Advanced Power Systems
for CubeSats
INTRODUCTION
• F. Brent Abbott – CEO AAC Microtec North America
• Honeywell Business and Commuter Aviation - Engineer
•
Biz Jet Avionics – Power and RF
• Honeywell Defense and Space – Business Development
•
Commercial and Classified satellite sub systems
• Surrey Satellite Technology US – Head of PM, Eng. & BD
•
Cosmic II, OTB-1, CYGNSS
INTRODUCTION
• Power is always precious on a CubeSat.
• Solar panel area must be increased to
meet the orbit average power
demands of new missions.
• Tailored solar panel configurations to
match orbit/mission is more important
than solar cell area.
• Good power management is also vital to
maximise efficiency and safety on-board.
• The most common failure of CubeSats is
negative power budget.
Clyde Space’s 3U SeaHawk CubeSat
Clyde Space’s 1U Outernet CubeSat
INCREASED UTILITY = INCREASED POWER DEMAND
• CubeSat missions are becoming
increasingly sophisticated.
• Increasing payload power
consumption and duty-cycles
• More data storage and onboard processing
• High downlink speeds
• More sensors and actuators for
attitude control.
• Heaters, propulsion, etc.
CPUT High data-rate S-Band Transmitter
Clyde Space / Mars Space Pulsed Plasma
Thruster
3U CUBESAT WITH DEPLOYABLE SOLAR PANELS
• Orbit average power of 20.8W (inc. 10% albedo)
• Power profile more spread-out over orbit
• Peak power is 40W
• 3U panels have 7 UTJ solar cells
• Top panel has 2 UTJ solar cells
45
40
35
30
25
20
15
10
5
0
Array Power (W)
-z power
-x power
-zdlead
+x power
+x sidepower
-xsidepower
-zdtrail
+xdep
-xdep
Total Power
0
50
100
Time (mins)
150
200
DEPLOYABLE PANELS
Double Deployeds
• 4 faces of solar cells (front and
back)
• Integrated Hold-Down and
Release Mechanism.
• Fully qualified.
• 100+ units on orbit.
Triple Deployeds
• Just completing qualification
testing at this time.
• Patent pending simple reset hold
down and release mechanism.
• Al frame provides increased
flatness and rigidity.
GEN3 CUBESAT EPS
•
•
•
•
•
3.3V, 5V, 12V regulated power buses + 8.2V unregulated battery bus: Off-The-Shelf design
supports over 90W
10x Latching Current Limit power distribution switches: eliminates need for separate
switchboard, saving volume
Maximum Power Point Tacking BCRs: >90% efficiency
Over/undervoltage, overcurrent protection, watchdog timer:
3G EPS range supports 1U – 12U with deployable panels as standard
LOW NOISE CUBESAT EPS
Flight Switches
13W BUCK BCRs x8
3.3V, 5V, and
12V PDMs
GEN3 BATTERIES
•
•
•
•
•
•
Hundreds of units supplied: world’s
most popular CubeSat battery
ISS / Manned Flight Compatible:
inhibit setup compliant with all
Agency requirements
8.2V EoC, Lithium Polymer cells:
proven, flight-heritage technology
with excellent energy density
Over-discharge/charge, overcurrent,
overvoltage, and low-temperature
protection
Scalable from 10Whrs to over
120Whrs.
12.3V version available.
DESIGN FOR MANUFACTURE AND TEST
Clyde Space has invested heavily in DFM and DFT, allowing us to scale our
manufacturing throughput to meet the demands of today’s volume-focused market.
FULL RANGE OF SUBSYSTEMS FOR CUBESATS
Computers
Power
Systems
Batteries
Structures
Pointing
Control
Solar panels
NSLSAT-1
▪ 6U communications mission
▪ High power payload Demonstration of 1Gbps
downlink
▪ Plans for constellation in discussion
SEAHAWK
▪
▪
▪
▪
Pair of 3U CubeSats flying multispectral imagers
x60 smaller than existing SeaWIFS asset
Revisit rate for IOD of 7 days
Downlinked via X-band to NASA NEN
FIRESAT
CURRENT MISSIONS SUMMARY
THANK YOU!
THANK YOU!
A 3U CUBESAT FOR EARTH OBSERVATION AND
ELECTRIC PROPULSION TECHNOLOGY
DEMONSTRATION
P. Gessini, G. Santilli, C. Vendittozzi, G. C. Possa, J. L. Ferreira – University of Brasília, Brazil
paolo.gessini@aerospace.unb.br
I. Uwarowa – Warsaw University of Technology, Poland
S.B. Gabriel – University of Southampton, UK
United Nations/Brazil Symposium on Basic Space Technology
“Creating Novel Opportunities with Small Satellite Space Missions”
Natal, Brazil – September 11-14, 2018
CONCEPT
•
UniPolar: a pioneer project, intended to jumpstart cooperation
between
•
•
•
•
•
Brazil (University of Brasília - UnB, …?)
Poland (Warsaw University of Technology, Warsaw Institute of Aviation)
UK (University of Southampton)
Other international partners…?
In the field of NanoSats
•
3U CubeSat
•
Earth Observation
•
•
Pollution, Climate change
Technology Demonstration
• Electric Propulsion (Ablative Pulsed Plasma Thrusters – APPTs)
PREVIOUS EXPERIENCE
•
University of Brasília
•
•
•
SERPENS , a 3U CubeSat, deployed from the ISS on September 17th, 2015
SERPENS II, another 3U CubeSat, currently being developed
Preliminary mission design studies (Acta Astronautica, April 2018)
SERPENS
•
First satellite in a program,
supported by AEB, created to foster
nanosatellite development by
Brazilian universities
•
UnB had leadership of the project
•
In cooperation with Universidade de
Vigo, CalPoly, Sapienza Università di
Roma, Morehead State University
SERPENS II
•
Second microsatellite in the program
•
UFSC has the leadership of the project
•
Many universities involved (UFSC,
UFMG, UFABC, UnB, UFRN, UFSM, USP)
•
UnB takes care of the APPT and of the
orbit determination system
PREVIOUS EXPERIENCE
•
Warsaw University of Technology
•
Two CubeSats
•
•
PW-Sat and PW-Sat2
Warsaw Institute of Aviation
•
Remote Sensing Division
Data analysis, image processing
• Multispectral camera Quercus
•
PREVIOUS EXPERIENCE
•
University of Southampton
•
Electric Propulsion (APPTs)
•
PPTCUP with Mars Space Ltd., a
spinoff company established in
2007, and Clyde Space Ltd.
