:: Project Proposal

EOS Engineering Consultancy & Software Ind. Co. has started the mini-UAV program. All the aeronitical tests were carring on by using computational analyze methods. System airframe and wing airfoil was tested already. 

EOS will be a small, lightweight, inexpensive and expendable unmanned aerial vehicle (UAV) that can fly autonomously for long durations. EOS is capable of providing low cost aerial surveillance imaging and carrying sensor payload packages.

EOS will also have hand-launch capability and it will be able to take off and land itself. 

:: Applications

Sea Surveillance :
• Fishing Industry
• Monitoring Fisheries
• Search and Rescue
• Environmental Monitoring
• Tracking "Targets-of-Interest"
• Sea-Life Monitoring
• Entertainment

• Weather

Land Surveillance :
• Search and Rescue
• Environmental/Pollution Monitoring
• Agriculture Moisture Data
• Wildlife Monitoring
• Livestock Monitoring
• Pipeline
• Fire Detection & Monitoring
• Hazardous Weather Monitoring

• Weather Sensing

:: Airframe
Composite, glass fiber, carbon fiber and kevlar materials are used for building airframe. This provides a very strong, durable and light weight structure impervious to the environment. The design of the aircraft is comprised of 5 self integrated system modules; payload, avionics, fuselage, wing and ground system. This modular concept allows for significant commonality across aircraft model families with flexibility to change mission specific aircraft configurations at will by simply replacing one module for another. The aircraft stores neatly in its transportation case for easy setup and deployment.

All airframe was designed by 3D computational airframe design tools and tested for aerodynamic characters and mechanical stresses. 

:: Airfoil & Computational Aerodynamic Tests

EOS Airfoil has optimum lift/drag ratio for low energy/high endurance. New types of airfoils was used to test the criterions and also scaled wing profiles was built for real weather tests. Airfoil selection and tests procedures were implemented by using public NACA, UIUC, NASA Databases and softwares. Also a software was devoloped for simulation of autopilot and other avionic system tests. 

Fuselage/nose and tail structure tests were also done by using computational analyses. EOS has T-tail single-elevator, single-rudder, semi-controlled multi-ailerons and flap for flight controls. Ailerons can also be used as flaps for low-Reynolds numbers during landing and take-off.

:: Engine & Drive System
EOS is powered by two pieces wing mounted, off the shelf, simple and highly reliable brushed or brushless electric engine produced with high flux magnet technology. Static trust is more than 1600 gr with Li-Polymer batteries. The maximum power consumption is 300 W @12V battery voltage (per motor). Low-cost and easy-change features are the most important design aims. The power system utilizes experimentaly between many motor-gear-prop alternatives and could reach over 67% total power efficiency which results in high flight duration and low consumption. System is able to carry an external battery pack to increase its endurance from 60 mins to more than 90 mins. Battery system is embedded into mid-wing panel and this wing panel is also works as a battery pack. Motors and controllers are also embedded into wing edges and they wors as a mounting assemble of wings. EOS power system is simple by using this multi purpose engineering methods.

:: Avionics
The avionics and semi-custom hardware & software with all integration will be performed by EOS. It is designed and implemented for the maximum endurance and have two seperate channels for data and video transmission. All tracking and position data were collected by using a 4 Hz integral GPS. Autopilot navigation will have a minimum resolution for each altitude, speed and ECEF location of 3 meters, and will have a resolution of 1° of attitude resolution ; heading accuracy is 1°. System is capable to navigate 200 way-points which are pre-programmable point. 

All avionic and control systems will be mounted inside the airframe. EOS was controlled by a custom developed microcontroller interfaced with 3 gyros, 3 accelerometers,  1 absolute and 1 differantial pressure sensors. Navigation is asissted by s GPS module and compass module. System can be pre-programmed through TCP/IP communication port. All other data logged during flight will communicate over wireless 900 MHz transciever.

:: Autopilot

EOS autopilot was designed for low-cost, mid range mini or micro uav's. It has onboard sensor-level IMU, 2-axes magnetometer, absolute pressure transducer as barometric altimeter and a differential pressure transducer as pitot sensor. The fullfeatured EOS autopilot is the lightest (24gr) and the smallest (70x45x15mm) board in its range. High efficient onboard power regulator, onboard servo in/out, onboard programmable digital I/O's and 12-bit analog inputs provides efficient reliable robust control and payload control.

EOS autopilot provides full control of a fixed-wing uav, including auto-take off and auto-landing with ultrasonic altimeter.

The system integrates an external GPS and an onboard magnetometer for INS. It uses 3-axes gyros and accelerometers for attitude estimation. The optimized embedded software enables attitude update  20 times per second and also control payload actuators as an vibration-free stabilizer. An external radio modem is used for telemetry, real time control (RPV) and payload control. It has also an onboard data logger for telemetry.

• Auto take-off & landing capability

• Autonomous waypoint navigation

• Return Home & Patrol & Emergency Modes

• Airspeed, Altitude Hold Modes

• Temperature Compensation for IMU sensors

• Onboard Magnetometer

• Wind estimation

• Auto - trim feature

• Onboard data logging

• 3 inputs for battery voltage monitoring (0...24 V)

• 1 inputs for current monitoring (0...60 A)

• 2 RS232 ports for payload control

• Hardware filter for IMU sensors

• EKF filter for attitude, position, altitude and airdpeed estimation

• 4 Hz, precise and fullfeatured telemetry update

• Aileron+Flap or Flaperon control, elevator+Rudder or V-Tail control

• Onboard power regulator

• Onboard servo in/out

• Easy connection and mounting

• Small size & weight

:: Communication
Aircraft state vector data is available at 20 Hz with GPS position data accuracy not more than 3 m or better in real time under conditions allowing carrier-phase differential corrections. Single command and control transciever and single video transmitter will be used. Stabilized scan platform attitude is also available in real time for payloads requiring this information. The ground-based antenna provides real-time support to maximum 3 km, with future ground station upgrades expected to extend this range. Custom ground systems are available for high-EMI environments.

:: Camera Turret
EOS can fly with an vibration-free internially stabilized camera turret fitted with either a day/night or IR micro-camera. A stabilized turret permits the ability to persistently stare at a point of interest rather than having to continuously 'swoop the aircraft' at the target as with other small UAVs.

Nose mounted 120° Tilt + 90° Pan Turret