PDR Peer Review November 28, 2005

1
IBEX Science Team Meeting November 07
Welcome and Introductions McComas/Hawes
Orbital Science Corporation November 7-8, 2007
2
IBEX Science Team Meeting November 07
Update from Headquarters Christian
Orbital Science Corporation November 7-8, 2007
3
IBEX Science Team Meeting November 07
Mission Status and Plan Through L30 Mark
Phillips
Orbital Science Corporation November 7-8, 2007
4
Outline

• IBEX Programmatics
• Mission Status
• Plan Forward

5
IBEX Organizational Chart
6
Institutional Responsibilities
Southwest Research Institute PI Institution
Various Institutions Science Team
Adler Planetarium E/PO
Ground Segment
Payload Segment
Spacecraft Segment
LMATC IBEX-Lo
Orbital Spacecraft
SwRI ISOC
LANL IBEX-Hi
SwRI CEU
ATK Solid Rocket Motor
Orbital MOC
7
Flight System Elements

• Flight System (FS)
• Full IBEX stack as it mounts on Pegasus (includes
  SCB, payload, SRM, Pegasus adapter cone, safe
  arm, and separation systems)
• Spacecraft Bus (SCB)
• Supports payload, performs nominal mission. Based
  on MicroStar platform.
• Payload (P/L)
• Consists of IBEX-Hi, IBEX-Lo, Combined
  Electronics Unit (CEU), and Harness
• Spacecraft (S/C)
• Combination of spacecraft bus and payload

MLB-138 MLB
STAR-27 SRM
Adapter Cone
MLB-231 MLB
MLB-315 MLB
Spacecraft
MLB Motorized Light Band separation system
8
IBEX In-Launch Vehicle
Fairing (simple model shown for clarity)
Adapter Cone
Standard Pegasus XL 3rd Stage
MLB-138 MLB
MLB-231 MLB
Spacecraft
STAR-27 SRM
9
IBEX S/C Simple Sun-Pointed Spinner
10
On-Orbit Operation

• Routine Operations
• Nominal orbit 40-50 RE x 7000 km altitude, 6-8
  days per orbit
• Sun-pointing spinning S/C (4 rpm)
• Science observations gt 10 RE altitude
• Engineering lt 10 RE
• Data download and command upload
• Adjust spin axis 6-8 (Earths orbital motion)
• Nearly full sky viewing each 6 months

11
Mission Phases

• The IBEX mission is divided into 5 phases
• Launch SRM burn phase
• Launch on Pegasus, SRM boost to high-apogee
  parking orbit
• Orbit raising phase
• Ground stations acquire spacecraft and develop
  orbit ephemeris
• Spacecraft uses a series of hydrazine burns to
  boost up to mission orbit
• Commissioning phase
• Spacecraft bus and payload subsystems checked out
• Nominal operations phase
• Spacecraft performs nominal mission, collecting
  down linking science data
• Special operations
• Spacecraft operates through off-nominal conditions

12
Orbit-Raising Overview
13
Nominal Operations Phase Overview

• In nominal operations phase same operations
  repeat each orbit
• Consists of
• High-Altitude Science Operations (HASO), 7.5
  days per orbit
• Low-Altitude Housekeeping Operations (LAHO), 1/2
  day per orbit

14
Spacecraft Configuration

• Central thrust-tube core structure
• Simple major-axis spinner mass balanced about
  spin axis
• Two axial and 4 lateral thrusters

15
IBEX Payload

• IBEX-Lo
• Energy range 0.01-2 keV
• Team LMATC (Lead), UNH, GSFC, APL, UBern

• IBEX-Hi
• Energy range 0.3-6 keV
• Team LANL (Lead), UNH, SwRI

• CEU
• Provides electronic support and control for
  payload
• Developed by SwRI

16
Ground and Space Network S/C Interface
17
Combined Operations with Pegasus
Ferry To RTS
Pegasus-OCA Mate
Staging Operations
VAFB
FS-LV Integration
RTS
Launch
18
Outline

• IBEX Programmatics
• Mission Status
• Plan Forward

19
Activities Since Last SWT

• Reviews
• Mission Operations Review July 9-10, 2007
• Payload Pre-Ship Review October 3-4, 2007
• Hardware
• Completed payload IT
• Completed payload cross-calibration
• Delivered payload to S/C and performed jumpered
  interface tests
• Payload integration into S/C underway