•
•
•
•
•
•
Dimensions: 100 mm x 100 mm x 33 mm
Mass: 280 g, with EMI shielding
Power draw: < 2.7 W
Impulse bit: 38 mNs
Specific Impulse: 600 s
Total Impulse: 42 Ns / 63 Ns
• Two versions available
• Further customizable
ABLATIVE PULSED PLASMA THRUSTER - APPT
•
Pulsed electric discharge
(capacitor charged at high
voltage) between two electrodes
across the surface of a
Polytetrafluoroethylene (PTFE) block
•
Propellant ablated and
accelerated partly by Lorentz
force, partly thermally
•
No moving parts, piping, tanks,
valves: simple and robust
•
Easily scalable to low and high
power values
•
Because of the above, used in spite
of low efficiency
•
Late-time ablation: part of propellant
ejected thermally, which decreases
specific impulse
MICROPROPULSION FOR NANOSATS
APPT FOR CUBESAT DRAG COMPENSATION
PRELIMINARY LAYOUT SCHEMATICS
•
3U-Structure
(Section view)
MB-CPU
3U CubeSat platform
•
Onboard power budget < 10 W
solar cells on satellite body and
on deployable panels
• Li-Ion battery package
•
•
Multi-spectral camera
(RGB+NIR)
MULTI-BAND
COMMUNICATION
MODULE
BATTERY
BUNDLE
A 3-axis ADCS
Star sensors
• Reaction wheels and
magnetorquer module
•
•
An X-band transceiver
•
•
data download
An S-band system
•
telecommunications, tracking
and command.
EPS
STAR SENSOR
PPT
ACDS
Solar Panel
PRELIMINARY LAYOUT SCHEMATICS
•
3U-Structure
(Section view)
MB-CPU
Payload
•
Two PPTCUP electric propulsion
systems
•
Both mounted at one end
•
•
Multi-spectral camera
(RGB+NIR)
MULTI-BAND
COMMUNICATION
MODULE
Thrusters can be fired together, for
orbit modification, or alternately, to
rotate the satellite about one of its
principal axes
• Technology demonstrator
BATTERY
BUNDLE
A compact multi-spectral camera
•
•
Four adjacent channels (0.48 – 0.9 mm)
Low spatial resolution (<100 m)
•
optical system and CCD detector
• Already space-tested
EPS
STAR SENSOR
PPT
ACDS
Solar Panel
MISSION
•
Technology Demonstration
•
By accurate orbit and attitude tracking the performance of the APPTs
can be assessed
PPTCUP electric propulsion system will thus be space-qualified
• Pointing accuracy desirable < 0,1º
•
•
Earth Observation
•
500 km Low-Earth Orbit, images with a spatial resolution of <100 m
•
By launching the satellite into a high-inclination orbit, the optical payload
could be used to monitor the spectral reflectance of polar caps
•
•
The data thus collected would be extremely useful for the investigation of
pollution and climate change
Images taken at lower latitudes could also be used, for example to monitor
deforestation in remote areas
•
Non-SSO makes corrections necessary for inconsistent lighting conditions
MULTI-SPECTRAL CAMERA FOR POLAR CAPS
MONITORING: PROBLEM
•
Polar caps are a sentinel of global change. These regions are
influenced by multiple physical and socio-economic drivers
and feedbacks, impacting both natural and human
environment
•
Air pollution is one such driver, impacting climate change, ecosystems
and health
•
•
Significant uncertainties still surround quantification of these effects
Air pollution includes
Harmful trace gases (e.g. tropospheric ozone) and particles (e.g. black
carbon, sulfates)
• Toxic substances (e.g. polycyclic aromatic hydrocarbons) that can be
transported to the Polar regions from emission sources located far outside
the region, or emitted within the Arctic from activities including shipping,
power production and other industrial activities
•
MULTI-SPECTRAL CAMERA FOR POLAR CAPS
MONITORING: GOALS
•
Estimate the variations of Albedo associated with the
precipitation of pollutants in the Polar areas
•
Perform spectral classification to distinguish the presence of
moss, lichens and other types of surface covering vegetation
•
Normalize the data collected on polar regions, in order to
integrate with other data from similar missions and so be able
to improve time analysis and determine more accurate trends
MULTI-SPECTRAL CAMERA FOR POLAR CAPS
MONITORING: PAYLOAD AND MISSION ANALYSIS
• Almost polar orbit
• Low spatial resolution and
large Swath
• High revisit time
Parameter
Spatial
Resolution
(m)
< 100
Swath (Km)
Revisit Time
(days)
Spectral
Resolution
(bands)
1230
<1
B,G,R,NIR
CONCLUSIONS
•
Electric Propulsion onboard NanoSats is not a widespread application yet
•
UniPolar will space-qualify PPTCUP, an APPT system developed by UK
partners
•
Traditionally, EO satellites have been quite large, with masses on the order
of hundreds of kg
•
Nowadays we have the capability of realizing this specific EO application,
with a much lower cost and similar performance, by using NanoSat
technology
•
This is extremely important in order to make access to space available to
low-budget actors, such as academic institutions and organizations in
developing countries
Thanks for your attention!
Any questions?
List of Exhibitors
ACCORD SOFTWARE & SYTEMS PVT. LTD.
