Vigilante UAV

References

Vigilante NAVY Unmanned Aerial Vehicles PMA 263

Vigilante UAV

In January 1998 a team led by Science Applications International Corporation (SAIC) has been awarded a contract by the US Navy's Joint Program Office for Unmanned Aerial Vehicles to conduct a demonstration of SAIC's Vigilante vertical take-off and land (VTOL) unmanned air vehicle (UAV). The potential value of the contract is an estimated $4.8 million, which includes $1.8 million for the base period and an additional $3 million in possible options. SAIC's Vigilante UAV System is a developmental system and has not been operationally deployed.

Unique to the Vigilante is that it is optionally piloted from within the craft, or it can be controlled from a ground station. It is set-up to be flown in three modes Manned, External Pilot (AKA R/C), Intelligent autopilot and mission control system.

SAIC's Vigilante is based on a commercial off-the-shelf (COTS) 2-seat experimental helicopter kit designed to be built and operated by recreational pilots. The first Vigilante, based on the 496 model, was started in April 1997 for the Ballistic Missile Development Organization (BMDO) and the Jet Propulsion Lab (JPL) to provide a stable, unmanned platform for an optical camera to monitor antiballistic missile tests.

The Vigilante needs only about 20 feet in diameter to execute its vertical take-off and landing. This means that the Vigilante can be transported on and deployed from frigates and other Navy ships which are likely to reach the battlespace before aircraft carriers. As a result, the Vigilante will be able to supplement the mission of the Navy's jet fighters by providing early reconnaissance and payload capabilities quickly and cheaply.

As modified for the Navy's use, the Vigilante will carry enough fuel to allow it to operate for up to 16 hours. Its imagery payload, the Wescam 12DS, has an infrared imaging sensor and a daylight color television camera. This same payload is being purchased by the US Marine Corps for its Pioneer UAV. Imagery will be transmitted to the surface at full rate using a C-band analog datalink. An additional datalink will support system command and control. The Vigilante's flight control system, however, is capable of fully autonomous (no human-in-the-loop) take-off, flight navigation, and landing.

Specifications
Manufacturer	SAIC, VA; USA
AV Type	Conventional Helo
AV Physical Description (ft/m)
Length	19.9/6.07
Height	7.8/2.39
Width	8.0/2.44
Wingspan	-
Rotorspan (diam)	23/7.01
Take-off Gross Weight (lbs/kg)	1085/492
Empty Weight	587/266-627/284 w HFE
Fuel Weight	315/143
Payload Weight	183/83
Speed (kts)
Max	135
Cruise	-
Endurance (hrs)	16
Altitude (ft/m)	13,000/3,975
Radius of Operation	500/925
Engine	Hirth F30 95hp/future HFE
Fuel	Diesel/future HFE
Landing Gear	Skids
Flight Control	Automated
Availability	Development
Take-Off/Landing	VTOL
AV Data Link(s)	C-Band/ +another
Payload	WESCAM or POP EO/IR
Sensor Options	WESCAM12DS-UAV Color daylight TV Infrared (InSb) array NIIRS-6 Auto tracker Slaves to navigation coordinate info AZ range: continuous 360° EL range: +90° to -120° 6 axis vibration isolation
Light Weight Synthetic Aperture Radar (SAR) optional	- All weather - Better than 1 ft resolution - 66 lbs
Ground Control Station (GCS)	Vigilante GCS based on successful system build for DARPA HAE UAV TCS Compatible Intuitive point and click tasking and control for AV sensors AV flown by waypoints or direct remote control Field unit flight control Sensors controlled in the field or in the command center

