Giulio.G.Rosanova@nasa.gov 301-286-5907 Lunar Reconnaissance Orbiter (LRO) SRR/Mechanical System August 16-18, 2005 Giulio.G.Rosanova@nasa.gov 301-286-5907

Lunar Reconnaissance Orbiter (LRO) Mechanical System Applicable Documents 431-RQMT-000004 LRO Requirements Document 430-PG-1410.2.1 Robotic Lunar Exploration Program Configuration Management Procedure 430-RQMT-000006 Robotic Lunar Exploration Program Mission Assurance Requirements Document 431-ANYS-000010 Radiation Analysis for the Lunar Reconnaissance Orbiter 431-PLAN-000005 LRO Systems Engineering Management Plan 431-PLAN-000110 LRO Contamination Control Plan 431-SPEC-000008 Electrical Systems Specification 431-SPEC-000012 LRO Mechanical Systems Specification 431-SPEC-000091 LRO Thermal Systems Specification 431-SPEC-000112 LRO Technical Resource Allocation Specification 431-SPEC-000113 LRO Pointing and Alignment Specification (ALL) LRO Instrument Mechanical Interface Control Documents (ALL) LRO Spacecraft Component Mechanical Interface Control Documents

Lunar Reconnaissance Orbiter (LRO) Mechanical System Level 2 Flow Down Key Requirements Level 2 Req. Level 3: Requirements Concept/Compliance Paragraph Requirement MRD-21 Mission Duration Mechanical Level 3 Requirements Paragraph 1.0 The Mechanical System shall be adequately designed and analyzed to support a 14 Month Mission Life. The Mechanical System shall be designed and analyzed to minimize Thermal/Structural Distortion and maximize Stability See PM, AM, IM, DPLY Level 4 Specs., Mech. CAD Model, Mech. Assembly Drawing Packages, Analysis Reports MRD-70 Structural Stability MRD-71 Fields of View MRD-73 Accessibility Paragraph 2.0 & Paragraph 3.0 The Mechanical System shall accommodate the LRO Components/Instruments/Tech Demo and their Requirements , including Optical FOV and Thermal Radiator FOV requirements, as well as pointing and alignment requirements. The Mechanical System shall accommodate the CRaTER, Diviner, LAMP, LEND, LOLA, & LROC, Instruments and their Requirements per Inst. MICDs The Mechanical System shall accommodate the Mini-RF Tech Demo and its Requirements per Inst. MICDs The Mechanical System shall accommodate the Spacecraft Components and their Requirements per MICDs. MRD-15 Solar Array Tracking MRD-16 Antenna Tracking Paragraph 3.0 The Mechanical System shall provide a release, deployment, and articulation system for the deployment and articulation of the Solar Arrays (SADAS). The Mechanical System shall provide a release, deployment, and articulation system for the deployment and articulation of the High Gain Antenna System (HGADAS)its See DPLY Level 4 Specs., Mech. CAD Model, Mech. Assembly Drawing Packages, Analysis Reports MRD-2 Launch Vehicle MRD-28 Vehicle Interfaces Paragraph 4.0 The Mechanical System shall be compatible with the DELTA II Launch Vehicles and their requirements per LRO-L/V Mission Specification (TBD Doc. #) The Mechanical System shall be designed to meet the mechanical requirements of the Delta II L/V as defined in the DELTA II Payload Planners Guides See LRO-L/V MICD. CAD Model, Mech. Assembly Drawing Packages, Analysis Reports

Lunar Reconnaissance Orbiter (LRO) Mechanical System Level 2 Flow Down Key Requirements Level 2 Req. Level 3: Requirements Concept/Compliance Paragraph Requirement MRD-49 Pointing Allocations Mechanical Level 3 Requirements Paragraph 5.0 The Mechanical System shall comply with LRO LRO Pointing and Alignment Specification 431-SPEC-000113, Includes Instrument, S/C Components, Solar Array & High Gain Antenna See PM, AM, IM, DPLY Level 4 Specs., Mech. CAD Model, Mech. Assembly Drawing Packages, Analysis Reports ??? Paragraph 8.0 The Mechanical System shall Adopt a Single String approach for the Mechanical / Structural Design and Development and perform adequate analyses and tests to verify design. Selective Redundancy shall be allowed MRD-76 Support Equipment Paragraph 11.0 The Mechanical System shall provide the LRO Observatory MGSE. MRD-69 Contamination Control Paragraph 14.0 The Mechanical System shall Incorporate Instrument Dry Purge Lines on Orbiter up to T-0 (umbilical break-away line).

Lunar Reconnaissance Orbiter (LRO) Mechanical Concept ADDITIONAL VIEWS TO FOLLOW

Lunar Reconnaissance Orbiter (LRO) Mechanical Verification Summary Verify all Mechanical / Structural Designs and Functionality Analysis Comply with LRO General Structural-Thermal Environments, Interface, and Veification Requirements Overall System Level Verification Matrix Verification by Analysis, and or Verification by Test of Proto-Type and/or Proto-Flight Units Facilitate Functional and Performance testing of the LRO Observatory S/A & HGA Deployment Monitoring (Potentiometers) S/A & HGA shall Survive in Deployed Position Immediately after Observatory Separation thru LTO Qualification Testing Mech System Orbiter Functional Testing Life Tests Deployment testing in T/V

Lunar Reconnaissance Orbiter (LRO) Mechanical Requirements Summary Mechanical System is ready to proceed to PDR