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Launch Services Program Briefing THEMIS Mission PDR

Launch Services Program Briefing THEMIS Mission PDR. Tammy Harrington November 12-13, 2003. Launch Services Program Overview. The Launch Services Program provides launch services for various classes of NASA and NASA sponsored primary and secondary payloads.

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Launch Services Program Briefing THEMIS Mission PDR

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  1. Launch Services Program BriefingTHEMIS Mission PDR Tammy Harrington November 12-13, 2003

  2. Launch Services Program Overview • The Launch Services Program provides launch services for various classes of NASA and NASA sponsored primary and secondary payloads. • The launch services are provided through commercial launch service contracts, based on payload class, and are managed by the Launch Services Program at KSC. The launch services provided for the individual missions are further managed by Mission Integration Teams. • The launch services for the THEMIS mission are provided through the NASA Launch Services contract (Boeing, Delta II 7925-10C Launch Vehicle).

  3. VA LAUNCH SERVICES PROGRAM OFFICE DIRECTOR S. FRANCOIS DEPUTY DIRR. LUGO ASSOC DIRECTOR VACANT DIR SECY D. FERTIG SECY C. LAFERRIERE REVISED 06/30/03 VA-1 C. VANASSE B. FASULO K. CROOK R. RIFFE ADMINISTRATIVE OFFICE VA-2 SENIOR LAUNCH DIR C. DOVALE LAUNCH DIRECTOR O. BAEZ LAUNCH DIRECTOR OFFICE VA-3 SR. CHIEF ENGR J. WOOD CHIEF ENGR D. BEDELL CHIEF TECHNOLOGIST M. LITTLEFIELD CHIEF ENGINEER OFFICE VA-A CHIEF J. LACKOVICH VAFB RO MGR J. DEMKO ADV PLANNING MGR D. FOSTER ADV PLANNING MGR N. BECK CHF KNOWLEDGE MGR M. RUETHER TECH ASSISTANT E. MOSER LAUNCH SERVICES SUPT M. VREELAND LAUNCH SERVICES ASST. K. DURHAM (P/T) STUDENT M. SMITH (SIS) PROGRAM PLANNING OFFICE VA-B CHIEF D. SIAS MSA M. DONAT D. CARNES K. CARR L. CHAMBERLAIN (Det /JP) E. CRUZ L. GOSPER R. GNAN L. HABER PROGRAM INTEGRATION OFFICE VA- C CHIEF A. MITSKEVICH SECY L. FOSTER - Temp D. BREEDLOVE R. ENGELHARDT H. FERNANDEZ W. HARDING T. HARRINGTON D. LAMPERT C. MAKO C. MALLOY VA- D MISSION MANAGEMENT OFFICE R. MUELLER T. NAIL A. SIERRA M. STELZER S. WHITTAKER SAFETY & MISSION ASSURANCE OFFICE CHIEF C. STAUBUS L. ANDRUSKE H. BURT K. HALE G. HENDRICKS D. NEWSOME (VAFB) E. NOONAN T. PALO J. ROEDER D. PALLO (Co-op) VA-E VA-F LAUNCH SITE OPERATIONS DIVISION VEHICLE ENGINEERING DIVISION CHIEF B. SEALE SECY C. NEPTUNE J. ROGERS CHIEF P. HANAN DEPUTY CHIEF J. ROBINSON MSA S. SENN VA-E1 VA-E2 VA-F3 VA-F5 VA-F4 VA-F6 VA-F8 COMMUNICATIONS AND TELEMETRY BRANCH LAUNCH SITE INTEGRATION BRANCH MISSION ANALYSIS BRANCH SYSTEMS ENGINEERING AND INTEGRATION BRANCH MECHANICAL SYSTEMS BRANCH ELECTRICAL SYSTEMS BRANCH ENGINEERING FIELD OFFICES CHIEF S. CLARKE J. CHIOU L. DELGADO L. DUNCIL T. FERTIG T. FRATTIN G. GALLOWAY G. GREGORY R. JOHANSON M. LACEY C. LOPEZ-ROURA J. MYERS G. O’SHAUGHNESSY A. PILOTO C. KLOBERDANZ (EOD 08/25/03) CHIEF D. LINDHORST C. ALVARADO T. DUNN A. GOMEZ R. HENRY J. HERNDON C. NGUYEN B. REID R. THOMPSON M. WOLTMAN N. WOOD L. FINLEY (Co-op) CHIEF M. HALLETT DENVER RO (VA-F8-A) LEAD - K. CASTILOW HUNT. BCH. RO (VA-F8-B) LEAD - M. HALLETT (Dual Function) SECY C. RENFRO CHANDLER RO (VA-F8-C) LEAD – W. WESTHOFF VAFB RO (VA-F8-D) D. JOHNSON M. LEVESQUE DULLES RO (VA-F8-E) F. BELLINGER DECATUR AL RO MSFC – PERSONNEL T. Harrison M. Giuntini CHIEF J. SHAVER J. AMADOR, PhD E. ANDERSON J. COWRAS S. COX T. DOAN E. KACHMAR D. KNOBLOCK M. LOUGHEED D. McNERNEY R. MIKULAS L. NGUYEN CHIEF F. STONE W. GRAVES K. HAUSER J. HUECKEL T. KHALILI (VAFB) C. KLEIN K. MEASE S. MICHEL M. MILLER R. MIZELLE T. MORAN (VAFB) T. RUCCI J. SCHNERINGER (VAFB) C. TATRO E. TUGG T. TURBYVILLE F. VALDES CHIEF D. PHAM J. BEHLING T. BULK D. CALERO J. CALVERT L. CRAIG T. DELAET W. ESPINOSA M. FALLER G. HADDAD J. HOFFMAN D. JOHNSON J. JOYNER S. LeVALLEY J. PAYNE G. SKROBOT (Det –OSP) D. SOLLBERGER M. STOWE (PDP) Launch Services Program Organization M. LOPEZ-TELLADO J. PALIN C. WHITTAKER CHIEF M. CARNEY A. ABDALLAH, PhD J. BAUSCHLICHER B. BEAVER R. CHOY D. COON J. GILES E. HADDOX D. LUDWICZAK E. NEW E. PICHARDO T. REINARTS, PhD P. SCHALLHORN, PhD T. SHEMANSKI B. SONG, PhD J. SUDERMANN D. TROUT E. VICTOR C. WALKER, PhD L. WALLS V. WIKANDER I. YUNIS, PhD C. BURKE (Co-op) K. CLINTON (Co-op) EOD 09/22/03 C MONTGOMERY(Co-op)

