Figure 4-2 SLS Configuration for EM-1 MSA The MSA a common interface between the MPCV and the ICPS upper stage. A diaphragm, attached to the inside bottom of the MSA hardware, isolates the ICPS volume from the MPCV volume. For the EM-1 mission, the MSA will accommodate secondary payloads and all support equipment consisting of brackets, cabling, a battery, and a deployment sequencer. The MSA will provide the payload structural interface. The SLS Program is responsible for installing 12 bracket assemblies and the SPDS and its associated harnesses in the MSA. The bracket assemblies will support up to 11 manifested secondary payloads with the twelfth bracket assembly supporting the deployment system sequencer and battery. ICPS The ICPS is an in-space propulsion system that performs the LEO insertion, trans-lunar injection (TLI), and ICPS disposal maneuver. As the upper stage on SLS, the ICPS is integrated with the MPCV via the MSA which transitions the Outer Mold Line (OML) diameter of the ICPS to that of the MPCV. SPDS The SPDS manages the deployment of secondary payloads at designated points along the primary mission trajectory. The SPDS is comprised of an avionics box (sequencer and battery), a deployer, distributed cable harnesses, and ground support equipment. The SLS Program
EM-1 secondary payloads should be aware that they will be subjected to prelaunch pad conditions for up to a period one to two months. Table 7-1 Natural Prelaunch Environmental Conditions Operational Phase Ground Interface Name GSDO Baseline Media Mass Flow Rate Max Back Pressure @ Max Flow Rate (psig) Temperature (°F) Maximum Humidity Ratio (gr/lb DA) Maximum Hydrocarbons (ppm) Airborne Particle Specification Comments Integrated and Stacked ICPS/FWD (MSA) Y Conditioned Air 12 0.7 65 - 85 37 15 ISO Class 8 Rollout ICPS/FWD (MSA) N --- --- --- --- --- --- --- No ECS during Rollout required for Block 1 MPCV configuration. On the Launch Pad ICPS/FWD (MSA) Y Conditioned Air 12 0.7 65-85 37 15 ISO 14644-1, Class 8 Y Gaseous Nitrogen 14 0.8 65-150 1 Humidity, Cleanliness, and Thermal Control The thermal environment during preparation in the KSC launch facilities is controlled by temperature, relative humidity, cleanliness and contamination. The GSDO Program has standard services that control these thermal environment parameters. If unique cleanliness requirements are required, the SPIM will facilitate necessary discussions on a case-by-case basis. Launch and In-Space Environments In-Space Thermal SLS is responsible for providing Secondary Payload Customers environment information up to the point where the secondary payload leaves the shadow of the ICPS. Secondary payloads can experience a wide range of temperatures in the natural in-space environment. Depending on the post deployment orientation and location of the secondary payload, one side may be exposed to the sun while the other is exposed to deep space. Proximity to the Earth or the Moon can expose the payload to reflected sunlight (albedo) and emitted infrared radiation from those bodies. All of these have to be taken into account along with the payload thermal design and thermal/optical properties of the surface materials in order to calculate temperatures for the hardware. With typical cubesat spacecraft, the payload could experience surface temperatures ranging from 200F <TBR-001> with direct Sun on one side to -143F <TBR-001> with deep space on the other side. The thermal environment prior to deployment will be defined in the SLS Secondary Payload IDRD and in the Secondary Payload-Specific ICD(s).
Mass Properties & C.G. Report Payload-Provided At major reviews (MCR/SRR/PDR/CDR/FRR) Risk Assessment Report Payload-Provided At major reviews (MCR/SRR/PDR/CDR/FRR) Various Review Presentation Payload-Provided At major reviews (MCR/SRR/PDR/CDR/FRR) Materials Identification & Usage Lists (MIUL) and Material Usage Agreement (MUA) Payload-Provided At major reviews & part of verification pack Top Assembly Drawing Payload-Provided At major reviews & part of verification pack Drawing Package Safety Circuits Deployed Configuration Grounding Diagram Other Safety Related Items Payload-Provided At major reviews & part of verification pack Engineering Analysis Thermal Analysis Venting Analysis Radio Frequency Analysis Structural Analysis Electrical & Bonding Analysis Propulsion Analysis Any Unique Payload Analysis Pressure Vessel Analysis Payload-Provided At major reviews & part of verification pack Deviation & Waivers Payload-Provided At major reviews & part of verification pack Payload Test Plan Payload-Provided Prior to CDR Safety Data Package Payload-Assisted At Phase II & III reviews
GSDO Ground Systems Development and Operations GSE Ground Support Equipment GSFC Goddard Space Flight Center GSRP Ground Safety Review Panel H Height HDBK Handbook Hz Hertz ICD Interface Control Document ICPS Interim Cryogenic Propulsion System IDRD Interface Definitions and Requirements Document IE Interface Engineer I/F Interface in Inch(es) ISO International Organization for Standardization ISPE Integrated Spacecraft and Payload Element JSC Johnson Space Center KeV Kilo Electron Volt(s) kg Kilogram(s) KNPR KSC NASA Procedural Requirements KSC Kennedy Space Center L Length LAS Launch Abort System
