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PHONE: 1-888-731-3092 EMAIL: [email protected] WEBSITE: WWW.SHADOWAIR.COM

S10-VT OBSERVER

mailto:[email protected]


http://www.shadowair.com


Typical Cockpit

CONTENTS

.................................................................................S10-VT Observer - General 6-7

.......................................................................S10-VT Observer - Specifications 8-9

...............................................................................S10-VT Observer - Inclusions 10

S10-VT OBSERVER

Technologically superior manned

system for providing persistent

situational awareness 24/7/365.

Engine-off glider mode operations

capitalize upon the element of surprise

for both conventional and asymmetrical

missions worldwide.

Certified Glider Mode Operations

• EASA Part 22 certified engine-off glider mode operations worldwide.

• The only recognized standard allow-ing powered aircraft to be operated in engine-off “glider” mode.

• Exceptionally high lift/drag (L/D) ratio ensures long duration glider flights absent updrafts or thermals.

• Significant flight hours accrue for each hour of engine run time and significantly reduce the required maintenance events.

Optional Dual-Mode Capability

• Standard S10-VT Observer can be easily upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

• Standard low cost dual sensor belly mount EO/IR camera system and Wi-Fi Mesh Downlink provides VoIP communication and streaming video > 45 mile range per antenna.

• Additional state-of-the-art belly mounted sensor packages designed to meet all mission requirements can be added as desired.

Crew Comfort and Safety

• Due to Observer’s low noise signature, coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.

• Sailplane technology provides a safe, low-speed, tight turning radius to keep moving targets centered in the field of view.

• In the unlikely event of a midair collision, the jettison-able canopy allows a parachute-equipped crew to bail out of the disabled aircraft.

S10-VT OBSERVER

6

OBSERVER can easily be upgraded to a

Dual-Mode manned/unmanned aircraft

system (UAS).

OBSERVER is designed to meet the

patrol requirements of law enforcement

agencies and news media networks.

OBSERVER is ideally suited for border

and coastal patrol in very austere

environments.

OBSERVER can be modified as required

to meet all of your airborne IDMASINT

and ISR requirements.

OBSERVER aircraft are certified

for engine-off glider mode

operation.

Conservative mission operational

tempo (OPTEMPO): 365 x 0.90 =

329 days per year @ 8 flight hours

per day @ maximum continuous

power (MCP). No scheduled

maintenance event to exceed 16

hours (i.e. overhaul/replacement).

OBSERVER aircraft are Conex box

deployable and trailerable.

Dual-Mode capability allows a pilot to fly a

manned mission, land, then fly the same

aircraft as a UAS from a Ground Control

Station (GCS).

While on-station in loiter mode at 36% power,

OBSERVER consumes a mere 2.37 GPH of

100LL Avgas/premium unleaded gas.

OBSERVER can accrue several hundred flight

hours between 100-hour maintenance events

due to the low number of engine run hours

required for sustained flight in all regimes.

7

Observer Specifications

DIMENSIONS & AREAS

External dimensions

Wing span 23.00 m

Wings, gross 18.70 m²

Wing aspect ratio 29.29

Length overall 8.42 m

Wheel track 1.15 m

Wheel base 5.42 m

POWER PLANT

• Mid plane engine, drive shaft, front reduction-gear, two blade front propeller with diameter = 1.63 m

• Jointed propeller fitting into nose of fuselage driven via reduction gear and carbon prop shaft

• Engine 115 hp MTOP (Max Takeoff Power) & 100 hp MCP (Max Continuous Power)

STRUCTURES

• Modular fuselage with mid steel frame module, housing the engine compartment, and carrying wing, main landing gear, forward fuselage and tail modules.

• The Carbon Fiber Reinforced Plastic (CFRP) wing consists of three modules (LH, Center-Section and RH Wing) plus winglets. Camber-changing flaps are incorporated throughout the wingspan.

• The center-section wing is detachable from the fuselage via four bolts and has quick-connectors for fuel lines, electrical components, and mechanical control components.

