SPACE LAUNCH SYSTEM (SLS)

Transcription

1 1 SPACE LAUNCH SYSTEM (SLS) MODEL ASSEMBLY INSTRUCTIONS Assemblies Described Orion Crew Capsule Service Module (SM) Interim Cryogenic Propulsion Stage (ICPS) Waldo3D Clermont, FL

2 2 Orion Crew Module (CM) Orion Crew Module Parts List Assembled View QTY Part 1 OrionCapsule-HeatShield 1 OrionCapsule-HeatShieldBodyConnector 1 OrionCapsule-Body 1 OrionCapsule-ForwardBulkhead 3 OrionCapsule-MainParachute 1 OrionCapsule-FCCover 4 OrionCapsule-DockingClamp 16 OrionCapsule-DockingHatch The Orion crew module (CM) is the reusable transportation capsule that provides a habitat for the crew, provides storage for consumables and research instruments, and serves as the docking port for crew transfers. The crew module is the only part of the MPCV that returns to Earth after each mission and is a 57.5 frustum shape, similar to that of the Apollo command module. As projected, the CM will be 5.02 meters (16 ft 6 in) in diameter and 3.3 meters (10 ft 10 in) in length, with a mass of about 8.5 metric tons (19,000 lb). It was manufactured by the Lockheed Martin Corporation. It will have more than 50% more volume than the Apollo capsule, which had an interior volume of 5.9 m3 (210 cu ft), and will carry four to six astronauts. After extensive study, NASA has selected the Avcoat ablator system for the Orion crew module. Avcoat, which is composed of silica fibers with a resin in a honeycomb made of fiberglass and phenolic resin, was formerly used on the Apollo missions and on select areas of the space shuttle for early flights. Source: Orion (spacecraft) -

3 3 Orion Crew Module Assembly OrionCapsule-DockingHatch OrionCapsule-DockingRing OrionCapsule-HeatShield OrionCapsule-Body OrionCapsule-MainParachute OrionCapsule-FCCover OrionCapsule-ForwardBulkhead OrionCapsule-HeatShieldBodyConnector

4 4 Interim Cryogenic Propulsion Stage Assembly ICPS Parts List Assembled View QTY Part 1 ICPS-Thruster 1 ICPS-ThrusterLOXSupportCage 1 ICPS-LOXTankBottom 1 ICPS-LOXTankTop 1 ICPS-LOXTankShroud 1 ICPS-LOX-LH2SupportCage 4 ICPS-SupportTankConnector 16 ICPS-SupportTank 2 ICPS-LH2TankTopBottom 1 ICPS-LH2TankCenter 1 ICPS-LH2TankShroud 1 ICPS-ServiceModuleAdapter Exploration Mission 1 (EM-1) in 2019, will use the Interim Cryogenic Propulsion Stage (ICPS). This stage will be a modified Delta IV 5 meter Delta Cryogenic Second Stage (DCSS), and will be powered by a single RL10B-2. Block 1 will be capable of lifting 70 t in this configuration, however the ICPS will be considered part of the payload and be placed into an initial 1,800 km by -93 km suborbital trajectory to ensure safe disposal of the core stage. ICPS will perform an orbital insertion burn at apogee, and then a translunar injection burn to send the uncrewed Orion on a circumlunar excursion. Source: Space Launch System -

5 5 ICPS Lower Assembly ICPS-LOXTankTop ICPS-LOXTankBottom ICPS-Thruster ICPS-LOXTankShroud ICPS-ThrusterLOXSupportCage ICPS LOX-LH2 SUPPORT CAGE TANKS ICPS-SupportTank ICPS-LOX-LH2SupportCage ICPS-SupportTankConnector

6 6 ICPS Upper Assembly ICPS-LH2TankShroud ICPS-LH2TankCenter ICPS-LOX-LH2SupportCage ICPS-ServiceModuleAdapter ICPS-LH2TankTopBottom

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