World Wide Vertical Take Off & Landing UAV (2003.11.22)
Type
Prime Manu.
  UAV Designation
Production status
Operational status 
Power plants
Dimensions (m) 
Wieghts (kg) 
Performance 
 
Comments
 Development Production Operation  Purpose Mission payload Launch, take-off type Recovery, landing type Min ground crews need System composite Datalink, comm frequency Engine
Propulsion
Wing span Wing area (§³) Length overall Height overall Wheel track Wheel base Wing aspect ratio Fuselage max width Weight empty Max fuel weight
Max payload
Max T-O/launch weight Max level speed (kt) Cruising speed (kt) Loiter speed (kt) Stall speed (kt) Service ceiling (ft) Max rate of climb (ft/min) Max range (nm) Max endurance (h)
Tilt rotor

Bell Textron

USA
Eagle Eye
Complete Underway   Tiltrotor UAV   Vertical or short take-off. Vertical landing.       ONe 450 shp  Rolls-Royce 250-C20R turboshaft. Two three-blade proprotors. prop dia= 2.49 m 4.63    5.46 1.74           166.6 liters 136 1,020           20,000 200 8.0  
1986 ~         GCS MPEG 46Mbyte  Real Flight MPEG 47Mbyte  Briefing PPT 7Mbyte                                            
Tilt rotor

Daedalus

USA
STF-9A
Complete                   Rotary   Span =                                 20,000 250 5.0 Tilt Wing
 

KARI SUDEC

South Korea
Smart UAV
 Underway     Experimental VTOL UAV.   Vertical take-off. Vertical, short or conventional landing.                                                 3.0  
2002-                                                              

Rotor Wing

CRW

Boeing

USA
Dragonfly Canard Rotor/Wing
Underway     VTOL reconnaissance and surveillance.   Vertical take-off. Vertical landing.       One 700 lb st Williams F112 turbofan.   Rotor = 3.66   5.26  1.60            272.5 91 600 >375         10,000 980 3.0  
1998~, First flight is scheduled for 2001.                                                              
Tail sitter

Boeing

USA
Heliwing
Underway      Prototype VLAR UAV.   Vertical take-off and then accelerates forward. Reduce speed and nose pitch up and then vertical landing.       One 240 shp Williams International WTS124 turboshaft. A pair of large-diameter (dia=2.13m), contrarotating prop-rotors. 5.18   2.44 2.29            181 90.5  658 80-180 (60 tested) (airplane mone)/ 0-100 (20) (helicopter mode)        3,500/ 2,000 20,000/ 15,000    5/ 3  
First flight test on 26 April 1995.                                                              
Prime Manu.
  UAV Designation
Production status
Operational status 
Power plants
Dimensions (m) 
Wieghts (kg) 
Performance 
 
Comments
 Development Production Operation  Purpose Mission payload Launch, take-off type Recovery, landing type Min ground crews need System composite Datalink, comm frequency Engine
Propulsion
Wing span Wing area (§³) Length overall Height overall Wheel track Wheel base Wing aspect ratio Fuselage max width Weight empty Max fuel weight
Max payload
Max T-O/launch weight Max level speed (kt) Cruising speed (kt) Loiter speed (kt) Stall speed (kt) Service ceiling (ft) Max rate of climb (ft/min) Max range (nm) Max endurance (h)
Free wing

Freewing

USA

Scorpion Model 60-25 / Model 100-50 / Manta / Marvel
Underway     Experimental multirole UAV.   Wheeled take-off, rail or RATO launch. Wheeled landing.       One 12 hp piston engine./ 52 hp Totax 447 two-cylinder in-line engine.   3.0/ 4.90   2.0/ 3.59           22.7 / 115  15.1 liters/ 45.4 liters 11.3 / 25.9 174 108 / 150   20 / 55   24,000 5,000 / 15,000 108 4.5 / 3.0 Tilt Wing; with Scaled Composites
                                                                 
