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Unmanned Systems


PLASMA FALCON 1.11 / 9 - 14 kg MTOW

Electrofluidsystems has developed a novel and modular high-end mini flying wing UAV system (UAS) with agile flight performance, swarm capability and the ability for high-altitude flights through heated pitot tubes, active flow control and plasma anti/de-icing or electro-thermal heating film structures on the leading edges of the outer wings. The PLASMA FALCON 1.11 is made of an advanced laser-sintered, additive manufactured structure with a honeycomb core reinforced prepreg glass fiber composite hull.



The world's first plasma flow controlled flying wing UAS has an improved performance at flight conditions which usually would stop other drones from flying because of strong crosswind induced flow separation and instability effects. The vehicles durability to crosswinds was increased by more than 60% and is thus higher than for other mini flying wing UAV systems. 

The high cruise speed and integrated plasma flow contol system makes the PLASMA FALCON system superior to existing flying wing drones. The sophisticated sliding discharge plasma actuators and generators were developed by our founder Berkant Göksel during his doctoral study at TU Berlin.



The 12 - 14 kg PLASMA FALCON 1.11 has a payload volume of 4.12 - 6.12 kg (34.3% - 43.7%), a very powerful 6.5 or 10.0 kW brushless electric motor for vertical takeoff and climb capabilities, a 360° ultrazoom visual system with fisheye navigation cameras and a high-end gyro-stabilized, long-range EO/IR gimbal system. Almost all variants have a thrust-to-weight ratio higher than one. That enables a high-speed self-launch from vertical ramps with 60 to 90 degrees. An optional eVTOL update kit is also available for a low-speed vertical launch from horizontal position.

Almost all Plasma Falcon UAS variants can be also delivered from High-Altitude Platforms (HAPS) in drag reducing swarm formations of four to six vehicles to enable efficient gliding for many hours. A swarm of four vehicles with a three wingspan distance in diamond formation has about 50% less total drag. So all following vehicles have a longer range. By repeated change of the lead position the range of all vehicles can be extended. In a V-type formation with three vehicles the overall drag can be reduced by 35% followed by an echelon formation with two vehicles and 25% drag reduction.


A subclass of the PLASMA FALCON 1.11 is the rotor-blown flying wing tail-sitter 9 - 13 kg CORONABAT 1.11 SIRIUS which has the EO/IR camera in nose configuration. These high-speed eVTOL UAV systems are powered by two or four high-speed propellers and use all advantages of the so-called "rotor-blown-wing" effect. They can start and land vertically from small restricted areas with 1.5 x 1.5 meters and have fast level flight speeds.


It is not widely known that bats keep the world record for the fastest level flight speed in the animal world. Brazilian free-tailed bats can reach 100 mph (160 km/h) in level flight. And this makes them faster than any bird on earth. 

Bird-hunting peregrine falcons are the masters or titans of the sky. They just kick their preys out of the sky with a slashing blow from their powerful feets and can reach speeds of up to 242 mph (389 km/h) when diving but are much slower in level or horizontal flight. The peregrine falcons can be outflown by pigeons which can reach speeds of up to 92 mph (148 km/h) in level flight.

Today, most of our mini and even small tactical UAVs are much slower than pigeons. So we need a paradigm shift and have to apply new flight control techniques and advanced aircraft designs. Bats and birds can flap and morph their wings. We cannot do so easily. And when we do, our drones are still slow flyers. But what we can already do is active flow control by flapping plasma fields.

There are four pre-serial prototypes for the PLASMA FALCON class. The 12.0 kg PLASMA FALCON 1.11 SIRIUS INTELLIGENCE with 4.12 kg (34.3%) payload volume has a maximum endurance of 107 minutes and a maximum range of 369 km at 207 km/h. The 14 kg version with a payload volume of 5.95 kg (42.5%) has a maximum range of 353 km (219 miles) at 224 km/h. The 14 kg version with canards can even reach 500+ km/h with three 3500 W electric motors and 7x15 racing propellers.