  4. Director, Launch Services Program Mission Mission Mission Mission Mission Integration Team Spacecraft customers Launch service contractor Mission Integration Team Mission Integration Manager Discipline Engineers, Launch Vehicle Dev, Mission Analysts, Mission Assurance, others Procurement, Finance Integration Engineer Launch Service Manager Launch Site Integration Manager KSC Range, support contractor, safety, launch operations, others Mission Integration Team • Total management of mission integration process • One team per mission • Core team membership drawn from Launch Services Program • Expanded core team includes all other support functions • Customer point of contact • Launch services mission point of contact

  5. Mission Integration Team • The Mission Integration Team, or MIT, is a multi-discipline team that is tasked by the ELV Launch Services Directorate with the responsibility of managing all integration and vehicle engineering aspects of the assigned mission. • The Mission Integration Team is led by the following: • Mission Integration Manager: Garrett Skrobot / (321) 476-3711/ Garrett.L.Skrobot@nasa.gov • Launch Services Manager : Bobbi Gnan / (321) 867-1179 / Roberta.P.Gnan@nasa.gov • Launch Site Integration Manager : Frank Valdes / (321)476-3703 / Francisco.Valdes@nasa.gov • Integration Engineer : Merri Anne Stowe / (321) 476-3613 / Merri.A.Stowe@nasa.gov • The primary areas of responsibility are as follows: • Mission Integration Manager (MIM) • The project manager and primary customer interface for mission specific integration. This person has overall mission management responsibilities for technical, contract deliverables, resources and schedule. • Launch Services Manager (LSM) • Provides program and business management for the launch services contract, including specialized support in procurement and resource management. • Launch Site Integration Manager (LSIM) • The interface for launch site processing of the spacecraft and is responsible for; advance planning for launch site processing, capturing and implementing spacecraft processing requirements, and acting as the spacecraft's consultant and advocate at the launch site. • Integration Engineer (IE) • Technical lead for the mission specific integration including mission unique requirements definition, development and verification, and providing the interface with the Vehicle Systems Branch for • gaining insight into fleet status and assigned hardware production issues.