20
IBEX Top Level Schedule
10/07/07
2005
2006
2007
2008
Task
A
M
J
J
A
S
O
N
D
J
F
M
A
M
J
J
A
S
O
N
D
J
F
M
A
M
J
J
A
S
O
N
D
J
F
M
A
M
J
J
P/L PDR
MPDR
CR
MCDR
MOR
MPER
MRR
FOR
F/LRR
PPER
IOC
Project Reviews
PPER
MPSR
Launch 6/15/08
Contract Award
SRR
CRR
ESA CS/ES
CAR
IBEX-Hi Sensor
TOF
EM TOF
Subsystems (LANL, UNH, SwRI)
Envir.
Cal
Detector Rework/Retest
Hi-Sensor IT (LANL)
Assy
IBEX-Lo Sensor
CS ESA
ES/TOF
EM TOF
Subsystems (GSFC, LMATC, UNH, APL)
Sens
Envir.
Cal.
Assy
TOF Rework/Retest
Test
Lo-Sensor IT (LMATC)
EM Mech HVPS
Optics
EM DB PWA
CEU
Assy/Test FM Elect.
FM Mech
Mechanical Electrical EM FM (SwRI)
Start FM
Vibe
FM
AIT
EM FM IT (SwRI)
TV
EM Start
Test
Lo Harn
Payload Harness
Net List
Test
Bakeout
Payload Harness (SwRI)
Reqmts Def.
Hi Harn
Payload Integration Test
Test
To S/C IT Launch Op
Integration Test (SwRI)
Struct Deliv
Adapt Cone
AC Plume Shield
Spacecraft Subsystems
Drwgs
Sep Sys
MLBs
Structure/Separation System
HPS-Therm
SCB-Therm
Det. Thermal Modelling
Blankets
Thermal
Q-Batt
BCR
S/A
F-Batt
BCR EDU to ATB
Power System
PCM
F-Batt
F-FC/ACE
F-FC/ACE
Mod E-MIU
E-FC to ATB
F-MIU
CDH System
F-MIU Slack
TX/RX
RF M/Q-Ant
Communication System
F-SCU
E-SCU/F-ACE
E-ACE
Gyro
ST Contract
Attitude Control System
ST Slack
Accels
CSS
ST
Qual Tank Fab Test
L/L
Start Tank Contract
Propulsion (Hydrazine)
HPS to SCB IT
Thrusters
Flt Tanks
Ship SRM to VAFB
Case Analysis
Case Procure
Propulsion (SRM)
Flt Harness Slack
Flt Harn to IT
Flt Harn Design
EDU Harn to ATB
Harness
B4.2 Obs CPT
B4.3 Obs Env
B4.0 SCB IT
B4.1 CPT 1
B5.0 Obsv CPT3
B2.0
B3.0
B3.1
B3.2
Flight Software
Script Pathfinding
Reserve
3.2w 2w
Avionics Test Bed IT
Start
Start VAFB Ops
ATB Elect
S/W Dev.
ATB IT
VAFB Ops
SCB RDY
Integr Compl.
Testing
CPT3
SCB Observatory IT
Start SCB IT
6/15
3 Wks Reserve
SCB CPT 1
Obs IT
Obs Env
HPS Fuel Stack/Spin
Obs CPT 2
IT
Comprehensive Test Plans
Launch Site Ops
MCC Accept Test
Flt Ops Rehearsal 5
Test Data Lines
Start Obs IT
Set up Dev Test Lab
Mission Ops Spec
GSD/MOPS FEPR
USN Contract
Gnd I/F Test
MOR
ICDs (F)
FOR
MCC-ISOC TP
Pre-Launch Gnd Data Sys/Msn. Ops
CONOPS Release
FRR LRR
MIWG2 RWG1 MURR
MIWG5 RWG2
MIWG6 GOWG1
MIWG4 RWG1
MIWG7 RWG3 LOWG
Avionics Build/Test
IOC
MIWG1
MIWG3
MRR
Launch Vehicle
Launch
MUPDR
MUCDR
LVRR
21
Recent Spacecraft Bus Activities

• Completed Static Test Firing of SRM Qualification
  Unit
• Flight Battery Delivered and Integrated
• Received 1.5 inch Spacer
• Completed Thermal Blanket Bake-out
• Completed FSW/ACS Build 4.2 Acceptance Testing,
  including FDC code
• Completed GSE bake-out
• Completed mechanical alignments
• Received the payload and supported set-up in
  clean room next to spacecraft
• Completed dry run of updated procedures and
  scripts required for CPT2
• Completed CPT2, including Payload CPT
• Started Payload Integration
• Received Transceiver and Completed Transceiver
  ATP Integration

22
Outline

• IBEX Programmatics
• Mission Status
• Plan Forward

23
Top Level IT Flow
24
Near Term Working Plan
The plan is updated dynamically as required in
the daily stand-ups
25
Plan for HV Verification after S/C Environments

