Eagle Eye UAV
The Bell Eagle Eye HV-911 has the appearance of a conventional aircraft with tilt rotors at the end of each wing that allow it to maneuver up or down and hover. Bell Helicopter Textron Incorporation (BHTI) became involved with the Unmanned Aerial Vehicle (UAV) program by taking the wind tunnel V-22 model, using off the shelf helicopter parts, i.e., engine, drive shafts, gear boxes, etc. and built the Eagle Eye tilt rotor UAV.
The Eagle Eye has a wing span of 15.2 ft, is 17.9 ft in length, is 5.7 ft high, and weighs around 2,000 pounds (depending on payload). The first flight test (hover only) were conducted at BHTI facility in Dallas, Texas during the winter/spring of 1992.
After successful hover flight tests, the government and contractor teams moved to Yuma Proving Grounds (YPG) for flight test during the third quarter of 1993. The flight tests were very successful and the Eagle Eye flew in helicopter mode, converted through the transition mode to aircraft mode. 35 flights were conducted with a total flight time of 15 hours. Average flight hour per sortie was .43 hrs/flt. Maximum airspeed attained was 159 knots at an operating altitude of 1,550 feet above Mean Sea Level (MSL).
The government had no further Vertical Take Off and Landing (VTOL) requirements and concluded all VTOL demonstration/development contract actions. BHTI continued to develop the Eagle Eye with in house R&D dollars.
In the spring of 1998 the government once again wanted a demonstration of VTOL air vehicle capabilities and contracted BHTI to demonstrate the flying qualities and performance characteristics of the Eagle Eye. This became a two Phase program. Phase I was a land based flight demonstration and Phase II will be sea based flight demonstration. Phase I was accomplished in April 1998. The aircraft has flown more than 43 times, exceeding 55.5 flight hours and achieving airspeed of more than 200 knots, with an altitude of 14,600 feet during the demonstration at Yuma Proving Ground.
Phase II of the program is scheduled for the last quarter of FY99 and will be conducted aboard a small Naval combatant.
In February 2003, Bell Helicopter, Textron Inc., was awarded a contract to commence concept and preliminary design work for its Eagle Eye tiltrotor, Veritical Takeoff and Landing Unmanned Aerial Vehicle (VUAV) for us in the Coast Gaurd Integrated Deep Water System. The VUAV is a short-range, low maintenance shipboard deployable unmanned aircraft. The VUAV will allow the Coast Guard to extend the surveillance, classification and identification capability of its major cutters through its speed, range, and endurance and at a lower cost. This asset will be used for maritime homeland security, search and rescue missions, enforcement of laws and treaties including illegal drug interdiction, marine environmental protection, and military preparedness. The Eagle Eye will be an interoperable asset integrated with supporting command, control, computers, communication, intelligence, surveillance, and reconnaissance (C4ISR) technology.
Specifications | |
| Manufacturer | Bell Helicopter - Textron, Texas |
| AV Type | Tilt Rotor |
| Length | 17.9/5.46 (ft/m) |
| Height | 5.7/1.73 (ft/m) |
| Wingspan | 15.2/4.63 (ft/m) |
| Rotospan (diam) | 9.5/2.90 (ft/m) |
| Take-Off Gross Weight | 2250/1020 (lbs/kg) |
| Empty Weight | 1300/590 (lbs/kg) |
| Fuel Weight | 750/340 (lbs/kg) |
| Payload Weight | 200/90 (lbs/kg) |
| Speed (kts) | Max 220, Cruise 0-185 |
| Altitude | 20,000/6,100 (ft/m) |
| Endurance | 6 hours |
| Radius of Operation | 110/200 LOS (nm/km) |
| Engine | Allison 250-C20 GT 420 shp |
| Fuel | Heavy.JP |
| Landing Gear | Wheeled/Retractable |
| Flight Control | Automated/Dual Redundant |
| Availability | Development |
| Take Off/Landing | VTOL/STOL |
| AV Data Link(s) | S-Band/UHF (TCDL future) |
| Payload | FLIR - EO/IR - SAR |
This matrix outlines performance demonstrated during the VTOL UAV landbased demonstration at Yuma Proving Grounds. This demonstration called for up to 50 flight hours in a 90 day period.