  6. Mission Plan Overview • KSC will develop a Mission Plan in support of THEMIS • Documents the services and products that the THEMIS Project, GSFC, UCB, and Swales can expect from KSC LSP, as well what KSC LSP expects from the THEMIS Project throughout the launch vehicle mission integration process • Mission plan typically based on 27 month integration cycle • THEMIS would like to initiate integration at L-30 months • THEMIS interface and mission requirements are being developed

  7. NASAExpendable Launch Vehicle Launch Services DirectorateKennedy Space Center THEMISMission Plan (February 2004) The KSC ELV Mission Integration Manager is responsible for the content of this plan, which can be found at: http://www.ksc.nasa.gov/elv/plan

  8. Welcome to the exciting and fast paced world of the ELV Launch Services Directorate at Kennedy Space Center. Our goal is to provide NASA Spacecraft Customers with reliable, cost effective launch services. What the following documentation reflects is the services and products that you can expect from us, as well as what we will need from you as we begin our voyage together. E L V M A J O R P R O C E S S F L O W Mission Design, Integration & Engineering Advanced Planning Baseline Mission Procure Launch Service Launch Site Operations Launch Management Post Launch Vehicle Production Insight The Mission Plan covers this portion of the Process Flow E X P E N D A B L E L A U N C H V E H I C L E S

  9. THEMIS Launch Service Contract • Launch date: Flight Planning Board (8/06) • Launch Vehicle Configuration: 7925 – 10C • Launch Site – Eastern Range SLC-17 • Authority to Proceed Options: • L-30 months – 02/2004 • L-27 months – 05/2004 • Contract initiation date: TBD, 02/2004 planned • Contract: Boeing NLS CLIN 19, firm mission • KSC ELV Launch Service includes: • Contracted launch service • Technical Insight consistent with NPD 8610.23 • Launch vehicle telemetry coverage • Payload Processing Facility: Commercial • Mission unique budget

  10. 7925: Launch Vehicle

  11. Spacecraft Separation SECO-1 Third Stage Burn Earth SECO-3 Restart-1 Restart-2 MECO SECO-2 Launch Three-Burn Orbit Profile

  12. SECO-1 (573 sec) SECO-2 (1288 sec) Stage II Ignition (276 sec) SECO-3 (4128 sec) Stage III Burnout (4306 sec) Restart-1 (1267 sec) Restart-2 (4013 sec) Stage III Ignition (4218 sec) MECO (262 sec) Spacecraft Separation (4593 sec) SRM Drop (3) (132 sec) SRM Drop (6) (66 sec) Three SRM Ignition (65.6 sec) Six SRM Burnout (63 sec) Eastern Range Launch Site, Flight Azimuth 93 deg, maximum capability to 9.0 deg inclined orbit, 637 Km (344 nmi) perigee, 70661 Km (38154 nmi) apogee 7925: Flight Profile

  13. Risk Category / KSC ELV Insight Summary • Category 3 mission per NPD 8610.7 • Delta II Certified to Category 3 • KSC ELV Mission Integration Team approach • Nominal Delta II Mission • Technical insight consistent with NPD 8610.23 • Launch vehicle production, assembly and launch • Spacecraft to launch vehicle Integration, requirements development & testing support • Mission unique hardware, analysis, testing • No unique or extraordinary insight requirements anticipated

  14. Mission Integration Progress • Integration Meetings • Bi-Weekly telecons on-going since 8/2003 • Analysis completed by KSC to date includes: • Performance verification • Sun angle data • Trajectory data • Additional analysis to be coordinated • Fairing envelope analysis • Early trajectory analysis by Boeing • Nutation time constant/coupled loads analysis • Documentation • S/C Interface Control Document template provided to Project in September • Delta II User’s Guide MDC00H0016, October 2000

