Aerospace projects 1

About our partner

Is a leader in the field of on-board software in the Czech Republic and it is one of the leadingCzech SMEs in the field of innovative R&D projects with a focus on aerospace projects.Is also experienced in other areas like custom embedded systems for industrial automation, PLCtechnology, data transmission and microwave high frequency applications.

Our partner is member of the following associations:
*Czech Space Alliance – Association of Czech SMEs involved in space industry
*ITS&S – Intelligent Transport Systems and Services– Association forTransport Telematics of the Czech and Slovak Republic
*Unmanned Systems Manufacturers Association – Association of companies engaged indevelopment, manufacturing and operation of UAV (Unmanned Aerial Vehicles) in the CzechRepublic
*UVS International – UVS International represents manufacturers of unmanned vehiclesystems (UVS), subsystems and critical components for UVS and associated equipment, aswell as companies supplying services with or for UVS and research organizations




Participates in two independent workpackages of the Iris programme

ATM Repeater Verification Testbed

Is member of team which definethe architecture of a simulator of thetelecommunication payload to be carriedon the satellite and implement thesimulator and its sub-components. Thisincludes simulation of the ATM repeaterand the Ground segment/Satellite KU-band & Aircraft/Satellite L-band radiolinks.

GUI for TC processor

Objective of another task is to develop a common data processing and graphical library for theTC Results Processor, to be used to support the test reports generation and further to design anddevelop the TC GUI module, TC Test manager and TC test processor interface. The develop -ment follows the ECSS standardization as applicable for the ground support equipment. Thedelivery consists of the Software module, the host platform HW and the appropriate documenta-tion.
Iris Programme Overview
Iris, element 10 of the ESA’s ARTES (Advanced Research in Telecommunications Systems) programme, aims to devel-op a new Air-Ground Communication system for Air Traffic Management (ATM). It is the satellite-based solution for theSingle European Sky Air Traffic Management (ATM) Research (SESAR) programme. It supports the implementation ofthe Single European Sky by looking at all aspects of Air Traffic Management. It also intends to modernize communicationinfrastructure and increase safety for air traffic participants. By 2020 it will contribute to the modernization of air trafficmanagement by providing digital data-links tocockpit crews in continental and oceanicairspace replacing a voice communicationchannel between the pilot and a controller.

Satellite-based solution for Air Traffic Management

Is a leader in the field of Space On-board Software in Czech Republic.
engineers have experience from earlier non-ESA Space projects and just finished ESAproject. The On-board SW development is compliant to the actual ECSS standardization.SWARM Accelerometer Instrument On-board Software (ESAproject)

