AAReST Coresat Detailed Design Reviesslab/PUBLICATIONS/Sept2017review_Telescope.pdf · AAReST...
Transcript of AAReST Coresat Detailed Design Reviesslab/PUBLICATIONS/Sept2017review_Telescope.pdf · AAReST...
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AAReST Coresat Detailed
Design ReviewSeptember 11 2017
14 September
2017
AAReST Payload CDR 1
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AAReST Subsystems
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
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Outline
• Review of Optomechanical Design
• Telescope Requirements
• Optical Systems status
– RMs, DMs, Camera Lens Assembly
• Overview of Active Element Control
– Rigid Body Actuation
– DM actuator control and measurement with
SHWFS
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Baseline Requirements
• Science Camera field of view: 0.34o
across diagonal
• PSF of each mirror Segment: 80%
encircled energy in 50μm diameter circle.
• Signal to Noise ratio: >100/lenslet for 50μs
exposure on Shack-Hartmann WFSs and
>100 on science imager for magnitude 2
stars or brighter
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Optical System Overview
7
Camera Optics
Collimating lens group
Focusing lens group
Wavefrontsensors
Primary Mirror segments (both rigid and deformable)
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Camera
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Mirror Boxes
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Active Element Control
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Optical Systems Status
• Theoretical performance prediction– Science cam SNR = 116
– WFS SNR = 110/lenslet
• Camera Lens assembly– Verify lenses are manufactured and aligned correctly
• Rigid Mirrors– Integration into testbed with science imager for coarse
alignment and SHWFS for fine WFE measurement
• Deformable Mirrors– Characterization using high order wavefront sensing
– Integration into testbed with SHWFS readout
– Active control in testbed using some flight like electronics.
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Active Element Control
• Rigid body control with three linear
actuators per mirror segment
– Flight like electronics complete
– Active in mirror boxes on testbed
• Deformable Mirror actuators controlled
using proto-flight electronics
– Flight like electronics and software ready for
integration
– Shape measurement with SHWFS
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Summary
• Optical system has been shown be designed to
meet baseline requirement.
• Camera Assembly and lenses are verified.
• Throughput has been computed to meet
requirements (test results to follow).
• Rigid mirrors alignment and figure have been
verified to produce a PSF that meets
requirements and matches simulation.
• DMs are in progress and actuator control is
being integrated.
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Future Work
• Bond rigid mirrors to mirror plate and
remove temporary mounts
• Execute calibration and closed loop
control of DMs using flight camera and
SHWFS.
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
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Requirements
In closed loop, DM must focus 80% of point source
energy to <50 μm diameter spot at focal plane
• Initial shape– Measured 2.6 μm RMS shape error. (<30 μm RMS defocus is
correctable)
– Radius of curvature ( +/-6 inch RoC is correctable)
– High order error (dimples etc.)• Must be measurable with SHWS
• Minimal impact on encircled energy
• Actuation– For perfectly spherical optic we need ~3 μm stroke to achieve
hyperboloid optical prescription
– To test real mirror with shape error, we will test with AAReST
camera in telescope testbed
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DM design - PZT and glass
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200 μm slumped D263 Schott glass
10 μm glass bead filled Epotek 301 epoxy
300 μm curved piezoceramic meniscus (PZT5A NCE51 from Noliac)
Ground plane
41 patterned electrodes
HV Multiplexer
Routing flex circuit
Side view
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Fabrication - Vacuum bag
bonding
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Masked ground
1.5 mm overhang
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Fabrication - Electrical routing
layer bonding• Electrical routing layer
– 0.5 oz copper
– 1 mil base Kapton
– 1 mil Kapton coverlay
• Connector
– TE connectivity
– 42 pos. 0.5 pitch FFC
• MG Chemicals silver epoxy
dripped into vias
– Add acetone to improve
flow
– Room temperature cure
– Tape is not tensioned!