   
Prime Manu.
UAV Designation
Production status  
Operational status          
Power plants
Dimensions (m)            
  Wieghts (kg)  
        Performance      
Comments
 Development
Production
Operation
 Purpose
Mission payload
Launch, take-off type
Recovery, landing type
Min ground crews need
System composite
Datalink, comm frequency
Engine
Propulsion
Wing span
Wing area (§³)
Length overall
Height overall
Wheel track
Wheel base
Wing aspect ratio
Fuselage max width
Weight empty
Max fuel weight
Max Payload
Max T-O/launch weight
Max level speed (kt)
Cruising speed (kt)
Loiter speed (kt)
Stall speed (kt)
Service Ceiling (ft)
Max rate of climb (ft/min)
Range (nm)
Max Endurance (h)
Coaxial Rotor

Kamov

Russia

Ka-137

Underway

 

 

 Multipurpose helicopter UAV.

 SKOL aerial reconnaissance system for the day/night surveillance, real-time detection and localisation of wheeled vehicle ground targets.

Conventional helicopter take off.

Conventional helicopter landing.

 

 SKOL system, Ka-137S air vehicle, a PPU-137 mobile GCS, a transportation vehicle/launch platform motorcar, and a crew of five.

 

One 65 hp Hirth 2706-R05 two-cylinder two-stroke in-line engine.

 

Rotor dia: 5.30

 

 

 2.325

1.74

 1.965

 

appx : 1.30

 

 

80

280

95

 78

 

 

9,840

 

At least 10.8

4.0

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Coaxial Rotor

BUAA

China

M-22
Complete(?)     Small RPH   Conventional helicopter take-off Conventional helicopter landing         Twin co-axial, two-blade contrarotationg rotors                     10 50               1.5 Similar configuration to Kamov Ka-137
First flight October 2000.                                                                
Coaxial Rotor

 

Bombardier

Canada

CL-227 Sentinel (Army)

Complete

Complete

Deployed

Land-base VTOL multi-application

FLIR, Day TV, comm relay, electronic jammer, decoys, snobuoy dispensers, mine detector, ECM, radars and laser designators

Conventional  VTO

Sierra Nevada UCARS system.

 

GCS, MCPS

 

One 51.5 shp Williams WTS34-16 turboshaft (- Pase3) Now one 60 shp Williams WTS125 heavy-fuel turboshaft.

Rotor

Rotor Dia 2.80

 

Body Dia 0.64

1.64

 

 

 

 

111

Multi fuel diesel, JP-5, Jet-A, heavy fuel.

54 kg

45

227

77

 

 

 

9,840

900

32.4

3.5

 

First flight on 25 August 1978.

US Army, US Navy(1993),

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

CL-227 Sea Sentinel (Navy, Marine)

Complete

Complete

Deployed

Configured for shipborne applications

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

US Marine (MAVUS)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

CL-227 Puma (TUAV)

Comple.te

Complete

Deployed

Modified version for TUAV competition

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

First flight in March 1996

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

CL-327 Guardian  
Complete Underway Deployed Multi-role VTOL surveillance

EO/IR, comm relay, SAR, active ECM.

Conventional  VTO

Sierra Nevada UCARS system.

2 for setup and operate. downsized GCS, TCS G/H-band One 125 shp Williams WTS117-5 heavy-fuel turboshaft. Rotor Rotor dia 4.0

 

0.76 1.84         150 150 kg 110 235 kg (std) 350 kg (max) 85 75 50   18,000 1,500 54 6.2 No Tail; Counter-Rotating Rotors
First flight on 30 November, 1997.