*StartUp SW – Mission critical SW (stored in PROM)
*ApplicationSW(stored inEEPROM)
*Engineering support during project phases B, C/D, E
*Accelerometer On-board Software features
*Science and Housekeeping data acquisition using multiple AD converters,measurement time-stamped with accuracy better than 1 millisecond
*ESA Packet Utilization Standard (PUS) TC/TM interface
*SW developed in C language, time critical routines in Assembly
*HW target was a significant performance constraint for the SW – x51 family 8-bit microcontroller (Spacequalified 80C32E at 12MHz with only 268 Dhrystones / 0.153 VAX MIPS)
*Priority scheduler for optimal utilization of limited CPU performanceMission background
The SWARM mission objective is to provide the best survey ever of the geomagnetic fieldand the first global representation of its variations on time scales from an hour to severalyears. The challenging part is to separate the contributions from the various magneticfield sources. SWARM, a constellation mission (3 identical satellites), will simultaneouslyobtain a space-time characterisation of both the internal field sources in the Earth and theionospheric-magnetospheric current systems. Launch is planned in 2012.
HXRS (Solar Hard X-Ray Spectrometer)
* Instrument On-board SW
* Technology: On-board SW: 80C166 CPU, Assembly;Ground support and test equipment SW: C++, Windows
Mission background
Czech Solar Hard X-Ray Spectrometer aboard the NASA & U.S. Department of Defense & U.S.Department of Energy – Multispectral Thermal Imager satellite (MTI). Launched on March 12th,2000 on a Taurus vehicle from VAFB, CA, USA, successful 18 month mission
MIMOSA(Czech microsatellite)
*Spacecraft OBC On-board SW
*Main instrument (Microaccelerometer MAC-03) On-board SW
*Technology: On-board SW: 80C166 CPU, Assembly;Ground support and test equipment SW: Linux, RTLinux, C/C++
Mission background
MIMOSA (Microaccelerometric Measurements of Satellite Accelerations) wasa Czech microsatellite, principal investigator of the project was Astronomical Insti-tute of Academy of Sciences (ASU CAS) Ondřejov, Czech Republic (Czech nation-al funding). Launched on June 30th, 2003 on Rockot KS / Breeze (Eurockot) fromPlesetsk in northern Russia.
Mimosa  STIX Instrument On-board Software (ESA project)
*Engineering support during project phase B
*StartUp SW – Mission critical SW (stored in PROM)
*Application SW (stored in FLASH memory)STIX On-board Software features
*Control of the instrument and interface to the spacecraft
*SpaceWire link interface, using the ‘CCSDS packettransfer protocol’ and ESA Packet Utilization Standard(PUS) TC/TM interface
*Housekeeping data acquisition and reporting
*FDIR (Failure detection, isolation and recovery) witha high level of autonomy
*Science data acquisition and storage in the instrumentinternal mass memory
*On-board data processing: Autonomous based on userparametrisation and Selective based on user TCrequests – possible to select data from the instrumentinternal archive in the mass memory
*SW developed in C language
*HW target: Leon 3FT IP core in FPGA
Mission Background
The Solar Orbiter is one of the Cosmic vision M-Class ESA missions. The mission goal is to understand (and evenpredict) how the Sun creates and controls the Heliosphere. STIX (Spectrometer Telope for Imaging X rays) is one of theSolar Orbiter’s on-board remote sensing instruments. STIX provides imaging spectroscopy of solar thermal and non-thermal X-ray emissions from approx. 4 to 150 keV, with unprecedented sensitivity and spatial resolution (near periheli-on), and good spectral resolution.

ESAGSTP projects

ESA’s General Support Technology Programme (GSTP) exists to convert promising engineeringconcepts into a broad spectrum of mature products.
OBCP-BB: Requirements and I/F definition for future OBCP Building Block
Spacecraft on-board autonomy is becoming more and more prevalent, in particular for deep spacemissions with long propagation delays and low telemetry bandwidths. One method by whichthe Spacecraft is able to maintain this autonomy is through the use of On-Board Control Proced-ures. This GSTP activity makes an assessment of the ECSS-E-ST-70-01C standard, a review theexisting OBCP technologies and determines requirements for its future implementation as a build-ing block prototype. As a part of the activity, a prototype OBCP Building Block implementation isproduced .
OSRAc: On-board Software Reference Architecture consolidation
Future modular reusable/reference on- board SW architecture with a goal to reuse the On-boardsoftware in a systematic manner. This GSTP study is following activities COrDeT and Domeng.


ACC Instrument EGSE Software
provided Accelerometer (ACC) instrument EGSE (Electrical GroundSupport Equipment) Software for the SWARM mission.

