1 / 20

OM Structure Summary May 20, 2003

OM Structure Summary May 20, 2003. Tia Ferguson Mechanical Design Engineer Science Directorate (SD22) Marshall Space Flight Center (MSFC) National Aeronautics and Space Administration (NASA) 256-961-7712 tia.ferguson@nasa.gov. Outline. Level I Mechanical Interface Requirements

brie
Download Presentation

OM Structure Summary May 20, 2003

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. OM Structure SummaryMay 20, 2003 Tia Ferguson Mechanical Design Engineer Science Directorate (SD22) Marshall Space Flight Center (MSFC) National Aeronautics and Space Administration (NASA) 256-961-7712 tia.ferguson@nasa.gov

  2. Outline • Level I Mechanical Interface Requirements • Level 1 Thermal Interface Requirements • Design Requirements • OM Design Summary • OM Weight Summary • Optical Subsystem Analysis • Integration, Testing and GSE • Mechanical Splinter Objectives

  3. Level 1 Mechanical Interface Requirements • Two lenses with support structures will be provided separately. Metering structure and aperture plate will be provided by EUSO system • Lens outer diameter is 2500 mm • Outer ring structure is outside of optical path (2600 mm outside diameter) • Outer ring depth is 100mm • Each Lens structure will attach to EUSO system at three location around outer ring • Three interfaces will allow radial expansion of lens system • Design launch loads for lens systems: TBD • Minimum natural frequency of lens systems: TBD • Present design has natural frequency 16 Hz

  4. OM Level 1 Thermal Interface • Current Design Baseline: Thermal control of OM is all passive, with temperature controlled by EUSO system • Operational temperature: system to maintain 10 +/- 10 C at all lens surfaces • Non-operational temperature: system to maintain 25 +/- 50 C at all lens surfaces • If required, heaters may be added to lens structure • thermostats, heaters and wiring provided by US • control and power provided by EUSO system • Any other adjustment between two lenses or focal plane and lenses to maintain focus needs to be considered at the EUSO system level

  5. OM Design Requirements • The structure shall maintain alignment of optical components during operational phases by meeting error budget allocations • OM shall be operational following exposure to non-operational temperature extremes • OM shall survive launch and return to optical alignment once on-orbit • OM shall be capable of being tested with the optical axis in a vertical configuration in the ground environment • Mission Life: 3 years

  6. View Through Lens Showing Lens Structure

  7. Design Summary • Outer ring (1250mm radius at inner edge) • 50mm x 100mm x 2mm wall thickness • Monolithic lens, 15mm in center • Lens 1: 4717 radius (12.6 outer edge thickness) • Lens 2: -3496.5 radius (10.7mm outer edge) • 12 radial struts • 25mm x 25mm x 2mm wall thickness • One inner ring (937 mm radius at center) • 25mm x 50mm x 2mm wall thickness • 48 flexures • 24 on outer ring • 24 on inner ring • 9mm x 2mm cross-section, radially compliant B B SECTION B-B

  8. Lens Structure Weight Summary Inner ring, 25 x 50 x 2 mm 5.5 kg 12 ribs, 25 x 50 x 2 mm 2.0 Outer ring, 50 x 100 x 2 mm 15.5 Flexures, 24+24 2.0 Rib attach brackets 3.5 Other brackets, estimate 7.5 Lens structure weight 36.0 Fasteners (<20%) 7.0 One lens structure assembly weight 43.0 Reserve, 25% 11.0 Total, one lens structure assembly 54.0

  9. OM Total Weight Summary Lens 1 structure (with 25% reserve) 54.0 Lens 2 structure (with 25% reserve) 54.0 Total structure 108.0 2 Lenses (PMMA, 15mm) 178.2 Reserve on Lens material (<5%) 8.8 Total Lens 187.0 OM Total Mass 295.0

  10. Analysis Finite Element Model (front) Finite Element Model (rear)

  11. Analysis Results

  12. Integration, Testing, and GSE • Integration: will occur in 4619, with use of alignment stand and tooling to assure lens alignment • Structural testing: will be performed to certify the OM for flight, including structural load testing, modal survey testing, random vibration testing, acoustic testing of the components and subsystem, as appropriate. • Ground Support Equipment: alignment stand, lens handling frames, GSE aperture plate and metering structure for testing, shipping containers, protective covers for lenses

  13. Objectives of Splinter • Define interface between lens structure and EUSO system • Discussion of error budget, and alignment maintenance • Thermal environment seen by the front lens • Discussion of baffle and lid design and impacts • Definition of loads and natural frequency requirements for lens systems • Presentation of details in analysis

  14. Lens Dimensions

  15. Lens Cross-Section

  16. Case 16: -Xlo (-1.8) Ymin (-9.94) -Zlo (-6.84)Lens Only, Out-of-plane (Z) Deflections (m)

  17. Case 16: -Xlo (-1.8) Ymin (-9.94) -Zlo (-6.84)Lens Only, von Mises Stress (Pa) Load step 16 Lens only von Mises stress

  18. Case 16: -Xlo (-1.8) Ymin (-9.94) -Zlo (-6.84)Frame Only, Out-of-plane (Z) Deflections (m)

  19. Case 16: -Xlo (-1.8) Ymin (-9.94) -Zlo (-6.84)Frame Only, von Mises Stress (Pa)

  20. Case 16: -Xlo (-1.8) Ymin (-9.94) -Zlo (-6.84)Flexure Only, von Mises Stress (Pa)

More Related