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Fabricated hardware
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AAReST Deformable Mirrorbox
Phaesics testbed mount
DM mount/demount
Test mount constructed from aluminum and acrylic to avoid stray magnetic torques on mirror
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Testing - Actuation of PZT1GSF3
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0.21 - 0.96 μm/V expected0.80 μm/V measured
0.13 - 0.65 μm/V expected0.58 μm/V measured
-50V actuation
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Testing - Best flattening result
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PZT1GSF3 - Best flattening
6.55 μm RMS surface error 724 nm RMS surface error
ADD SCALE
PZT1GSF3 - Resting shape
Dominated by astigmatism
Actuator size limited
Surf
ace
erro
r (μ
m)
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Testing - Best flattening result
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Residuals are the same size as influences
Res
idu
al s
hap
e (
μm
)
Infl
uen
ce (
μm
/V)
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Testing - Slumped glass dimples
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GSF3 modes 1-36 removed 975 nm RMSGSF3 10.42 microns RMS
Hei
ght
(mic
ron
s) 7.4 μm depth
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Testing - DM in the AAReST
testbed
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Mirror errors are within range of AAReST wavefront sensor
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Testing - DM in the AAReST
testbed
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Mirror errors are within range of AAReST wavefront sensor
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Testing - DM in the AAReST
testbed
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Computed slopes
Next step is to close the loop with the AAReST testbed...
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PZT1GSF3 measured PSFPZT1GSF3 simulated PSF
Testing – PSF and RoC
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Slumping glass at Caltech (JPL
R&TD grant)
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Cotroneo et al. (2016) SPIE 99650C-5
Shap
e e
rro
r (m
icro
ns)
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Conclusions and future work• Achievements
– Designed and built ultra-lightweight deformable mirrors that
demonstrate large stroke.
– Built mirrors that can correct for their own sphere-subtracted
shape errors, up to the actuator size limit.
– Deformable mirrors can be measured and actuated within the
AAReST testbed.
• Future work
– Mid-spatial frequency error in the DM prevents meeting AAReST
encircled energy requirement.
– Bonding procedure imparts focus shift that cannot be actuated
away.
– Continue producing mirrors
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
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Subsystem Requirements
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Functional:
• Image star using a sparse aperture primary mirror
• Work to reconfigure primary mirror
• Provide feedback on mirror shape
• Take engineering images of CoreSat during MirrorSat reconfiguration
Constraints:
• Mass < 4kg
• Volume < 10 x 10 x 35 cm
• Power < 5 W
Performance:
• 80% encircled energy radius < 90% diffraction limit
• 0.3° full field-of-view
• Bandwidth: 465 – 615 nm
• SNR > 100
Environmental:
• Survive launch on PSLV with acceptable optical and mechanical performance
• Survive temperatures of -50oC to +50oC
• Function in vacuum environment
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Mechanical Overview
• Materials:
– Titanium for optical mounts; Al6061 for all other parts;
– Mask gears of dissimilar material to prevent cold welding
– RTV silicone (low outgassing) padding for B/S and SHWS
• Key accomplishments:
– Assembly procedures created and executed
– Fit check, integration with optics, motor functionality, dummy electronic boards
• Mass: 3.1 kg < 4 kg
• Volume: 29.8 X 9.6 X 8.0 cm3 < 35.0 X 10.0 X 10.0 cm3
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Mechanical Overview
• Materials:
– Titanium for optical mounts; Al6061 for all other parts;
– Mask gears of dissimilar material to prevent cold welding
– RTV silicone (low outgassing) padding for B/S and SHWS
• Key accomplishments:
– Assembly procedures created and executed
– Fit check, integration with optics, motor functionality, dummy electronic boards
• Mass: 3.1 kg < 4 kg