           
CL-427 (TUAV)
Complete Underway   // //

Conventional  VTO

 Sierra Nevada UCARS system. // // // One 125 shp Williams WTS117-5 heavy-fuel turboshaft.   Rotor = 13

 

   2.12         135 160 kg 150 300 kg (std) 340 kg (max) 120       18,000 1,400 108 8.0 No Tail; Counter-Rotating Rotors

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Coaxial Rotor

EADS Dornier

Germany
Seamos
Complete   2006 - 2008 Maritime recommaissance and target acquisition VTOL UAV. Multimode sea surveillance radar and an EO/IR sensor. Conventional helicopter take-off (automatic). Conventional helicopter landing (automatic).       One 450 shp Rolls-Royce  250-C20R/ 1S turboshaft.   Dia: 6.10   2.89  2.50       1.50    350 180 1,125 90 55-80     12,000 980 110 4.7 No Tail; Counter-Rotating Rotors
                                                                 
Coaxial Rotor

Gyrodyne

USA

QH-50
                                                                 
                                                                 
Prime Manu.
  UAV Designation
Production status
Operational status 
Power plants
Dimensions (m) 
Wieghts (kg) 
Performance 
 
Comments
 Development Production Operation  Purpose Mission payload Launch, take-off type Recovery, landing type Min ground crews need System composite Datalink, comm frequency Engine
Propulsion
Wing span Wing area (§³) Length overall Height overall Wheel track Wheel base Wing aspect ratio Fuselage max width Weight empty Max fuel weight
Max payload
Max T-O/launch weight Max level speed (kt) Cruising speed (kt) Loiter speed (kt) Stall speed (kt) Service ceiling (ft) Max rate of climb (ft/min) Max range (nm) Max endurance (h)
Twin rotor

Kaman

USA
K-MAX
 Underway Underway   Optionally piloted helicopter    Vertical take-off. Vertical landing.       One 1,350 shp Honeywell T-53-17A-1.   Rotor dia= 14.73 disc 340.9 15.83 4.14         2,334

865 liters/

699

   2,948 100       4,575   300    
                                                                 
Ducted Fan

Aurora

USA
Underway     VTOL UAV   Vertical take-off. Vertical landing. Parechute for emergency.   GCS                                                
                                                                 
Ducted Fan

AD & D

Israel
Hornet
 Complete Underway   VTOL UAV   Vertical take-off. Vertical landing. Parechute for emergency.   GCS   Four 22 hp Hirth F33-15A single-cylinder piston engines.   Dia 2.20     2.30         145     260 40       IGE 8,000; OGE 5,000     30 min  
                                                                 
Ducted Fan

Allied Aerospace

USA
LADF (Lift- Augmented Ducted Fan)
Underway      Small VTOL battlefield tactical UAV.   Vertical take-off from ground or ship's deck, then pitching ovwr into horizontal flight with lift provided by duct and optional wings.  Vertical landing on ground or ship's deck.                                                    
                                            363                  
Ducted Fan

Sikorsky

USA
Cypher¥°
Complete  Underway Available  Close-range VTOL UAV.  TV camera. Vertical take-off. Vertical landing; parachute emergency recovery system.       One 52 hp UEL AR 801 rotary engine. Two four-blade coaxial. Rotor dia= 1.20   Overall dia=1.89   Max body depth= 0.55         75 22.5   113     70     8,000   16.3 2.5  
                                                               
Cyhper¥± (Dragon Warrior)
Underway      Close-range VTOL tactical UAV.  Daylight TV camera, FLIR and laser designator. Vertical take-off. Vertical landing; parachute emergency recovery system.       Two Herbrandson piston engines. Two four-blade coaxial. 3.05                   11.3- 15.9 109 125           100 2.0  
                     Rotor dia =0.99                                          
Prime Manu.
  UAV Designation
Production status
Operational status 
Power plants
Dimensions (m) 
Wieghts (kg) 
Performance 
 
Comments
 Development Production Operation  Purpose Mission payload Launch, take-off type Recovery, landing type Min ground crews need System composite Datalink, comm frequency Engine
Propulsion
Wing span Wing area (§³) Length overall Height overall Wheel track Wheel base Wing aspect ratio Fuselage max width Weight empty Max fuel weight
Max payload
Max T-O/launch weight Max level speed (kt) Cruising speed (kt) Loiter speed (kt) Stall speed (kt) Service ceiling (ft) Max rate of climb (ft/min) Max range (nm) Max endurance (h)