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ZL Series EASA Type Certificate Certified Liquid-Cooled Piston Aero Engine with Dual Fuel Options
Product Details
| Displacement: | 2.0 L / 2000 Cc | Bore × Stroke: | 86 Mm × 86 Mm |
|---|---|---|---|
| Compression Ratio: | 9.5:1 (Gasoline G Version) / 17.5:1 (Heavy Fuel D Version) | Rated Take-off Power: | 147 KW / 200 HP @ 4000 Engine RPM |
| Max Continuous Power: | 122 KW / 166 HP @ 3600 Engine RPM | Propeller Reduction Ratio: | 2.85:1 |
| Max Propeller RPM: | 1400 RPM | Dry Weight: | 51 Kg (112.4 Lbs) |
| Overall Dimension: | 640 Mm × 480 Mm × 460 Mm | Specific Fuel Consumption: | Gasoline: 275 G/kW*h; Heavy Fuel: 205 G/kW*h |
Product Description
ZL Series Inline Liquid-Cooled Piston Aero Engines
Full English Technical Datasheet (Detailed Version, EASA TC Marked for ZL-200)
Three core models: ZL-200 (4-cyl, EASA Type Certificate Certified), ZL-400 (6-cyl, EASA TC Under Certification), ZL-600 (8-cyl, EASA TC In Planning). Dual fuel options: Gasoline Spark Ignition (G) / Heavy Fuel Compression Ignition (D, Jet-A / Diesel).
Complete Technical Specifications
ZL-200 Inline 4-Cylinder 200HP (EASA TC Fully Certified)
| Item | Full Technical Data |
|---|---|
| General Layout | Straight 4-cylinder, 4-stroke, liquid-cooled, single turbocharger, geared propeller drive, all-aluminum integrated cylinder block & head |
| Displacement | 2.0 L / 2000 cc |
| Bore * Stroke | 86 mm * 86 mm |
| Compression Ratio | 9.5:1 (Gasoline G Version) / 17.5:1 (Heavy Fuel D Version) |
| Rated Take-off Power (5-min limit) | 147 kW / 200 HP @ 4000 engine RPM |
| Max Continuous Cruise Power | 122 kW / 166 HP @ 3600 engine RPM |
| Propeller Reduction Gear Ratio | 2.85:1 |
| Max Propeller RPM | 1400 RPM |
| Dry Weight (w/o fluids & prop) | 51 kg (112.4 lbs), 12-16 kg lighter than equivalent opposed piston engines |
| Overall Outer Dimension (L*W*H) | 640 mm * 480 mm * 460 mm |
| TBO (Time Between Overhaul) | 2000 flight hours or 12 years, whichever comes first |
| Certified Service Ceiling | 5,500 m (Gasoline G) / 6,500 m (Heavy Fuel D) |
| Fuel Type & Ignition System | • G Version: 95/98# aviation gasoline, spark ignition, multi-point EFI • D Version: RP-3 Jet-A / EN 590 0# diesel, high-pressure common rail compression ignition |
| Specific Fuel Consumption | • Gasoline: 275 g/kW*h • Heavy Fuel: 205 g/kW*h (30% fuel saving vs gasoline variant) |
| Control System | Dual-channel redundant FADEC Full Authority Digital Engine Control, single-lever power management, built-in real-time fault diagnosis & flight data recording |
| Lubrication System | Dry sump forced circulation lubrication, synthetic aviation oil compatible |
| Cooling System | Closed-loop liquid cooling with electronic thermostat, stable heat dissipation under high altitude & high load |
| Electrical Output | 28V DC dual alternator, total 1200W power supply |
| Environmental Adaptability | Operating ambient temp: -30℃ ~ +55℃; integrated anti-corrosion coating for coastal high-salt air; preheating system for heavy fuel cold start |
| Airworthiness Certification | Official EASA Type Certificate (TC) issued, fully compliant with CS-E engine standards; also under CCAR-22 certification for domestic civil aviation |
ZL-400 Inline 6-Cylinder 400HP (EASA TC Under Certification)
| Item | Full Technical Data |
|---|---|
| General Layout | Straight 6-cylinder, 4-stroke, liquid-cooled, twin parallel turbochargers, heavy-duty reduction gearbox |
| Displacement | 3.0 L / 3000 cc |
| Bore * Stroke | 86 mm * 86 mm |
| Compression Ratio | 9.8:1 (G) / 18:1 (D) |
| Take-off Power (5-min rated) | 294 kW / 400 HP @ 3800 engine RPM |
| Continuous Cruise Power | 245 kW / 334 HP @ 3400 engine RPM |
| Propeller Gear Ratio | 3.0:1 |
| Max Propeller RPM | 1267 RPM |
| Dry Weight | 98 kg (215.6 lbs) |
| Overall Dimension (L*W*H) | 760 mm * 530 mm * 510 mm |
| TBO | 1800 flight hours or 10 years |
| Service Ceiling | 6,000 m (Gasoline) / 7,000 m (Heavy Fuel) |
| Fuel Compatibility | Dual modular fuel kits switchable between aviation gasoline & Jet-A/diesel |
| Specific Fuel Consumption | Gasoline: 282 g/kW*h; Heavy Fuel: 210 g/kW*h |