• Volume: 29.8 X 9.6 X 8.0 cm3 < 35.0 X 10.0 X 10.0 cm3
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Boom Interface
Frangibolt interface
Light Shield
Collimator lens
Imaging lens
SHWS MaskBeam-
splittersImaging detector
Electronics Mount
Baffle BIC Mask motor
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Mechanical Overview
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Thermal Testing Results
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Test Criteria Pass/Fail Comment
Survivability Pass No damage in optics,
mechanical assembly
Motor Alignment Pass Gears mesh after test cycles
Science Camera
Performance
Pass Slight shift in spot location;
no change in shape/size
SHWS
Performance
Pass No spots obscured;
negligible change in Zernike
coefficients (7 nm max
defocus)
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Vibration Testing Results
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Test Criteria Pass/Fail Comment
Survivability Pass No damage in optics or
mechanical assembly
Motor Alignment Pass Gears mesh after test cycles
Science Camera
Performance
Pass Slight shift in spot location; no
change in shape/size
SHWS Performance Pass Slight shift in spot location; No
spots obscured; negligible change
in Zernike coefficients (17 nm max
defocus)
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Conclusion and Remaining Tests
• Camera meets all requirements
– Mechanical, functional requirements met
– Optical performance as expected
– Environmental testing done to show survivability and
functionality
• Remaining work:
– New optics and B/S have arrived. Installation
happening now!
– Vibration testing to check electronics survivability
– Fabrication of external interfaces
– Verification of power requirement (currently met by
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
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Mirror Boxes OverviewRequirements Overview
• House mirrors and electronics
• Restrain mirrors during launch
• Provide rigid body rotation and axial motion of the mirrors
• Respect weight limit of 1 kg each
40
Mirrors & Mounts
Picomotors
Launch Restraint
System
Electronics
Frame
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Outline
41
• Accomplishments
• Rigid mirror box tests
− Vibration tests
− Bond strength tests
• Deformable mirror box tests
− Vibration tests
− Failure analysis and new design
• Separation device tests
• Picomotors position control
• Summary and systems readiness level
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Accomplishments
Assembly
• Fully assembled mirror
boxes from CAD models
• Assembly procedures
42
Testing
• Vibration tests of both mirror boxes
• Bond strength tests between rigid mirror and supporting plate
• Separation device tests
Integration
• Integration of rigid mirror box on optical testbed
• Optical alignment
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New Mirror Mounts Design
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2017
AAReST Payload CDR
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Picomotors Position Control
14 September
2017
AAReST Payload CDR 44
Encoders help estimate mirror position within an interval
Shaft
Mirror
Picomotor
CH1CH2
CH1
CH2
Voltage
221 nm
Encoder interval: 41𝜇𝑚
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Encoder Shaft• Encoder shafts laser engraved at micron pitch. Markings validated on transducer
• Alignment procedure with non-contact laser measurement
• Integrated into RM box on testbed and awaiting testing
14 September
2017
AAReST Payload CDR 45
428 lines 0.845deg:Engraved line: 30.5587+-1.14217reflective interval: 38.6588+-1.93625Angular pitch of rotary jig: 0.833151deg
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Flight parts
• Flight mirrorbox parts arrived from
manufacturing
• Aluminum bead blasted and hard black
anodized– Reduces stray light around optics
– Electrically insulates burnwire mechanisms
• Invar parts bead blasted and coated with
0.0005” high-phos. electroless nickel
– Protects invar from corrosion
14 September
2017
AAReST Payload CDR 46
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Flight parts
14 September
2017
AAReST Payload CDR 47
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Systems Readiness Level
4814 September
2017
AAReST Payload CDR
Rigid Mirror Box Deformable Mirror Box
Completed
• Assembly procedure
• Successful vibration tests of box
structure in all shaking directions
• Mirror bonding procedure
• Successful bonding tests
• Integration and mirror alignment on
