KZO Tactical UAV System Overview

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KZO TUAV / FTS / 08.02.2006 / Chart 1

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Observe copyright as per ISO 16016

Content

System Elements Air Vehicle

Ground Control Station Data Link Vehicle

Launch Vehicle

Refurbishing Vehicle Technical Summary

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System Elements

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Air Vehicle (1)

HW Design (1)

Compact Tail-Less Low-Set Wing Configuration

Foldable Wings for Transport and Refurbishing

Radar Absorbing / Radar Transparent GFRP / CFRP Design

Thermal De-Icing through Engine Cooling Air

Booster Launch with Booster Drop after Burn-Out Parachute / Air Bag Landing

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Air Vehicle (2)

HW Design (2)

Front Section of IR-Payload (Camera and Stabilisation Platform) connected to Air Frame by means of a Manacle Ring

All Electronics in one Unit for easy Access for Maintenance

On-Board Electronic Unit (Flight Control System, Payload Electronics, Video Tracker, Video Data Compression, Video Data Recorder , GPS Receiver) in one Housing

ADT-ELU, Crash-Recorder and IMU mounted to Housing of On-Board Electronic Unit

Flight Control by Dead Reckoning updated by Rho-Theta

Measurement of DLV, Need for GPS only for Reconnaissance “Behind the Hill”

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Air Vehicle

Characteristics Wing Span 3.4m Width (transport) 1.0m Length (flight) 2.3m Height 1.0m Take-Off Weight 161kg Payload Weight 35 Kg

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Air Vehicle

Payload Characteristics (2) Camera Infra Red 8 -12 µm 96 x 4 Detector Elements 576 x 768 Pixel (Interlaced) Zoom 1:8 with the following pre-selected FOV (v x h)

– Wide FOV 28,8°x 38,4°

– Mid FOV 10,1°x 13,5°

– Narrow FOV 3,6°x 4,8°

Video Tracker (Correlation or Cycloid)

Digital Video Data Recorder, 10 min Recording Time (Compressed Video Data incl. PID)

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Ground Control Station

Characteristics

Three Identical Operator Stations for Online / Real Time Mission Planning and Mission Modification, Flight Control and Image Exploitation

Sheltered for EMI, NBC and NEMP Protection Air-Conditioned 15ft ISO-Standard

Height Adapted to Road-/Railway-Transportation

External Power Supply by Towed GPU, Supply during Transport Possible to Handle extreme Temperatures, Internal Uninterruptible Power Supply (UPS)

Transportable by

Truck (5t Payload) Railway

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Ground Control Station

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Ground Control Station

Function

Mission Planning

Listing of Mission Elements: Shows the arrangement of the mission

Map functions

Toolbox with buttons for mission planning

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Ground Control Station

Function

Flight Control &

Mission Modification

Listing of Mission Elements: Shows the arrangement of the mission

Map functions

Toolbox with buttons for mission planning

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Ground Control Station

Function

Exploitation of Recorded Video

Image Enhancement

Video Replay Control Payload Control

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Data Link Vehicle

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Data Link Vehicle

Characteristics

Deployment Time 20 min Evacuation Time 20 min

Mast System with Automatic Alignment Capability by Means of Inclinometer (11 m High)

Ground Data Terminal

Data Link Vehicle Control Unit with Build-In Test and Indication of GDT HW Status / Faulty LRU’s

I/F to Ground Control Station for Transmission of TM, TC and Video Data to Air Vehicle

Connected to GCS by means of Rugged Fibre Optic Cable Autonomous Operation with Internal Power Supply

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Data Link Vehicle

Ground Data Terminal

Ground Data Terminal for

TM, TC and Video Data Transmission to the Air Vehicle

Air Vehicle Position Measurement Weight: 164 kg

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Data Link

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Observe copyright as per ISO 16016 HW Design

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Launch Vehicle

Characteristics

Transport of Air Vehicle to Launch Site (Shock and Vibration Isolated) Time for Launch on Launch Site < 10min

Launch Control System

Automatic Pre-Flight Test of the Air Vehicle before Launch Automatic Launch Sequence

Operated by Touch Screen

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Refurbishing Vehicle

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Refurbishing Vehicle

HW Design

15ft ISO-Shelter Air-Conditioned

Height adapted for Road-/Railway-Transportation EMI, NBC and NEMP Protection

Truck (5t Payload), Off-Road

Automatic Test System for Air Vehicle Test

External Power Supply by Towed GPU, Supply during Transport Possible to Handle extreme Temperatures, Batteries for Air Vehicle Engine Start, and Supply of Test System in Case of GPU Failure

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Air Worthiness Certification

Requirements for Air Worthiness Certification for Peace Time Operation in Germany

Probability to Leave the Assigned Area shall be 1 x 10-5_/h

Probability for an Uncontrolled Flight or Crash shall be 1 x 10-5_/h

Failure Rate of Flight Path Monitoring shall be 1 x 10-3_/h

In Case of a Technical Failure which may Endanger Flight Safety an Emergency Procedure / Emergency Device shall be Foreseen

Probability for the Activation of the Emergency Procedure / Emergency Device shall be 2 x 10-3_/h

The Failure Rate of the Emergency Procedure / Emergency Device shall be 1 x 10-5_/h

Conditions for Air Worthiness Certification

Launch and Landing in Restricted Ground Areas Flight in Restricted Air Space

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Technical Summary

Day and Night / Nearly all Weather Operation, De-Icing Stealthy Air Vehicle, Radar & IR - Reduction

High Precision Navigation and Target Localisation, with and w/o GPS High Jam-Resistant Digital Data Link

No Airfield and no Additional Landing Aids Required, Precise Landing Safe and Reliable Start and Landing, Booster / Parachute

Highly Automated Mission Planning Computer Aided Sensor Control

Target Tracking / Image Enhancement Rapid Deployment of System

Hand-Over Operation / Dual UAV Control 24 h Observation Interface to C3I-system