The next bigger PLASMA FALCON 1.66 SIRIUS INTELLIGENCE with 20 (25) kg and the all weather, day and night, multi-mode, multi-domain SAR/MTI radar NanoSAR NSP-2 from IMSAR and a high-end Electro-Optical/Infrared (EO/IR) gimbal camera for a powerful sensor-fusion has a maximum endurance of 243 (178) minutes or 4.05 (2.96) hours and an extraordinary range of 723 (591) km at optimum 179 (200) km/h using off-the-shelf LiPos. Custom-made Li-ion batteries with 8C continous discharge and a power density of up to 382 Wh/kg enable a range of 800+ km.

A fuel cell module makes only sense with liquid hydrogen tanks as the energy density of a 6.0 kg system with two standardard two-liter hydrogen tanks (1376 Wh) is not sufficient with 229 Wh/kg. The new batteries have now energy densities of up to 321 Wh/kg for 10C or even 382 Wh/kg for 8C delivering 1813 Wh or 2300 Wh. So a more complex liquid hydrogen fuel cell system is more suitable for the next bigger Corona Bat variants with 2.22 and 3.33 m wingspan for extended range capabilities.

Electrofluidsystems selected the gyro-stabilized and ruggedized electro-optical-infrared (EO-IR) gimbal Merio Milvus 7HD-LP (270 g) camera to replace the previous NextVision NightHawk2 (250 g) for nose integration in the Corona Bat 1.11. The new camera with MIL-STD 461/810 certification has higher optical/IR resolutions and can withstand -40°C. The Merio Milvus 7HD-LP with optical camera (1920x1080, zoom x160), LWIR (1280x1025, zoom x8) and the NightHawk2-UZ with optical camera (1920x1080, zoom x40), LWIR (1280x720, zoom x4) are both available in the Plasma Falcon 1.11 with underbody gimbal integration.


Electrofluidsystems is once again setting new standards in drone technologies and also demonstrates for the first time the possible use of advanced satellite camera heads and ultrasonic sensors from automotive ADAS (Advanced Driver Assistance Systems).

These camera heads have good day and night vision and also work in the most adverse weather conditions with temperatures ranging from -40°C to 85°C.  The camera systems are certified according to IP67K and are therefore dustproof and waterproof. The heated lenses even have an IP69K rating and are extremely robust even at very high pressures and speeds.

Corona Bat 1.11 Sirius Intelligence with 9 kg is currently the most advanced high-tech mini reconnaissance, surveillance and intelligence (ISR) drone and the world's first mini UAV with heated high-end pitot probes certified for flights up to 33,000 ft. The air data computers of the high-tech probes from the Swiss company Simtec AG usually only fit into tactical drones with a wingspan of more than 2 meters of classic fuselage-wing designs. Corona Bat 1.11 has integrated two redundant high-end pitot probes with separate heating units that are approved for high-altitude flights and temperatures as low as -55°C.


TECHNICAL SPECIFICATIONS

Plasma Falcon Class with Modular Payload Volume

Plasma Falcon 1.11 with 12 kg

Sirius Interceptor

Sirius Intelligence Surveillance Reconnaissance (ISR)

Plasma Falcon 1.11 with 14 kg

Sirius Interceptor

Sirius Intelligence Surveillance Reconnaissance (ISR)

Plasma Falcon 1.11 Cnrd 14 kg

Sirius Interceptor

Sirius Intelligence Surveillance Reconnaissance (ISR)

Plasma Falcon 1.66 w. 20 - 25 kg

Sirius Interceptor

Sirius Intelligence Surveillance Reconnaissance (ISR)