Country
India
List of Product & Services
IRNSS(NavIC) Receivers, GNSS Receivers, GNSS/NavIC based Time
Server, MSS Terminal, IRNSS based Vehicle Tracker, GNSS Simulator,
FAA certified GPS Receiver, CDMA Transceiver, ADS-B Ground Station
AEROSPACE ENGINEERS PRIVATE LIMITED
India
AgniKul Cosmos Private Limited
India
AIDIN TECHNOLOGIES PRIVATE LIMITED
India
Rubber components – Sealing Rings, Sheets & Diaphragms, Bellows,
Extrusions & Hoses, Metal Bonded components, Harness Clamps,
Dynamic Seals, Conductive Bellows, Unions & Connectors, Cockpit (a)
Canopy Seals, Vibration Isolators, Metallic components like Lubrication
oil pumps, High, Medium & Low pressure hose assemblies, Tail cone
assembly. Machining components made from Aluminium alloy, Steel
alloy, Titanium, Magnesium Alloys, Inconel, Tungsten, Nickel Chromium
alloy, Graphite, Composite, Brass, Copper, Phenolic Resin & Fiber Glass,
Composite components using technologies like compression moulding for
DMC, SMC & wet layup, Transfer moulding for DMC, Vacuum bag
moulding of prepregs, Hot air oven curing of prepregs, Polyurethane hard
foams, etc., Machining of PTFE, Delrin, Nylon, FRP, etc.,
100 kg class orbital launch vehicle (AgniBaan), 19.6 kN thrust
LOX/Kerosene Engine
Fabrication, Assembly and Testing to Customer specifications of Space
grade PCBs and subsystems, Offset Management, Obsolescence
Mitigation, RF and Microwave, GaN based Solid State Power Amplifiers,
RF Cables, Coaxial Connectors Assembly, System design and
development for EW Systems, Power Electronics, Mixed Signal and
Embedded
India
India
GNSS Simulators for Space applications, NTP/PTP Servers, Cryogenic
Noise Standard, 4. IRIG time code Generators/Readers, Pulse Phase
Noise Test System, Time & Frequency Distribution Systems, Signal
Generators, Rubidium FREQ Standards, Calibrated Noise Sources,
Electronic Loads, RF Power Meters, Peak/CW USB Power Sensors,
Waveguide Components, Arbitrary Wave form Generators
Connectors, Flex
France
Orbital Systems, Launchers, ENS Satellites and Spacecraft Probes and
Rovers, Defence, Telecom Satellites, Propulsion, Space Equipments
AIMIL Ltd
AIRBORN INTERNATIONAL
AIRBUS DEFENCE AND SPACE
Alpha Design Technologies Pvt Ltd
India
ALTAIR ENGINEERING INDIA PVT LTD
India
Amphenol Omniconnect India Pvt Ltd
India
AMT GROUP
India
Manual Flyaway VSAT, NavIC Messaging Receiver, Miniature NavIC
Receiver,NavIC Receiver for Vehicle Tracking, Distress Alert Transmitter,
Dual Frequency Antenna, Satellite based - Supply, Installation &
Commissioning and Maintenance of Equipment for Distance Education
and Telemedicine Network, Supply, Installation & Communication and
Maintenance of HTS Earth Station and Remote VSATs, Frontend
Amplifier-Frontend Receiver 0.5-40GHz, Channelised Receiver 0.518GHz, RF Conditioning Unit, C Band SSPA, Two Way MSS Terminal for
Vessel tracking, Multiband Terminal (UHF & S-Band) - Modules, Model of
Nose Cone Assy of GSLV-III, Rudder/Flapperon of Su-30
HyperWorks Software, PBS Suite Software, Partner Alliance Software,
Solid Thinking Software, Carriots Software
LMR Cables for Low loss Application, RF Coaxial cables and assemblies
with space Legacy, Microwave Cable Assemblies for general purpose
application, 4. Phase Track Cable Assemblies for Phased Array Radar, 5.
Miltech Cable Assemblies (MIL-T-81490, MIL-C-87104 Qualified for Air
Born Platforms), Silverline Test Cable assemblies upto 110 GHz
AMT Allmatic Precision Machine Vice, AMT Precision Drilling cum
Tapping Machine, AMF Zero Point Positioning Systems, Centerdrill
Specialist in Thermal Drilling
List of Exhibitors
ANALYTICAL GRAPHICS INC
Country
India
ANANTH TECHNOLOGIES LIMITED
India
ANANYA TECHNOLOGIES PVT LTD
Antrix Corporation Limited (ACL)
ASIA SATELLITE TELECOMMUNICATIONS COMPANY
LIMITED (ASIASAT)
India
India
List of Product & Services
Telemetry Telecommand Systems, Power Distribution Systems, Core
Power & Shunt Packages, Launch Services, AOCE Systems, DC/DC
Convertor, Small Satellites
Line Replacable Unit, Ground Support Equipment, MIL1553 Data Bus
Coupler, Cable Harness Manufacturer, MIL1553 Data Bus Harness
AsiaSat 4, AsiaSat 5, AsiaSat 6, AsiaSat 7, AsiaSat 8, AsiaSat 9, DTH,
Hong Kong Occasional Use Services, TV Distribution, VSAT
AMPL’s space product portfolio includes C-Band T/R modules, 8x8, 4x4
switch matrices, S-band transmitters, X-band QPSK transmitters, X-band
phase shifters, power amplifiers, 2,3,4 and 12-way power dividers for
Radar Imaging Satellite (RISAT), Ku-band MMIC-based receivers, Tile
control units, TR controller units, Integration Blocks, CAL switch matrix, Sband Digital Phase shifters, beacon source, 8x8 routers for BES, V/UHF
T/R modules for ST radar, L-Band T/R modules for wind profile radars, LBand TRU, multi-layer printed antenna for Multi-Object Tracking Radars
(MOTR), Quad Super Heterodyne Receivers, MSS Type-D briefcase
terminals for disaster communications, MSS Loco terminals and
SATCOM-based automatic weather stations for meteorology applications.
AMPL’s space service portfolio is based on its robust and state-of-the-art
infrastructure capable of catering to space-grade requirements. AMPL
offers screening services for components to meet stringent space-grade
requirements to ensure reliability of the products. AMPL has in-house
screening facilities certified by ISRO for carrying out screening tests
according to Space requirements. AMPL has pioneered in the supply of
products screened for space requirements. Many ISRO launch
vehicles/satellites have components screened by AMPL.
