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

2. Colorado Space Grant Consortium
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
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 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

4. 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 minutes
Aerofins Release
Lightband separator requiring 12V for 1 minute (May Change)
Tip Mass Release
2 Frangibolts 28V for 30 Sec
FITS
4 composite hinges requiring 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 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
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 x m)
Volume = m3 / Wing
(0.067 ft3) / Wing
Deployment Hinge
Separation Device
Restraint Panel
Colorado Space Grant Consortium

10. Solar Array Subsystem Overview - Deployed
Deployed driving requirements - Power - 13 Vdc and 60
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. Colorado Space Grant Consortium
Frangibolt
Colorado Space Grant Consortium

12. Colorado Space Grant Consortium
Specifications
Colorado Space Grant Consortium

13. Colorado Space Grant Consortium
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 28V per
Hinge for 1 minute
2-4 Hinges required
High/Low output
(Switch signaling final
deployed position)
Colorado Space Grant Consortium

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

16. Colorado Space Grant Consortium
Aerofins Mounting
Cups
Cones
Colorado Space Grant Consortium

17. Colorado Space Grant Consortium
Cup Cones
Colorado Space Grant Consortium

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

19. Colorado Space Grant Consortium
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. Colorado Space Grant Consortium
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
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22. Colorado Space Grant Consortium
HOP Puller
FITS Attachment
Aerofin Attachment
Bracket
Posts
HOP
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23. Pulleys and Cables
- All cables will be steel and run - through piping or eye hooks
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24. FITs Solar Array Release
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25. Colorado Space Grant Consortium
Aerofin Release
Colorado Space Grant Consortium

26. Colorado Space Grant Consortium
HOP Release
Ring
Forces (lb)
Coefficent of
Static Friction
Coefficient of
Kinetic Friction
Factor of
Safety
Min Stowed
Pull
Force (lb)
Min Deployed
Pull Force (lb) 12
0.2
0.15 2
41.6
31.2 40
Total (lb)
Stroke
Length (in)
104
0.31
Colorado Space Grant Consortium

27. Colorado Space Grant Consortium
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. Colorado Space Grant Consortium
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. Colorado Space Grant Consortium
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