Length

0.97 m

0.97 m

0.97 m

1.45 m

Wingspan

1.11 m

1.11 m

1.11 m

1.66 m

Maximum Static Thrust

137.2 N with 12x14

80 - 150 N with jet engine

137.2 N with 12x14

111.7 N w. 3x 7x15

148.9 N w. 4x 7x15

80 - 150 N with jet engine

137.2 N with 12x14

111.7 N w. 3x 7x15

148.9 N w. 4x 7x15

80 - 150 N with jet engine

226.4 N with 18x14

195.0 N with 16x16

161.2 N w. 135x14

137.2 N with 12x14

229.7 N w. 3x 10x14

148.9 N w. 4x 7x15

306.3 N w. 4x 10x14

322.4 N w. 2x 135x14

274.4 N w. 2x 12x14

150 - 300 N with jet

Maximum Take-off Weight

12.00 kg

117.7 N

14.00 kg

137.3 N

14.00 kg

137.3 N 

20.00 (25.00) kg

196.2 (245.3) N

Empty Weight

4.62 kg

1-Motor

4.62 (5.60) kg

1-Motor (3-Motors)

4.79 (5.19) kg

1-Motor (3-Motors)

6.00 kg

1-Motor

Battery Weight

3.26 kg

3.26 (3.26) kg

3.26 (3.26) kg

7.20 kg 

Optional Fuel Cell System (FSC) Weight

-

-

-

-

Basic Payload Weight in Wing Section

1.34 kg

2.15 (1.96) kg

1.98 (2.07) kg

1.60 + 0.70 (1.6+2.60) k

or 

1.60 + 0.70 (1.60 + 0.96 + 1.64 Auxiliary LiPo Battery 487 Wh or 622 Wh) kg

Extra Payload Weight in Fuselage Section

2.78 kg

or 

1.18 kg Auxiliary Battery 211 Wh + 1.60 kg

3.97 (3.18) kg

or

1.18 kg Auxiliary Battery 211 Wh + 2.12 (2.78) kg

3.97 (3.48) kg

or

1.18 kg Auxiliary Battery 211 Wh + 2.30 (2.78) kg

4.50 (2.60 Auxiliary LiPo Battery 492 Wh + 5.00) kg

or

2.60 (2.60) Auxiliary Battery 492 Wh + 1.90 NanoSAR (5.00) kg

Total Payload Weight and Volume

4.12 kg

34.3%

6.12 (5.14) kg

43.7 (36.7) %

5.95 (5.55) kg

42.5 (39.6) %

6.80 (11.8) kg

34.0%(47.2%)

Operating Temp. Range

-40° to +55°C

-40° to +55°C

-40° to +55°C

-40° to +55°C

Optimal Cruise Speed on Ground Level

207 km/h 

129 mph

226 km/h

141 mph

224 km/h

139 mph

179 (200) kmh

111 (124) mph

Maximum Cruise Speed

428 km/h or 266 mph with 12x14

435 km/h or 270 mph with 12x14

500+ km/h 311+ mph w. 3x 7x15

500+ km/h 311+ mph w. 4x 7x15

445 km/h or 276 mph with 12x14

500+ km/h 311+ mph w. 3x 7x15

500+ km/h 311+ mph w. 4x 7x15

326 (328) km/h or 202 (204) mph with 18x14

338 (340) km/h or 210 (211) mph with 16x16

375 (378) km/h or 233 (235) mph with 135x14

397 (401) km/h or 247 (249) mph with 12x14

423 (427) km/h or 263 (265) mph w. 3x 10x14

518 (524) km/h or 322 (326) mph w. 4x 7x15

Total Battery Energy

836 Wh w. 18.8 Ah, 12s, 10C

or

1048 Wh w. 23.6 Ah, 12s, 8C for Propulsion

+

118 Wh or 150 Wh for Plasma Systems, Pitot Tube Heating and Electronics

+

Optional 211 Wh or 405 Wh Auxiliary Battery in Fuselage for Mid-Range Intelligence, Surveillance & Rec.(ISR)