ASTRA MICROWAVE PRODUCTS LIMITED
India
AXON INTERCONNECTION AND WIRES PVT LTD
AZISTA INDUSTRIES PRIVATE LIMITED
BAE SYSTEMS
BHARAT ELECTRONICS LIMITED
India
India
India
India
CARLISLE TRADING & MANUFACTURING (I) PVT LTD
CENTER FOR INNOVATION
India
India
Centum Electronics Limited
CERAMICS SCIENCES CORPORATION
CHIME PERFORMANCE POLYMERS PVT LTD
India
India
India
Micro D & Harnesses, Nano D & Harnesses, R F Cable Assembles, Bus
Cable, Coupler Harnesses, Bus Bar For Power Distribution Systems,
LVDS Cables, Atox Resistant Cables, High Voltage Cables, ESCC Wires
& Cables, Axomach Assesmbles for High Data Rate
Micro Satellite
Brakes, Carbon - Carbon, Hydraulics
LTCC based TR Modules in X, C and S Band Frequency range, KU Band
ALC Channel Amplifiers/SSPAs, reaction wheel commutation electronics
module for satellites [ISRO], DC-DC converters 3W to 100W for space
applications[ISRO], Solar array Drive Assembly - Angle sensor for
satellites [ISRO], Earth Sensor assembly for GEO satellites/ Sun Sensor
assemblies [ISRO], Crystal oscillators (VCXO, TCXO & Clock oscillators)
for spaceapplication [ISRO], Modules for Meteorological payload
applications [ISRO], Modules like Relay Drivers, Thruster Drivers,
Magnetic Torquer Drivers and Multiplexers (analog and digital) for space
applications [ISRO], Acceleration sensor electronics for launch vehicle
and satellite applications [ISRO]
Dupont Vespel, Dupont Kalrez, Delrin & Nylon Rods
List of Exhibitors
Centro Nacional de Estudios Espaciales CNES (French
Space Agency)
CUMING MICROWAVE CORPORATION
DATA PATTERNS (INDIA) PRIVATE LIMITED
EOS GMBH INDIA BRANCH OFFICE
Country
France
4ru
India
India
Eternus Performance Materials Private Limited
India
FARO BUSINESS TECHNOLOGIES (I) PVT LTD
FINE LINE CIRCUITS LIMITED
India
India
HICAL TECHNOLOGIES PRIVATE LIMITED
HONEYWELL MICROELECTRONICS USA
HTA ENTERPRISES
Indian Institute of Remote Sensing (IIRS)
India
USA
India
India
INFINEON TECHNOLOGIES INDIA PVT LTD
India
INTECH DMLS PVT LTD
INTER-CONTINENTAL MICROWAVE
ISRO Inertial Systems Unit (IISU)
ISRO Propulsion Complex (IPRC)
ISRO Telemetry, Tracking and Command Network
(ISTRAC)
India
India
India
India
ITGLOBE INC. (SAMKALPA SYSTEMS PVT LTD.)
JSC GLAVKOSMOS
K.NARKHEDE VIDYALAYA AND JUNIOR COLLEGE
BHUSAWAL
India
India
Russia
India
List of Product & Services
Space Agency
Rugged Military Electronics, COTS/MOTS Modules, Satellite Onboard
Computers, V/UHF Tranceivers, Nano Satellite, Launch Vehicles
Electronics, Communication Systems (Modem), Automatic Test
Equipments, Check out Systems for Launch Vehicles, Check out
Systems for Missiles, Aircraft cockpit display, Radar and Radar
Electronics, Missile Seekers, Avionics LRUs, ELectronics Warfare LRUs,
Fire Control Systems for Missiles and torpedoes, Un-Manned Air Vehicles
(UAV) Electronics, Built to print activities in space electronics
Carbon Fiber Composites, Carbon Fiber based Thermally Stable
Structures, High Precision Machined Titanium / Aluminum / Special Steel
Components, Cryogenic Composite Structures (Umbilical Housing &
Flight Adaptors), Carbon Fiber Payload Structures, Honeycomb Sandwich
Structures, Custom Made Foam Core Sandwich Structures, Finite
Element Analysis & Optimization (Composite Materials), One off
Prototyping and New Developments, Joint Research and Development
Projects
Faro Factory Array Imager, Faro Edge Scanarm HD, Faro Gage, Faro
Laser Tracker Vantage
Actuators, Motors, Solenoids, Transformers, Electromechanical
Assembly, Box Builds, Chassis Integration Cabinet Integration, Position
Sensors
Space Grade RF Transistors, Space Grade Rad-Hard MOSFETs, Space
Grade Diodes
Antenna Feed, LPFT Straightener, closed Impeller, Exhaust Unit, Pre
Burner impeller, Manifold, Fuel Vales, Tanks, DfAM Services, Machining
services
Simulation, Modelling and Analysis software tool, Hyperspectral Imagery
and Wavelet data compression and storage technology, Calibration Kits,
Space-grade RF, Microwave and Millimeter wave products, Composite
Materials – Quartz, Kevlar, Carbon – Honeycomb structures, Test &
Measurement equipment, Device Characterization products, DC-DC
Converters, LTCC substrates, Space-grade cable assemblies – High
Power, High Voltage, LVDS, data cables, Sealant Materials, Space-grade
isolators, circulators, Limiters, multiplexers, switches, pto-electronics
components
Turnkey / Package Solutions, Earth Observation Services, Launch
Services, Coordination of ROSCOSMOS State Space Corporation
international projects, Manned flights to the ISS, Scientific Experiments,
Export of Russia Space industry products, R&D Engineering Center,
Training, Consulting Services
List of Exhibitors
KALPANA CHAWLA CENTRE FOR SPACE AND NANO
SCIENCES
KERALA START UP MISSION
KEYSIGHT TECHNOLOGIES
KEYSTONE ENGINEERING
KOHESI BOND
KSAT – KONGSBERG SATELLITE SERVICES
Laboratory for Electro-Optics Systems (LEOS)
Country
India
India
India
India
India
Norway
India
List of Product & Services
Organise Professional Coursework related to Space Science and
Technology, Organise Semi Technical exposure Workshop on aspects
related to Space Science and Technology for UG/PG Students, Organise
Outreach Programs related to Space Science and Technology, To do
Professional research work related to Space Science and Technology
Electronic Test & Measurement Equipment
Adhesives, Sealants, Coatings, Pottings, Encapsulants, Low Outgassing
Adhesives, Cryogenic Adhesives, One & Two Part Epoxies, Sodium
Silicates, Bubble Panel (Hydroformed Panel)
Ground Network Services, TT &C, Data Accquisition 4. LEOP & Launch
Support, Sounding Rocket support, Data Handling, Hosting Services 8.