• Adding post spacecraft environments verification
  for Payload even further ensures flight
  readiness!
• Detailed visual inspection always planned
• Lo TOF section removed and inspected (foils,
  MCPs, etc.)
• Hi detector cover removed (foils, MCPs, etc.)
• Added inspection of HV wires
• Remove cover and inspection of all HV wires in
  detector
• Added HV operations in TV cold cycle
• Added LV powering of all HV cables to verify
  connectivity and no shorting in IBEX-Hi
• Added resistance measurement to verify CEM
  circuit in IBEX-Hi

26
HV Verification in Spacecraft TVAC

• ALL payload optics HVs will be brought to nominal
  operating levels during last Cold Operational
  Cycle
• Vacuum must be low enough and RGA data will be
  reviewed before turning up high voltages
• All non-detector voltages will be up for a few
  hours
• Because of a potential small risk that the
  detectors could be contaminated from S/C
  outgassing in the TV environment, MCP and CEM
  voltages will only be brought up to a reduced
  voltage for a limited time where occasional
  background counts start to appear.
• TVAC tests will show
• MCP and CEMs HV cables still connected
• Optics HV cables are not shorted to ground or
  arcing
• MCP and CEMs are still functional
• MCP and CEMs are still quiet
• TVAC test will not show
• If one of the HV cables going to a sensor optical
  element broke and is floating
• Additional inspection added (discussed next)

27
Plan for HV Verification Post TVAC Inspection
and Test IBEX-Hi

• Voltage measurements
• With V/16 plug installed, CEU will command
  limited HV to all IBEX Hi components
• Outer detector cover will be removed to allow
  access to HV connections internal to IBEX-HI
• TOF voltage will be measured directly on TOF
  housing
• Inner ESA voltage will be measured on feed
  through that connects to ESA
• CEM voltage will be measured on HV Dist. Board
  connection points
• Outer ESA, collimator and deflection rings
  voltages will be measured directly on the
  individual component

28
Plan for HV Verification Post TVAC Inspection
and Test IBEX-Hi

• Resistance measurements
• Counting on TVAC already proving detectors
  connected, but additional verification possible
• With CEU off, resistance will be measured 1) on
  HVDB across input and return of each CEM, and 2)
  input of CEM to ground
• If measurement is open, something is broken and
  floating
• If resistance is lower than expected, something
  is shorted that should not be
• Resistance, voltage, and TV measurements of
  IBEX-Hi will definitely tell if multipliers are
  working correctly and verify ALL HV connections

29
Plan for HV Verification Post TVAC Inspection
and Test IBEX-Lo

• Voltage measurements
• Like Hi, with V/16 plug installed, CEU will
  command limited HV to all IBEX Lo components
• Cover of HV connections will be removed to allow
  access to HV connections between IBEX-Lo and the
  CEU
• Solar array is already planned to be removed for
  illumination test providing access to IBEX-Lo HV
  cover and connections
• All CEU to Lo HV connections will be inspected
  and voltage measured
• Like Hi, the collimator and deflection rings
  voltages will be measured directly on the
  individual component
• MCP and PAC HV in IBEX-Lo are internal to sensor
• All internal HV connections in IBEX-Lo have been
  in place without change since Sensor Integration
  in Bern, have undergone Vibration and Acoustic
  Testing, and have functioned nominally through
  all Calibrations and TV

30
VAFB Processing Flow
31
Review Timeline

• SRR Sept 7-8, 2005
• CEU and Payload Flight Software EPR Oct 13-14,
  2005
• Collimator EPR Oct 18-19, 2005
• Combined Sensor EPR Nov 8-10, 2005
• Spacecraft Preliminary EPRs Nov 29-Dec 2, 2005
• Payload PDR Dec 12-13, 2005
• Mission PDR Jan 17-18, 2006
• Combined Payload Final EPRs Jun 20-23, 2006
• Spacecraft Final EPRs June 27-30, 2006
• Mission CDR Sept 13-18, 2006
• Payload Pre-Environmental Review March 27-28,
  2007
• Mission Operations EPR April 4-6, 2007

32
Review Timeline

• Mission Operations Review July 10-11, 2007
• Payload Pre-Ship Review October 3-4, 2007
• Pre-Environmental Review November 27-28, 2007
• Flight Operations Review February 2008
• Mission Pre-Ship Review March 2008
• EPO Launch Review March 2008
• Launch Vehicle Readiness Review May 2008
• Flight Readiness Review June 2008
• Launch Readiness Review June 2008