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conformal, un-cooled IR detector arrays that can be incorporated into the wing of the aircraft to provid
low aerodynamic drag at minimum weight and power requirements; 2) an optic flow collision avoidance
and navigation system for use in GPS-denied environments and urban canyons; and 3) transition to digital
protocols for up- and downlink communications.
A
2003. Its fuel cell is shaped to also serve as the wing.
2
BAE Concept
Landing Ring
Flight Control Vanes
Tailored Duct (Hover/Cruise)
GFE Payload
Locations
Fuel Tank
Optimized Fan
MAV-like Avionics Pods with
Integral Collision Avoidance
Pusher Engine “Lifting Stators”
Aurora Concept Honeywell Concept
Manufacturer Aurora Flight Sciences, BAE Systems, Honeywell
Sponsor DARPA/ Army
Weight 112 lb dry
Length TBD inches
Duct Dia 20-36 inches
Payload 22 lb
Engine Type Heavy Fuel - Cycle type TBD
Ceiling 11,000 ft *
Radius ~10* nm
Endurance 120* min
* Design requirement; not yet demonstrated.
ackground: DARPA and the Army have been exploring scalable designs for an organic air vehicle
CS
se
B
(OAV) since FY02. DARPA recently began a follow-on to the original OAV program. The new
program is called OAV-II. The OAV-II is aimed at a larger system transported aboard one of the F
ground vehicles. Aurora Flight Sciences, BAE Systems and Honeywell were awarded contracts for Pha
I of a competitive program to develop and demonstrate a prototype FCS Class II UA using only ducted
fan technology for achieving hover and stare capability. The OAV is envisioned as an UA that can be
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UAS ROADMAP 2005
launched and controlled from a high-mobility multipurpose wheeled vehicle (HMMWV) or robotic
vehicle to provide over-the-hill RSTA. The OAV-II program is closely coupled to the Army Science
Technology Objective (STO) that is being conducted by the U.S. Army CECOM, Night Vision and
Electronic Systems Directorate (NVESD) for development of a RSTA mission equipment package (M
for the Class II UA. In Phase III of the OAV-II program the Class II MEP will be integrated with the
DARPA-developed UA. The combined system will be used to demonstrate Class II RTSA and target
designation capabilities in early FY09. http://www.darpa.mil/tto/programs/fcs_oav.html.
and
EP)
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UAS ROADMAP 2005
2.5 UNMANNED AIRSHIPS
A number of unmanned airship projects, both free-flying and tethered (aerostats), have been initiated to
provide synergistic capabilities to those provided by unmanned aircraft, most notably extended
persistence. Such airships are capable of endurances ranging from 5 days (RAID) to a month (JLENS)
and primarily provide local area surveillance for defensive roles, such as force protection and cruise
missile detection. A number of aerostats are now employed in the force protection role in Iraq and
Afghanistan. Psychological operations (TARS) and border monitoring (TARS) are other niche roles in
which they can complement aircraft. There appears to be potential for synergy between airships and UAS
that enhance capability or reduce cost in several mission applications including force protection, signals
intelligence collection, communications relay and navigation enhancement. Airships most significant
challenge appears to be limited mobility.
2.5.1 Advanced Airship Flying Laboratory
User Service: Navy
Manufacturer: American Blimp Corporation
Inventory: 0 Delivered/1 Planned
Background: The Advanced Airship Flying Laboratory
(AAFL) will serve as a prototype test bed for improving the
state-of-the-art of airship systems technologies, ISR sensors,
related processors, and communications networks. The
initial airship systems to be developed and tested will be bow thrusters for slow speed control authority to
reduce ground crew requirements; heavy fuel engines to increase efficiency, safety, and military
operations interoperability; and automated flight controls to increase payload, altitude, and reduce flight
operations costs. AAFL will be equipped with dedicated hard points, equipment racks, high bandwidth
network interfaces, and 5 kW of power for rapid integration to test a great variety of Network Centric
Warfare payload options from a persistent ISR platform.
Characteristics:
AAFL AAFL
Length 200 ft Tail Span 55 ft
Volume 275,000 ft3 Payload Capacity 1,000 lb
Performance:
Endurance 48 hr Altitude 20,000 ft
Sensor Various Sensor Make TBD
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UAS ROADMAP 2005
2.5.2
V
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unmanned aircraft systems roadmap(21)
