Presentation on theme: "National Aeronautics and Space Administration Secondary Payloads Overview George Norris NASA Marshall Space Flight Center."— Presentation transcript:
National Aeronautics and Space Administration Secondary Payloads Overview George Norris NASA Marshall Space Flight Center
2 Background NASA has taken steps to increase the scientific and exploration capability of SLS by providing accommodations for Cubesat Class payloads on EM-1 Requirements for Secondary Payload Accommodations on Exploration Missions were approved January 2014 Large support base for this capability across the agency, government and the international community
Orion: Carries astronauts into deep space RS-25 Engines: Space Shuttle engines for the first four flights are already in inventory Solid Rocket Boosters: Built on Space Shuttle hardware; more powerful for a new era of exploration Core Stage: Newly developed for SLS, the Core Stage towers more than 200 feet tall Interim Cryogenic Propulsion Stage: Based on the Delta IV Heavy upper stage; the power to leave Earth Stage Adapter: The Orion MPCV Stage Adapter will be the first new SLS hardware to fly. SLS Configuration
SLS Secondary Payload Accommodations 5 Eleven 6U/12U payload locations 6U volume/mass is the current standard (14 kg payload mass) Payloads will be “powered off” from turnover through Orion separation and payload deployment Payload Deployment System Sequencer; payload deployment will begin with pre-loaded sequence following MPCV separation and ICPS disposal burn Payload requirements captured in Interface Definition and Requirements Document 5 ~56° ~22° ~21° ~Ø156” ~8°
SLS Secondary Payload Accommodations Payloads will provide deployers per NASA provided specifications No resources or telemetry provided by launch vehicle once installed State vector data at deployment will be provided to ground operators for predictions Payloads responsible for acquiring communication and telemetry bandwidth 6
Secondary Payload Deployment System (SPDS)
Selected Deployer 6U (PSC) Deployer is COTS w/modifications COTS Features − Externally accessible separation connector − Redundant signal for door activation − Accommodates 14 kg payloads − Spring jettison rate of 4.6 ft/sec − Access for battery charging, once integrated − No pyrotechnic devices − Existing GSE attachment/handling points − External conductive surface, chassis grounding Modifications − Addition of captive fasteners for mounting − Possible addition of vibration isolators − Possible addition of thermal blanket Note: Last two modifications are payload driven based on their designs.
9 Payload Deployment
11 Mission Integration SLS Secondary Payload Mission Integration Team will be responsible for end-to- end integration and coordination between SLS Vehicle and secondary payloads –MI Function will integrate all phases of the lifecycle including Engineering Integration, Operations Integration, S&MA, and Ground Processing Payloads will be assigned a Secondary Payload Integration Manager (SPIM) to guide payload through integration lifecycle –SPIM will develop ICD’s to capture mission-specific, payload-specific requirements and verification plan MI team will CoFR integrated payload complement to SLS/SPIE to facilitate ISPE CoFR and verification
Secondary Payloads Concept of Operations ICD developed for each payload detailing interface and safety requirements and applicable verification requirements Phased Safety Reviews conducted Phase 0/I (at PDR level design maturity) Phase II (at CDR level design maturity) Phase III (prior to payload delivery to KSC) Cubesat integrated into dispenser and final testing performed Final verifications complete Integrated Payload (dispenser/cubesat) delivered to NASA Payload Integrated in MSA Final Battery charging prior to first rollout to pad 12
Secondary Payloads Key Documentation Secondary Payloads User’s Guide General capabilities, interfaces and processes Publicly Releasable SLS EM-1 Safety Requirements for Secondary Payloads Safety Requirements for EM-1 MSA Secondary Payloads Publicly Releasable SLS EM-1 PSRP Process Document Defines Phased Review approach Outlines Safety Panel details Publicly Releasable Increment Definition and Requirements Document Direct requirements flow down, interface requirements, safety requirements Generic Payload Verification Plan included Controlled Document 13
Questions? 14 NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration.
EM-1 DRO Trajectory and Timeline Plan Disposal Maneuver, start time dependent on duration of blowdown, 5-10 minutes Time End of TLI burn. T-0-3Hrs Grd launch window up to 2 Hrs long (depends on launch day in weekly window) DRO Mission Scenario— Weekly Launch Window with Lunar Arrival ~3.5 to 8.5 days..early in window is longest trip time End of the disposal maneuver, the ICPS is at 26,750 km Earth Radius inertial velocity of km/s ICPS/MPCV Separation 10 minutes after end of TLI burn ICPS attitude hold for 5 minutes 25 minutes Passive Thermal Control (BBQ Roll 0.5 deg/sec), oriented Sun Normal, attitude transitions not shown Blowdown while in a transverse spin to minimize delta V. Starts 30 minutes after separation. Highly variable, tank propellant driven, 0-30 minutes Orient for Disposal Maneuver, minutes long Post-disposal, duration dependent on ACS propellant usage, battery life, and mission requirements. ACS fuel driven, low thrust. Engine bell forward in line of velocity vector. X T0+8 hrs ICPS Batt dies X Deployme nt Window Opens, app 4-5 hours post T-O Disposal Maneuver, start time dependent on duration of blow down, 5-10 minutes No BBQ roll after disposal maneuver complete. 16