 ACC Instrument EGSE functionality: 

*Used during the instrument development, verification / validation testing on theinstrument level and during the Spacecraft integration 
*Communication front end for generating, handling an receiving TC(telecommand) / TM (telemetry) packets, according to the appropriate ESAstandards (Ground Systems and Operations, Telemetry and TelecommandPacket Utilization ECSS-E-70-41) 
*Load and dump SW (including EEPROM patching) 
*Receive and parsing of Housekeeping and Science data 
*Automatic communication logging
 *Simulation of the spacecraft OBC (On-board computer) functionality 
*Allows generate all TC packets for the ACC instrument. 
*Open architecture – allows user to write own test scripts including TC packetsequences in widely known PHP scripting language 
*Automatic Data parsing 
*EGSE SW functionality provides packet filtering, automatic conversion,generated logs and error logs 
*Packet Analyzer including Validar module provides functionality for autonomous validation of singlepackets and packet sequences 
*Test front end for testing of ACCHW, both digital and analogue partwith specific test of HW 
*Control of EGSE HW modules:HW module for two serial RS422interfaces, digital I/O interface toPPS generator and instrumentinternal relays control, communic-ation with MCU-controlled instru-ment electronics checkout unitand remote-controlled powersupply 
*Support for autonomous andoperator assisted instrument SWand HW tests 
*Provides on-line view (tabular andgraphical) of the instrument statusand control of instrument opera-ACC EGSESW screenshottion 
*TC TM FE LAN module 
*Provides communication interface for C&C messages from Core GSE (GSE for the SWARM space-craft including all on-board instruments) in the integrated configuration 
*Technology: Linux/C++/Qt/PHP


engineers have experience from several space projects – from a successful implementation ofthe data processing for satellite payloads (spectrometers & accelerometers).SphinX (Fast Soft X-ray Spectrophotometer) on-board of CORONAS-PHOTON spacecraft
* Data processing SW
* Technology: Ground segment SW: Linux, C, C++, Shell scripts, IDL,NASA Solarsoft packages, SQL, JAVA, PHP, Firebird
Sphinx Data processing SW features
* The purpose of software is to analyze and process incoming datadumps, downloaded from the Spacecraft operational center. Theinputs for the processing are SphinX spectrometer science (X-ray)data and auxiliary data – housekeeping/ technological data and S/Cposition/orientation data.
* Processed data will be accessible locally using the interactive visual-ization tool and remotely using web server (data catalogue and visual-ization).
*Properties: Two synchronized Linux Servers, Creating of FITS filesfrom telemetry dumps, Measurements stored in a Firebird database,IDL ThickClient for interactive data visualisation, WebServer witha catalogue, PDF generator.

Mission background
CORONAS is a Russian program for study of the Sun and solar-ter-restrial connections physics by series of spacecrafts, which provideslaunching of three solar-oriented satellites onto the near-Earth orbit.CORONAS-PHOTON (Complex ORbital Observations Near-Earthof Activity of the Sun) is the third satellite in this series. Two previ-ous missions of the project are “CORONAS-I” (launched on March2, 1994) and “CORONAS-F” (launched on July 31, 2001). DataProcessing Ground Segment software for SphinX – a fast Soft X-raySpectrophotometer for the Russian CORONAS Solar Mission hasbeen developed in cooperation with Astronomical Institute,Academy of Sciences of the CR, v. v. i. The end customer is SpaceResearch Center of the Polish Academy of Sciences.CORONAS-PHOTON has been launched on January 30th, 2009 on Tsyklon-3 from LC-32, Plesetsk, Russia
 HXRS (Solar Hard X-Ray Spectrometer) 

*Data processing SW
*Automated downloads of the data files from the mission data server in the USA
*Data processing – conversion from raw data to FITS format
*Technology: C/C++, Windows, UNIX/Solaris, NASA SolarsoftMIMOSA(Czech microsatellite)

*Ground segment SW – automated data transfers and processing
*Ground station control SW – automated communication with the satellite
*Technology: Linux, C++


 Embedded electronics, prototype manufacturing, UAV control systems and payloadsCCUAS LABS- The Hacker Model Prod. and Evolving Systems’

 Competence Center forUnmanned Aerial Systems Laboratories 

*specializes on electronics, especially in embedded microcontrollers, data transmission andmicrowave high frequency applications. 
*team of qualified engineers have experience (20 years – since 1989), hardware andsoftware tools needed for working with the latest technolo-gies. 
*Our objective is our satisfied customer. 
*can handle complete developments, product moderniz- ationor only give advice or consultation in the field of datacommunications and microwave high frequency circuits. 
*have been working on certificates necessary for gettingbetter in military and avionics business.

