The CubeSat satellite is a smart option for reliable and low cost space mission development. Growing
CubeSat performances lead to more extensive nanosatellite application. Currently,
Telecommunication and Earth Observation missions are under development both in single and
constellation configurations. The main targets for the future nanosatellite are: accurate attitude
pointing, high data rate transfer, increased power generation. The on board power/energy availability
reduces or limits the CubeSat performances in terms of processing capabilities, power transmission
and attitude/orbit maneuvers. Following these constraints, the IMT has developed an innovative unit,
named nano-Solar Array Drive Assembly (SADA) for 3U CubeSat, with the aim of increasing the
photovoltaic energy generation (up to an average 35W EOL). It is composed by two independent
Solar Arrays (Wings Assembly) and Rotatory Mechanisms / Logical Unit (SAC – Solar Array
Control). The aim of SADA is to align constantly the two Solar Arrays to the Sun direction, around
one axis. The rotatory system is composed by drive gear sets, stepper motors and slip rings. The high
value of gearhead reduction ratio and two dedicated photodiodes (as solar sensors) allow a fine
pointing accuracy (<5°). Several operation modes are implemented and controlled by the On Board
Computer through the I2C and CAN buses: autonomous (sun detection and pointing), slave or
cooperative. An advanced and smart control algorithm was developed and implemented in the logic
unit. The Solar Array points along the maximum solar flux direction, maximum output speed up to
4°/s (step size 0.004°). A system failure control avoids the thermal and power damaging in case one
or both wings are blocked. SADA is fully compliant with all CubeSat form factor (3U or greater) and
BUS (CSKB – CubeSat Kit Bus). The Solar Wings, during the launch phase, are stowed beside the
CubeSat structure (opposite side faces). The overall thickness is less than 9 mm, compliant to ISIPOD
dispenser. The Logical and Drive unit (SAC), small (90 x 90 x 12 mm) and light (185 gr), is allocated inside the satellite. The Wings are electrically connected to the SAC, by means of two 16 channels
slip rings (1A per contact) for a continuous rotation, without cable saturation. The Alignment
Calibration System assures that the unit runs correctly up to 10 mm of misalignment between the
SAC and the geometric satellite center, along Z direction. The generated power is not handled by
SAC, but by PDU through Standard Molex Connectors. The two wings, stowed during the launch
phase, are deployed in orbit. In order to increase the system reliability, the deployment is based on
two redundant thermal cutter systems. In the final configuration, the 3U CubeSat has two wings, each
one 300 x 300 mm and 36 AzurSpace 3J solar cells.
Modern Roaming for Notes and Nomad – Cheaper Faster Better Stronger
SADA Solar Array Drive Assembly: Functional Testing and Results
1. SADA
SOLAR ARRAY DRIVE ASSEMBLY
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
2. Company presentation
Company activities
Company capabilities
SADA design
Mechanical design
Electronics design
Control law design
SADA functional testing
Deployment test
Sun tracking test
Calibrations
Results & Conclusions
Solar Array Drive Assembly: agenda
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta 1
3. • Nano/Microsatellite
• On-board unit
• Space commercial
• Space scientific
• Defense
• Characterization
• Testing
• Materials
• Processes
Company overview…
• Equipment for space & defense
• Engineering support
• Product assurance
• QA, software QA
• Reliability, safety
• Component testing
private SME
founded in 1991
System Engineering Parts Engineering
Det Norske Veritas
(DNV)
UNI EN ISO
9001:2008
Quality
Managment
System
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta 2
4. Company overview: facilities…
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
RomaValenzano(BA)
13 Employees
6 Employees
Main Office:
Via C. B. Piazza, 30
00161 Roma - ITALY
Tel.: +39-06-44292634
Fax: +39-06-44292634
Email: imtsrl@imtsrl.it
URL: www.imtsrl.it
Technological Lab.:
c/o Tecnopolis
Via per Casamassima
70010 Valenzano (BA)
Tel: +39-080-4670360
Rome
Valenzano (BA)
3
5. Company overview: our projects…
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta 4
Scientific Payload
Antenna Deployment SystemBattery Pack
On Board Computer
Electrical Power System
6. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA general architecture…
• Rotational resolution of 0.004°
• Sun pointing accuracy < 5°
• Operational speed max 4°/s
• CubeSat standard compliance
• SAC thickness < 120mm
• Stowed solar array < 8mm
5
7. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA wings assembly…
• 18x 3J solar cells
• PCB rigid/flex
• Yoke
• Slip ring
• Centering system ±10mm
6
8. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA electronics design: SAC unit…
1:4096 gearhead
Full-wave stepper motor control
7
RSP1
RSP2
RSP3
Right Wing
Right Motor
LSP1
LSP2
LSP3
Left Wing
Left Motor
TZA
SSC Left
TZA
SSF Left
TZA
SSC Right
TZA
SSF Right
ADC
12 bit
DMA
RAM
H-bridge
Motor
stages
H-bridge
Motor
stages
Solar Array Control Unit
Temperature
CAN BUSI2
C MCU core
SSC resolution ≈ 700nA
