBL 06.1

486/3.1A 1 GYRO

PH-2 FLT SAF REV

PH-2 GND SAF REV

PH-3 FLT SAF REV

PH-3 GND SAF REV

NBL 06.2

ARCHIVE 1.1

MSO

(LAUNCH DATE 08/07/08)

FUNC TEST

IR2@ BALL

DEINTEG COMPLT

RE-INTEG COMPLT

SSE CDR

5.4.6 GSRR 5.4.6

RSU 1004

RSU 1007

PERR

T/V CALIB TEST#3

PER-2

SLIC PER

FSS ACSTC

NBL 06.3

NBL 07.4

NBL 08.1

NBL 08.2

NBL 08.3

NBL 08.4

NBL 07.5

NBL 07.6

NBL 07.2

NBL 07.3

NBL 07.1

2005

8.6.1

NBL 08.5

5.4.7

PSR

PRR

QUEEN V5.1

SR-4.1 SR-4.2

486/R3

INSTALL FLT

DETECTEMI/

EMC#2

SLIC ACSTC

START KSC TESTING

NBL 08.6

NBL 08.7

- ACS- STIS

CDR PERCEB-R DELV ACS-RREPAIRS

15

SRR PDR PER LVPS DELV

COMPL JISs

ORUC ACSTC

IMAX DEL TO CARRIER

08/10/07

PDR

CVR DEL

LVPS DELV

Line 2 - WFC3 T/V CALIB TEST #2 and EMI/EMC #1 moved one to two months to the right. SCR pending

Line 3 - STIS REPAIR LVPS DELV moved two months to the right. SCR pending

5.4.7.1



Goddard Space Flight CenterSummary of SM4 Work Remaining

(Major Work Elements)● WFC3 and gyros● Soft Capture and Rendezvous System● STIS replacement hardware, repair tools, and techniques● Shuttle/payload analytical and physical integration● Flight hardware environmental test● Ground system and flight software changes● Mission operations plans and procedures● Mission level integration and test

– Includes end-to-end system verification/validation

● Simulations and Training● Payload processing (KSC)● Launch and mission execution● Post flight de-integration● Servicing mission observatory verification



Goddard Space Flight Center ACS Failure History

MEB1 / LVPS2

MEB2 / LVPS1

CEB

● Side 1 failure on June 19, 2006– LVPS1 failure left CEB inoperable

from Side 1

– Most likely cause of ACS failure resides within LVPS1 Board #3, component U2-7, MFL2815D Interpoint DC-DC converter

– Next most likely cause is short to ground in +35V step-up transformer T6 on same LVPS board

● Side 2 failure on January 27, 2007– ACS PDU Side 2 fuse is open

– Failure most likely in LVPS2 Hold section electronics

• Specific component failure likely will remain unknown

APB




MEB2 / LVPS1

CEB

Vicinity of TPS

MEB1 /LVPS2Inside Possible ESM

Interference For Panel Removal

HRCCEBInside

WFC CEB Inside

ESM

ACS Mockup

MEB1 / LVPS2

Thermal Saddle (Heat Pipes Inside)

ACS Worksite Accessibility and AccessPanel Locations

APB

+V1




ACS Present ConfigurationCurrent State of ACS (post Bus C Test)



Goddard Space Flight CenterConcept for ACS Repair

(Not yet Approved by NASA Headquarters)

Repaired State Simplified Electrical Block Diagram

MEB

Side 1

APB

LVPS OOPERATE Bus

HOLD Bus

+15, -15, +35

+5

WFC CEB

WFC CCD

HRC CEB

HRC CCD

LVPS H LVPS H

MEB

Side 2

APB

LVPS O

HOLD Bus

OPERATE Bus

+5

Failed Element

Suspect Element

PDU 20 Amp FusePDU 20 Amp Fuse

Side 1 used to operate the entire instrument except for the CEBs which are

replaced/powered by a new boxSide 2 is inoperable

+15, -15, +35

New Element

New Power Supply




Concept for ACS Repair(Not yet Approved by NASA Headquarters)

ACS Repair Architecture - Replace CEB Cards

CEB Replacement Module

Power Supply Module

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