2nd generation UAV avionics
engineers have designed a control system for the new generation of Czech UAV, used as
aerial targets, developed in a consortium “” together with Hacker Model Production. hasdesigned the on-board electronic systems andsupplied an embedded software and Ground UAV controlsoftware.New UAV (Unmanned aerial vehicle) production lines havebeen introduced in cooperation with a partner companyHacker Model Production a. s.
*90 – mini unmanned reconnaissance carrier “Electric ray”
*400 – autonomous aerial target system
*700 – autonomous aerial target system (jet engine)
*Scanner – reconnaissance and surveillance system 

The progressive introduction of UAVs for both military and civilscopes is an important change in Aeronautics. Various countriesaim to introduce UAV systems in civil airspace in the time-frame2010-25, according to many projects and initiatives. Civilian UAVflight operations may include very important tasks, such as: NaturalDisaster and Emergencies Assistance; Nuclear Facilities Protection;Pipeline Inspection; Assessment and Monitoring; Scientific MissionParticipation, Contamination Measurement, Surveillance of publicgatherings, Riot Control, etc



400 Aerial Target

The  400 is an autonomous aerial target used to provide a threat-representative target drone to support the Ground-to-Air Weapon System evaluation, testing and training programs.


The   400, manufactured, is constructed of carbon fiber and epoxy- based materials.

The  400 is capable of speeds from  80 km/h  (49 mph)  to  400 km/h (244 mph) true airspeed at sea level. The drone can achieve flight altitudes from 30 m (100 ft) above ground level to 3,000 m (10,000 ft) mean sea level.
Maneuvers include G-turns up to 20 Gs, and other aerial acrobatic turns.

The drone is launched from a rail system. The drone can land by using a parachute recovery system. Recovered targets are repaired, tested and reused. The  400 can carry a full range of  current  target  payloads  which  include  infrared  and  radar  enhancements  and  a chaff/flare dispenser set.


A realistically moving aerial target provides efficient shooting practice and combat firing for anti-aircraft missile systems SHORAD/VSHORAD, thus improving the quality and efficiency of the gunner/operator training. Five prototype targets of 3 different sizes (wing span 1.5 m, 1.9 m and 2.5 m) have been built to date, in 2009 – 2011.

 General Characteristics of  400 V1.5

Primary function:   Aerial target
Power plant:   Combustion engine w/ propeller
Wingspan:   1.9 meters (6.3 ft) 
Length:   1.35 meters (4.5 ft) 
Height:   0.56 meters (1.8 ft)
Weight:   19 kg empty, 21.5 kg max. 
Maximum speed:   400 km/h (244 mph)
Ceiling:   3,000 meters (10,000 ft)
Range:   30 km (18 mi)

*) Valid for the medium-sized model




The  Scanner is a medium endurance unmanned aircraft system. The  Scanner’s primary mission is reconnaissance and surveillance in support of the operational commander. Surveillance imagery from video cameras and forward looking cameras are distributed in real-time. 


 The  Scanner is a system, not just an aircraft. A fully operational system consists of one aircraft (with sensors), a Ground Data Terminal, an Image Receiving System, a  Scanner Satellite Link, along with operations and maintenance crews for deployed 24-hour operations. 

The basic crew for the  Scanner is a pilot and a payload operator.  Scanner follows a conventional launch sequence from a semi-prepared surface under direct line-of-sight control. The take-off distance is typically 50 m (165 ft) and landing 100 m (330 ft).

 The mission is controlled through real-time video signals received in the Ground Data Terminal. Command users are able to task the payload operator in real-time for images or video on demand. The surveillance and reconnaissance payload capacity is 10 kg (22 lb), and the vehicle carries electro optical and infrared cameras. The aircraft can be equipped with sensors as the mission requires. The cameras produce full-motion video. 