optical testbed
Future Work
• Vibration tests with flight
electronics and flight mirror (using
PSLV standard)
• Separation device tests with flight
electronics, in vacuum
Completed
• Assembly procedure
• Preliminary vibration tests
(successful up to -6dB NASA
standard)
• New mirror mounts design
• Vibration tests with new mounts, spherical DM, and flight electronics (using PSLV standard)
Future Work
• Integration on optical testbed
• Separation device tests with flight
electronics, in vacuum
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Optical Alignment Fixture
AAReST Mirror Box 49
Needs• Temporarily support rigid mirror in vertical position when box is mounted onto optical
table for alignment procedure
• Free rotation of the mirror and highly sensitive in plane adjustment (µm level
sensitivity)
• Fix mirror in its new position, after alignment, to allow for bonding procedure
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
14 September
2017
AAReST Payload CDR 50
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Overview
• Telescope Electronics Overview
• Current Status
• Mirror Electronics
– Multiplexer board
– HV board
– Microcontroller board
• Camera Electronics
– Motherboard
– Shack Hartmann board
• Interface
51
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Mirror Electronics Overview
52
PicomotorDrivers x3
PicomotorPower (150 V)
Mirror Variable Bias (0-240 V)
Mirror Variable Electrode Supply (0-480 V)
41 optoisolator switches and multiplexer for routing electrode and bias voltages
Multiplexer Board
HV Board
Microcontroller Board
Deformable Mirror
MirrorSat/CoreSat
Voltage Regulators
MicrocontrollerCurrent Limiters
Separation Device
XBee
Picomotor Encoders Thermopiles
SPI I2C
I2C
Contact Switch
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Camera Electronics Overview
53
Shack Hartmann Board
Motherboard
Science Camera
Boom Inspection Camera
Baumer Camera
SHWS 1 SHWS 2Mask Motor Temp. Sensor
UART + Power
Optics
Daughter Board
XBee
USB USB
GigE, 12 V, 0.3 A
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Current Status
54
Board Status
Mirror Electronics
Multiplexer board Flight boards ready and tested
HV board Flight boards ready and tested
Microcontroller board V2.0 functional, too much in-rush current
Camera Electronics
Motherboard V1.0 functional, designing V2.0
Shack-Hartmann board V1.0 functional, need minor changes for V2.0
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Mirror Electronics
14 September
2017
AAReST Payload CDR 55
Optoisolator
switch
FFC connector for
electrode routing layer
on the mirror
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Camera Electronics
14 September
2017
AAReST Payload CDR 56
CoreSat interface
connector
LVDS Switch
Connector for motor
and thermistors
Mask motor driver
Camera Motherboard Shack Hartmann Switch Board Baumer Support Board
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Future Work
• Redesign motherboard with new ethernet port, USB
connectors and UART interface
• Change burn wire circuit and resolve boost converter
related startup issues in mirror electronics
• Complete cabling for camera and mirrorboxes
• Integrate temperature sensors, encoders, separation
detection switches and other electronics inside
mirrorboxes
14 September
2017
AAReST Payload CDR 57
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
14 September
2017
AAReST Payload CDR 58
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Outline• Requirements
• Mirror box
– Software architecture
– Driver update
• Camera
– Driver update
• Telescope startup procedure
• Error handling
• Future work
14 September
2017
AAReST Telescope 59
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Requirements of AAReST OBSW
• Mirror software– Communicate with camera through XBee and with
MirrorSat through UART as backup
– Automated failure detection and safe mode reset
– Actuate picomotors and electrodes
• Camera software– Communicate with CoreSat through UART (USB or
SSH protocol)
– Communicate with 4 mirrors through XBee
– Automated failure detection and safe mode reset
– Take images and analyze them14 September
2017
AAReST Telescope 60Both software run in non hard real time mode
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Mirror Box Software Architecture
14 September
2017
AAReST Telescope 61
Update Scheduler
List
Execute Schedule
1. Execute action function
2. Send feedback
3. Report in Register file
Registerfile
Data parsing
1. Save data
2. Error check
3. Parsing
