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 Max Back Maximum Ground Pressure Maximum Airborne Operational GSDO Mass Flow Temperature Humidity Interface Media @ Max Hydrocarbons Particle Comments Phase Baseline Rate (°F) Ratio Name (ppm) Specification Flow Rate (gr/lb DA) (psig) Integrated ICPS/FWD Conditioned ISO Class Y 12 0.7 65 - 85 37 15 and Stacked (MSA) Air 8 No ECS during Rollout required ICPS/FWD Rollout N --- --- --- --- --- --- --- for Block 1 MPCV (MSA) configuration. Conditioned Y 12 0.7 65-85 37 Air On the ICPS/FWD ISO 14644-1, 15 Launch Pad (MSA) Class 8 Gaseous 14 0.8 65-150 1 Y Nitrogen 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).
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).
sls-secondary_payload_users_guide.docx