The system is composed of three major components, which can be deployed for operations in the field. The  Scanner aircraft can be disassembled and packed into a container for travel.


The  Scanner system was designed in response to the needs of police and military to provide medium-duration intelligence, surveillance and reconnaissance information.

 It has many other uses: promotion, real estate sales, technical documentation of historic buildings, digs registration, comparison of geological changes, agriculture, detection of illegal buildings and junkyards, searching for missing persons or fugitives, measurement of concentrations of noxious gases, traffic monitoring, residential area monitoring, and security patrol.

General Characteristics of  Scanner V1.3

 Primary Function:  Reconnaissance, airborne surveillance and target acquisition
Power plant:  Engine with propeller; 1 x 11 hp
Wingspan:  3 m (10 ft)
Length:  2.15 m (7 ft)
Height:  0.85 m (2.7 ft)
Maximum take-off weight:  25 kg (55 lb)
Payload:  10 kg (22 lb)
Speed:  Cruise speed around 80 km/h (49 mph), maximum up to 150 km/h (92 mph)
Range:  6.5 km (3.8 mi), limited by datalink range
Ceiling:  1,000 m (3,300 ft)
Endurance:  2 hr
Crew (remote):  Two (pilot, payload operator)
Ground control system:  Two suitcases, containing pilot and payload operator consoles
                                                            (GDT = Ground Data Terminal, IRS = Image Receiving System)


UAV sense and avoid systems and communication payloads 

ARCA (Adaptive Routing and Conflict mAnagement) control system 

The goal of the project is to develop an autonomous on-board flight system able to guide a UAV towards a specific destination modifying its own flight trajectory in reaction to a variety of external situations, maintaining the separation with other aircrafts. In restricted airspaces this system will allow a UAV to separate from other UAV by coordinating with them and autono mously solving possible trajectory conflicts. The system will also offer the same capabilities for the non restricted airspace, including separation from commercial aircraft. This capability will only be exploitable if particular operational conditions are met (e.g. all commercial traffic is equipped with devices for providing navigation information such as the ADS-B; adequate ATM procedures are defined to deal with equipment failures). Path Planning and Conflict Detection & Resolution functionalities with an innovative  approach based on the emerging  frameworks  of Multi-agents  Systems  and Game
Inspection; Assessment and Monitoring; Scientific Mission Participation, and others. Although many aircraft currently allow an autopilot to be programmed by providing waypoints, most require an element of human piloting when routes are modified.

Partners in the Adaptive Routing and Conflict mAnage- ment for Unmanned Aircraft Vehicles (ARCA) Project, which is a 30 months project funded under the Eurostars Programme, the first European funding and support programme specifically dedicated to SMEs, fostering collab- orative research and innovation.

Long Range Communication Relay System


•  Communication relay system

•  Airborne re-translation

•  Range of the system up to 50 km

•  Data communication rate 8 Mbps both uplink and downlink

•  System based on OFDMA

•  Typical deployment in situations with large distances of variable coverage

•  Possible     deployment     to     multiple receivers at the same time



Autopilot Overview 

The autopilot is designed as a modular system consisting  of  a UAV  Control  Unit  and  various sensors (GPS,  gyroscope,  accelerometers, altimeter,   …) communicating   through  two independent CAN buses for high reliability. The data collected by various sensors is combined by a unique algorithm statistically evaluating validity of the data. Data from one particular sensor are merged with data obtained by another sensor based on sensor noise probability guess, which leads to more precise calculation of the UAV’s state.  This   topology   benefits   from   using  of redundant  sensors  that  are  working  simultaneously  without  switching.  When  sensor  malfunction  occurs,  only  noise  probability  increases. Classical switching to backup device does not use all available sensors during normal operation.

