dino pdr 16 may 2015 mechanisms shilling, tim lowrey, anthony mcarthur, grayson

DINO PDR April 18, 2023

MechanismsMechanisms

Shilling, Tim

Lowrey, Anthony

McArthur, Grayson

Colorado Space Grant Consortium


IntroductionIntroduction

• 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



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



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 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)



Gravity Gradient Tether (GGT)Gravity Gradient Tether (GGT)

• Anthony



Flow Chart - GGT

Input and Control

Lightband10 watts @ 12V for 1 minute

High/Low output(Switch signaling final

released position)



Thin Film Solar Array (FITS)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



Flow Chart - FITS

Input and Control

Frangibolt 125 watts @ 28V


released position)

Frangibolt 225 watts @ 28V


released position)



Solar Array Subsystem Overview - StowedSolar 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

Restraint Panel

Separation Device



Deployed driving requirements - Power - 13 Vdc and 60 Watts @EOL

Deployed Solar Array1.10 m2 / Wing Fold Integrated Thin Film Stiffener (FITS) Stainless Steel CIGS Array

85 Watts BOL - AMODeployed Solar Array Meets All Requirements

1.257 m

0.439 m0.439 m

1.636 m

Solar Array Subsystem Overview - DeployedSolar Array Subsystem Overview - Deployed



Frangibolt



Specifications



AerofinsAerofinsGeneral

•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



Flow Chart - Aerofins

Input and Control

Aerofins

H.O.P18 watts @ 28Vfor 1.5 minutes

Composite Hinges10 watts @ 28V per Hinge for 1 minute2-4 Hinges required


deployed position)


released position)



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



Aerofins MountingCups

Cones



Cup Cones



Complete Aerofin Assembly

To HOP

Release

Cup

Cone

Aerofin

Side Panel

IRS



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



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



Release System - Pin

Stowed Released

Stainless Steel Construction

.25in stroke

.175in opening

Opening

PIN



HOP Puller

HOP

Posts

Bracket

FITS Attachment

Aerofin Attachment



Pulleys and Cables- All cables will be steel and run -

through piping or eye hooks



FITs Solar Array Release

Ring Force (lb) Coefficent of Static Friction Coefficient of Kinetic Friction Factor of Safety Min Stowed Pull Force (lb) Min Deployed Pull Force (lb)100 0.2 0.15 2 40 30

Number of Springs Stowed Force per Spring (lb) Deployed Force per Spring (lb)3 13.33333333 10

Stroke Length (in) Min K Value Min Stowed Compression (in) Min Deployed Compression (in)0.25 13.33333333 1 0.75

FITs Solar Arrays Latch



Aerofin Release

Ring Force (lb) Coefficent of Static Friction Coefficient of Kinetic Friction Factor of Safety Min Stowed Pull Force (lb) Min Deployed Pull Force (lb)30 0.2 0.15 2 12 9

Number of Springs Stowed Force per Spring (lb) Deployed Force per Spring (lb)2 6 4.5

Stroke Length (in) Min K Value Min Stowed Compression (in) Min Deployed Compression (in)0.25 6 1 0.75

Aerofins



HOP Release

Ring Forces (lb)

Coefficent of Static Friction

Coefficient of Kinetic Friction

Factorof

Safety

Min StowedPull

Force (lb)Min Deployed Pull Force (lb)

12 0.2 0.15 2 41.6 31.2

12

40

40

Total (lb)Stroke

Length (in)

104 0.31



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



Testing Plan, Aerofins

Aerofin Structure

Sled Air table

CTD Hinge

StructureAir table

Sled



Testing Plan, Release System

Gravity



Parts ListIn-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



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

dino pdr 16 may 2015 mechanisms shilling, tim lowrey, anthony mcarthur, grayson

Documents

dino pdr

aerofins fits

grayson slide

second slide

instantaneous slide

previous slide

final released position

release deployment