Yarara-W Technical Description

YARARA UAV
Technical Description
1
General Characteristics
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.
2
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
RECONNAISSANCE
& SURVEILLANCE
TARGET
ACQUISITION
BORDER PATROL
LAW
ENFORCEMENT
MONITORING
APPLICATIONS
CRITICAL
INFRASTRUCTURE
PROTECTION
CONVOY SECURITY
BATTLE DAMAGE
ASSESSMENT
3
FORCE
PROTECTION
Technical Characteristics
Power Plant
The YARARA UAV has an integrated power plant
composed of: engine, electric generator, fuel
system, oil system and electronic control unit.
Type
Wankel – Electronic Injection
Fuel
Gasoline or Heavy Fuel (JP8)
The power plant is a Wankel type engine with
electronic fuel injection that has been specially
developed for UAVs.
Control System
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).
Propeller
It is important to note that Cabure’s has both
gasoline or heavy fuel (JP8) power plant
options.
4
Power Plant Specifications
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.
Maximum Power
Electrical Generator
Electronic Control Unit
8 HP
250 Watts
2 Blades: 24" x 12"
Technical Characteristics
Avionics & Video Transmitter
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.
Autopilot
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.
5
Video Transmitter
Technical Characteristics
Ground Control Station (GCS)
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
6
Video Receiver
GCS
Mission Planning and
Control Software
Antennas
Digital Video Recorder
Technical Characteristics
Payload: Day/Night Stabilized Electro-Optical Sensor
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
7
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
Component Weights [kg]
Airframe
15,6
Power Plant
4
Avionics + Electrical System+ Batteries
3,5
Fuel
6,4
Payload
5,5
TOTAL
35,0
Avionics +
Electrical
System +
Batteries
10%
Fuel
18%
Power Plant
11%
8
Payload
16%
Airframe
45%
Technical Characteristics
Dimensions
9
Technical Characteristics
Performance
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]
Operational Range [km]
+ 3000
+ 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.
10
MTOW: Maximum Take-Off Weight
FW: Fuel Weight
LOS: Line Of Sight
11