| Control Architecture | Dual redundant FADEC, single lever throttle, automatic power derating for fault protection |
| Electrical Supply | Dual 28V alternators, total 1800W output |
| Airworthiness Progress | EASA TC certification procedures launched, bench & flight test completed; expected full certification by late 2027; only for unmanned industrial platforms for overseas delivery currently |
ZL-600 Inline 8-Cylinder 600HP (EASA TC In Long-Term Planning)
| Item | Full Technical Data |
|---|---|
| General Layout | Straight 8-cylinder inline, 4-stroke liquid-cooled, two-stage serial turbocharging, high-torque reinforced gearbox |
| Displacement | 4.0 L / 4000 cc |
| Bore * Stroke | 86 mm * 86 mm |
| Compression Ratio | 10.0:1 (G) / 18.5:1 (D) |
| Take-off Power | 441 kW / 600 HP @ 3600 engine RPM |
| Max Continuous Power | 370 kW / 503 HP @ 3200 engine RPM |
| Propeller Reduction Ratio | 3.2:1 |
| Max Propeller RPM | 1125 RPM |
| Dry Weight | 142 kg (312.4 lbs) |
| Overall Dimension (L*W*H) | 880 mm * 570 mm * 540 mm |
| TBO | 1600 flight hours or 10 years |
| Max Service Ceiling (Heavy Fuel Optimized) | 7,500 m |
| Fuel Configuration | Heavy fuel (Jet-A/Diesel) as primary factory option; gasoline variant optional for light manned aircraft |
| Specific Fuel Consumption | Gasoline: 290 g/kW*h; Heavy Fuel: 218 g/kW*h |
| Control System | Triple-redundant FADEC with multi-sensor fault isolation, auto emergency landing power control logic |
| Electrical Output | 2*28V high-power alternators, total 2400W |
| Airworthiness Status | EASA TC certification in long-term R&D roadmap; mass production for ton-class heavy-lift UAVs only, no overseas manned aircraft export eligibility for now |
Universal Core Competitive Advantages
- Outstanding Power-to-Weight Ratio
All-aluminum monoblock inline liquid-cooled design delivers 10-18 kg lighter dry weight than same-power horizontally opposed engines, with compact footprint to fit narrow fuselage & unmanned helicopter nacelles. Inline layout generates lower vibration during hover & long endurance cruise, improving airframe stability. - Modular Dual-Fuel Architecture
One base engine structure supports quick switch between spark ignition gasoline kit and compression ignition heavy fuel kit to match diverse operation scenarios. Gasoline for low-altitude sightseeing; heavy fuel for plateau, offshore, firefighting & Defense missions with universal Jet-A supply. - ZL-200 EASA Type Certificate Global Compliance (Unique Selling Point)
ZL-200 holds official EASA TC complying with EU CS-E civil aviation standards, directly eligible for manned aircraft export to EU, UK, Southeast Asia, Australia and Middle East without extra regulatory exemptions. ZL-400 / ZL-600 cannot be installed on overseas manned aircraft due to incomplete EASA certification. - 95% Domestic Localization & Stable Supply Chain
Core crankshaft, cylinder, turbocharger, FADEC ECU are fully mass-produced domestically, eliminating overseas component supply disruption risks. Annual production capacity reaches 2,000 units in 2026, with order backlog covered through 2027. - Multi-Redundant FADEC Digital Control System
Dual/triple-channel independent ECUs with cross-monitoring; real-time engine condition monitoring, automatic fault isolation and smooth power derating to support controlled forced landing. All flight operational data can be stored, exported and analyzed for maintenance scheduling. - Full-Spectrum Harsh Environment Reinforcement
Liquid cooling avoids airflow limitation at high altitude; heavy fuel variants equip low-temperature preheating modules. Entire engine assembly adopts salt-spray anti-corrosion coating to adapt coastal marine, mountain wildfire and high-plateau thin-air environments. - Low Lifecycle Operation & Maintenance Cost
Modular single-cylinder assembly design; defective single cylinder can be replaced separately without full engine disassembly. Standard universal aviation lubricants, filters and spare parts are widely available at domestic general aviation service stations, no exclusive imported consumables required.
