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Mechanisms

Mechanisms. Shilling, Tim Lowrey, Anthony McArthur, Grayson. Introduction. Mechanisms includes restraints and release for: Aerofins FITS thin film solar arrays Gravity gradient tether The mechanisms will release the deployables in a predetermined order Gravity Gradient Tether FITs

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Mechanisms

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  1. Mechanisms Shilling, Tim Lowrey, Anthony McArthur, Grayson

  2. Introduction • Mechanisms includes restraints and release for: • Aerofins • FITS thin film solar arrays • Gravity gradient tether • The mechanisms will release the deployables in a predetermined order • Gravity Gradient Tether • FITs • Aerofins • The restraint mechanisms are based around Planetary Systems’ Lightband, Starsys’ HOP (High Output Paraffin Actuator) and TiNi Aerospace’s Frangibolt Colorado Space Grant Consortium

  3. Subsystem RequirementsImposed on Structures • Must retain mechanisms in a failsafe manner • Must release the deployables in a reliable fashion • Must release the deployables in the order discussed on the previous slide • Must meet power and thermal requirements Colorado Space Grant Consortium

  4. Subsystem RequirementsImposing on Others • 5-7 Hi/Low lines to signal different stages of deployment • Aerofins Released: 2 • Aerofins Final Deployed Position: 2 • FITS Released: 2 (?) • Tether Released: 1 • 1 HOP requiring 18W at 28V for 1.5-2 minutes • Aerofins Release • Lightband separator requiring 10W @ 12V for 1 minute (May Change) • Tip Mass Release • 2 Frangibolts 25W @ 28V for 30 Sec • FITS • 4 composite hinges requiring 10W @ 28V for 1 minute • Two per Aerofin • Two Aerofins • Thermal control of composite hinges (maintain hinge temperature between 88 and 92 deg. Celsius by cycling power to hinges) • Minimum of two controls, one per aerofin • Requires data lines for two thermal couple (Sampling once per second) Colorado Space Grant Consortium

  5. Gravity Gradient Tether (GGT) • Anthony Colorado Space Grant Consortium

  6. Flow Chart - GGT Input and Control Lightband 10 watts @ 12V for 1 minute High/Low output (Switch signaling final released position) Colorado Space Grant Consortium

  7. Thin Film Solar Array (FITS) • Responsibility • Microsat • FITS • Restraint Panel • Deployment Hinges • CSGC • Restraint/release system hardware • General • Provided by Microsat • Released with the in-house release system (IRS) • Preloaded to 100lb • Upon Release deployment is almost instantaneous Colorado Space Grant Consortium

  8. Flow Chart - FITS Input and Control Frangibolt 1 25 watts @ 28V Frangibolt 2 25 watts @ 28V High/Low output (Switch signaling final released position) High/Low output (Switch signaling final released position) Colorado Space Grant Consortium

  9. Solar Array Subsystem Overview - Stowed Stowed Solar Array Envelope (0.318 x 0.184 x 0.033 m) Volume = 0.0019 m3 / Wing (0.067 ft3) / Wing Deployment Hinge Separation Device Restraint Panel Colorado Space Grant Consortium

  10. Solar Array Subsystem Overview - Deployed 0.439 m 0.439 m 1.257 m 1.636 m Deployed driving requirements - Power - 13 Vdc and 60 Watts @EOL Deployed Solar Array 1.10 m2 / Wing Fold Integrated Thin Film Stiffener (FITS) Stainless Steel CIGS Array 85 Watts BOL - AMO Deployed Solar Array Meets All Requirements Colorado Space Grant Consortium

  11. Frangibolt Colorado Space Grant Consortium

  12. Specifications Colorado Space Grant Consortium

  13. Aerofins • General • 2 Composite panels • Solar Arrays mounted to Panels • Deployed with 4 composite hinges from CTD • Held down for launch with an in-house release system (IRS) based on Starsys’ HOP • Will be released concurrently with the FITS, but activated after the FITS are deployed. • May be deployed simultaneously or separately • Responsibility • CTD • Composite aerofins • Composite Hinges • (With Mounts) • Ability to interface with Restraint/release system hardware • CSGC • Restraint/release system hardware Colorado Space Grant Consortium

  14. Flow Chart - Aerofins Input and Control Aerofins H.O.P 18 watts @ 28V for 1.5 minutes High/Low output (Switch signaling final released position) Composite Hinges 10 watts @ 28V per Hinge for 1 minute 2-4 Hinges required High/Low output (Switch signaling final deployed position) Colorado Space Grant Consortium

  15. Composite Hinges • Provided by Composite Technology Development (CTD) • Rigid in cooled State • When Heated returns to Original Shape • 4 composite hinges requiring 10W @ 28V for 1 minute Colorado Space Grant Consortium

  16. Aerofins Mounting Cups Cones Colorado Space Grant Consortium

  17. Cup Cones Colorado Space Grant Consortium

  18. Complete Aerofin Assembly Cup Aerofin To HOP Release IRS Cone Side Panel Colorado Space Grant Consortium

  19. Release System - HOP • Pin Puller • Less then 120g • 50 lbs of force • One HOP releases 4 Deployables • Total travel of HOP release Pin: .3in • Activated with 28V at 18 watts for 2 minutes, which heats up the wax inside the piston, expanding it and causing the pin puller to move • HOP releases rings that attach to the release system via steel cable • Simultaneous release of FITs and then simultaneous release of Aerofins Colorado Space Grant Consortium

  20. Release System - Latch • Multiple springs to ensure failsafe • Stainless steel construction (Chemically treated to reduce Friction) • Aluminum 6061 Case • All moving components are of the same material to ensure against thermal expansion issues Colorado Space Grant Consortium

  21. Release System - Pin Stainless Steel Construction .25in stroke .175in opening Stowed Released Opening PIN Colorado Space Grant Consortium

  22. HOP Puller FITS Attachment Aerofin Attachment Bracket Posts HOP Colorado Space Grant Consortium

  23. Pulleys and Cables - All cables will be steel and run - through piping or eye hooks Colorado Space Grant Consortium

  24. FITs Solar Array Release Colorado Space Grant Consortium

  25. Aerofin Release Colorado Space Grant Consortium

  26. HOP Release Colorado Space Grant Consortium

  27. Testing Plan, GGT • Short length deployments on an air table • < 2ft • Tests Lightband separation kickoff • Medium length deployment on a KC-135 • < 6ft • Tests Coulomb damper • Test tip off parameters • Long length deployment using a vertical test • > 10ft • Test kickoff with damping Colorado Space Grant Consortium

  28. Testing Plan, Aerofins CTD Hinge Aerofin Structure Structure Air table Sled Sled Air table Colorado Space Grant Consortium

  29. Testing Plan, Release System Gravity Colorado Space Grant Consortium

  30. Parts List • In-House • IRS • Aluminium: < $50 • Steel Cable: < $10 • Springs: < $10 • Pulley system: <$20 • Mounting brackets • Testing equipment • FITS • Aerofins • Tip mass • Coulomb damper • Guides • Outsourced • Aerofins: Free • HOP: Free • FITS: Free • Arrays • Hinges • 2 Fringebolt: Free • Actuator • 6 bolts: $20 each • Reset Tool: TBD • Tip mass • Lightband • Tether Colorado Space Grant Consortium

  31. Issues and Concerns (Things to be done) • Run Finite Element Analysis on Mechanisms • Research material chemical treatments and coatings that will reduce friction • Procure suitable steel cabling • Reduce size and mass of components • Coefficients of friction Colorado Space Grant Consortium

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