InterfaceSPI
Interface
I2C
InterfaceUART Interface ADC Interface
DriverPicomotor
driverHV
driver
Multiplexer
driverTemperature
driver
AlgorithmPosition a
picomotor
Actuate an
electrodeHealth keeping
0x05 0x01 0x01 0x00000064 0x01
Command from camera
Mirror
Scheduler
Loaded by bootloader from external EEPROM
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Mirror Box Software update
• Hardware testing of mirror deformation
and HV supplies control
• Scheduler implemented, integrated with
algorithm and driver layer
• Undergoing tests with flight hardware
14 September
2017
AAReST Payload CDR 62
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Camera Software Architecture
Jan 2017 AAReST Telescope 63
Shell scripts
Shell scripts/.exe file
• Each layer create independent processes; monitored by telescope “scheduler”, terminate itself at end of execution
• Each process owns a dedicated log• Each layer accessible through CoreSat – camera interface
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Camera software updates
• Implementation of Algorithm and Drivers
on flight CPU
• Preliminary tests of Algorithms with Flight
Hardware
• Scheduler layer framework updated, under
implementation
14 September
2017
AAReST Payload CDR 64
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Future work
• Camera side
– Implementation of camera scheduler layer
– Finish and test camera drivers on telescope
CPU
– Tailoring of Linux kernel
• Mirror side
– Flight operation testing on telescope testbed
14 September
2017
AAReST Payload CDR 65
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Detailed discussions for this week’s
review• Framework of Camera scheduler layer
• Failure identification and recovery (FIDR)
strategy for camera
• Comm protocol between coresat and camera
• How often to save health and safety data
• General system level testing strategies
14 September
2017
AAReST Payload CDR 66
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Presentation Agenda
• Telescope Overview
• Deformable Mirrors
• Camera Instrument
• Mirror boxes Overview
• Electronics
• Software
• Boom Subsystem
14 September
2017
AAReST Payload CDR 67
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Subsystem Overview
14 September
2017
AAReST Payload CDR 68
Purpose:
• Guarantee successful deployment of the composite boom
• Ensure alignment of optical systems after deployment
Main components:
• Kinematic mounts
• Separation device
• Composite boom
Stage 1
DeploymentStage 2
Deployment
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Subsystem Overview
14 September
2017
AAReST Payload CDR 69
Separation Device constrains boom during storage and releases stage 1 during deployment.
Kinematic Mount allows adjustment of camera relative to CoreSat before final storage; It corrects for misalignments.
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Boom Subsystem Requirements
14 September
2017
AAReST Payload CDR 70
Optical axis Lateral offset
Angular offsetDeformed boom
Spacecraft
Focal length
Requirement Value
Focal length [1] 1163 ± 1 mm
Maximum admissible lateral offset [2] ± 3 mm
Maximum admissible angular offset [2] ± 1°
Maximum lateral tip deflection (dynamic) [3] ± 0.20 mm / s
Maximum longitudinal tip deflection (dynamic) [3] ± 0.05 mm / image
[1] From the CDR (2015)
[2] Given by Kathryn Jackson
[3] From the PDR (2013)
Camera
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Boom testing
• Previous review
– Viscoelasticity
– Stage 1 and 2 deployments
– Launch vibration (NASA qualification level)
– Separation device
– Deployment accuracy
• New results
– New boom length
– Folding fixture
– Offloading jig
– Kinematic mount redesign
14 September
2017
AAReST Payload CDR 71
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Stage 1 Deployment
14 September
2017
AAReST Payload CDR 72
Objectives:
• Demonstrate reliable and repeatable stage 1 deployment
• Validate the kinematic mount and the separation device
Kinematic Mount
Separation Device
Rigid Frame
(Coresat)
Clamped
(Camera end)
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Stage 1 Deployment
14 September
2017
AAReST Payload CDR 73
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Stage 2 Deployment Test
14 September
2017
AAReST Payload CDR 74
Objectives:
• Ensure a reliable and repeatable stage 2 deployment
• Determine maximum acceleration due to deployment
2.9 m
0.25 m
0.68 m
Stowed configuration
J-rail (12 ft)
Coresat(27.7 kg)
Camera(3.43 kg)
Boom
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Stage 2 Deployment
