YARARA UAV

Technical Description

1

General Characteristics

2

The YARARA UAV is a low cost solution for tactical UAV requirements. It is a rugged, modular and easy to deploy system that combines in a single airframe several options for the military, security and civilian markets. The unique concept of a self-contained integrated propulsion unit allows a high sortie rate and easy field maintenance. The YARARA UAV is an available solution for UAV requirements from UAV training to tactical ISR missions using advanced avionics and data links, all in rugged proven platform. The YARARA system (3 UAVs, GCS and support equipment) in three boxes weighting less than 250 kg permits rapid deployment and high mobility in small vehicles or helicopters to the area of operations. The YARARA UAV can be operated in several operational modes such as manual, assisted manual or programmed for autonomous operation. It uses advanced avionics and precise GPS navigation. YARARA UAV launch and recovery uses standard take-off and landing procedures in non prepared air strips and is equipped with flaps for enhanced performance. Its landing gear design allows hard landings and improves its operational safety in heavy cross wind scenarios. With a wingspan of 4 meters and a maximum takeoff weight of 30 kg, the YARARA UAV provides aerial observation, day or night, at line-of-sight ranges of more than up 50 kilometers. The YARARA UAV delivers real-time color or infrared imagery to the ground control station and to remote viewing stations. Other payloads can be installed and integrated based on user requirements.

General Characteristics Applications

3

APPLICATIONS

RECONNAISSANCE & SURVEILLANCE

TARGET ACQUISITION

FORCE PROTECTION

CONVOY SECURITY

BATTLE DAMAGE ASSESSMENT

CRITICAL INFRASTRUCTURE

PROTECTION

LAW ENFORCEMENT MONITORING

BORDER PATROL

Technical Characteristics Power Plant

4

Power Plant Specifications

Type Wankel – Electronic Injection

Fuel Gasoline or Heavy Fuel (JP8)

Control System Electronic Control Unit

Maximum Power 8 HP

Electrical Generator 250 Watts

Propeller 2 Blades: 24" x 12"

The YARARA UAV has an integrated power plant composed of: engine, electric generator, fuel system, oil system and electronic control unit. The power plant is a Wankel type engine with electronic fuel injection that has been specially developed for UAVs. The power plant has electronic fuel injection controlled by an electronic control unit (ECU). The ECU allows for continuous correction of the injection timing based on the varying atmospheric conditions (pressure and temperature). It is important to note that Cabure’s has both gasoline or heavy fuel (JP8) power plant options. The on-board electrical generator provides the aircraft a significant amount of electrical to powers , actuators, avionics and payloads as well as meet power plan needs.

Technical Characteristics Avionics & Video Transmitter

5

The YARARA UAV has an advanced military grade autopilot. The autopilot uses an external GPS unit for inertial navigation and radio link communications with the ground control station (GCS). The autopilot can guide the UAV autonomously and/or receive dynamic user commands through the GCS which can control the UAV or its payload. The autopilot uses an inertial measurement unit (three-axis rate gyros, accelerometers and magnetometers) for attitude estimation, as well as differential and absolute air pressure sensors for airspeed and altitude measurement. It also includes wind estimation and auto-trim capabilities. The autopilot provides intelligent, autonomous flight control of the UAV with GPS waypoint navigation and autonomous takeoff, flight and auto-landing capabilities. The video transmitter is plugged into the payload and sends video in real time to the GCS.

Autopilot

Video Transmitter

Technical Characteristics Ground Control Station (GCS)

6

The GCS is composed of: interface unit (to communicate with the autopilot), video receiver, laptop, radio control (to command the UAV), mission planning and control software, antennas (for communications), and digital video recorder. The GCS can be independently transported for each mission or it can be integrated in a vehicle.

Interface Unit

Video Receiver

GCS Antennas

Mission Planning and Control Software Digital Video Recorder

Technical Characteristics Payload: Day/Night Stabilized Electro-Optical Sensor

7

This payload is a two axes stabilized, single-sensor imaging payload with a rigid structure. This payload is built on a one line replaceable unit (LRU) open architecture carrying a single sensor that can be switched in minutes. Sensors contain either a “day” continuous zoom color camera or a “night” uncooled thermal imaging camera.

Specifications

Platform Two Axes Stabilized

Field of Regard: Azimuth = ±170° - Elevation = -90° / +20°

Thermal Sensor Uncooled Detector 8-12 μm

320 x 240 pixels

Day Light Sensor CCD Color with Near IR Continuous Zoom 10 x

Technical Characteristics Weights

8

Component Weights [kg]

Airframe 15,6

Power Plant 4

Avionics + Electrical System+ Batteries 3,5

Fuel 6,4

Payload 5,5

TOTAL 35,0

Airframe 45%

Power Plant 11%

Avionics + Electrical System + Batteries

10%

Fuel 18%

Payload 16%

Technical Characteristics Dimensions

9

Technical Characteristics Performance

10

Speeds

Maxium Speed [km/hr] 163

Never Exceed Speed [km/hr] 170

Stall Speed (flaps off) [km/hr] 67

Stall Speed (with flaps) [km/hr] 61

Maximum Rate of Climb [m/s] 6,5

NOTE: Speeds obtained in standard atmosphere conditions at sea level for MTOW = 35 kg.

Operational Performances

Maximum Ceiling [m] + 3000

Operational Range [km] + 30 (LOS)

Takeoff / Landing Distance [m] < 100

Endurance (V = 90 km/hr) [hr] 6,0

NOTE: Endurance obtained at standard atmosphere conditions at sea level for MTOW = 35 kg and FW = 6,4 kg.

MTOW: Maximum Take-Off Weight FW: Fuel Weight LOS: Line Of Sight

11