Last Revision: 09/08/2021020
OVERVIEW
EnduroSat's 3U Single Deployable Solar Array
is a two-part structure, combining one
stationary panel and one deployable panel
each holding seven highly efficient Azur
Space 3G30A triple junction solar cells with
up to 30% efficiency. They can be connected
in parallel or used independently. The
deployable solar array improves the satellite’s
energy generation capability, radiation and
temperature resilience to ensure smooth
operation in LEO.
The two panels are connected both
mechanically and electrically. The solar panel
can be deployed via a triple redundant burn
wire mechanism with double feedback which
can be controlled either directly via a digital
input (high or low logic level) or via
bi-directional communication from the OBC
(Onboard Computer).
The solar array contains a microprocessor
with proprietary embedded software
algorithms to guarantee deployment and
status feedback to the OBC.
The solar array comprises temperature
sensors, Sun sensors, and a gyroscope
(optional). A connector for an external
magnetorquer and an RBF (Remove Before
Flight) pin are also available. Through our
connector system on the PCB, multiple solar
panels can be easily connected in an
electrical series or parallel configuration
based on the client’s EPS (Electrical Power
System). The 3U Single Deployable Solar Array is fully
compliant with the CubeSat standard. Also,
customization of the panel with additional
external connectors and interfaces to access
the internal satellite modules can be provided
upon request.
SOLAR PANEL FEATURES
• One stationary + one deployable 3U Solar
Panel. Each solar panel contains seven solar
cells connected electrically in series
• Hinge: short side, 90 degrees
• Primary and back-up burnwire deployment
mechanism
• Triple redundancy for guaranteed deployment.
Various embedded software algorithms + option
for direct control with digital input logic and two
feedback channels
• 224 cm2 effective cell area for seven solar cells
(per solar panel)
• Up to 8.4W per solar panel in LEO
• Voltage at Maximum Power 7S1P: 16.86V
• Current at Maximum Power 7S1P: 0.5A
• Voltage at Maximum Power 7S2P: 16.86V
• Current at Maximum Power 7S2P: 1A
• Single 5V power supply is required
• Typical current consumption during
deployment: 1.1A @5V (2 sec)
• Typical idle mode current consumption:
11mA @ 5V
• Low Power MCU with FRAM
• Fifteen unique user configurable addresses –
0x51 : 0x5F
• Test mode for command verification and
preventing unwanted solar panel deployment –
Address – 0x50
• External FRAM Memory
• Two Pico-Lock connectors for RS-485 interface
(the two connectors help several deployable
solar panels to be connected on the same I/F
minimizing the length of cables and power lines
• Two Pico-Lock connectors for I2C interface
• One Pico-Lock connector for UART interface
• One Pico-Lock connector for direct
deployment of the solar panel. Control of the
primary and back-up burning lines with two
independent feedbacks for successful
deployment
• Connector for Remove Before Flight (RBF)
pin
• SCIC connector
• Two Sun sensors (one for the stationary and
one for the deployable solar panel). The Sun
sensor on the deployable solar panel can be
mounted on either side.
• Three temperature sensors (one on the
stationary and two on the deployable solar
panel)
• Fully configurable gyroscope (optional)
• Integrated H-Bridge for control of external
magnetorquer • Multiple panels can be connected in series
or parallel. The stationary and the deployable
solar panels can either be connected in
parallel with blocking diodes (integrated within
the solar panel) or be used separately • Protocols: ESTTC
• Local and remote (in-flight) secure update of
the application firmware • Space-grade silicone adhesive with minimum
outgassing behaviour according to
ECSS-Q-70-02A (corresponds to former
ESA PSS-01-701)
• Mass: 270.20 ± 0.05 g
SOLAR CELL FEATURES
• Efficiency: up to 30%
• Size: 30.18 cm2
• Very low solar cell mass (81-89 mg/cm2)
• Triple junction solar cells InGaP/GaAs/Ge
• Fully qualified under ESA standard
ECSS E ST20-08C for LEO and GEO
• Internal by-pass diode
• High radiation resistance
• Coverglass CMX 100AR (100 µm thick)
MECHANICAL LAYOUT
* All dimensions are in mm.
Top View
Side View
PRODUCTION PROCESS
QUALITY STANDARDS
• IPC-A-600
• IPC-TM-650
• IPC-A-610 Class 3 • J-STD-001 • IEC 61340 All EnduroSat’s products are cleaned and
packed in a clean room Class 6, ISO 14644.
TESTS
A full campaign of tests at qualification
level has been performed on a
qualification engineering model:
qualification tests, level and duration tests
following the ESA standard
ECSS-E-ST-10-03C and GEVS standard
GSFC-STD-7000A.
• Random Vibration • Sinusoidal Vibration • Pyroshock Test • Thermal Cycling • Thermal Vacuum • Total Ionizing Dose RELATED PRODUCTS
• 3U Structure
• 6U Structure
• 1U Solar Panel XY
• 1U Solar Panel Z
• 1.5U Solar Panel
• 3U Solar Panel
• 6U Solar Panel • EPS Type II
• OBC (Onboard Computer)
• UHF Antenna
• UHF Transceiver
CONTACTS