DINO PDR 1272020 Mechanisms Shilling Tim Lowrey Anthony

DINO PDR 12/7/2020 Mechanisms Shilling, Tim Lowrey, Anthony Mc. Arthur, Grayson

DINO PDR 12/7/2020 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 Ti. Ni Aerospace’s Frangibolt Colorado Space Grant Consortium

DINO PDR 12/7/2020 Subsystem Requirements Imposed 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

DINO PDR 12/7/2020 Subsystem Requirements Imposing 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 18 W at 28 V for 1. 5 -2 minutes – Aerofins Release • Lightband separator requiring 10 W @ 12 V for 1 minute (May Change) – Tip Mass Release • 2 Frangibolts 25 W @ 28 V for 30 Sec – FITS • 4 composite hinges requiring 10 W @ 28 V 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

DINO PDR 12/7/2020 Gravity Gradient Tether (GGT) • Anthony Colorado Space Grant Consortium

DINO PDR 12/7/2020 Flow Chart - GGT Input and Control Lightband 10 watts @ 12 V for 1 minute High/Low output (Switch signaling final released position) Colorado Space Grant Consortium

DINO PDR 12/7/2020 Thin Film Solar Array (FITS) Responsibility General Microsat • Provided by Microsat • FITS • Released with the in-house release system (IRS) • Restraint Panel • Deployment Hinges • Preloaded to 100 lb CSGC • Upon Release deployment is almost instantaneous • Restraint/release system hardware Colorado Space Grant Consortium

DINO PDR 12/7/2020 Flow Chart - FITS Input and Control Frangibolt 1 25 watts @ 28 V High/Low output (Switch signaling final released position) Frangibolt 2 25 watts @ 28 V High/Low output (Switch signaling final released position) Colorado Space Grant Consortium

DINO PDR 12/7/2020 Solar Array Subsystem Overview - Stowed Solar Array Envelope (0. 318 x 0. 184 x 0. 033 m) Volume = 0. 0019 m 3 / Wing (0. 067 ft 3) / Wing Deployment Hinge Separation Device Restraint Panel Colorado Space Grant Consortium

DINO PDR 12/7/2020 Solar Array Subsystem Overview - Deployed 0. 439 m m 1. 257 m 1. 636 m Deployed driving requirements - Power - 13 Vdc and 60 Watts @EOL Deployed Solar Array 1. 10 m 2 / 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

DINO PDR 12/7/2020 Frangibolt Colorado Space Grant Consortium

DINO PDR 12/7/2020 Specifications Colorado Space Grant Consortium

DINO PDR 12/7/2020 Aerofins General Responsibility • 2 Composite panels CTD • Solar Arrays mounted to Panels • Composite aerofins • Deployed with 4 composite hinges from CTD • Composite Hinges • 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. (With Mounts) Ability to interface with Restraint/release system hardware CSGC • Restraint/release system hardware • May be deployed simultaneously or separately Colorado Space Grant Consortium

DINO PDR 12/7/2020 Flow Chart - Aerofins Input and Control Aerofins H. O. P 18 watts @ 28 V for 1. 5 minutes High/Low output (Switch signaling final released position) Composite Hinges 10 watts @ 28 V per Hinge for 1 minute 2 -4 Hinges required High/Low output (Switch signaling final deployed position) Colorado Space Grant Consortium

DINO PDR 12/7/2020 Composite Hinges • • Provided by Composite Technology Development (CTD) Rigid in cooled State When Heated returns to Original Shape 4 composite hinges requiring 10 W @ 28 V for 1 minute Colorado Space Grant Consortium

DINO PDR 12/7/2020 Aerofins Mounting Cones Colorado Space Grant Consortium Cups

DINO PDR 12/7/2020 Cup Cones Colorado Space Grant Consortium

DINO PDR 12/7/2020 Complete Aerofin Assembly Aerofin Cup To HOP Release IRS Cone Side Panel Colorado Space Grant Consortium

DINO PDR 12/7/2020 Release System - HOP • • Pin Puller Less then 120 g 50 lbs of force One HOP releases 4 Deployables Total travel of HOP release Pin: . 3 in Activated with 28 V 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

DINO PDR 12/7/2020 Release System - Latch • • Colorado Space Grant Consortium 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

DINO PDR 12/7/2020 Release System - Pin Stainless Steel Construction. 25 in stroke. 175 in opening Stowed Released Opening PIN Colorado Space Grant Consortium

DINO PDR 12/7/2020 HOP Puller FITS Attachment Aerofin Attachment Bracket Posts HOP Colorado Space Grant Consortium

DINO PDR 12/7/2020 Pulleys and Cables - All cables will be steel and run through piping or eye hooks Colorado Space Grant Consortium

DINO PDR 12/7/2020 FITs Solar Array Release Colorado Space Grant Consortium

DINO PDR 12/7/2020 Aerofin Release Colorado Space Grant Consortium

DINO PDR 12/7/2020 HOP Release Ring Forces (lb) 12 Coefficent of Static Friction Factor of Safety Coefficient of Kinetic Friction 0. 2 0. 15 Min Stowed Pull Force (lb) 2 Min Deployed Pull Force (lb) 41. 6 31. 2 12 40 40 Total (lb) 104 Stroke Length (in) 0. 31 Colorado Space Grant Consortium

DINO PDR 12/7/2020 Testing Plan, GGT • Short length deployments on an air table • < 2 ft • Tests Lightband separation kickoff • Medium length deployment on a KC-135 • < 6 ft • Tests Coulomb damper • Test tip off parameters • Long length deployment using a vertical test • > 10 ft • Test kickoff with damping Colorado Space Grant Consortium

DINO PDR 12/7/2020 Testing Plan, Aerofins Aerofin CTD Hinge Structure Air table Sled Air table Colorado Space Grant Consortium Structure

DINO PDR 12/7/2020 Testing Plan, Release System Gravity Colorado Space Grant Consortium

DINO PDR 12/7/2020 Parts List In-House • IRS Outsourced • Aerofins: Free • Aluminium: < $50 • HOP: Free • Steel Cable: < $10 • FITS: Free • Springs: < $10 • Arrays • Pulley system: <$20 • Hinges • Mounting brackets • 2 Fringebolt: Free • Testing equipment • Actuator • FITS • 6 bolts: $20 each • Aerofins • Reset Tool: TBD • Tip mass • Coulomb damper • Lightband • Guides • Tether Colorado Space Grant Consortium

DINO PDR 12/7/2020 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