Earth Observation Services
Hardware for Launch vehicles, Hypersonic Wind Tunnel systemsTracking
Radars, Solar Array Deployment Mechanisms, Deck Panels, Bull Gear
Mechanisms, 32 m Dish Antenna
LARSEN & TOUBRO LIMITED
Liquid Propulsion Systems Centre (LPSC)
LUCAS SIGNATONE CORPORATION
LUNA OPTOELECTRONICS / ADVANCED PHOTONIX
INC
India
India
India
MACHINE HOUSE (INDIA) PRIVATE LTD
Master Control Facility (MCF)
MAURY MICROWAVE CORPORATION
India
India
India
MEASAT Global Berhad
MICRO LAMBDA WIRELESS INC
MICROCHIP
MISHRA DHATU NIGAM LTD
NanoAvionics, LLC
National Atmospheric Research Laboratory (NARL)
National Remote Sensing Centre (NRSC)
NATIONAL SPACE ORGANIZATION (NSPO), TAIWAN
NEWSPACE SYSTEMS
NITTE MEENAKSHI INSTITUTE OF TECHNOLOGY
North Eastern-Space Applications Centre (NE-SAC)
NTLab
PAHWA METALTECH PVT LTD
India
Malaysia
India
India
Antivibration mounts, Vibration testing service, Levelling elements, Air
spring dampeners
Broadcast Distribution (UHS/HD/SD), Co-location, IP over Satellite
Transit ("iPOST"), Multi-homed IP Transit, Managed Bandwidth Services
(MBS), Occasional Usage Services, Transponder Leasing,
Uplink/Downlink Connectivity, Video Playout(UGD/HD/SD)
Super alloys, Titanium & Titanium Alloys, Special Steels, Molybdenum,
Special Weld Consumables 6. Magnesium Alloys, Fastners (Titanium,
Superalloys, Special Steels) 8. Columbium Alloy, Soft magnetic alloys
(Softmag series), Soft Iron
India
Nano-Satellite platforms, Nano-Satellite Subsystems, Green Chemical
Lithuania Propulsion
India
India
Space Components, Spacecraft Subsystems, Spacecraft Bus, Systems
Engineering, Mission Operation, Ground Communication Service,
Satellite Integration & Test, Remote Sensing Data, Radio Occultation
Data, Payload Instrument
R.O.C
India
India
India
Integrated circuits for navigation, RF Front-End ASICs, OEM modules for
satellite navigation, GNSS-aided INS/AHRS, CRPA-based GNSS
Belarus receivers, GNC equipment development
Non-Sparking Tools
India
List of Exhibitors
Country
PARK CONTROLS & COMMUNICATIONS (P) LTD
India
PES University
PHASE MATRIX INC
India
India
PREMIER EXPLOSIVES LIMITED
India
RAPID DMLS INC
India
RAY-Q INTERCONNECTION INDIA PVT LTD
RENESAS
S M CREATIVE ELECTRONICS LTD
India
India
India
SAANKHYA LABS PVT LTD
India
SAINT GOBAIN
SAPHYRION
Satish Dhawan Space Centre (SDSC)
SCIENTIFIC RESEARCH INSTRUMENTS COMPANY
LIMITED (SRICO)
Semi-Conductor Laboratory (SCL)
India
India
India
SERVOCONTROLS AEROSPACE INDIA PVT LTD
India
India
India
List of Product & Services
Airborne Flight Instrumentation /Airborne Recorder System / Health &
Utility Management System (HUMS), Time Reference System / NTP
Server / Video Time Inserter / Time Code Reader / Time Display Unit /
Distribution Amplifier / Count Down Time Generator-Translator, Airborne
RF Telemetry Transmitter / Power Amplifier / Power Divider / Notch
Filters, Control Systems for Military Tank Turret Control, Airborne
Guidance, Airborne Engine, Airborne Generator, End to End Data
Acquisition System including Telemetry Receiver, Bit Synchronizer,
Decommutator and Universal Data Acquisition Application Software
PISat – student satellite of PES University, UWDES - small satellite
deorbit kit, Magnetic Torquers (1.5Am2), 4-Pi Sun sensor, Class 100,000
clean room facility, S-band ground station
Propellants, Pyro Devices, Rocket Motors, Pyrogen Igniter, Detonators,
Pyro Cartridges, Chaffs & Flares, Mob Control Devices, O & M Services,
SPP SDSC SHAR, Sriharikota, O & M Services, SFC Complex, Jagdalpur
Metal 3D Printed Aerospace & Defence Components, Multiaxis
Machining, Metal Additive Manufacturing, CMM Inspection, Reverse
Engineering, Inconel and Titanium Rotor Blades and Stator Vases,
Medical Implants / Surgical tools
Components Distribution for cable harness Industries, Engineering
Support-Design & Development, Proto with complete manufacturing files,
On job training at customer site, Off the Shelf stock
Electronic Components, Power Supply, Telemetry System
Vessel Tracking Terminal, Locomotive Tracking Terminal, L-Band
Broadcast Receiver, S-Band Satellite Modem, Burst Demodulator, Time
Division Modulator, USB Dongle Receiver
Omni Seals, RULON Polymer, MELDIN Polymer, NORGLIDE, NORBOND
TAPES
Scientific Research Instruments
Supply of servovalve, repair, service and refurbishment of various types
of servo valves in clean room, Design development and supply of
Custom built manifold blocks for aerospace applications, Design
development and supply of Custom built electromechanical and
electrohydraulic actuators, Supply of Position transducers, Linear, Rotary
and Wire draw type for aerospace and space applications, Design
development and supply of wheel hub landing gear with brake unit for
aircrafts, Design Development of Nano satellite, Precision manufacturing
of aerospace and space components i.e., lens holders, electromechanical
rotary actuators, POD assembly, cylinders, Supply of Piezoelectric motors
and shutters for Space, Aerospace and defense applications, Design
development and supply of various test rigs i.e., Impulse fatigue test rig,
Refuel shutoff valve test rig, PDOS test rig, Rotor brake test rig, High
pressure power packs, MRA/TRA etc, Design development and supply of
3/6 DOF motion platforms both electromechanical and electrohydraulic,
Development of launchers
List of Exhibitors
SHELL-N-TUBE PVT LTD
Si2 MICROSYSTEMS PVT LTD
SIERRA MICROWAVE TECHNOLOGY, LLC
SLN TECHNOLOGIES PVT LTD
SONA COLLEGE OF TECHNOLOGY
Space Applications Centre (SAC)
SPUR DTDS MICROWAVE PRIVATE LIMITED
Country
India
India
India
India
India
India
India
SUMERU MICROWAVE COMMUNICATIONS PVT LTD
India
SYNERGISTIX INDIA PRIVATE LIMITED
India
SYRATRON TECHNOLOGIES PVT LTD
India
TATA ADVANCED MATERIALS LIMITED
India
TECNOMIC COMPONENTS PVT LTD
TECSOL MARKETING PVT LTD
India
India
TELEDYNE E2V
TENCATE ADVANCED COMPOSITE USA
Times Microwave Systems
U R Rao Satellite Centre (URSC)
ULTRACOR INC
France
USA
USA
India
India
