1. 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
NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration. The capability to deploy small satellites allows SLS to fully utilize excess capability on the planned exploration missions. With the planned mission trajectories, cubesat payload developers will have an opportunity to operate in deep space, a capability not realized to this point.
Thank the audience and organizers.
There should be time for questions and answers.

3. SLS Configuration Orion: Carries astronauts into deep space
Stage Adapter:
The Orion MPCV Stage Adapter will be the first new SLS hardware to fly.
Interim Cryogenic Propulsion Stage:
Based on the Delta IV Heavy upper stage; the power to leave Earth
Core Stage:
Newly developed for SLS, the Core Stage towers more than 200 feet tall
1) The Block 1 SLS leverages heritage hardware and technology to support affordable development and reduce risk.
2) The SLS Program is finding ways to upgrade those systems to improve performance.
3) SLS is designed with an approach that will enable evolution into the most powerful launch vehicle ever flown.
Solid Rocket Boosters:
Built on Space Shuttle hardware; more powerful for a new era of exploration
RS-25 Engines:
Space Shuttle engines for the first four flights are already in inventory

4. SLS Configuration MSA Diaphragm MPCV Stage Adapter (MSA)
Interim Cryogenic Propulsion Stage (ICPS)
Launch Vehicle Adapter (LVSA)
Core Stage

5. SLS Secondary Payload Accommodations
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
~56°
~22°
~21°
~Ø156”
~8°
6U mass of 14kg with expected deployer 5

6. 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
The MPCV-to-Stage Adapter produced at MSFC will fly with Orion on EFT-1 next year. Drove design of brackets and available resources
Trickle charge may be available while in VAB and access to MSA is available

7. Secondary Payload Deployment System (SPDS)

8. 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
EM-1 launch window is typically 7 days each Month
Lunar Transfer Time varies within the launch window but has a 3.5 to 8.5 day bound. The provided state is in the middle of the launch window and ~ 6 days.
Payload deployment window starts approx L+4.5 hours
Allows time for safe distance after Orion separation, disposal manuevers including transverse spin, ICPS blow down
All payloads must be deployed prior to the expiration of the sequencer battery life. No TLM will be available through the ICPS system
May choose to cluster ejections for some instruments while others may be deployed at variable intervals.

10. Animation

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
NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration. The capability to deploy small satellites allows SLS to fully utilize excess capability on the planned exploration missions. With the planned mission trajectories, cubesat payload developers will have an opportunity to operate in deep space, a capability not realized to this point.
Thank the audience and organizers.
There should be time for questions and answers.

12. 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

13. 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
SLS EM-1 PSRP Process Document
Defines Phased Review approach
Outlines Safety Panel details
Increment Definition and Requirements Document
Direct requirements flow down, interface requirements, safety requirements
Generic Payload Verification Plan included
Controlled Document

14. NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration.
Questions?
NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration. The capability to deploy small satellites allows SLS to fully utilize excess capability on the planned exploration missions. With the planned mission trajectories, cubesat payload developers will have an opportunity to operate in deep space, a capability not realized to this point.
Thank the audience and organizers.
There should be time for questions and answers.

15. BACKUP Thank the audience and organizers.
NASA’s Space Launch System (SLS) will provide unprecedented capability to further advances in science and exploration. The capability to deploy small satellites allows SLS to fully utilize excess capability on the planned exploration missions. With the planned mission trajectories, cubesat payload developers will have an opportunity to operate in deep space, a capability not realized to this point.
Thank the audience and organizers.
There should be time for questions and answers.

16. Orient for Disposal Maneuver, minutes long
EM-1 DRO Trajectory and Timeline Plan
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
Deployment Window Opens, app 4-5 hours post T-O
Disposal Maneuver,
start time dependent on duration of blowdown, 5-10 minutes
Disposal Maneuver, start time dependent on duration of blow down, 5-10 minutes
No BBQ roll after disposal maneuver complete. 16