FUEL CAPACITY

Maximum of 120 liters of fuel:

» 2 x 60 liters (Center-Section wing tanks)» 1 x 50 liters (optional tank in empennage baggage compartment)» Tank Selection: Left - Right - Both

8

WEIGHT & LOADING

» WEIGHTS

Maximum Take Off Weight 850 kg

Maximum Landing Weight 850 kg

Empty weight Aircraft 660 kg

» LOAD LIMITS

Crew total and crew support max 180 kg

Payload total max 10 kg

Service Ceiling 30,000’

Fuel total max 120 ltr

» TYPICAL LOAD CONFIGURATIONS

Surveillance & Utility mission: Crew (2x) total 180 kg

Endurance 8 hrs Payload total 10 kg

Range 800 nm Fuel total 120 ltr

Long range ferry flight: Crew (2x) total 180 kg

Endurance 9+ hrs Payload total ----- kg


Full payload single mission: Crew (1x) total 105 kg

Endurance 10+ hrs Payload total 10 kg

Range 929+ nm Fuel total 120 ltr

For loading purposes, individual weight & balance computations are required before each flight mission

Observer Specifications

9

Observer Inclusions

One S10-VT Observer manned aircraft equipped as follows:

• S10-VT Observer EO/IR Payload: SkyFusion Pak EO/IR simultaneous digital image capture based on altitude, speed,

overlay and location. Camera can track or be locked on a specific point of interest (SPOI). Real-time camera control

via ground control station or aircraft. Camera stabilization with programmable capture offsets. Multi-interface, all-

weather, multi-platform capable.

• My Location moving map display with flight path, image points and flight boundaries. Video and IR streaming from

aircraft. Multiple user access to real-time data. Geo-rectified stitched image overlaid on Google map with image zoom.

• SkyLINK Mesh Datalink with > 45 mile range per antenna. Full motion video. VoIP communication. Email specific

JPEG or Google Earth snapshots with one button. Create large regional networks. No FCC license required. One

antenna included (add antennas as required to increase range).

• Internet connection in areas with 3G/EVDO cellular coverage.

• sDVR spatial recorder

• VMS-HD recorder

• Solid State Digital Avionics

• Oxygen Cylinder x (2)

• Oxygen Mask x (2)

• Headset x (2)

• Parachute x (2)

• Synthetic Vision EFIS

• VFR Instrumentation

• IFR Instrumentation

• Onboard satellite imagery

• Transponder

• ELT

• XM Data Link Weather

• Traffic Alert System

• Three-axis Autopilot

• All Weather JAXIDA covers

• GPS and INS

• VHF/FM radio system

• Communications relay

$ 773,174.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $675

Wet = $725

Dry (Crew) = $975

Wet (Crew) = $1,025

*Rates based on 1,200 hours per year

10


S10-VTX OSPREY





Propeller Mechanism

CONTENTS

.............................................................................S10-VTX Osprey - General 13-14

...................................................................S10-VTX Osprey - Specifications 15-16

...............................................................................S10-VTX Osprey - Inclusions 17

S10-VTX OSPREY







missions worldwide.



• The only recognized standard allow-ing powered aircraft to be operated in engine-off glider mode.




• Standard S10-VTX Osprey can be easily upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

• Under-wing hard-points can carry two 60 kg loads.

• A lower cost belly mount sensor system is also an available option.

• State-of-the-art sensor packages designed to meet all mission requirements can be carried in underwing quick-change pods.


• Due to Osprey’s low noise signature, coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.



S10-VTX OSPREY

13

OSPREY can easily be upgraded to a

Dual-Mode manned/unmanned aircraft

system (UAS).

OSPREY is designed to meet the patrol

and interdiction requirements of military

and law enforcement agencies.

OSPREY is ideally suited for border and

coastal patrol and interdiction missions in

austere environments.

OSPREY can be modified as required to

meet all of your airborne IDMASINT and

ISR requirements.

OSPREY aircraft are certified for

engine-off glider mode operation

and capitalize upon the element of

surprise for conventional and

asymmetrical threat interdiction.








OSPREY aircraft are Conex box


Dual-Mode capability allows a pilot to fly a

manned mission, land, then fly the same

aircraft as a UAS from a Ground Control

Station (GCS).


OSPREY consumes a mere 2.37 GPH of


OSPREY can accrue several hundred flight

hours between 100-hour maintenance events

due to the low number of engine run hours


14

Osprey Specifications

DIMENSIONS & AREAS

External dimensions

Wing span 23.00 m




Wheel track 1.15 m

Wheel base 5.42 m

POWER PLANT

• Mid plane engine, drive shaft, front reduction-gear, two blade front propeller with diameter = 1.63 m

• Jointed propeller fitting into nose of fuselage driven via reduction gear and carbon prop shaft


STRUCTURES




• Two external payload stations are located inboard of the separation between center and outer wing sections.

