Aerospace projects 1
About our partner
ARTES 10: IRIS PROGRAMME
ATM Repeater Verification Testbed
GUI for TC processor
ACC Instrument EGSE functionality:
DATA PROCESSING SOFTWARE
UNMANNED AERIAL SYSTEMS
Embedded electronics, prototype manufacturing, UAV control systems and payloadsCCUAS LABS- The Hacker Model Prod. and Evolving Systems’
Competence Center forUnmanned Aerial Systems Laboratories
HAES AERIAL TARGET UAV
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
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
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.
GROUND CONTROL SYSTEM
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.
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.
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.
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.
PLC CONTROL OF CHILLERS
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.
INDUSTRIAL CONTROL SYSTEMS AND ROBOTICS
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
GENERIC EMBEDDED CONTROL FRAMEWORK
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.