Gasoline vs Heavy Fuel Version Comparison
Gasoline Spark Ignition (Suffix G)
- Certified Fuels: Lead-free aviation gasoline 95# / 98#
- Pros: Lower unit procurement cost, fast cold start, smooth low-altitude noise signature, simpler ground maintenance workflow
- Cons: Low flash point raises storage & transportation safety risks; prone to vapor lock at high altitude; higher specific fuel consumption shortens flight endurance
- Best Fit: Light sport aircraft, flight trainers, small sightseeing fixed wings, short-range survey UAVs (ZL-200 G is the only EASA-certified variant for global manned aircraft export)
Heavy Fuel Compression Ignition (Suffix D, Mainstream for Industrial Platforms)
- Certified Fuels: Jet-A / RP-3 aviation kerosene, EN 590 road diesel, Defense JP-8
- Pros: High flash point for safe storage on vessels, wildfire sites & border outposts; 30% lower fuel consumption extends flight duration by ~25%; no vapor lock at extreme altitude; shared fuel supply with ground vehicles & marine equipment
- Cons: Slightly higher initial engine purchase cost; preheating required for cold start below -15℃
- Best Fit: Heavy-lift unmanned helicopters, long-endurance cargo VTOLs, forest fire suppression UAVs, plateau border supply drones, ship-borne maritime search & rescue platforms
Target Application Scenarios by Model
ZL-200 (4-Cyl, EASA TC Certified - Global Manned Export Preferred)
- Manned General Aviation: Light sport aircraft, glider tow planes, flight training trainers, low-altitude sightseeing aircraft (EU & global export supported by EASA certificate)
- Medium Industrial UAVs: Large agricultural crop sprayers, long-distance power line inspection fixed wings, small fire reconnaissance UAVs, short-haul cargo VTOLs
- Special Equipment: Power generation unit for tethered firefighting UAVs, compact ground-effect ship propulsion
ZL-400 (6-Cyl, EASA TC Under Certification - Overseas UAV Only)
- Medium unmanned helicopters, mid-size cargo vertical take-off & landing aircraft
- High-load agricultural spraying drones, river & coastal offshore patrol UAV fleets
- Domestic composite light manned aircraft, emergency rescue reconnaissance platforms
- Port security monitoring unmanned systems (export limited to unmanned industrial use only)
ZL-600 (8-Cyl, No EASA TC - Heavy-Duty Industrial Exclusive)
- Ton-class coaxial heavy-lift unmanned helicopters (matching VT-1000 heavy-lift UAV platform)
- Large cargo delivery drones, plateau remote border material airdrop systems
- High-capacity forest fire suppression UAVs, mountain power tower component sling-lifting drones
- Naval ship-borne vertical replenishment, long-endurance maritime search & rescue systems (domestic industrial projects priority)
Limitations & Restrictions
- Inline longitudinal layout occupies longer installation space than horizontally opposed engines, incompatible with ultra-compact micro UAV nacelles;
- ZL-600 high-displacement eight-cylinder model has larger dry weight, not suitable for UAVs under 500 kg MTOW;
- Heavy fuel compression ignition variants need preheating procedure under -15℃ ambient temperature, cold start time longer than gasoline spark ignition models;
- ZL-400 & ZL-600 lack valid EASA Type Certificate, cannot be installed on manned aircraft for overseas civil aviation export; only industrial unmanned projects are acceptable for cross-border delivery.
Product Highlights
ZL Series Inline Liquid-Cooled Piston Aero Engines: ZL-200 (4-cyl, EASA TC Certified), ZL-400 (6-cyl, EASA TC Under Certification), ZL-600 (8-cyl, EASA TC In Planning). Dual fuel options: Gasoline Spark Ignition / Heavy Fuel Compression Ignition. Outstanding power-to-weight ratio, modular dual-fuel architecture, multi-redundant FADEC control, full-spectrum harsh environment reinforcement.
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