836 Wh w. 18.8 Ah, 12s, 10C

or

1048 Wh w. 23.6 Ah, 12s, 8C for Propulsion

+

118 Wh or 150 Wh for Plasma Systems, Pitot Tube Heating and Electronics

+

Optional 211 Wh or 405 Wh Auxiliary Battery in Fuselage for Mid-Range Intelligence, Surveillance & Rec.(ISR)

836 Wh w. 18.8 Ah, 12s, 10C

or

1048 Wh w. 23.6 Ah, 12s, 8C for Propulsion

+

118 Wh or 150 Wh for Plasma Systems, Pitot Tube Heating and Electronics

+

Optional 211 Wh or 405 Wh Auxiliary Battery in Fuselage for Mid-Range Intelligence, Surveillance & Rec.(ISR)

1813 Wh w. 35.0 Ah, 14s, 10C

or

2300 Wh w. 44.4 Ah, 14s, 8C for Propulsion

+

487 Wh or 622 Wh for Plasma Systems, Pitot Tube Heating,  Electronics & NanoSAR NSP-2

+

Optional 487 Wh or 622 Wh Auxiliary Battery in Wing for Long-Range ISR Mission Electronics

+

Optional 492 Wh or 944 Wh Auxiliary Battery in Fuselage for Long-Range ISR with NanoSAR NSP-2

Specific Energy

297 Wh/kg with 10C off-the-shelf battery

or

382 Wh/kg with 8C custom-made battery

297 Wh/kg with 10C off-the-shelf battery

or

382 Wh/kg with 8C custom-made battery

297 Wh/kg with 10C off-the-shelf battery

or

382 Wh/kg with 8C custom-made battery

321 Wh/kg with 10C off-the-shelf battery

or

382 Wh/kg with 8C custom-made battery

Cruise Power

529 W at 207 km/h with 12x14

603 W at 226 km/h with 12x14

568 W at 226 km/h w. 3x7x15

584 W at 226 km/h w. 4x7x15

648 W at 224 km/h with 12x14

624 W at 224 km/h w. 3x7x15

639 W at 224 km/h w. 4x7x15

699 (936) W at 179 (200) km/h with 18x14

646 (862) W at 179 (200) km/h with 16x16

621 (849) W at 179 (200) km/h with 135x14

608 (833) W at 179 (200) km/h with 12x14

700 (960) W at 179 (200) km/h w. 3x 10x14

601 (826) W at 179 (200) km/h w. 4x 7x15

VTOL Power

-

-

-

-

Vertical Takeoff Capability

Self-launch from 60° - 90° ramp with thrust for vertical lift for 147 km/h with 12x14

Self-launch from 60° - 90° ramp with thrust for vertical lift for 151 km/h with 12x14 or 3x 7x15

Self-launch from 60° - 90° ramp with thrust for vertical lift for 151 km/h with 12x14 or 3x 7x15

Self-launch from 60° - 75° ramp with thrust for vertical lift for 124 (142) km/h with 18x14 or 16x16

Endurance and Flight Range on Ground Level for Sirius Interceptor w. 90% Battery Energy

for 

Mid-Range Interception with Extra Payload in Fuselage

85.2 - 107 min and 294 - 369 km at 207 km/h with 12x14 and 836 - 1048 Wh w. 297 - 382 Wh/kg

16.1 - 20.2 min and 101 - 126 km at 375 km/h with 12x14 and 836 - 1048 Wh w. 297 - 382 Wh/kg

8.64 - 10.8 min and 62 - 77 km at 428 km/h w. 12x14 & 836 - 1048 Wh w. 297 - 382 Wh/kg