FUEL CAPACITY


» 2 x 60 liters (Center-Section wing tanks)» 1 x 50 liters (optional tank in empennage baggage compartment)» Tank Selection: Left - Right - Both

15

WEIGHT & LOADING

» WEIGHTS

Maximum Take Off Weight 980 kg

Maximum Landing Weight 980 kg


» LOAD LIMITS



External loads below wing max (at two stations) 2 x 60 kg

Fuel total max 120 ltr






Endurance 10+ hrs Payload total ----- kg




Range 900+ nm Fuel total 120 ltr


Osprey Specifications

16

Osprey Inclusions

One S10-VTX Osprey manned aircraft equipped as follows:

• S10-VTX Osprey EO/IR Payload: Three-axis IMU gyro stabilized (direct-drive brushless motors) three channel multi-

spectral system with selectable spectral bands and optics (450 nm - 850 nm) and Field of Views (FOVs) from 10 degrees

full angle to 40+ degrees predicated by target color/size/area search rate. Multiple lenses available (8 mm - 70 mm)

delivering resolutions (GSD) from 2.2 - 19 inches at 2000’ above ground level. Data rate 15 Hz (standard) or ~ 120

MBs. FOV 5.5 -50 degrees full angle predicated by lens selection (8-70 mm focal lengths). Optical Zoom 26x video

(3.5 -91 mm) Super HAD NTSC video (30 Hz). Fixed FOV (50 mm) long-wave infrared (LWIR) camera for detecting

thermal signatures and for general night ISR. Zoom video can also be used for situational awareness and verification of

multi-spectral detections. Multi-interface, all-weather, multi-platform capable.

• eNfusion Satellite Communications Downlink

• High Definition (HD) Target Tracker: simultaneous tracking of 100 targets (including beneath forest and dense canopy).

• In-mission Look-Ahead Video Awareness (LAVA) for on-the-ground real-time situational awareness.

• Four under-wing hard-points

• Two under-wing pods


• VMS-HD recorder

• Moving map display


• Air Conditioning



• Headset x (2)

• Parachute x (2)





• Transponder

• ELT





• GPS and INS


• Satellite Phone


$ 2,176,686.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $1,250

Wet = $1,300

Dry (Crew) = $1,550

Wet (Crew) = $1,600


17


S15 TALON





Typical Cockpit

CONTENTS

.........................................................................................S15 Talon - General 20-21

...............................................................................S15 Talon - Specifications 22-25

...........................................................................................S15 Talon - Inclusions 26

S15 TALON







missions worldwide.



• The only recognized standard allow-ing powered aircraft to be operated in engine-off glider mode.




• Standard S15 Talon can be easily upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

• Hard points can carry either four 60 kg loads or two 80 kg loads.

• A lower cost belly mount sensor system is also an available option.

• State-of-the-art sensor packages designed to meet all mission requirements can be carried in underwing quick-change pods.


• Due to Talon’s low noise signature, coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.



S15 TALON

20

TALON can easily be upgraded to Dual-

Mode manned/unmanned aircraft system

(UAS) capability.

TALON is designed to meet the patrol



TALON is ideally suited for border and



TALON can be modified as required to

meet all of your IDMASINT and ISR

requirements.

Dual-Mode capability allows a pilot to fly a manned

mission, land, then fly the same aircraft as a UAS

from a Ground Control Station.


TALON consumes a mere 2.37 GPH of 100LL

Avgas/premium unleaded gas.

The aircraft is capable of accruing several hundred

hours of flight time between 100-hour maintenance

events due to the low number of engine run hours


TALON aircraft are certified for












TALON aircraft are Conex box


21

Talon Specifications

DIMENSIONS & AREAS

External dimensions

Wing span 18.00 m




Wheel track 1.90 m

Wheel base 2.00 m

POWER PLANT

• Mid plane engine, drive shaft, front reduction-gear, three blade front propeller with diameter = 1.70 m

• Optional five-blade propeller to further reduce the noise signature


STRUCTURES




• Two of four external payload stations are at the separation between center and outer wing sections at 6 m wingspan. The two remaining stations are closer to the fuselage.

