Transcript SDO Systems Retreat

SDO Flight Dynamics Subsystem
Mission PDR
R. L. DeFazio
S. F. Andrews
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 1
Agenda
•
FDS Driving Requirements
•
FDS Launch & Early Orbit Operations
•
FDS Nominal Mission Operations
•
Trade Studies
•
Flight Dynamics System (FDS) Diagram
•
FDS Software Functional Diagrams
•
FDS Software Heritage
•
FDS Testing
•
FDS Schedule
•
FDS Documentation
•
Risks, Issues and Concerns
•
Backup Slides
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 2
FDS Driving Requirements
Launch and Early Orbit Requirements
•
Perform orbit determination and acquisition data
generation
•
Plan, execute and calibrate orbit maneuvers to circularize the
orbit at 102 degrees West longitude
•
Maneuver SDO to place it on its nominal East-West
station keeping profile
•
Generate applicable FDS products to support spacecraft and
instrument checkout
•
Perform star tracker alignment and calibration plus gyro and
guide telescope calibration
•
Perform momentum management once per orbit while
perigee remains at 300 km. altitude
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 3
FDS Driving Requirements (Continued)
Mission Orbit Requirements
•
Perform orbit determination and prediction
o
Position accuracy:
< 150 meters
o
Velocity accuracy:
< 10 cm./second
•
Generate and deliver acquisition data for all supporting
networks
•
Perform attitude validation of the on-board attitude
•
o
Accuracy without/guide telescope: 120 arc seconds
o
Accuracy with/guide telescope:
25 arc seconds
Perform attitude maneuver slew planning to support science
planning and sensor calibration
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 4
FDS Driving Requirements (Continued)
Mission Orbit Requirements (Continued)
•
Generate FDS products required for scheduling and planning
science and insuring spacecraft health and safety
•
Perform East-West station keeping maneuver about (2) times
per year
•
Perform monthly momentum management maneuvers
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 5
Orbit Raising Diagram
Earth
TMF2
TRANSFER ORBIT
a.k.a GTO
AMF1 TMF1
AMF2 TMF3
AMF3
AMF4
LONGITUDE
PHASING ORBIT
TRIM ORBIT
GEOSYNCHRONOUS
ORBIT
SDO Preliminary Design Review (PDR) – March 9-12, 2004
DRIFT ORBIT
Flight Dynamics Page 6
A Week in the Life of the SDO FDS in the MOC
S
COLLECT
S-BAND
TRACKING
FROM WHSS &
nd
2 NETWORK
M
EXTRACT
PLAYBACK
ATTITUDE DATA
FROM
TELEMETRY
VALIDATE
ONBOARD
ATTITUDE
PREPROCESS
TRACKING DATA
T
W
PLAN
STATIONKEEPING
MANEUVER
(IF REQUIRED)
EXECUTE
STATIONKEEPING
MANEUVER
(IF REQUIRED)
COMPUTE
POST-MANEUVER
EPVs & IIRVS
(IF REQUIRED)
CALIBRATE ADS
SENSORS,
STARTRACKERS,
ETC.