SSF resolution ≈ 50nA
9. • Photodiode
• Phototransistor
• Sun Sensor Coarse
• Sun Sensor Fine
• AzurSpace 3J cells
• 2.35V @ 0.5A
• Average power 40Wh
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA solar wings…
3
SC1 SC2 SC3
SC4 SC5 SC6
SC7 SC8 SC9
SC10 SC11 SC12
SC13 SC14 SC15
SC16 SC17 SC18
Solar Panel 1
Solar Panel 2
Solar Panel 3
PT
PD SSC SSF
TEMP
SP+ SP-
SC1 SC2 SC3
8
10. • Redundant configuration
• Two resistors for each Dyneema arm
• 2.7A@5V for each wing
• Current telemetries
• High power MOSFET
• Timed actuations
• Optical feedback
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
Current
sense
VTC
LTC1
LTC2
RTC1
RTC2
Left
Wing
ITC
Current
sense
VTC
ITC
Current
sense
VTC
ITC
Current
sense
VTC
ITC Right
Wing
ADC
SADA thermal cutter actuators…
9
11. • ADC@12 bit
• 750nA resolution on SSC
• 50nA resolution on SSF
• 2-pole Butterworth filter
• Digital filtering
• Multi-region sensitivity
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA sun sensors…
Right
SSC
Left
SSC
Right
SSF
Left
SSF
TZA TZA TZA TZA
ADC
12 bit
DMA
RAM
CPU
(control law)
10
12. • Each wing composed by 3 main panels
• Coupled by hinges
• Coupled by springs
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA control law: oscillation damping…
• Use sliding window in the acquisition
• Filter on comparing four measures
• Computing variance value using Bessel’s correction avoid biased estimate
• Control based on the Mahalanobis distance
Sunsensorcurrent
time
11
13. • Four operating areas
• Slope switching levels
Two rotary mechanism
Two independent controls
• Azimuth independent
• Maximum Power PointTracking
• Standard P&O algorithm
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA control law: sun sensors feedback…
(a)
(b)
(c)
(d)
12
14. • SSC operation
• SSF sensing near 90° elevation (area a)
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA control law: algorithm…
Null current on SSC (ε)
SSF current greater than threshold (δL)
𝐼 𝑘 − 𝐼 𝑘−1 = Δ 𝑘
• Δk>0, same direction as previous period
• Δk<0, invert direction in the next period
(a)
(b)
SSC: slope remain almost constant
(area b)
13
15. • Actual value stored as previous value
• improve positioning (area c)
• SSC current slope very tight
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA control law: algorithm…
take measures from SSF
same code, same routines
code efficiency
• Execute until solar panels reach the max
• Avoid chattering (area d – smaller box)
Power saving (area d – greater box)
Check if the motion is convenient
(c)
(d)
14
!
16. • Dummy arrays were used:
same inertia of the real solar panels
same mass of the real solar panels
Different stiffness of the real solar panels
Avoid complex off-loading system
• Deployment test (ECSS-E-ST-33-01C)
• Sensors calibration routine
• System calibration
• Backlash measurement and compensation
• Functional tests of tracking algorithm
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA laboratory functional verifications…
15
17. • ECSS-E-ST33-01C
• Predicted nominal ground test cycles
• Nominal in-orbit operation cycles
• 3 expected ground deployment cycles
• 1 expected deployment cycle
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA deployment test…
3𝑥4 + 1𝑥10 = 22 𝑐𝑦𝑐𝑙𝑒𝑠
16
18. Offsets highlighted from analog sensor (analog filtering)
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA sensor calibrations…
Coarse sensor Fine sensor
Left wing 2µA 20nA
Right wing 1µA 500nA
17
19. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA system calibration: slip ring test…
• Verify the repeatability
• Verify sensor response @different light irradiance
• Lamps used for light illuminance
• 3 cycles on each wing
• 360° rotation on each cycle
Slip ring conduction verify
• Maximum offset of each curve ≈0.2%
• Below 5° pointing specification
18
20. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA system calibration: light response…
Lamps used for different illumination beam
Repeatability measures during illuminance variations
Measures with illuminance variations Repeatability with illuminance variations
19
21. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA backlash compensation…
Two cycles of 360° with motion inversion
20µA before – 1.5µA after
Measured backlash of 3.8° firmware compensation
20
22. Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA tracking algorithm verification…
• A complete turn was performed
• Maximum current value has been computed
• Tracking algorithm executed
Pointing accuracy < 5°
21
23. • Power transfer output: 43W max
• Output torque: 25mNm
• Pointing accuracy: <5°
• Step size: 0.004°
• Configuration: 2 channels, 2 solar arrays
• Release mechanism: 2x 1.7A for each solar array
• Range of motion: slip rings allow free rotation
• ADC acquisition @12 bit (temperature sensing)
• CubeSat standard
• 3U structure
• CAN BUS
• I2C
• Power consumption:
• Idle 160mA
• Holding 430mA
• Tracking 460mA
• Mass:
• SAC 185gr
• WING 331gr without solar cells
• TOTAL 850gr
• 2 sun detection, fine and coarse for each wing
• 4 independentTZA stages
• 2 poles analog filtering
• Digital damping filters
• Digital measure filters on 16 samples
Michele Marino – IMT srl Rome,Italy / ESA 4S Symposium 2016, La Valletta - Malta
SADA characteristics…
22