FUEL CAPACITY


» 2 x 75 liters (Center-Section wing tanks)» 2 x 45 liters (outer RH/LH wing tanks)» 1 x 50 liters (optional tank in empennage baggage compartment)» Automatic fuel management system

22

WEIGHT & LOADING

» WEIGHTS

Maximum Take Off Weight 1,050 kg

Maximum Landing Weight 1,000 kg


» LOAD LIMITS




Fuel total max 290 ltr / 210 kg




Range 800 nm Fuel total 118 ltr / 85 kg


Endurance 20 hrs Payload total ----- kg







23

PERFORMANCE

TAKE OFF AND LANDING / CROSSWIND LIMITS

» Take-off distance on concrete runway at 1050 kg MTOW

Take-off run ~ 200 m ( 660’)

Take-off distance over 15 m (50’) obstacle ~ 500 m (1660’)

» Landing distance on concrete runway at max landing weight 1000 kg

Landing run ~ 200 m ( 660’)

Landing distance over 15 m (50’) obstacle ~ 500 m (1660’)

» Crosswind component max 37 km/h (20 knots)

CRUISE / CLIMB / GLIDE / FUEL CONSUMPTION / SERVICE CEILING

• Clean configuration data (i.e. gear retracted; no under wing pods)

• Range excludes climb and fuel reserves

• Range/cruise speed with pods approximately 10-15% less than clean configuration

Best SBFC estimated 0.26 kg/kWh. All data ±7.5% tolerance at time of brochure publication

Cruising speed at 5000 m (16,600’) and 100% MCP 190 knots (350 km/h) TAS (fast to station)

Cruising speed at 5000 m (16,600’) and 75% MCP 145 knots (270 km/h) TAS (economy)

Cruising speed at 5000 m (16,600’) and 35% MCP 75 knots (140 km/h) TAS (typical loiter)

Cruising speed at MSL and 100% MCP 150 knots (275 km/h) EAS/TAS



Max rate of climb at MSL and MTOW 5.0 m/s (1000 fpm)

Max rate of climb at 16,600’ and MTOW 4.0 m/s (800 fpm)


Min. rate of sink at MSL and MTOW (dead engine) < 1.0 m/s (200 fpm)

Best glide ratio at MSL and MTOW (dead engine) > 35

Fuel consumption at 100% MCP 25.0 liters/hour



Service Ceiling ( ≥ 0.5 m/s) 25,000’


24

FLIGHT CHARACTERISTICS

» Static longitudinal stability

» Agile maneuverability due to high aileron differentiation

» Docile stall behavior in straight-and-level flight, as well as in turns, due to

airfoil characteristics and high aileron differentiation

DESIGN SPEEDS & G-LIMITS

STALL SPEEDS AT MTOW @ MSL

» Stall speed in landing configuration 1000 kg VS0 = 46 knots (85 km/h)

» Stall speed in loiter configuration (neutral flaps) 1000 kg VS1 = 49 knots (90 km/h)

» Stall speed in fast cruise configuration (negative flaps) 1050 kg VS1 = 60 knots (110 km/h)

DESIGN SPEEDS

» Design speed (IAS @ MSL) VD = 205 knots (380 km/h)

SPEED OPERATING LIMITATIONS

» Never exceed speed (IAS @ MSL) VNE = 166 knots (310 km/h)

Maneuvering load factor nA = 3.8 (CS23)

CENTER OF GRAVITY

» Allowable in-flight CG range will be approximately 200 mm

» Standardized ballast within the forward fuselage or the vertical tail can be used to trim nonstandard loading conditions

» The CG limits of the under-wing pods have been designed to ensure the aircraft stays within allowable CG-limits whether or not the pods are mounted

NOISE

The noise level will be measured according to EASA part 21, subpart I.