(IF REQUIRED)
DUMP
MOMENTUM
(IF REQUIRED)
PERFORM S-BAND
ORBIT
DETERMINATION
COMPUTE
INSTRUMENT
CALIBRATION
PLANS
(IF REQUIRED)
COMPUTE AND
UPLOAD
ON-BOARD
TABLES & EPVs
(IF REQUIRED)
T
EXTRACT
PLAYBACK
ATTITUDE DATA
FROM
TELEMETRY
VALIDATE
ONBOARD
ATTITUDE
CALIBRATE
STATIONKEEPING
MANEUVER
(IF REQUIRED)
S
COLLECT
S-BAND
TRACKING
FROM WHSS &
nd
2 NETWORK
UPDATE
PROPELLANT
USAGE
PREPROCESS
TRACKING DATA
PERFORM S-BAND
ORBIT
DETERMINATION
COMPUTE
(8-DAY) ORBIT
EPHEMERIS
STARTING
TUESDAY @ 0:00
UTC
COMPUTE
(37-DAY) ORBIT
EPHEMERIS
STARTING
THURSDAY @ 0:00
UTC
COMPUTE &
DELIVER
EPVs & IIRVs
COMPUTE &
DELIVER
EPVs & IIRVs
COMPUTE THE
REAL TIME
ATTIUDE DISPLAY
(RTADS)
COMPUTE &
DELIVER (35-DAY)
FDS PRODUCTS
SET STARTING
FRIDAY @ 0:00
UTC
RUNS
CONTINUOUSLY
F
Note: RTADS IS RUNNING NEAR CONTINUOUSLY
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 7
List of FDS Products for SDO


















•


Earth & Lunar Shadows
Beta Angles
Spacecraft Longitude Drift Table
Apogees & Perigees
Right Ascension of Ascending & Descending Nodes
Predicted Attitude Dependent Ground Station Visibility (Omnis)
Predicted HGA View Periods of SDO Dedicated Antennas
Predicted Attitude
Predicted RFI (Sun and other Spacecrafts)
Predicted SDO Orbital State Vectors (Geocentric & Heliocentric)
Maneuver Command File & Planning File
Sensor Visibilities & Interference (e.g. sun, moon)
Ground Track
Propellant Usage Summary
Maneuver Summary (maneuvers performed)
Two-way Range (Clock Correction)
Spacecraft Local Time
Extended Precision Vectors (EPVs)
2-Line Elements
Acquisition Data (IIRVs, SPICE Files
Science Planning Aids (Instrument CalibrationProducts)
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 8
FDS Trade Studies
•
•
Right ascension of ascending node (RAAN) trade study
•
Optimized RAAN at 200 degrees to minimize the number
of shadowed days per year
•
Initial inclination was 28.5 degrees and remained
28 deg. < IM < 30 degrees over a 10 year mission
High gain antenna viewing of SDO ground station
•
Evaluated unobstructed viewing of the future SDO
antennas at the White Sands ground stations by HGAs
•
Studied several potential spacecraft models, including
varied antenna boom lengths, dish diameters and solar
configurations
•
Goal is attainable to have at least six months of
unobstructed viewing from a given HGA without
switching antennas or rolling the spacecraft
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 9
FDS Trade Studies (continued)
•
•
SDO orbit raising maneuver profiles
•
Generate SDO orbit raising profiles using various
thruster configurations to determine feasibility
•
Determine the number and duration of orbit maneuvers
required to raise the orbit to geosynchronous
Study attitude slew constraints for performing East-West
station keeping maneuvers
•
•
Evaluate the impact of keeping the spacecraft X-axis to
within 45 degrees of the sun line
Evaluate omni antenna and star tracker coverage to verify
interference free operations
•
Omnis using +/- 70 deg. FOV provide adequate coverage
with a s/c roll needed for station keeping coverage
•
Glint in star tracker FOV (58 deg.) can be eliminated by
adjusting mounting location
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 10
SDO Flight Dynamics System
D
CM
D
CM
TLM
TLM
HMI / AIA