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	Sorties	94	10
xx	--m1=mode 1-- --m2=mode 2 (autopilot)--	Total Flight Time (hrs)	7.5 (total) 0.3 hrs (mode 2)	0.9 (total) 2 min (mode 2)
xx	xx	Longest Sortie (hrs)	1.0 hrs	14 min
Radius of Action2	110 nm	Max Range	500 ft	500 ft
xxxx	xxxx	Max Rng Ltd by ?	visual	visual
xx	xx	External Pilot Datalink range	500 ft	500 ft
xx	xx	Internal Pilot Datalink range	n/a	n/a
xx	xx	Payload Datalink range	500 ft	not demoed
Time to Station3	< 1 hr	Time to Max Range	not demoed	not demoed
Time on Station4	3 hr	Time @ 20nm loiter	not demoed	not demoed
Airspeed	0 to 150 kts	Max Airspeed (kts)	approx 30	approx 15
Maximum Operating Altitude	at least 13,000 ft MSL	Max Altitude (ft MSL)	130 AGL	30 AGL
Shipboard Launch/ Recovery Area	all air capable ships – 24’ Spot	Avg Distance from Intended Ldg Point(ft)	xx	not meas’d
Launch/ Recovery Wind-Over-Deck	up to at least 20 kts	Launch/Recovery Max Wind (kts)	9 / 10G15-20	3 / 6
Shipboard Launch/ Recovery Capability	Automatic with manual backup and waveoff capability; touch and go	xx	xx	xx
xx	xx	Auto T/O & Ldgs	0/0	0/0
xx	xx	Manual T/O & Ldgs	94 / 94	10 / 10
xx	xx	Touch & Go’s	84	9
xx	xx	Waveoffs Int/Unint	0/0	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 --numbers are at the field--	- 20 deg F to 120 deg F	Max/Min OAT (deg F)	97 / 69	79 / 73
--numbers are at the field--	xx	Max/Min HP (in HG)	29.20 / 29.05	29.11 / 29.07
Recover at TOGW --fuel dens of 6.5 lb/gal--	Yes	Recover at TOGW max TO/final LDG wt (lbs)	936 / 787	846 / 833
Launch/Recovery Accuracy	9.8 ft during launch/recovery;	TO/LDG accuracy	not calc’d	not calc’d
Spatial Location Accuracy	82 ft in-flight	NAV accuracy	not calc’d	not calc’d
xx	xx	TGT accuracy	n/a	n/a

PARAMETER	OBJECTIVE	METRIC	DEMONSTRATED
xx	xx	xx	Total	Last Flt
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	not demo	not demo
xx	xx	Automatic lost link	local loss demoed	local loss demoed
xx	xx	Automatic loiter	not demo	not demo
Payload Capacity	at least 200 lb; 2.5 kW power for payload; internal/external payload area of at least 2 ft3; day/night passive imagery sensor	Max Payload carried: Weight Power Cu	209 lb with EO/IR TAMAM POP	175 lb
Navigation Lights	comply with FAA regulations; capable of activation/deactivation from GCS at maximum range	Ext Lights control From GCS	not demoed	not demoed
Mission Reliability5	at least 75%	xx	xx	xx
xx	xx	Avg Flt Hrs/Sortie	0.08	xx
xx	xx	Takeoff Times: Planned vs. Actual	xx	0600-0800 vs 0620-0902
xx	xx	Sortie Completion % CANX – WX CANX – MAINT CANX – OPS	xx	100 0 0 0
xx	xx	Maint Actions/Flt Hr Maint Hrs/Flt Hr	xx	xx
xx	xx	Down Gripes	1	0
xx	xx	In-flight Aborts	5	0
xx	xx	Data Set Completion % Plan vs. Actual	YPG flights overall approx < 10%	xx

Notes:

(1) All performance objectives are specified under standard day conditions unless otherwise noted
(2) Air vehicle performance objective using line-of-sight datalink. Datalink range does not need to support demonstration of this objective.
(3) With 200 lb modular mission payload, flying in 25 kt headwind.
(4) With 200 lb modular mission payload.
(5) Mission Reliability is defined as the capability to complete a mission without a critical failure that would prevent the continuance of the mission. A successful mission includes mission planning, AV launch, AV proceeding to and loitering at the target area while performing planned or immediate tasks while simultaneously relaying MMP information to the supported commander, and AV recovery. Inclement weather, last minute changes in airspace coordination, and airspace interlopers will not count against mission success.

Flight Preparation

Air Views

Communication

Intelligence

References

Vigilante UAV

Specifications