74.7 min and 281 km at 226 km/h with 12x14 and 836 Wh

79.3 min and 299 km at 226 km/h w. 3x 7x15 and 836 Wh

18.8 min and 117 km at 375 km/h with 12x14 and 836 Wh

20.2 min and 126 km at 375 km/h w. 3x 7x15 and 836 Wh

9.27 min and 67 km at 435 km/h with 12x14 and 836 Wh

69.5 min and 259 km at 224 km/h with 12x14 and 836 Wh

72.2 min and 270 km at 224 km/h w. 3x 7x15 and 836 Wh

22.8 min and 142 km at 375 km/h with 12x14 and 836 Wh

25.0 min and 156 km at 375 km/h w. 3x 7x15 and 836 Wh

10.5 min and 78 km at 445 km/h with 12x14 and 836 Wh

140 - 178 (105 - 133) min and 417 - 529 (348 - 442) km at 179 (200) km/h with 18x14 and 1813 - 2300 Wh

152 - 192 (114 - 144) min and 451 - 572 (378 - 480) km at 179 (200) km/h with 16x16 and 1813 - 2300 Wh

158 - 200 (115 - 146) min and 469 - 595 (384 - 487) km at 179 (200) km/h with 135x14 and 1813 - 2300 Wh

161 - 204 (117 - 149) min and 479 - 608 (391 - 496) km at 179 (200) km/h with 12x14 and 1813 - 2300 Wh

140 - 177 (102 - 129) min and 416 - 528 (340 - 431) km at 179 (200) km/h w. 3 x10x14 and 1813 - 2300 Wh

163 - 207 (118 - 150) min and 485 - 615 (395 - 501) km at 179 (200) km/h w. 4x 7x15 and 1813 - 2300 Wh

20.9 - 26.5 (21.4- 27.2) min and 114 - 144 (117 - 148) km at 326 (328) km/h with 18x14 and 1813 - 2300 Wh

23.8 - 30.2 (24.7- 31.4) min and 134 - 170 (140 - 178) km at 338 (340) km/h with 16x16 and 1813 - 2300 Wh

16.2 - 20.6 (16.6- 21.1) min and 101 - 129 (105 - 133) km at 375 (378) km/h w. 135x14 and 1813 - 2300 Wh

13.9 - 17.7 (14.5- 18.5) min and 092 - 117 (97 - 123) km at 397 (401) km/h with 12x14 and 1813 - 2300 Wh

10.2 - 12.9 (9.60- 12.2) min and 072 - 91 (68 - 87) km at 423 (427) km/h w. 3x 10x14 and 1813 - 2300 Wh

5.51 - 6.99 (5.03- 6.38) min and 48 - 60 (44 - 56) km at 518 (524) km/h with 4x 7x15 and 1813 - 2300 Wh

Endurance and Flight Range on Ground Level for Sirius Intelligence w. 90% Battery Energy

for

Long-Range ISR Mission with Extra Battery in Fuselage

or for 

Kinetic Long-Range Interception with Extra Battery in Fuselage

106 - 148 min and 368 - 511 km at 207 km/h with 12x14 and 1046- 1453 Wh w. 277 - 382 Wh/kg

20.2 - 28.0 min and 126 - 175 km at 375 km/h with 12x14 & 1046- 1453 Wh w. 277 - 382 Wh/kg