SOC
EVE
SOC
White Sands
SOWG
FDS Products
External Networks
White Sands
SDO Flight Dynamics System (FDS)
FREEFLYER
TDF
Orbit
Determination
SDO State Vector
State
Vectors
SDO Ephemeris
SDO Maneuver Plans
CMD Sheets
ACQ Data
DRIFT Table
Prod
Calibration
Requests
TLM CMD
EPH
Playback TLM
(Sequential Print)
ASIST
MATLAB ADS &
Utilities
(MTASS)
STK PRO/VO
Planning,
Scheduling
&
Monitoring
Calibration
Tables
Attitude Solutions
& Residuals
Pseudo
Telemetry
Prod
Trending
MPS
EPH
RTADS
Real Time
Telemetry
Slew
Plans
FDS Product Directory
GTDS/RTOD
S-Band
Tracking
Data
TLM
SOCKET
FOR
STK/VO
Real Time Attitude
Determination System
Scheduling Products
MOC Display
Acquisition Data & Station Scheduling
Mission Operations Center (MOC)
TDE in FDF
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 11
SDO Orbit Determination Process
TRACKING
DATA FR:
GROUND
STATION
STATE
VECTOR
FORCE MODELS
FILES
DATABASE FILES
STATE
VECTOR
FILE
EPHEM
GENERATION
FAX
GTDS/RTOD
MOC
TRACKING
DATA
SERVER
S-BAND ORBIT
DETERMINATION
L/V STATE
VECTOR
(ETR)
FTP
TRACKING FILE &
DATA ARCHIVE
(PC)
S-BAND
RAW
TRACKING
DATA FILE
(UNIX)
FDS
PRODUCTS
FILE
TDF & PREPROCESSOR
S-BAND TRACKING DATA
(PC)
SDO
ORBIT DETERMINATION
PROCESS USING
GTDS/RTOD
(PC)
ARCHIVE
(PC)
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 12
SDO Orbit Maneuver Planning Process
SDO
STATE
VECTOR
FILE
TELEMETRY
DATA FOR
MANEUVER
PLANNING &
CALIBRATION
FORCE MODELS
DATABASE FILES
GEOTOOL
ANALYTICAL
ASCENT
MANEUVER
PLAN
ANALYSIS / PRODUCTION TASKS
FREEFLYER
(PC)
GENERATE
SDO
ASCENT
PROFILE
ORBIT PROPAGATION
W / FINITE MANEUVER
MODELING
EPHEMS
8 DAY EPHEM;
5 WEEK EPHEM
STK FORMAT
GSFC
FORMAT
GENERATE ORBIT
EPHEMERIS WITH
ASCENT MANEUVERS
MISCELLANEOUS
PRODUCT
GENERATION
PERFORM PRECISION ENGINE
MODELING FOR MANEUVER
PLANNING AND CALIBRATION
SDO
EPVs
&
IIRVs
SDO Preliminary Design Review (PDR) – March 9-12, 2004
SDO MANEUVER
PLANNING FILES
SDO
MANEUVER COMMAND
SHEET WITH
POST-MANV. EPV
FDS
PRODUCTS
FILE
FREEFLYER (PC)
MISSION ANALYSIS
MANEUVER PLANNING
&
ORBIT PROPAGATION
Flight Dynamics Page 13
SDO Product Generation Process
STK
e.file
FORMAT
EPHEM
PRODUCT TIMESPAN
STK DATABASES
SDO - STK PRODUCTS
ASC. & DSC.
NODES
TIMES,
LONGITUDES
& ORBIT NO.
APOGEES
&
PERIGEES
SPACECRAFT
SHADOW
TIMES
(ALL
SHADOWS)
ATTITUDE
DEPENDENT
GROUND
STATION
VISIBILITIES
HGA
GROUND TRACK
VIEWPERIODS
DATA
FOR DEDICATED
SDO ANTENNAS
SOLAR
BETA
ANGLE
FDS
PRODUCT
FILE
PREDICTED
SOLAR &
GROUND
STATION RFI
ACQUISITION
DATA
EPVs
& IIRVs
SCIENCE
PLANNING AIDS
& PRODUCTS
SPACECRAFT
LOCAL TIME
SPACECRAFT
2-WAY
RANGE
STK PRO
(PC)
SDO STK PRODUCTS
SDO STK
PRODUCT
GENERATION
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 14
SDO Attitude Computations Process
Attitude Solutions & Residuals
ASIST
SDO
TELEMETRY
OBC Validation Reports and Plots
ATTITUDE DETERMINATION AND CALIBRATION
IRU Alignment,
Scale Factor, Bias
Playback
(ASIST Seq. Print)
TP
Real Time
(ASIST TSDS
Socket)
RTADS
DA
BLS
EKF
ATTVAL
CHKEPH
IRUCAL
Star Tracker
Alignment
BUILD
UPLINK
TABLES
ALICAL
Pseudo Telemetry
EPHEMERIS
MOC
DISPLAY
DATABASE
FILES
Wheel Speeds
SDO ATTITUDE
OPERATIONS
PROCESS USING
MATLAB
(PC)
ATTITUDE CONTROL PLANNING UTILITIES
Slew Command Parameters
THRUSTER
CALIBRATION
DATA
MOMENTUM
MANAGEMENT
UTILITY
SLEW PLANNING
UTILITY
