1. 1 NASA’s Goddard Space Flight Center 2005/4/14 LRO/CRaTER Technical Interchange Meeting LRO Mechanical Systems Giulio Rosanova / 543 301-286-5907 / Giulio.G.Rosanova@nasa.gov

2. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 2 LRO Baseline (Deployed 0n Orbit) Propulsion Module High Gain Antenna Avionics Module IM Optical Bench /Radiator Solar Array X (Thrust) Y Z (NADIR)

3. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 3 LRO Baseline (Deployed on Orbit) Instrument Module Propulsion Module Solar Array High Gain Antenna Avionics Module Optical Bench / Radiator X (Thrust) Z (NADIR) Y

4. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 4 LRO Baseline (Stowed) Instrument Module Propulsion Module Solar Array High Gain Antenna Avionics Module

5. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 5 LRO Nomenclature SPACECRAFT BUS ORBITER Propulsion Electrical Mechanical Thermal PROPULSION MODULE Electrical Mechanical Thermal INSTRUMENT MODULE CRaTER Diviner LAMP LEND LOLA LROC INSTRUMENTS HGA Dish Deployables Gimbals Boom HIGH GAIN ANTENNA SYST Solar Cells Substrate Deployables Gimbals Boom SOLAR ARRAY SYSTEM Electrical Mechanical Thermal AVIONICS MODULE SPACECRAFT

6. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 6 LRO Coordinate System Definition THRUST DIRECTION (+X) NADIR (+Z) RHR (+Y) Coordinate Axis Origin Located at center of L/V Separation Plane ZENITH (-Z) Velocity Vector +/- X axis

7. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 7 Mechanical Baseline Design 110 in. (2.8 m) 79 in. (2.0 m) 82 in. (2.1 m)

8. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 8 LRO Launch Vehicle Interface DELTA-II 3-Stage 9.5 ft. P/L Envelope 100” DIA. (2.54m)

9. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 9 Mechanical System Requirements Mechanically Accommodate LRO Instrument Suite Provide Mechanically Stable Instrument Bench for Pointing Requirements Meet Instrument FOV Requirements Provide Thermal Radiator Area for Instruments Provide Orbiter Purge System for Instruments Compatibility with DELTA-II Class Launch Vehicle Instruments shall comply with “LRO Structural Loads and Mechanical Environments Specification” (430-SPEC-000022) Fairing Doors for Instrument Access on Launch Pad T-0 Purge Available

10. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 10 Mechanical System Requirements Comply with LRO Alignment, Pointing Jitter Budget Instrument Pointing/Alignment Errors Thermal Distortion after Off-Pointing and/or Eclipse, G-Sag High Frequency Jitter –Deployed Structures First deployed Frequency: ≥1 Hz Verify all Mechanical / Structural Designs and Functionality Qualification by Test Use Simulators to Verify Interfaces Provide Orbiter Wiring Mock-Up Instrumenters to provide Hi-Fi Mass simulators for complex Designs –Used for LRO Orbiter Structural Qualification Testing

11. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 11 LRO Instruments INSTRUMENTMASSFOV(R) CRaTER5.60 kg60º Full Angle Nadir & Zenith Diviner9.98 kg160º Full Angle Nadir Centered LAMP5.00 kg40º Full Angle Nadir Centered LEND23.20 kg20º Full Angle Nadir Centered (4) LOLA10.60 kg<<1º Nadir Centered (2) LROC14.40 kgNAC (2)- 60º Full Angle WAC- 120º ct X 30º dt

12. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 12 LRO Fields of View

13. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 13 CRaTER Fields of View

14. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 14 CRaTER Fields of View

15. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 15 CRaTER Fields of View

16. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 16 CRaTER 30ºZ-80ºN Fields of View

17. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 17 CRaTER 30ºZ-80ºN Fields of View

18. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 18 CRaTER 30ºZ-80ºN Fields of View

19. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 19 Instrument Design Requirements Design Limit Load: 12 g’s any axis Minimum Factors of Safety Minimum Frequency Requirement: 35 Hz (50 Hz Recommended) Overall acoustic environment: 149.6 dB qual, 146.6 dB acceptance Random Vibration Environment for Instruments and Components

20. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 20 **Total Mass: 2490 lbm (1129 kg) **CG (Origin at center of clampband IF) **Mass Moments of Inertia LRO FEM: Configuration F

21. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 21 Fundamental Mode: Lateral Direction f n = 19.6 Hz f n = 19.9 Hz **Mass scaled to launch vehicle capability (1480 kg)

22. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 22 Fundamental Mode: IM f n = 46 Hz

23. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 23 Mechanical Topics for TIM –CAD Models: (PRO-Engineer), (SOLID-WORKS), (IDEAS) –Identify CRaTER Orientation wrt LRO Coordinate System –Identify Access zones to support testing do you Require? (i.e., sources required for calibration, etc) –Identify Connector Locations and Access/Stay-Out Zones Required? –Identify Optical Reference Surfaces (as required)? Alignment cube/reference mirror surfaces: size, and location? –Identify GSE Handling Points – Will Aperture Doors or Shutter be Considered? –FEA Models: (FEMAP), (NASTRAN)

24. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 24 Mechanical Topics for TIM –Identify your Design Heritage? (have some MLA info) What were the design limit loads? What factors of safety were used? What was the random vibration environment? What was the instrument’s first frequency ? What Analysis Documentation Exists? What Verification Test Reports Exist? Is the instrument sensitive to shock or acoustics? –Do you require Access while on the Launch Pad? –Do you require T-0 Purge at Launch? –Mechanical Mass Simulator Required Simple Designs over 50 Hertz (i.e. LAMP, CRaTER) mass and CG only. –Mass Simulator must be Qualified before Orbiter Structural Testing.

25. NASA’s Goddard Space Flight Center 2005/4/14 Mechanical Systems Giulio Rosanova/543 25 LRO Mechanical System Development Flow MECHANICAL Design & Analysis Mechanical System Assy. Functional Mechanical Qualification Testing Orbiter I&T MECHANICAL Fabrication Spacecraft I&T PROP. Module (FLT) Build & Proof Orbiter Environmental Testing Launch Activities PROP. Module (PTyp) Build S/C Bus (PFlt) Build Inst. Module (PFlt) Build Deployables (PFlt) Build & Test LRO S/C Subsystems / Components INSTRUMENTS 12/06 9/06 4/07 1/07 10/07 2/08 LRD 10/08 PM Pluming Assy. 10/06 1/07 10/07 7/07 CDR 4/06 7/08 INSTRUMENT MASS SIMS. 12/06