LRO/CRaTER. Technical Interchange Meeting. LRO Mechanical Systems. Giulio Rosanova / /

Transcription

1 LRO/CRaTER Technical Interchange Meeting LRO Mechanical Systems Giulio Rosanova / / Giulio.G.Rosanova@nasa.gov 1

2 LRO Baseline (Deployed 0n Orbit) High Gain Antenna IM Optical Bench /Radiator Avionics Module Propulsion Module X (Thrust) Solar Array Y Z (NADIR) 2

3 LRO Baseline (Deployed on Orbit) Optical Bench / Radiator Instrument Module Solar Array Avionics Module Propulsion Module High Gain Antenna X (Thrust) Z (NADIR) Y 3

4 LRO Baseline (Stowed) High Gain Antenna Instrument Module Avionics Module Propulsion Module Solar Array 4

5 LRO Nomenclature ORBITER SPACECRAFT INSTRUMENTS CRaTER Diviner SPACECRAFT BUS LAMP PROPULSION MODULE AVIONICS MODULE INSTRUMENT MODULE Propulsion Electrical Mechanical Thermal Electrical Mechanical Thermal Electrical Mechanical Thermal SOLAR ARRAY SYSTEM Solar Cells Substrate Deployables Gimbals HIGH GAIN LEND ANTENNA SYST LOLA HGA Dish LROC Deployables Gimbals Boom Boom 5

6 LRO Coordinate System Definition Coordinate Axis Origin Located at center of L/V Separation Plane ZENITH (-Z) RHR (+Y) THRUST DIRECTION (+X) NADIR (+Z) Velocity Vector +/- X axis 6

7 Mechanical Baseline Design 82 in. 79 in. (2.1 m) (2.0 m) 110 in. (2.8 m) 7

8 LRO Launch Vehicle Interface DELTA-II 3-Stage 9.5 ft. P/L Envelope 100 DIA. (2.54m) 8

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 ) Fairing Doors for Instrument Access on Launch Pad T-0 Purge Available 9

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 10

11 LRO Instruments INSTRUMENT MASS FOV(R) CRaTER 5.60 kg 60º Full Angle Nadir & Zenith Diviner 9.98 kg 160º Full Angle Nadir Centered LAMP 5.00 kg 40º Full Angle Nadir Centered LEND kg 20º Full Angle Nadir Centered (4) LOLA kg <<1º Nadir Centered (2) LROC kg NAC (2)- 60º Full Angle WAC- 120º ct X 30º dt 11

12 LRO Fields of View 12

13 CRaTER Fields of View 13

14 CRaTER Fields of View 14

15 CRaTER Fields of View 15

16 CRaTER 30ºZ-80ºN Fields of View 16

17 CRaTER 30ºZ-80ºN Fields of View 17

18 CRaTER 30ºZ-80ºN Fields of View 18

19 Instrument Design Requirements Design Limit Load: 12 g s any axis Minimum Factors of Safety Type of Hardware Tested Flight Structure metallic Tested Flight Structure beryllium Tested Flight Structure composite* Pressure Loaded Structure Pressure Lines and Fittin gs Untested Flight Structure metallic only Ground Support Equipment Transportation Dolly/Shipping Container Design Factor of Safety Yield Ultimate N/A Minimum Frequency Requirement: 35 Hz (50 Hz Recommended) Overall acoustic environment: db qual, db acceptance Random Vibration Environment for Instruments and Components Frequency (Hz) Over All Protoflight/Qual Level g2/hz g2/hz g2/hz g2/hz 14.1 grms Acceptance Level g2/hz g2/hz g2/hz g2/hz 10.0 grms 19

20 LRO FEM: Configuration F **Total Mass: 2490 lbm (1129 kg) **CG (Origin at center of clampband IF) X Y Z in m **Mass Moments of Inertia Inertias about I/F (lbm*in2) Inertias about I/F (kg*m2) Ixx Ixy Ixx Ixy Iyy Iyz Iyy Iyz Izz Izx Izz Izx Inertias about C.G. (lbm*in2) Inertias about C.G. (kg*m2) Ixx Ixy Ixx Ixy Iyy Iyz Iyy Iyz Izz Izx Izz Izx

21 Fundamental Mode: Lateral Direction **Mass scaled to launch vehicle capability (1480 kg) fn = 19.6 Hz fn = 19.9 Hz 21

22 Fundamental Mode: IM fn = 46 Hz 22

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) 23

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. 24

25 LRO Mechanical System Development Flow MECHANICAL Design & Analysis INSTRUMENT MASS SIMS. PROP. Module (PTyp) Build 12/06 S/C Bus (PFlt) Build 9/06 4/06 CDR Inst. Module (PFlt) Build 12/06 Mechanical System Assy. Functional 1/07 Mechanical Qualification Testing Deployables (PFlt) Build & Test INSTRUMENTS 7/07 MECHANICAL Fabrication 10/07 9/06 PROP. Module (FLT) Build & Proof 10/06 PM Pluming Assy. 4/07 Spacecraft I&T 10/07 Orbiter I&T 2/08 1/07 LRO S/C Subsystems / Components Orbiter Environmental Testing 7/08 Launch Activities LRD 10/08 25