UAV Control Unit


 The key feature of the autopilot is to stabilize the aircraft. The considered variables are: 

•  direction (heading)
•  horizontal speed
•  altitude 

The controlled variables are:

•  control of the engine thrust
•  aerodynamic control surfaces (roll, pitch and yaw)

 The heading is controlled by a combina- tion of deflection of the rudder (or elevat- ors in case of the rudder-free airframes) and  ailerons.  The  horizontal  speed  iscontrolled  by  adjustment  to  the  enginethrust. The rate of climb to a given altitude is achieved by the application of a combination of elevator deflection and engine thrust.

Automatic Flight Control System 

The Automatic Flight Control System (AFCS) – higher level intelligence of the autopilot – which accepts the commands from the operator (respectively UCS), compares the state (orientation, position, …) of the UAV with what is commanded and instructs the other layer of the system to make appropriate corrections. It contains the memory to store mission (a list of way points and how to fly through them) and flight program able to react to unpredicted events. 



UAV Control System

 The  UAV Control System (UCS) is a NATO STANAG 4586 compatible system designed to control  400 aerial targets and other STANAG 4586 compatible UAV or UGV and UUV. The system is not limited to one vehicle at a time but can receive telemetry data and sensor imagery from multiple vehicles in parallel thereby enabling it to combine data from several sources and  control  several  vehicles  and  their  payloads.  According  to  STANAG  4586  multiple  levels of interoperability are feasible between different UAVs and their UAV Ground Stations (UGSs). To achieve maximum operational flexibility the UCS supports Level 4: Control and monitoring of the UAV, less launch and recovery.

UCS Architecture 

All  UAVs  controlled  by  the  system  communicate with Core UCS (CUCS) through STANAG 4586 defined Data Link Interface (DLI). The CUCS unit processes the telemetry and other data collected from   the  UAVs.   The  data  is   provided  further to compatible  C4I  Systems  and  through  Human Computer Interaction (HCI) module to the vehicle and payload operators.

 UCS Configurations 

There are several configurations of the UCS available to meet specific requirements of various missions. Mobile configuration is designed to provide basic functionality focusing on maximum mobility  and  easiness  of  use  in  complicated  situations.  Room  and  Car  configurations  offer a reasonable trade-off between full featured functionality, lower mobility and more complex human- computer interaction requiring more qualified operators.

Payload Control 

The payload carried by the vehicle can be sensor systems and associated recording devices that are installed on the air vehicle, or they can consist of stores, e.g. weapon systems, and associated control/feedback mechanisms, or both. The data link element consists  of  the  Air  Data  Terminal  (ADT) in the air vehicle and  the  Ground   Data Terminal (GDT), which may be located on surface,  sub-surface  or  air  platforms.  The control of the UAV System and communication with its payloads is achieved through the UCS and data link elements. The UCS element incorporates the functionality to generate, load and execute the UAV mission and to disseminate usable information data products to various C4I systems or a custom external system.





Software for PLC Control system, validation and verification

•   has delivered software for chillers used in nuclear industry for chilling water in the second – ary circuit of a nuclear power plant.

•  Verification of the software product was conducted according to the internal Software Requirements.

•  Validation of the software product was conducted according to the Customer Requirements.

•  The PLC testbed was used to imitate a behaviour of the system in real time with automatic, complex simulation. Requirements are validated and evalu- ated graphically.

•  The  testbed  provides  automated  generation  of test protocols.

•  The software complies to the safety stand- ards IEC 61508, IEC 62138 and RCC-E.
•  The  platform  Siemens  Simatic  STEP-7- PLC is used in safety-related applications (Class B).

•  Chiller systems can be used in all industries.

•  The Programmable Logic Controllers (PLCs) perform the supervisory control of the chiller systems and employ other sub-systems that also have embedded programmable controllers.


Automatic testbed for PLC SW verification

•  The test bed is based on PC applications driven by external scripts.