List of Product & Services
Vacuum Jacketed Super Insulated Pipelines, Vaporizers, CryoMobile Cryogenic Tanks, Cylinder Fillings Systems, Phase Separators, Gas
Mixers, Gas Cylinder Filling Manifolds, Wide Neck DEWARS, Cryogenic
Heat Exchangers, Liquid Helium Dewar, Cryostats for Industries &
Researches, Design Engineering & Establishment of Cryogenic Storage
& Distribution System, High Pressure Pneumatic Regulation &
Distribution System, Any Custom made cryogenic application System
Turnkey Design & Manufacturing, ASIC Design and Fabrication, SIPSystem In Package:- IC Packaging, Integrate Multiple Dies & Dissimilar
Technologies, MEMS Packaging, Manufacturing, PCB Assembly
Antenna Control Servo System for 32 mtr. Deep Space Network Antenna
used in Chandrayaan-1 (Indian Moon Mission) and Mangalyaan (Indian
Mars orbital Mission) mission of ISRO, Signal Conditioners and Data
Acquisition Systems
Radiation Hardened Electronic Components, RF Components, Systems
and Sub Systems, Electro-Mechanical Components, Printed Circuit
Boards, Space Hardware Fabrication
GFRP Compression Molded Antenna system upto Ka Band 2. VSAT
Antennas, Communication on the Pause (Vehicle Mounted Antenna
System) 4. Antenna Control System, Monopulse Antenna System for
Tracking and Telemetry Application 6. Doppler Weather RADAR Antenna
System (Pedestals and Antenna Control Unit Monopulse Comparator L,
S, X , Ku and Ka band frequency 8. Hat Feed, Ring Focus Feed for Man
Pack SATCOM Antenna Carbon Fibre (CRFP) Reflectors
EPO-TEK Epoxies, NuSil Silicones, Ferro Ceramic tapes and metallic
pastes
RF & MW Components, Waveguide Components, RF Coaxial Cable
Assemblies, Micro-D & Nano Connectors, Filters, Antennas, MMIC
Components, Microwave PCB & Laminates, IR Detectors, EEPROMs,
Diodes
Solar Panel substrates, Yokes, PS3A Panels, PLA V4 Panels, IS 3/4
Panels, CFRP Tubes, Aluminum Deck Plates with Aluminum honeycomb
core – L40, IS 2/3 L, EB Deck, EB Mk-III, Heat Shield Decks, Wire
Tunnels
Microsemi Corporation, Cirrus Logic, Synqor, Apacer, PCB Technologies,
Mercury Systems, Amphenol Socopax, CML Microcircuits, Halo
Magnetics, Firecomms
Space Qualified RF & Electronic Products-PCB
Mil-Aero processors, ADCs and DACs, Space package assembly, Space
product qualification
LMR Cables for Low loss Application, RF Coaxial cables and assemblies
with space Legacy, Microwave Cable Assemblies for general purpose
application, 4. Phase Track Cable Assemblies for Phased Array Radar, 5.
Miltech Cable Assemblies (MIL-T-81490, MIL-C-87104 Qualified for Air
Born Platforms), Silverline Test Cable assemblies upto 110 GHz
List of Exhibitors
UNIFIED GLOBAL TECH (I) PVT LTD
UNIVERSAL SWITCHING CORPORATION
Country
India
India
VENUS TECHNOLOGIES
India
VIASAT INC
Vikram Sarabhai Space Centre (VSSC)
VIRGINIA DIODES INC
VPT INC
W L GORE & ASSOCIATES INC
USA
India
India
India
India
WIPRO 3D (A DIVISION OF WIPRO ENTERPRISES (P)
LTD)
India
XILINX DEVELOPMENT CORPORATION
India
List of Product & Services
Space Grade Crystal & LC BPFs, Space Grade Isolators & Circulators,
Space Grade Inductors, Space Grade Single Layer Capacitors, Space
Grade Resistors, Space Grade Oscillators, hin Film metalized pattern
substrates, Space Grade Trimmer Capacitors, MIL-PRF-39012 and MILPRF-55339 in series BNC, N, SMA and TNC connectors and adapters,
MIL-DTL-3933 Attenuators AND MIL-DTL-39030 Terminations
ESA Qualified PCB Connectors of Smiths Interconnect (Hypertac), NASA
Qualified 2mm c PCI Connectors of Smiths Interconnect (Hypertornics),
Programmable Power Supplies / Customized Power Suppliers, Battery
Management Systems (Enarka Instruments), AC-DC, DC-DC Converters,
EMI Filters
Antenna Systems, Real-time Earth Observation, Satellite Grounds
Systems, Remote Sensing Antennas, Satellite Design, Antennas, Kaband Communications, On-the-move Broadband Satcom, Telemetry
TT&C, Satellite Data Transmission
Additive Manufacturing Consulting: Design & Adoption, Engineering
Design, Design for Additive Manufacturing, Additive Engineering, Post
Processing of Additive Manufactured Parts, Research & Development
Services – custom parameters development, custom metal powder
development, Testing & Validation of components made by AM
FPGA, System-on-Chip (SoC), RFSoC, MPSoC, VIVADO Software, SDx
Software Tool Chain
iEPS Type A, Type B and Type C Datasheet
ISIS-iEPS2_0-DS-00001, version 1.0
Compact and highly configurable power system suitable for up to 3U
CubeSat missions.
iEPS Type A, Type B and Type C
Datasheet
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Applications
The iEPS is a compact solution which follows a PC104 form
factor, tailored for 1U-3U sized platforms and LEO
missions. Available in three configurations which supply
from 22.5Whr to 45Whr.
Product Features
-
-
Communication over I2C, UART for testing
FRAM-based MCUs for improved radiation
tolerance
Low (idle) power consumption, dedicated
emergency low power mode for EPS
survivability
Easy to disconnect battery harness
Hardware over-current protection
Hardware supervisor including watchdog
Low-power MCU for control and Telemetry
(TLM)
I2C Watchdog (stack reset on comms failure)
Firecode stack reset capability
protection. The iEPS provides 3.3V and 5V regulated
buses, as well as an unregulated bus. An add-on
daughterboard allows additional configurations to
suitably power the system and payload instruments.
Compatibility
-
Flight heritage and quality assurance
-
-
Hardware based maximum power point
tracking
-
-
GaN-FETs implemented for improved power
conversion efficiency and performance
-
-
Automatic integrated battery heater control
-
Optional Features
-
-
Optional battery capacities:
o
2-cell pack: 8V and 4A or 32W
o
4-cell pack: 16V and 4A or 64W
Customizable voltage output channels through
mountable add-on daughterboard.1
Interoperable with ISIS Solar Panels, On-Board
Computer (iOBC) and Antenna System (AntS)
Compliant to CubeSat standard.
-
Design based on heritage from PEASSS
Cubesat (2016).