10.8 min & 77 km at 428 km/h w. 12x14 & 1046 Wh w. 277Wh/kg

93.6 min and 353 km at 226 km/h with 12x14 & 1048 Wh

99.3 min and 374 km at 226 km/h w. 3x 7x15 & 1048 Wh

23.5 min and 147 km at 375 km/h with 12x14 & 1048 Wh

25.3 min and 158 km at 375 km/h w. 3x 7x15 & 1048 Wh

11.6 min and 84 km at 435 km/h with 12x14 & 1048 Wh

87.1 min and 325 km at 224 km/h with 12x14 & 1048 Wh

90.5 min and 338 km at 224 km/h w. 3x 7x15 & 1048 Wh

28.5 min and 178 km at 375 km/h with 12x14 & 1048 Wh

28.5 min and 196 km at 375 km/h w. 3x 7x15 & 1048 Wh

13.1 min and 97 km at 445 km/h with 12x14 & 1048 Wh

216 (161) min and 642 (536) km at 179 (200) km/h with 18x14 & 2792 Wh

233 (175) min and 695 (582) km at 179 (200) km/h with 16x16 & 2792 Wh

243 (178) min and 723 (591) km at 179 (200) km/h with 135x14 & 2792 Wh

248 (181) min and 738 (603) km at 179 (200) km/h with 12x14 & 2792 Wh

215 (157) min and 641 (523) km at 179 (200) km/h w. 3x 10x14 & 2792 Wh

251 (182) min and 746 (608) km at 179 (200) km/h w. 4x 7x15 & 2792 Wh

32.2 (33.0) min and 175 (180) km at 326 (328) km/h with 18x14 & 2792 Wh

36.7 min (38.1) and 207 (216) km at 338 (340) km/h with 16x16 & 2792 Wh

25.0 min (25.6) and 156 (161) km at 375 (378) km/h w. 135x14 & 2792 Wh

21.5 min (22.3) and 142 (149) km at 397 (401) km/h with 12x14 & 2792 Wh

15.6 min (14.8) and 110 (105) km at 423 (427) km/h w. 3x 10x14 & 2792 Wh

Max. Flight Altitude

0 - 9,144 m (30,000 ft)

0 - 9,144 m (30,000 ft)

0 - 9,144 m (30,000 ft)

0 - 9,144 m (30,000 ft)

First Flight

2026 (prop)

2026 (prop)

2026 (prop)

2027 (prop)

2027 (jet)

Brushless Electric Motor with High-Pitch Propeller

1x 6500 W with 12x14

or

1x 10 kW with 12x14

1x 10 kW with 12x14

or

3x 4100 W with 7x15

or

4x 3500 W with 7x15

1x 10 kW with 12x14

or

3x 3500 W with 7x15

or

4x 3000 W with 7x15

1x 15 kW with 18x14, 16x16,  135x14 or 12x14

or

2x 6500 W with 135x14 or 12x14

or

3 x 5600 W w. 3x 10x14

or

4 x 6500 W with 7x15


Corona Bat 1.11 also features a globally unique plasma anti-de-icing system, powered by two RF piezo plasma and two HV-DC DC voltage generators. This enables the efficient ignition of sliding discharges, which run several centimeters along the leading edge and thus also contribute to active flow and direction control. The drone can thus be controlled at high speed even without rudder deflection when necessary. These are usually technologies used on very advanced hypersonic guided missiles.

Corona Bat 1.11 also includes an alternative, electro-thermal anti-de-icing system based on innovative heating film structures, which can replace the plasma actuator films on the leading edges of the outer wings. For this purpose, the plasma generators are replaced by two additional heating units. These are identical heaters that are also used for the high-end heated pitot probes.

The additional battery power with 118 Wh is also used to heat the 835 Wh motor battery when necessary. The new battery has an energy density of 297 Wh/kg or even 382 Wh/kg in custom-made configurations for the Plasma Falcon 1.11 and 320 to 382 Wh/kg for the next bigger Plasma Falcon 1.66. That enables an long-range flights at high cruise speeds going beyond what is available today with classical sailplane-type fuselage-wing configurations.


With PlasmaFalcon CoronaBat UAV systems Electrofluidsystems redefines the next generation of swarm-capable, highly maneurable, high-speed mini UAS for real-time surveillance assisted by an AES-256 encrypted dual video telemetry system and the Mesh Rider Dual Radio from Doodle Labs with a handheld high-end GCS controller based on the ruggedized and robust Panasonic FZ-S1. 

The CoronaBat UAV system has two onboard DroneCore2 modules from Airvolute with each having a powerful 1024-core NVIDIA AI computer Jetson Orin NX 16 GB. The main autopilot is based on the US-made hardware Cube Blue with ADS-B antenna from CubePilot with two additional Cube Blue units on the DroneCore2 modules for triple autopilot redundancy.

The Cube Blue is identical to the Cube Orange with the main difference being that it is manufactured in the USA. The Cube Blue is designed for operators that require a US-made flight controller option, such as government or military operators.