  15. THEMIS KSC Engineering Team • Mission Unique Integration Engineer – Merri Ann Stowe • Leads mission unique engineering team assigned to THEMIS • Flight Design – Bill Benson • Dynamics loads – Dr. Isam Yunis • Environments – Dr. Brian Song • Thermal – Dr. Tom Reinarts • Software – Bill Benson • Controls – Jim Suderman • Contamination - Chris Rawlins • EMC/EMI/RF – Noel Sargent • Elec Sys Interface – Jim Hoffman • Mech Sys Interface – Greg Galloway • Delta II Fleet Vehicle – Vehicle Systems Lead – JJ Joyner • Systems engineers for all major subsystems • Follow all vehicle issues for all missions until resolution • Chief Engineer – James Wood/Darren Bedell • Oversees engineering review process and chairs Engineering Review Board (ERB)

  16. Typical NLS Integration ScheduleSpacecraft Input Timelines Input from Input required from Spacecraft Integration Products Spacecraft Team Team Due: ICD/Mission Specification/Verification Matrix ………………… Interface Reqmts Document (IRD) ATP (L-27mo) Loads Analyses • Spacecraft Environmental Testing Plans…………………. Testing Plans Test-9 weeks • Spacecraft Test Data Summary…………………………….. Test Data or Report (if available) Test Completion + 4 week • Preliminary Design Loads Cycle (PDLC)…………………. PDR Pre-Test Spacecraft Dynamic/FEM Model ATP (L-27mo) • Final Design Loads Cycle (FDLC) …………………………. CDR Pre-Test Spacecraft Dynamic/FEM Model L-78 weeks and Mass Prop Report • Verification Loads Cycle (VLC) ……………………………. Test-verified (correlated) Spacecraft Model L-38 weeks and Mass Prop Report Trajectory/Performance Analyses • Trajectory Feasibility Analysis (TFA)……………………… Best avail mission reqmts ATP (L-27mo.) • (e.g., S/C mass, orbit, tracking) • Preliminary Mission Analysis (PMA)………………………… Updated mission reqmts and Mass Prop Report L-66 weeks • Detailed Test Objectives (DTO)……………………………… Updated mission reqmts w/ L-windows and Mass Props L-39 weeks • Final Mission Analysis (FMA)………………………………… Final mission reqmts including L-windows L-5 weeks • Final Mass Properties Report…………………………………. Final Mass Properties Report L-5 weeks Other Engineering/Analyses • Payload Compatibility Drawing (preliminary)…………….. PDR drawings and Fairing Requirements L-99 weeks • Payload Compatibility Drawing (final)…………………….. Final drawings L-78 weeks • Spacecraft Separation Analysis (initial) …………………. Initial Nutation Time Constant input L-66 weeks • Spacecraft Separation Analysis (Final)……………………. Final Nutation Time Constant input L-4 weeks • Integrated Thermal Analysis (ITA)………………………… Spacecraft Geometrical/Thermal mathematical models L-38 weeks • Payload Fairing Venting Analsysis……………………….. Identify Spacecraft ventable/non-ventable volumes L-26 weeks • RF Compatibility Study ……………………………………. Input for RF application for radiating on-site L-8 weeks • Launch Vehicle Insignia (Project/NASA Logo) ………….. Final drawings L-43 weeks

  17. Typical NLS Integration ScheduleSpacecraft Input Timelines (continued) Input from Input required from Spacecraft Integration Products Spacecraft Team Team Due: Launch Site Related Documentation • Spacecraft Launch Site Test Plan …………………………. Testing plans at launch site L-34 weeks • Spacecraft Integrated Test Procedures…………………… Testing Requirements that include both SC and LV L-20 weeks • Spacecraft Launch Site Standalone Test Procedures … Standalone Test Procedures L-18 weeks • Spacecraft-to-Blockhouse wiring diagrams …………….. LV Flight Harness/Spacecraft GSE wiring requirements L-78 weeks • Launch Site Support Plan (LSSP) – KSC document …… Launch Site Support Requirements L-60 weeks Range Safety Documentation - Spacecraft Missile System Pre-launch Safety Package (MSPSP) • Draft Spacecraft MSPSP ……………………………………. EWR 127-1 requirements PDR-45 days • Preliminary Spacecraft MSPSP …………………………… EWR 127-1 requirements CDR-45 days • Final Spacecraft MSPSP……………………………………. EWR 127-1 requirements Spacecraft arrival -45 days

  18. Safety Overview • A Range Program Introduction/Safety TIM will be held following the PDR on November 14 • Early start on process • KSC LSP Safety and Flight Assurance Office has established processes and procedures for launch vehicle insight and risk mitigation