Design features for low altitude stealth missions:

» Upward emitting exhaust and cooling outlet system/emissions shielded to the ground

» Air cooler inlet has noise absorbers; mask hot surface of air cooler inlet (optional)

» 3-blade low-speed propeller with RPM-optimized through front-reduction-gear

» Optional 5-blade low-speed propeller to further reduce the noise signature

» Aerodynamically clean airframe surface


25

Talon Inclusions

One S15 Talon manned aircraft equipped as follows:

• S15 Talon EO/IR Payload: Four-Axis, gyro stabilized, High Definition three-chip color CCD low light capability

MWCIR camera with 20:1 continuous zoom/thermal lens (true optical zoom magnification). Inertial measurement unit

provides situational awareness. Laser Range Finder determines target distance up to 20 km. Multi-interface, all-








• VMS-HD recorder






• Headset x (2)

• Parachute x (2)





• Transponder

• ELT





• GPS and INS


• HF radio system

• Satellite Phone


$ 3,932,438.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $1,750

Wet = $1,800

Dry (Crew) = $2,050

Wet (Crew) = $2,100


26

2008-2009 SEASON

The HAVOC System






The HAVOC System

CONTENTS

........................................................................The HAVOC System - General 29-30

..............................................................The HAVOC System - Specifications 31-34

..........................................................................The HAVOC System - Inclusions 35

The HAVOC System

HAVOC is a technologically superior

solution for providing persistent

situational awareness to monitor

conventional and asymmetrical threats.

The HAVOC System

• HAVOC = three specially equipped S15 Talon Dual-Mode manned/unmanned aircraft systems and one mobile ground control station (GCS).

• Computer algorithms instantly control each airborne task required for complex tactical flight.

• HAVOC flies the aircraft and performs routine flight tasks.

• The Mission Commander manages all sensors, weapons systems and mission updates.

IP-Based Open Architecture

• Modular planning tool creates and executes operator defined mission plans.

• Allows real-time modifications for rapidly changing tactical situations.

• Control multiple UAS/sensors in an IP-based setting adaptable to wide-ranging communication networks.

• Control up to 12 unmanned aircraft and as many as 20 sensors or ground control stations.

Rules-Based Expert System

• Technologically superior rules-based expert system makes instantaneous decisions for all mission dynamics.

• Control multiple aircraft and sensor systems in the same airspace while sharing information and working together as a rules-based team.

• Individual aircraft share messages such that all know each other’s location, sensor information and current systems status.

The HAVOC System The HAVOC System

29

HAVOC is a turnkey solution of three

Dual-Mode manned/UAS aircraft and

one mobile Ground Control Station.

HAVOC is designed to meet the patrol



HAVOC is ideally suited for border and



HAVOC can be modified as required to

meet all of your IDMASINT and ISR

requirements.

HAVOC’s Dual-Mode capability allows a pilot to

fly a manned mission, land, then fly the same

aircraft as a UAS from a Ground Control Station.


the aircraft consumes a mere 2.37 GPH of


The aircraft is capable of accruing several

hundred hours of flight time between 100-hour

maintenance events due to the low number of

engine run hours required for sustained flight in

all regimes.

HAVOC aircraft are certified for












HAVOC aircraft are Conex box


30

HAVOC Specifications

DIMENSIONS & AREAS

External dimensions

Wing span 18.00 m




Wheel track 1.90 m

Wheel base 2.00 m

POWER PLANT

• Mid plane engine, drive shaft, front reduction-gear, three blade front propeller with diameter = 1.70 m

• Optional five-blade propeller to further reduce the noise signature


STRUCTURES




• Two of four external payload stations are at the separation between center and outer wing sections at 6 m wingspan. The two remaining stations are closer to the fuselage.

FUEL CAPACITY


» 2 x 75 liters (Center-Section wing tanks)» 2 x 45 liters (outer RH/LH wing tanks)» 1 x 50 liters (optional tank in empennage baggage compartment)» Automatic fuel management system

31

WEIGHT & LOADING

» WEIGHTS

Maximum Take Off Weight 1,050 kg

Maximum Landing Weight 1,000 kg


» LOAD LIMITS




Fuel total max 290 ltr / 210 kg






Endurance 20 hrs Payload total ----- kg







32

PERFORMANCE

TAKE OFF AND LANDING / CROSSWIND LIMITS

» Take-off distance on concrete runway at 1050 kg MTOW

Take-off run ~ 200 m ( 660’)

Take-off distance over 15 m (50’) obstacle ~ 500 m (1660’)

» Landing distance on concrete runway at max landing weight 1000 kg

Landing run ~ 200 m ( 660’)

Landing distance over 15 m (50’) obstacle ~ 500 m (1660’)

» Crosswind component max 37 km/h (20 knots)