One of the two AI-computers can be used for the SWARMPILOT with four navigation cameras and the optional blockchain platform SWARMCHAIN for more secure communication and coordination of swarming unmanned aerial vehicles (SUAVs).



Electrofluidsystems Plasma Falcon / CoronaBat 1.11 with its huge payload bay is also a 1:20 (Plasma Falcon / CoronaBat 22.2) and 1:27 (Plasma Falcon / CoronaBat 30.0) scale model for a new generation of flying wing cargo aircrafts with ultra-efficient 550 PS RED AIRCRAFT A03 Diesel engines which can be also modified to work with hydrogen fuel using plasma combustion systems. The standard A03 high-altitude engine with 500 PS can provides 375 PS at 35,000 ft (10,668 m). 

At 45,000 ft (13,716 m) altitude, the CoronaBat 22.2 needs 460 PS to fly with a speed of 400 km/h. Otto Aviation uses advanced multi-stage turbo chargers and heat exchangers in the Celera 500L to compensate the dramatic power drop at altitudes from 10,668 m to 15,000 m where the standard engine only provides 170 PS (see for the US patent 9,446,835 B2 from William Otto).


The payload bay of both versions can be easily accessed through the front door and in case of the bigger 8,600 kg variant with 30.0 m span can carry different standard cargo containers like LD-1, LD-2 or LD-3 and also different bulk cargo packages on 463L master pallets (HCU-6/E) as shown in the concept visualization above. The CoronaBat 30.0 will have a rear clamshell door to release airdrop pallets.

Electrofluidsystems optionally piloted flying wing cargo UAV CoronaBat 22.2 can also fly with sustainable aviation fuel-powered GE Catalyst turboprop engines and reach a constant cruise speed of 507 km/h (272 kts) at 13,176 m (45,000 ft) altitude. The same engine can also power the upscaled CoronaBat 30.0. 


PLASMA RAY 1.11 / 11 - 18 kg MTOW

The stingray-shaped PLASMA RAY is an electric VTOL (eVTOL) UAV with 1.11 m wingspan and a maximum take-off weight (MTOW) of 11 - 18 kg. The deliverable payload weight is 4.0 - 8.2 kg. The near-term vision is to extend the product family to 1.66 m - 3.33 m wingspan until 2027. The AI swarm controller (SWARMPILOT) will enable coordinated flights in half-diamond and full diamond-shaped formations, reducing drag and increasing range by up to 50%.

The first pre-serial prototypes of the PlasmaRay with 1.11 m wingspan will use 12 electric ducted fan (EDF) jets from Schuebeler (DS-30-AXI HDS) and three kind of different brushless electric motors. There will be three basic versions for the PlasmaRay:


1. PlasmaRay 1.11 will use four LiPo batteries with each 426 Wh (23 Ah, 5s) with a specific energy of 205 Wh/kg to power all of the 12 EDF jets for horizontal flight and vertical take-off and landing (VTOL). The total energy storage is 1,704 Wh for a constant specific energy of 205 Wh/kg. A first low-cost prototype will be built using modern 3D-printers. The pre-serial prototypes will have a state-of-the-art prepreg structure.

2. H2PlasmaRay 1.11 will use two 800 W fuel cell power modules from Intelligent Energy with four liters of hydrogen (1,412 Wh) stored in two 300 bar tanks with each 2 liters to power two of the 12 EDF jets for horizontal flight. The specific energy for the overall H2-system with fuel cells, hybrid batteries, hydrogen regulators and tanks is 249 Wh/kg. Two additional LiPo batteries with each 204 Wh (11 Ah, 5s) and a specific energy of 192 Wh/kg will provide power for 10 of the 12 EDF jets for 2 min VTOL. The total energy storage is 1,820 Wh for an average specific energy of 233 Wh/kg.

