Future space missions will have larger telescopes in order to look deeper into space while improvising on spatial resolution. The primary mirrors for these telescopes will be so large that using a monolithic mirror will be nearly impossible because of the difficulties associated with its fabrication, transportation, and installation on a launch vehicle. The feasibility of launching these huge mirrors is limited because of their small launch fairing diameter. The aerodynamic shape of the fairing requires a small diameter, but the height of the launch vehicle, which is available for designers to utilize, is larger than the fairing diameter. This paper presents the development of an axial deployment mechanism based on the screw jack principle. The mechanism was designed and developed, and a prototype was constructed in order to demonstrate a lab model.

1. INTRODUCTION
 2. GOAL AND SCOPE
 3. DESIGN APPROACH FOR FOLDABLEMECHANISM
 4. MECHANISM FOLDING STRATEGY
 5. DESIGN OF MECHANISM COMPONENTS
  5.1 Design of Segment
  5.2 Design of Mechanism Base Plate
  5.3 Design of Shafts
  5.4 Design of Hinge Arms
  5.5 Design of Cup Bearing
 6. DESIGN CHALLENGES AND REDUCTION OFMASS
 7. SELECTION OF MATERIALS
 8. ANALYSIS
  8.1 Modal Analysis
  8.2 Static Structure Analysis
 9. FABRICATION
 10. REALIZATION AND INTEGRATION
 11. DISCUSSION AND RESULTS
  11.1 Ground Testing and Validation by Testing Mechanism
 12. CONCLUSION
 ACKNOWLEDGEMENTS
 REFERENCES

• Dignesh Thesiya(Mechanical Engineering Department, Noble Engineering College) Corresponding Author
• Arra Srinivas(Space Application Centre, Indian Space Research Organization)
• Piyush Shukla(Space Application Centre, Indian Space Research Organization)