PARAMETER |
OBJECTIVE |
METRIC |
DEMONSTRATED |
|
| xx | xx | xx | Total |
Last Flt |
| Air Vehicle | VTOL | xx | xx | xx |
| xx | xx | Sorties |
43 | 1 |
| xx | xx | Total Flight Time (hrs) |
55.5 | 2.3 |
| xx | xx | Longest Sortie (hrs) |
2.3 | 2.3 |
| Radius of Action2 | 110 nm | Max Range (nm) |
20.6 | 20.6 |
| xx | xx | Max Rng Ltd by |
datalink | datalink |
| xx | xx | External Pilot |
20.6 | approx 1.0 |
| xx | xx | Internal Pilot |
20.6 | 20.6 |
| xx | xx | Payload |
20.6 | 20.6 |
| Time to Station3 | < 1 hr | Time to 20 nm loiter point (min) |
approx 9 minutes | approx 9 minutes |
| Time on Station4 | 3 hr | Time @ 20nm loiter (hrs) |
1.7 | 1.7 |
| Airspeed | 0 to 150 kts | Max Airspeed (kts) |
190 kias* | 180 kias |
| Maximum Operating Altitude | at least 13,000 ft MSL | Max Altitude |
14,005 Hp** | 10,000 Hp |
| Shipboard Launch/ Recovery Area | all air capable ships 24 Spot | Avg Distance from Intended Ldg Point (ft) |
xx | 2 |
| Launch/ Recovery Wind-Over-Deck |
up to at least 20 kts | Launch/Recovery |
12/16G32 | 2-5 /VAR |
| Shipboard Launch/ Recovery Capability | Automatic with manual backup and waveoff capability; touch and go | n/a | n/a | |
| xx | xx | Auto T/O & Ldgs |
0/0 | 0/0 |
| xx | xx | Manual T/O & Ldgs |
43/43 | 1/1 |
| xx | xx | Touch & Gos |
1 | 0 |
| xx | xx | Waveoffs Int/Unint |
0/1 | 0/0 |
| Environmental Protection | full EMI protection | EMI SOFT |
No EMI Noted | No EMI Noted |
| xx | Protected from and resistant to degrading effects of sand, dust, and salt-laden air; operate in light icing | Sand/Dust degradations |
None Noted | None Noted |
| AV Operational Temperature | - 20 deg F to 120 deg F (start, T/O) | Max/Min OAT(deg F) |
93/49 | 84/77 |
| xx | --note these numbers are at the field-- | Max/Min Press in Hg |
29.72/ 29.00 |
29.15 |
PARAMETER |
OBJECTIVE |
METRIC |
DEMONSTRATED |
|
| xx | xx | xx | Total |
Last Flt |
| Recover at TOGW | Yes | Recover at TOGW |
1954 / |
1954 / |
| Launch/Recovery Accuracy |
9.8 ft during launch/recovery; | TO/LDG accuracy (ft) |
5 / 10 |
2 |
| Spatial Location Accuracy | 82 ft in-flight | NAV accuracy (ft) |
34.6 |
not calcd |
| xx | xx | TGT accuracy |
n/a |
n/a |
| Navigation Capability | autonomous navigation; automatic execution of lost link and emergency recovery procedures; automatic loiter on command; transmit magnetic heading information and self-location | xx | xx | xx |
| xx | xx | Auto-navigation |
waypoint select and designate | waypoint select and designate |
| xx | xx | Automatic lost link |
3 links plus return home | 3 links plus return home |
| xx | xx | Automatic loiter |
0 kias inertial velocity demoed | not demoed |
| Payload Capacity | at least 200 lb; 2.5 kW power for payload; internal/external payload area of at least 2 cubic feet; day/night passive imagery sensor | Max Payload carried: Weight (lbs) |
209 (includes TM gear) | 200 (includes TM gear + FSI 3000 FLIR/TV) |
| Navigation Lights | comply with FAA regulations;
capable of activation/ deactivation from GCS at maximum range |
Ext Lights control
|
Strobe only | Strobe only |
| Mission Reliability5 | at least 75% | xx | xx | 100% |
| xx | xx | Avg Flt Hrs/Sortie |
1.3 |
2.3 |
| xx | xx | Takeoff Times: |
xx | 0700/ |
| xx | xx | Sortie Completion % CANX WX |
xx | 100% 0 0 0 |
| xx | xx | Maint Actions/Flt Hr Maint Hrs/Flt Hr |
xx | 0 |
| xx | xx | Down Gripes |
9 | 0 |
| xx | xx | In-flight Aborts |
9 | 0 |
| xx | xx | Data Set
Completion |
approx 95% | 100% |