3. LH2PlasmaRay 1.11 will also use two 800 W fuel cell power modules from Intelligent Energy with three liters of liquid hydrogen (3,345 Wh) stored in two cryogenic tanks. The specific energy for the liquid H2-system with all components is 569 Wh/kg. Two additional LiPo batteries with each 204 Wh (11 Ah, 5s) and a specific energy of 192 Wh/kg will be again available for 2 min VTOL. The total energy storage is 3,753 Wh for an average specific energy of 475 Wh/kg and is thus two times higher than for the H2PlasmaRay 1.11.

The specific energy for the H2-system is getting much better for the next bigger scale models of the air taxi concept shown below. The H2PlasmaRay 1.66 for instance as a 1:4 scale model will use two 2.4 kW fuel cell power modules from Intelligent Energy. Ten of these 4.8 kW fuel cell pairs (2.4 kW + 2.4 kW) will be used in the air taxi H2PlasmaRay 6.66 which stands for regional air mobility and sustainability as hydrogen is the future for a zero-carbon aviation.
 
 

TECHNICAL SPECIFICATIONS


PLASMARAY 1.11

H2PLASMARAY 1.11

LH2PLASMARAY 1.11

Length

0.78 m

0.78 m

0.78 m

Wingspan

1.11 m

1.11 m

1.11 

Maximum Take-off Weight

17.8 kg

17.8 kg

17.8 kg

Empty Weight

5.4 kg

5.8 kg

5.8 kg

Battery Weight

8.4 / 6.3 / 4.2 kg

(4 / 3 / 2 x ...)

2.2 kg

(2 x ....)

2.2 kg 

(2 x ...)

Fuel Cell System (FCS) Weight

-

5.7 / 4.3 kg

(2 x 800 W FCS from IE plus 4 liters H2)

5.7 / 4.3 kg

(2 x 800 W FCS from IE plus 3.0 / 1.5 liters LH2

Payload & Package Weight

4.0 / 6.1 / 8.2 kg

4.1 / 5.5 kg

4.1 / 5.5 kg

Cruise Speed

233 - 266 km/h

187 - 218 km/h

187 - 218 km/h

Maximum Cruise Speed

300+ km/h

300+ km/h

300+ km/h

Flight Range

150+ / 110+ / 70+ km

150+ / 70+ km

340+ / 170+ km

Endurance

40+ / 30+ / 20+ min  

(with 1 min VTOL)

50+ / 25+ min  

(with 2 min VTOL)

110+ / 55+ min  

(with 2 min VTOL)

Flight Altitude

0 - 5,500 m

0 - 5,500 m 

0 - 5,500 m

Total Energy

1,704 / 1,278 / 852 Wh

1,820 / 1,114 Wh

3,753 / 2,080 Wh

Specific Energy

... Wh/kg  (LiPo)

... Wh/kg  (H2 + LiPo)

... Wh/kg  (LH2 + LiPo)

VTOL Power

11,790 W

11,790 W

11,790 W

Cruise Power

2,000 W

1,600 W

1,600 W

First Flight:

2027

2027

2027

Electric Ducted Fan (EDF) Motor

5+5+2 Schübeler DS-30-AXI HDS

5+5+2 Schübeler DS-30-AXI HDS

5+5+2 Schübeler DS-30-AXI HDS



PLASMARAY 1.11 and H2PLASMARAY 1.11 UAV systems are plasma flow controlled, swarm capable eVTOL demonstrators for a new class of hydrogen fuel-cell powered, hyperfast air taxis with 6.66 m (900 - 1,000 kg), 8.88 m (1,850 - 2,000 kg), 11.1 (3,000 kg), 13.3 m (5,700 kg), 18.0 m (10,500 kg) and 19.9 m (13,500 kg) wingspan.

Electrofluidsystems also works on new heavy cargo BWB aircraft concepts based on the PlasmaRay design. A 4,700 kg PlasmaRay system would use 36 Vasyfan VF-570 lift fans (with each having 150 kg static thrust).


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