14 September
2017
AAReST Payload CDR 75
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New Boom Length
• Objective: optimize the boom length, and the
camera and kinematic mount positions based on
the following constraints:• Keep the same spacing between the hinges
• Respect the designed optical focal length
• Reduce stress in the first hinge from the kinematic mount by
increasing as much as possible the length of the first segment
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New Boom Length
• Main Parameters1. Focal length: 1163 mm
2. Camera-to-collar optical offset: 82.575 mm
3. Mirror box optical offset: 77.1026 mm
4. Mirror box total height: 105 mm
5. Distance between top of structure and KM collar: 155.75 mm
6. Length of Coresat (excluding clearance): 325 mm
7. Length of camera: 296 mm
8. Offset between front of camera and collar: 84 mm
8 (2)
5
43
6
7
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New Boom Length
14050 475
8101158
1408
200
~ 90 mm
Camera as low as possible
(without going into the clearance)
~113 mm
~200 mm~85.3 mm
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Old Boom Length
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Folding fixture
• Objective: provide a reliable and repeatable way of
folding the hinges that does not create cracks
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Folding fixtureFixed
Slide
Screw to control
movement
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Folding jig
• Tested with old hinges first, then new hinge (never
folded)
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Folding jig
• Tested with old hinges first, then new hinge (never
folded)
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Folding jig
• Tested with old hinges first, then new hinge (never
folded)
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Folding jig
• No visible damage appeared at the hinge
location (folded 3 times)
• Folding is sometime a bit unstable (usually
the inside tape spring flatten first, but it
can be the opposite)
• You need to manually force the boom to
fold in the right direction
• When fully flatten, the 2 tape spring are
not always well aligned for complete
folding (they need to slip to get to the right
position for folding)
• Seems to provide a way to fold the boom
with better repeatability
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Boom Offloading Rig
• The objective of the offloading rig is the prevent the boom
from deflecting under gravity loading. This will ensure that the
boom alignment done on the ground will remain valid once in
space
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Boom Offloading Rig
CoreSat
Kinematic MountBoom
Optical
table
Offloading rig
Boom/camera
interface
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Boom Offloading Rig
Linear bearing
Low friction pulley
Weight
Adapter
Stiff frame
(8020)
Cable
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Offloading Jig
2-axis sliding plateform Pulley
Offloading weight
Camera interface
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Offloading Jig
Plane 2
Cylinder
Plane 1
• Measure planes 1 and 2, and cylinder with the Faro arm scanner
• Clean point clouds and fit planes and cylinder
• Project cylinder axis on plane 2 to obtain an origin
• Use plane 1 normal as the rotational orientation
XZ
Y
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New Kinematic Mount Design
• Problem:
• When folded, boom cross-section width increase
• Aging seems to amplify this phenomenon
• Therefor, the boom can be stuck inside the collar mounts
• Objective:
• Ensure reliable boom deployment even if boom change cross-
section due to aging
• Modifications:
• Removed one side of the collar mount
• Increased size of remaining support
• Changed Vectran cable path
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New Kinematic Mount Design
5mm (Previously 4mm)
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New Kinematic Mount Design
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Summary
• We completed the design of the boom
subsystem
• We studied the viscoelastic behavior of the
composite boom
• We successfully performed:
– Vibration testing
– Deployment testing (both stages)
– Accuracy testing following aging
14 September
2017
AAReST Payload CDR 94
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Future Work
• Anodize kinematic mount parts
• Cut the boom to final length
• Vibration of full folded boom
14 September
2017
AAReST Payload CDR 95