Cube Class 3U, 6U, 12U, larger, or different class xU Unit Number of deployable objects within payload (cluster or 1, 2, …., x Transmission Frequency Identify what frequency your payload will use to communicate with ground or other. Stipulate difference between receiving and transmitting frequencies. MHz & Watts GROUND TRANSPORT TO KSC Resource Definition Units Payload Power No power in transport, acceptable? Yes or No Temperature Ambient Environment (45° to 100°F), acceptable? Yes or No Vibration Define, if any, shipping "g" limits? g Shock Define, if any, drop shock limits? g Environment Monitoring Does the payload need thermal /vibration limit/shock limit / humidity monitoring during ground transport? Yes or No: If Yes, List Environments to be Monitored Other List any other needs or resources to the payload. Optional
PRE/POST PAYLOAD IN MSA (AT MPCV FACILITY OR AT VAB) Resource Definition Payload Needs Power Is 28Vdc trickle charge [TBR] needed? Yes or No If yes, what amperage? Amps If yes, how long is trickle power needed? hours, days, or weeks List type & power size of battery in payload. NiCad, Li ion, etc. Volts & watts Environment Restrictions Are there any environment restrictions (temp., humidity, etc.)? Show Appropriate Unit Facility Support Will you perform any test & before payload/deployer installed in MSA? Yes or No If Yes, brief description of activities. List needed services. Power, N2, etc. List needed equipment. Table, lighting, etc. Other List any other needs or resources to the payload. Optional
PAYLOAD THE PAD (PRELAUNCH) Resource Definition Units Payload Needs Pad Dwell Time Can payload handle 2 months on pad without services (i.e. trickle charge)? Yes or No If No, what is maximum dwell time? Dry N2 Purge Can payload handle a 6 to 12 hour dry nitrogen during vehicle tanking, prior to lift-off? Yes or No Can payload handle a temperature of (-100°F to 80°F)? Yes or No List any other needs or resources to the payload. Optional
PAYLOAD DURING ASCENT (LAUNCH THROUGH MPCV DEPARTURE & DISPOSAL BURN (~4 5 HOURS) Resource Definition Units Payload Needs Ascent Can payload handle maximum vibration of [TBD-002]? Yes or No Can payload vent air during ascent at the rate of x.x psi/sec? Yes or No Does the payload contain any pressure vessels or trapped gas enclosures? Yes or No If Yes, then describe volumes & pressures. List any other needs or resources to the payload. Optional DEPLOYMENT (POST ICPS DISPOSAL BURN, PRE SHUTDOWN) FIRST OPPORTUNITY IS L+ 4 TO 5 HOURS. MOON WILL BE 3.5 TO 8.5 DAYS AWAY DEPENDING ON WINDOW. LAST CHANCE FOR DEPLOYMENT WILL BE 8 TO 9 DAYS [TBR] DAYS AFTER ICPS DISPOSAL BURN. Resource Definition Payload Deployment Describe point when payload is to be deployed. or days
Communication State method for communicating w/ground or other points. Description How long deployment will payload start transmitting data? sec., min., Other List any other needs or resources to the payload. Optional Disposal What is method of payload disposal? Earth reentry, crash on Moon, deep space, other OTHER INFORMATION: OPTIONAL
AGREEMENT FOR {PAYLOAD NAME} Appendix D of the SLS Secondary Payload User’s is to implement a co-signed Payload Integration Agreement (PIA) between the Secondary Payload Customer and the FP30/Exploration and Space Transportation Development Office as the binding agreement for meeting and implementing the latest technical integration requirements and management processes required to fly a secondary payload on the Space Launch System (SLS) vehicle. This PIA is applicable to all secondary payloads that will be integrated into the SLS stack. The PIA defines the management agreements by both parties and results in: (1) a co-signed PIA that will address management agreements; (2) the PIA becomes a separate standalone document; and (3) the PIA provides direction to applicable documentation so that the Secondary Payload Customer shall be in compliance with the latest requirements. The sections are preliminary and require further definition but aim to initially introduce and address potential sections of the PIA. PURPOSE The Payload Integration Agreement (PIA) documents the agreements to manage and execute the roles and responsibilities of the technical integration requirements, processes, services, and resources between the Secondary Payload Customer and the FP30/Exploration and Space Transportation Development Office for transportation services via the SLS vehicle. The effectivity of this co-signed PIA commences upon the last required signature of this document and continues through payload deployment from the SLS vehicle. REQUIREMENTS It is the responsibility of the Secondary Payload Customer or the FP30/Exploration and Space Transportation Development Office to verify compatibility of secondary payload/deployer physical and functional interfaces with the applicable SLS interface agreements and documents. FP30, on behalf of the SLS Program, however, intends to provide maximum flexibility in determining the manner or method to be used to accomplish this verification. All secondary payload/deployer physical and functional compliance shall be accomplished prior to installation for flight. DESCRIPTION The Secondary Payload Customer provides a top-level description that describes the basic function(s) and research objectives of the secondary payload. UNIQUE AGREEMENTS, CONSTRAINTS, OR SERVICES The Secondary Payload Customer or FP30, on behalf of the SLS Program, provides any unique deviations required from the management responsibilities or technical agreements.