  19. Risk Assessment and Management • KSC will use an existing Risk Process • Matrix format • Probability vs Impact • On-site personnel at LSPs and ongoing engineering review boards ensure timely identification of risks and assessment of corrective action • Formal risk process begins at Authority to Proceed for launch vehicle mission integration • ATP for THEMIS is February, 2004

  20. Risk List for MRO • KSC has identified two potential risks to be formally documented at ATP • Probe carrier interfaces with the Delta launch vehicle third stage • Unique design and interaction with third stage need to be fully understood to assess level of risk • Risk mitigation • Early discussions on design and implications • Early coordination with Boeing as required • Performance verification • Boeing is updating performance curves for the Delta II launch vehicle • Possible reduction of mass to orbit • Risk mitigation • Early discussions on trajectory options • Early trajectory analysis from Boeing • All potential risks are being identified early to assist in mitigation efforts as they relate to technical, cost, and schedule implications

  21. Launch Service Program Summary • Integration efforts with THEMIS have been initiated early and are ongoing • This joint effort has led to the initial development of a detailed plan for successful integration • Potential risks/threats defined early • Allows for proper mitigation strategy development • Launch Service Program is ready to proceed in support of the THEMIS program

  22. BACK UP CHARTS

  23. Mission Integration Team (continued) The Extended Mission Integration Team is available to support the MIT and S/C Customers. The Extended Mission Integration Team consists of the following members: Vehicle Systems Provides launch vehicle insight utilizing expertise in areas such as flight controls, structures, mechanical/fluids and propulsion. Launch vehicle fleet changes or anomalies are assessed for their applicability to vehicles assigned to NASA missions and the risks of these are evaluated. Recommendations for disposition of these risks are developed and forwarded to the ELV Project for consideration. In addition, the Vehicle Systems group provides core vehicle engineering support to Mission Integration for aiding in the development of mission unique modifications and in support of integrated operations. Resident Office Provides on-site launch vehicle insight into design, fabrication and testing of the launch vehicles assigned to NASA missions, in coordination with the Vehicle Systems Branch. Provides a local point of coordination with the launch vehicle providers to facilitate communication of KSC ELV concerns and information exchange. Offices are established at each of the major production centers and at VAFB. Mission Analysis Branch Performs mission analysis in the areas of flight design, loads and environments, flight controls, flight software and thermal design in support of advance mission studies and mission integration activities. Throughout the integration process, each discipline works to assure that the mission analysis requirements are properly defined. In addition, review and/or IV & V of mission unique design requirements is performed in order to confirm all requirements have been met. The Extended Mission Integration Team is continued on the next page.

  24. Mission Integration Team (continued) Safety and Flight Assurance (S&FA) Safety and Flight Assurance Office (SFAO) Ensures mission success through application of safety assurance and quality assurance processes applied to the review and assessment of Launch Service Provider's (LSP) safety and quality programs (NASA-STD-8709.2). Implements NASA ELV Safety and Mission Assurance Standards for spacecraft operations while at NASA facilities (NASA-STD-8719.8), and for launch vehicle operations from procurement through launch. Civil service (NASA, DCMA) and contractor personnel located at KSC and resident offices perform safety and flight assurance activities related to LSP launch vehicle processing. Provides coordination with KSC Safety and Range Safety. Activities include: review and assessment of Launch Service Provider processes, Software Assurance and review of LSP Quality and Safety Program Plans. Communications & Telemetry Provides engineering and communications services for launch vehicle and spacecraft. Support includes voice, video, data, timing, RF and network communications as well as telemetry processing of expendable launch vehicles and selected spacecraft telemetry streams. The Electromagnetics Effects lab provides engineering and services for Electromagnetic Compatibility (EMC), Frequency Control and Analysis (FCA), and the Reradiating Antenna System (RAS) for KSC, the Eastern Test Range and NASA facilities at VAFB. EMC capabilities include specification testing and resolution of hardware, system and facility EMC compatibility problems as well as surveillance, RF interference resolution, and radar beacon transponder measurements for all launch vehicles in support of Range Safety.

  25. Mission ICD • Contract Document between NASA/KSC and the Launch Service Provider • Approval signature from LSP • Approval signature from NASA/KSC • Approval signature from Customer Approval: Customer Approval & Configuration Control: Launch Service Provider Approval: NASA/KSC

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