•  Tested application requirements are separated into Test Cases.

•  Subject of verification can be the whole application, its part or even subsystem function library.

•  Assistance with preparation of hardware and software design specifications.

•  Assistance with preparation of hardware  and software requirements specifications.

•  Test Cases are gathered in an input script file.

•  Plug-in board for PC provides analogue  and digital  inputs and outputs.

•  Console application running on Windows OS.

• Input script files and output report files in the CSV or MS Excel format.

•  Test protocols are generated, revisions saved.

•  The testbed  imitates a behaviour of a system in real time with automatic, complex simulation. Requirements are validated and displayed graphically.

•  Used in safety-related chiller application evaluation.

•  Used with Siemens SIMATIC S7 PLCs.




Prototype design & manufacturing, robotics, control systems, RF applications

 is well experienced in the design of control systems and robotics and in the field of prototype manufacturing. We specialize  on electronics, especially in embedded microcontrollers                including   DSPs  (Digital signal processors)   and  FPGAs, data  transmission and microwave high frequency applications.

‘s team of qualified engineers has experience (since1989), hardware and software tools needed for working with the newest technologies. ‘s objective is to satis-fy a customer.

can  handle  complete  developments, product modernization or only give an advice or a consultation in the area of data communications and microwave high frequency circuits and industrial automation.

Uniaxial robot designated to contactless imprinting with inkjet printing head



Framework overview


The generic embedded control framework consists of 3 components:


•  Control Unit (CU)

•  Control Library that wraps all low level hardware

•  Control GUI

The Control framework can be configured in 2 ways:

•  XML dription of control process – this way is aimed for simple tasks

•  C/C++ programming – for advanced users

Features of CU

•  2 independent CAN buses
•  3 independent serial buses
•  Micro SD card slot
•  Ethernet connector
•  USB connector (micro USB)
•  Logic inputs/outputs
•  JTAG connector
•  RTC with battery backup


The CU has two alternative power sources: USB cable and external power cable.

 Technical parameters   CU
General inputs/outputs:  5 x
COM port level:  TTL ( provides also TTL to RS232 converter)
COM protection:  none
Ethernet:  RJ45 CAT 5
Ethernet protection:  nne (onchip)
CAN:  compliant to 2.0a
CAN maximum transmission speed:  1 MBd
Mass memory:  Micro SD and SDHC cards supported
Humidity:  < 95 % non condensing
Temperature:  -40 … 85° C (industrial)
RAM (external):  32 MiB (configurable)
RAM (internal):  192 kiB
EEPROM:  256 kiB (configurable)
Unit PCB size:  70 x 90 mm
Power:  6 … 15 V (external)  or 4.5 … 5 V (USB)
Power consumption:  50 mA at 12 V (External) 100 mA at 5 V (USB)
Weight:  44 g
CPU:  ARM family

Features of Control Library

The  Control  Library  gives   user   a friendly access to the low level hardware functionality.

•  CAN Open layer

•  Ethernet layer

•  FAT disk access

•  RTC access

•  Library with components/blocks for control process

Features of control GUI

The Control GUI gives a possibility to monit- or, configure and debug the control process. The GUI can display a content of any point, modify point values, paint charts and display logs from control process. Well known blocks like PID controller have their own dialog.

The GUI can connect to the CU through ethernet / UDP connection (using a propriet- ary protocol) or through a serial port.

The control points can be used as inputs and or  outputs  e. g.  into  control  blocks,  math blocks, switches.

The Control network can be stored in XML format on SD card.

Several points can be mapped to PDO/SDO variables from CAN Open external sensors.

More complex blocks and custom functional- ity  can  be  compiled  as  custom  functional blocks.

Services and support

is ready to support the customers with tailoring of  CU firmware according to their specific needs.

The HW (CU) can be modified (e. g. using different sizes of external memories).
Can also design custom CAN Open terminals – external sensors, actuator drivers, HMI terminals.