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2001. Called the ER/MP UAS, it is envisioned as a medium altitude, endurance UA, its preliminary
requirements closely resemble Hunter’s capabilities. Funding started in FY04 and an IOC is planned for
2007, the ER/MP acquisition approach is to procure an in-production system. The ER/MP request for
proposal (RFP) was released in September 2004. Two contractor teams successfully completed the
System Concept Demonstration in March 2005. A Milestone B decision was made on April 20, 2005,
with a single contractor award expected in May 2005. A key requirement is that the ER/MP UA must be
controllable from the RQ-7 Shadow ground station. Five systems (12 aircraft each) are planned for
Increment 1, with each system increasing to 18 aircraft in Increment 2.
2.2 CONCEPT EXPLORATION UAS
X-50 Dragonfly Canard Rotor/Wing (CRW)
User Service: DARPA
Manufacturer: Boeing
Inventory: 2 Delivered/2 Planned
Background: The CRW concept combines the VTOL
capability of a helicopter with the high-subsonic cruise speed (as
high as 400 kt) of a fixed-wing aircraft. CRW intends to achieve
this by stopping and locking the rotor and using it as a wing to
achieve high speed forward flight; the canard and tail provide additional lifting and control surfaces. For
both rotary and fixed-wing flight modes, the CRW is powered by a conventional turbofan engine. The X-
50 is a technology demonstrator designed to assess and validate the CRW concept. Hover tests were
conducted in December 2003 and March 2004, but a hard landing resulted in significant damage to the
first air vehicle. The second X-50 is now being readied to continue the flight testing, planned for summer
2005. http://www.darpa.mil/tto/programs/crw.html.
Characteristics:
X-50 X-50
Length 17.7 ft Rotorspan 12 ft
Gross Weight 1,485 lb Payload Capacity none
Fuel Capacity 160 gal Fuel Type Jet-A, JP-8
Engine Make Williams F115 Power 700 lbf
Performance:
Endurance 1/2 hr Max/Loiter Speeds 220/0 kt
Ceiling 20,000 ft Radius 30 nm
Takeoff Means Hover Landing Means Hover
SECTION 2 - CURRENT UA PROGRAMS
Page 15
UAS ROADMAP 2005
2.2.2 A-160 Hummingbird
User Service: DARPA/Army/Navy
Manufacturer: Boeing/Frontier
Inventory: 4 Delivered/10 Planned
Background: The A160 Hummingbird is designed to
demonstrate the capability for marked improvements in
performance (range, endurance, and controllability), as
compared to conventional helicopters, through the use of a rigid rotor with variable RPM, lightweight
rotor and fuselage structures, a high efficiency internal combustion engine, large fuel fraction, and an
advanced semi-autonomous flight control/flight management system. The patented Optimum Speed
Rotor (OSR) system allows the rotor to operate over a wide band of RPM and enables the A160 rotor
blades to operate at the best lift/drag ratio over the full spectrum of flight conditions. First flight occurred
in January 2002. In flight testing, using a 4-cylinder racing car engine, the A160 has achieved 135 kt
speed, 7.3 hour endurance on an 18% fuel load, 7,000 ft altitude, and wide variation in rotor RPM.
Autonomous flight achieved for take-off, waypoint flight, landing, and lost-link return to base. Current
plans are to test with a 6-cylinder engine, then migrate to a turboshaft engine, and ultimately to a diesel
engine, to achieve high endurance (24+ hours) and high altitude (30,000 feet). The DARPA contract ends
in 2007. http://www.darpa.mil/tto/programs/a160.html.
Characteristics:
A-160 A-160
Length 35 ft Rotorspan 36 ft
Gross Weight 4,300 lb Payload Capacity 300+ lb
Fuel Capacity 2,500 lb Fuel Type Gasoline
Engine Make 6-cylinder car Power 390 hp
Performance:
Endurance 18 hr at 15kft Max/Loiter Speeds 140+/0 kt
Ceiling 28,000 ft Radius 1,700 nm
Takeoff Means Hover Landing Means Hover
SECTION 2 - CURRENT UA PROGRAMS
Page 16
UAS ROADMAP 2005
2.2.3 Cormorant
A
naissance, or
d a
User Service: DARPA
Manufacturer: Lockheed Martin
Inventory: 0 Delivered/TBD Planned
Background: The Cormorant project is currently conducting a
series of risk reduction demonstrations for a multi-purpose UA that
is “immersible” and capable of launch, recovery, and re-launch
from a submerged SSGN submarine or a surface ship. Such an U
could provide all- weather ISR&T, BDA, armed recon
SOF and specialized mission support. In particular, the combination of a stealthy SSGN submarine an
survivable air vehicle could introduce a disruptive capability to support future joint operations. If the
current demonstrations are successful, follow-on efforts could involve building an immersible and flyable
　
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