CRUISE / CLIMB / GLIDE / FUEL CONSUMPTION / SERVICE CEILING

• Clean configuration data (i.e. gear retracted; no under wing pods)

• Range excludes climb and fuel reserves

• Range/cruise speed with pods approximately 10-15% less than clean configuration

Best SBFC estimated 0.26 kg/kWh. All data ±7.5% tolerance at time of brochure publication

Cruising speed at 5000 m (16,600’) and 100% MCP 190 knots (350 km/h) TAS (fast to station)

Cruising speed at 5000 m (16,600’) and 75% MCP 145 knots (270 km/h) TAS (economy)

Cruising speed at 5000 m (16,600’) and 35% MCP 75 knots (140 km/h) TAS (typical loiter)




Max rate of climb at MSL and MTOW 5.0 m/s (1000 fpm)



Min. rate of sink at MSL and MTOW (dead engine) < 1.0 m/s (200 fpm)

Best glide ratio at MSL and MTOW (dead engine) > 35




Service Ceiling ( ≥ 0.5 m/s) 25,000’


33

FLIGHT CHARACTERISTICS

» Static longitudinal stability

» Agile maneuverability due to high aileron differentiation

» Docile stall behavior in straight-and-level flight, as well as in turns, due to

airfoil characteristics and high aileron differentiation

DESIGN SPEEDS & G-LIMITS

STALL SPEEDS AT MTOW @ MSL

» Stall speed in landing configuration 1000 kg VS0 = 46 knots (85 km/h)

» Stall speed in loiter configuration (neutral flaps) 1000 kg VS1 = 49 knots (90 km/h)

» Stall speed in fast cruise configuration (negative flaps) 1050 kg VS1 = 60 knots (110 km/h)

DESIGN SPEEDS

» Design speed (IAS @ MSL) VD = 205 knots (380 km/h)

SPEED OPERATING LIMITATIONS

» Never exceed speed (IAS @ MSL) VNE = 166 knots (310 km/h)

Maneuvering load factor nA = 3.8 (CS23)

CENTER OF GRAVITY

» Allowable in-flight CG range will be approximately 200 mm

» Standardized ballast within the forward fuselage or the vertical tail can be used to trim nonstandard loading conditions

» The CG limits of the under-wing pods have been designed to ensure the aircraft stays within allowable CG-limits whether or not the pods are mounted

NOISE

• The noise level will be measured according to EASA part 21, subpart I.

Design features for low altitude stealth missions:

» Upward emitting exhaust and cooling outlet system/emissions shielded to the ground

» Air cooler inlet has noise absorbers; mask hot surface of air cooler inlet (optional)

» 3-blade low-speed propeller with RPM-optimized through front-reduction-gear

» Optional 5-blade low-speed propeller to further reduce the noise signature

» Aerodynamically clean airframe surface


34

HAVOC InclusionsThree S15 Talon Dual-Mode manned/UAS aircraft and one Ground Control Station (GCS) equipped as follows:

• HAVOC Mobile Ground Control Station (GCS) trailer, hardware and software.

• S15 Talon EO/IR Payload: Four-Axis, gyro stabilized, High Definition three-chip color CCD low light capability

MWCIR camera with 20:1 continuous zoom/thermal lens (true optical zoom magnification). Inertial measurement unit

provides situational awareness. Laser Range Finder determines target distance up to 20 km. Multi-interface, all-


• Control/Data Links: C-Band Line-of-Sight (LOS); Ku-Band SATCOM Beyond-Line-of-Sight (BLOS).




• Manned/Remotely Piloted/Fully Autonomous




• VMS-HD recorder






• Headset x (2)

• Parachute x (2)





• Transponder

• ELT





• GPS and INS


• HF radio system

• Satellite Phone


$20,763,000 (Price subject to change)

Hourly Lease Rate Schedule* - 3 Talon UAS platforms

- 1 Ground Control Station (GCS)

- For capabilities equal to a Predator A

UAV at less than half the cost!

*Rates based on 1,200 hours per year per platform

35

ShadowAir LTD Airborne ISR Solutions

Toll-Free: 1-888-731-3092 Email: [email protected] Website: www.ShadowAir.com



http://www.ShadowAir.com

http://www.ShadowAir.com

shadowair specifications prices brochure reduced

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