Attitude History Predicts (STK .a FILE)
Delta-H Command Parameters
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 15
SDO FDS Software Heritage
FDS
Element
Implementation
Approach
Heritage
New Development
Risk
STK/VO
Graphical
Model Update
Many GSFC Missions
NA
FreeFlyer
Engineer
& NASA
Pack
Modify
Database
For Biprop
System
Terra, EO-1, Aqua
Medium
RTOD
Reuse
Aqua
NA
GTDS
Reuse
Many GSFC Missions
Tracking
Data
Preprocessor
Reuse
(Ready in
mid-2003)
None
NA
MATLAB
ADS
Reuse/Modify
SMEX,EO-1,etc.
Low
MATLAB
RTADS
Reuse/Modify
SMEX,EO-1,etc.
AutoProduct
Reuse/Modify
Terra, EO-1, Aqua
Low
Launch
Window
Reuse/Modify
GOES-(I-M)
Low
NA
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Low
Flight Dynamics Page 16
SDO FDS Testing
•
Run system tests as soon as functions of the FDS are ready
•
Develop an acceptance test plan that exercises all FDS
functions and interfaces
•
Perform preliminary interface testing as soon as
corresponding systems are available
•
Be ready for acceptance testing / formal interface testing of
Release 1 (L-25 months) and Release 2 (L-18 months)
•
Participate in certification of the S-Band links of the SDO
White Sands antennas
•
Participate in ground system end-to-end testing
•
Continue to exercise software through simulations and
training until launch
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 17
SDO FDS Schedule
Subsystem & Element
CY 2003
Q4
CY 2005
CY 2006
CY 2007
CY 2008
Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4
Q1 Q2 Q3 Q4
4/8
8/03
3/04 5/04
2/05
CY 2004
Q1 Q2 Q3 Q4
Q1 Q2 Q3 Q4
Q1 Q2 Q3 Q4
LAUNCH
MISSION MILESTONES
SRR/
SCR
ICR
PDR CR
PER
CDR
PSR
Ground System Reviews
9/03
Ground System Development & Test
SRR
5/04
PDR
1/05
1/08
FORR
1/07
CDR
MOR
1/07 Acceptance 1/08
GSRT
Test End
End
FDS Reviews and Milestones
FDS Design Peer Reviews
FDS Requirements, System
Design, Implementation, and Test
FDS Software Releases
12/03
12/04
PDR Peer
CDR Peer
Review
Reviews
Requirements
1 = Spacecraft Integration
= Schedule Reserve
2 = Instrument Integration
3 = Environmental Testing
4 = Launch Site Operations
Starting MOC/FDS
8/05 System Integration
S/W & H/W Design
Implementation/Test
R1 6/06
R2 1/07
Sims & Training
FDS Simulations and Training
4/07
4/08
FDS Documentation
FDS Document.
6/08
6/07
FDS Ant. Certification of WHS
A.C.
1/07 4/07
Ground System Readiness Testing
CTV
Acc Test
1/07
E-T-E
Spacecraft I&T
1
SDO Preliminary Design Review (PDR) – March 9-12, 2004
2
3
4
Launch
Flight Dynamics Page 18
FDS Documentation
Document
Delivery Date
Delivered
Inputs to Ground System DMR
9/15/03
Yes
Inputs to Ops Concept Document
9/15/03
Yes
Inputs to MOC ICD
By Ground System PDR
In Preparation
FDS Level 4 Requirements Document By Spacecraft PDR
Yes
FDS Product Development Plan
Before Spacecraft PDR
Yes
WHS Antenna Certification Plan
By Ground System PDR
Draft Ready
FDS Design Document
By Spacecraft CDR
Draft Ready
FDS Acceptance Test Plan
By Spacecraft CDR
In Preparation
FDS Operations Handbook (Final)
By Launch – 1 month
No
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 19
Risks, Issues and Concerns
•
None noted at this time
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 20
Conclusions
•
Flight Dynamics requirements are well understood
and our design is adequate to successfully meet
them.