Second generation improvements flown on
the Hiber 1,2 Cubesats (2018).
Qualification Thermal Testing, -40 to +80 ºC.
Design qualification load Static +10.8 [g], three
axes.
Sine and Random Vibration ASAP5
Qualification Levels.
Flight units thermally acceptance tested for
workmanship.
IPC-A-610 Class 3 PCB and assembly, flight
units thermally acceptance tested.
Ordering information
Please contact
information
sales@isispace.nl
for
ordering
General Description
The ISIS Electrical Power System (iEPS) is the secondgeneration compact power system for nanosatellites. It
is an off-the-shelf Electrical Power System available in
three standard configurations (Type A/B/C), ideal for
powering 1U – 3U Cubesats. The system leverages wide
bandgap semiconductor technologies, implementing
GaN-FETs to improve solar power conversion efficiency
and performance. It is equipped with an integrated
heater, hardware-based Maximum Power Point
Tracking (MPPT) and hardware voltage and over-current
1
Only voltages lower than the battery voltage are possible.
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
other than provided for by this document, is not permitted except with express written permission of ISIS – Innovative Solutions In Space.
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iEPS Type A, Type B and Type C
Datasheet
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Specification
Parameter
Value
Unit
Environmental Characteristics
Operational temperature
-40 to +70(a)
°C
+85(a)
°C
Storage temperature
-40 to
Storage lifetime
12
months
90
mW
Electrical Characteristics
Static (Idle) consumption
Number of output channels [VD0]
Solar panel input
Power output
Output voltage [VD0]
Battery segment
8.0(b)
Type A
6.5 –
Type B and C
12.8 – 16.0(b)
Number of output channels for each domain VD1 and VD2
4
Output voltage [VD1]
5
Output voltage [VD2]
3.3
Maximum output current per channel for [VD0], [VD1] and [VD2]
2.5
Total maximum output current for VD1 domain
4(c)
Total maximum output current for VD2 domain
3.95(c)
3
Number of MPPTs inputs
Maximum input voltage
(+2 on DB)
Type A
8.0(b)
Type B and C
16.0(b)
V
V
A
A
V
Minimum input voltage to start MPPT
3.5
V
Minimum input voltage if another channel’s voltage is sufficient to start MPPTs
2.0
V
Maximum input current per channel
2(d)
A
Battery Cell Nominal Voltage
3.6
V
Battery Cell Min/Max Voltage (absolute maximum)
2.5, 4.2(e)
V
Battery Cell Nominal Capacity
3200(e)
mAh
Battery Pack Configuration
Battery Pack Operating Voltage (Hardware limits)
Battery Pack Operating Voltage (Software bounded range
enhances longevity)
Type A
2 in series
Type B and C
4 in series
Type A
5.5 – 8.0
Type B and C
10.9 – 16.0
Type A
6.5 – 8.0
Type B and C
12.8 – 16.0
V
V
Battery Pack Max Input Current
Bounded by satellite
design
-
Battery Pack Max Output Current
4
A
Maximum heater power
Maximum input voltage
EGSE
1
Maximum input current
Type A
1.2
Type B and C
2.5
Type A
8
V
Type B and C
16
V
Charge Batteries
1
Power Satellite
W
A
4
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
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iEPS Type A, Type B and Type C
Datasheet
Parameter
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Value
Unit
Physical characteristics
Mass
Volume (excluding CSKB)
Type A
184 ± 5
Type B
310 ± 5
Type C
360 ± 5
Type A
96 x 92 x 26.5
Type B PCB
96 x 92 x 11.3
Type C PCB
96 x 92 x 16
4-cell battery
94 x 89 x 21.0
Grams
mm3
Digital characteristics
I2C Specifications
Bus logic low-level input voltage
0- 1
V DC
Bus logic low-level output voltage
0.47 – 0.6
V DC
Bus logic high-level voltage
2.3 - 3.3
V DC
Standard-mode
Up to 100
Fast-mode
Up to 400
kbits/sec
Supported I2C modes
Supported address types
7 bits
-
I2C node type
Slave only
-
I2C general call supported
No
-
(a)
Estimated values only
Unregulated battery voltage.
(c)
If only one voltage domain is used (VD1 or VD2) the current limit for this domain is 6A.
(d)
Contact ISIS if higher input current is required.
(e)
For default cells, can vary for special cell selection.
(b)
Functional Description
The sections below provide an overview iEPS and detail the functioning of the main segments. Followed by
information on the role of the MCU, features of the daughterboard and a detailed block diagram visualizing
the system architecture. The iEPS is divided into three main segments. The battery segment, satellite segment
and the solar panel segment. A single MCU gathers housekeeping data and controls the iEPS. Additionally, a
standard daughterboard can be added to the iEPS to increase functionality.
Battery segment
The battery segment is used to charge the batteries or alternatively power the satellite. The Lithium-Ion
batteries can be charged from either the Solar Panels or from the Electrical Ground Support Equipment (EGSE).
This segment includes battery heaters and control, also protects the batteries from short circuits and can
completely disconnect the batteries if needed.
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
other than provided for by this document, is not permitted except with express written permission of ISIS – Innovative Solutions In Space.
iEPS Type A, Type B and Type C
Datasheet
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Satellite segment
The satellite segment is used to distribute the power to the satellite. This segment can provide battery voltage
output, four 3.3V switchable outputs along with four 5V switchable outputs. One switchable output of each
voltage domain is configured as permanent. For each output current, voltage and power are measured. The
system includes over voltage protection and a 2A fixed current limit. This segment also facilitates slew rate
control at 6V/ms.
Solar power segment
The solar panel segment consists of three channels, each equipped with an individual hardware based MPPT
(Maximum Power Point Tracker). The MPPTs use GaN FETs to preserve solar power conversion efficiency and
are less susceptible to radiation damage than comparable Silicon components. Several solar cell strings can be
connected in parallel to the same channel input if they have the same voltage domain. The MPPTs assume
that any parallel strings connected to one MPPT input have blocking diodes. Two more channels are available
on the daughterboard of iEPS. The solar panel interface delivers power to both the battery segment and the
satellite segment. If no batteries are connected the solar panels can be used to power the satellite.
Controller
The MCU on the iEPS interfaces with the three building blocks: solar panel, battery and satellite segment. For
the solar panel segment the MCU gathers data from the MPPTs. In the battery segment the MCU is used as an
additional safeguard by setting a software bound and entering the emergency low power mode. On the
satellite segment the MCU controls all the output load switches and gathers data on the battery power
consumption and each of the output’s switches.