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 21
Back up Materials
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 22
Apogees & Perigees During Orbit Raising
Period
(sec)
Partial Pass
37875.8
37876.4
37809.4
44028.0
43946.8
43947.0
43900.1
55543.6
55418.9
80330.8
80258.6
86096.3
86095.9
86172.4
86136.5
86101.2
Partial Pass
Apogee
(km)
35796.0
35796.2
35796.3
Not in Pass
35800.8
35806.0
35805.8
35805.3
35811.4
35817.1
35831.1
35831.0
35831.4
35832.0
35832.5
Not in Pass
35786.0
35786.3
Time of Apogee
(UTC)
17 Apr
18 Apr
18 Apr
19
19
20
20
21
21
23
24
25
26
27
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
28 Apr
29 Apr
SDO Preliminary Design Review (PDR) – March 9-12, 2004
2008 17:34:17
2008 04:07:32
2008 14:40:47
Not in Pass
2008 01:15:12
2008 13:26:48
2008 01:39:54
2008 13:53:01
2008 02:08:22
2008 17:29:55
2008 07:06:02
2008 05:25:24
2008 05:19:33
2008 05:15:45
2008 05:14:14
Not in Pass
2008 05:17:40
2008 05:22:14
Perigee
(km)
Not in Pass
299.8
299.6
299.5
5299.7
5299.8
5300.1
5300.6
14300.6
14301.4
31850.1
31850.3
35699.8
35699.4
35749.0
35748.5
35748.2
35782.9
Time of Perigee
(UTC)
17
18
18
19
19
20
20
21
22
22
23
24
25
26
27
28
29
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Apr
Not in Pass
2008
22:50:54
2008
09:24:10
2008
19:57:25
2008
07:20:14
2008
19:33:21
2008
07:46:28
2008
19:59:34
2008
09:47:37
2008
01:12:13
2008
19:57:15
2008
18:15:07
2008
17:26:21
2008
17:20:05
2008
17:15:57
2008
17:11:46
2008
17:06:00
2008
15:42:18
Flight Dynamics Page 23
SDO FDS Hardware Complement
Item
Function
Need Date(s)
PC (Windows TBD)
Orbit Determination (P),
Product Generation (P) &
Orbit Maneuver Support (P)
From Start of MOC
Integration to End of
Mission
PC (Windows TBD)
Attitude Support (P),
RTADS (P)
From Start of MOC
Integration to End of
Mission
PC (Windows TBD)
RTADS (P)
STK/VO (P)
From Start of MOC
Integration to L+60 days
PC (Windows TBD)
PC (Monitor Only)
Orbit Determination (B),
Product Generation (B) &
Orbit Maneuver Support (B)
Attitude Support (B)
Display RTADS
From Start of MOC
Integration to L+60 days
From Start of MOC
Integration to End of
Mission
(P) Prime
(B) Backup
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 24
FDS Software Implementation Plans
•
The FDS will be a PC-based system
•
FDS requirements will be met using heritage COTS
and GOTS software where applicable
•
When existing software requires modification, the mods will
be spec’ed, implemented and tested under the direction on
the FDS Lead Analysts. Code 583, the Mission Applications
Branch, will help oversee the preparation of FDS software
•
If new software is required, it will be developed in the same
manner as modified software
•
Automation approaches for the FDS such as
GMSEC/AUTOFDS are being explored
SDO Preliminary Design Review (PDR) – March 9-12, 2004
Flight Dynamics Page 25