Daughterboard
The daughterboard provides two additional solar panel channels, as well as seven switchable outputs in three
voltage domains. Also included on the daughterboard is the option to read out data from outboard/solar panel
sensors (thermistors and photodiodes).
Detailed interface information and CAD models of the entire iEPS may be delivered on request.
Electrical Description
The ISIS Electrical Power System (iEPS) is the second-generation compact power system for nanosatellites
designed and manufactured by ISIS. It is an off-the-shelf Electrical Power System available in three standard
configurations (Type A/B/C), ideal for powering 1U - 3U CubeSats. Type A is the compact configuration with
an iEPS board and top-mounted 2-cell battery pack, Type B consists of an iEPS board and 4-cell battery back
and the Type C configuration includes the iEPS board, four-cell battery pack and a daughter board with
additional satellite and solar panel interfaces. Figure 1 shows a detailed block diagram of the iEPS.
This second-generation system leverages wide bandgap semiconductor technologies, implementing GaN-FETs
to improve solar power conversion efficiency and performance. The system is equipped with hardware based
Maximum Power Point Tracking (MPPT), voltage and over-current protection. The iEPS provides 3.3V and 5V
regulated buses, as well as an unregulated bus. An add-on daughterboard (DB) allows additional configurations
to suitably power the system and payload instruments.
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
other than provided for by this document, is not permitted except with express written permission of ISIS – Innovative Solutions In Space.
iEPS Type A, Type B and Type C
Datasheet
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2x Output
load switch
MPPT4
DC/DC
VD3 (<Vbat)
4x Output
load switch
DC/DC
VD4 (<Vbat)
1x Output
load switch
iEPSv2
Daughterboard
MPPT5
CSKB light
VBAT_MPPT
VBAT
1x Output load
switch
MPPT 1
ABF
Reset
DC/DC
5V/3.3V
3.3V
4x Output load
switch
MPPT 2
EGSE
VBAT
5V
4x Output load
switch
CHARGE
VBAT
INHIBIT
SEP SW
MPPT 3
MCU
SEP_SW
SEP_SW 1
SEP_SW 2
iEPSv2
Automated
heater
control
SEP_SW
VBAT_POS
Model A
Model B
Temp Heater Temp
sensor2
sensor1
Figure 1 iEPS detailed block diagram
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iEPS Type A, Type B and Type C
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Solar panel input to battery output efficiency
The efficiency of MPPTs for the four-battery cell configuration is shown Figure 2 . The efficiency of the MPPTs
in the two-battery cell configuration is shown in Figure 3. Efficiency is measured for the entire chain from solar
panel input to battery output. All efficiencies include static losses.
iEPSv2 Solar cell input to four-battery efficiency at different input
voltages
100,00%
95,00%
Efficiency [-]
90,00%
85,00%
5 [V]
80,00%
10 [V]
7,5 [V]
75,00%
12,5 [V]
14 [V]
70,00%
0,0
0,5
1,0
Load current [A]
1,5
2,0
Figure 2 iEPS Solar cell input to four-battery efficiency at different input voltages
iEPSv2 Solar cell input to two-battery efficiency at different input
voltages
100,00%
95,00%
Efficiency [-]
90,00%
85,00%
80,00%
75,00%
4.8 [V]
7,2 [V]
70,00%
0,0
0,5
1,0
Load current [A]
1,5
2,0
Figure 3 iEPS MPPT converter input to two-battery efficiency at different input voltages input voltages
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
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iEPS Type A, Type B and Type C
Datasheet
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Battery input to CSKB efficiency
Efficiencies of output power bus at different voltage domains are shown for the four-battery configuration in
Figure 4 and two-battery configuration in Figure 5. Efficiency is measured from battery input to the output on
the CSKB. All measurements include static losses.
iEPSv2 four-battery to output load switches
efficiency
100,00%
95,00%
Efficiency [-]
90,00%
85,00%
80,00%
75,00%
70,00%
3.3 [V]
5 [V]
Vbat (16 [V])
65,00%
60,00%
0,0
0,5
1,0
1,5
2,0
2,5
3,0
Load current [A]
Figure 4 Output bus efficiencies with four-battery cell configuration.
iEPSv2 two-battery to output load
switches efficiency
100,00%
95,00%
Efficiency [-]
90,00%
85,00%
80,00%
75,00%
70,00%
3.3 [V]
65,00%
5 [V]
Vbat (8 [V])
60,00%
0,0
0,5
1,0
1,5
2,0
2,5
3,0
Load current [A]
Figure 5 Output bus efficiencies with two-battery cell configuration.
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
other than provided for by this document, is not permitted except with express written permission of ISIS – Innovative Solutions In Space.
iEPS Type A, Type B and Type C
Datasheet
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Mechanical Description
The ISIS iEPS design is fully compatible with the CubeSat standard as defined by CalPoly and compatible with
ISIS CubeSat structures. When supplied, the iEPS Type A is already fully assembled, with the 2-cell battery pack
integrated to the motherboard as shown in Figure 6. Both the Type B and Type C motherboards are supplied
independent from the 4-cell battery pack as it can be place freely within the stack, see Figure 7 and Figure 8.
The Type C motherboard and its daughterboard as supplied integrated to each other as per Figure 8.
Figure 6 Type A (Motherboard + Battery pack (2 Cells))
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
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iEPS Type A, Type B and Type C
Datasheet
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Figure 7 Type B (Motherboard)
Figure 8 Type C (Motherboard + Daughterboard)
Disclaimer
The contents of this document are subject to the relevant provisions in the contract concluded between the
parties. ISIS – Innovative Solutions In Space B.V. (“ISIS”) shall not be liable, in full or in part, for any damage
arising out from the application or use of any product or circuit described herein, in case such application or
use are carried out in a manner not in line with the instructions and warranties provided in the User Manual,
Safety Manual, product information sheets or any other document provided by ISIS upon the delivery of the
product (“Documents”). Further, ISIS shall not be liable for any damage caused by any use which exceeds the
function(s) of the product, or does not conform to such function(s) as described in the Documents. ISIS shall
not be liable for any damage arising from a use which is not carried out in a manner conforming to acceptable
practices in the aerospace industry.
ISIS warrants that the product is supplied after relevant tests had shown the product is in good order and
functioning, as far as these tests may indicate and predict product functionality.
© 2019. All rights reserved. Disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes
other than provided for by this document, is not permitted except with express written permission of ISIS – Innovative Solutions In Space.