Product Brief Introduction
The SW240B micro turbojet UAV gasoline engine is an independently‑developed high‑thrust miniature gas‑turbine power solution engineered for heavy‑duty civilian unmanned aerial vehicles and top‑tier recreational RC jet platforms. As an enhanced high‑output UAV gasoline engine, it integrates self‑developed brushless starting assembly, bubble‑eliminating four‑eye fuel pump and single‑bus V3 intelligent ECU control unit, resolving common drawbacks of conventional micro‑jet hardware including unstable fuel delivery, messy internal wiring and limited safety‑oriented control features.
Boarding a compact lightweight integrated framework, this drone gasoline engine measures 115.5 mm outer diameter, 278.5 mm overall length with a net dry weight of merely 1740 g. It maximizes available cabin volume for aerial survey sensors, data‑transmission payloads and other civilian mission equipment. The power unit runs on standard aviation kerosene with a 3%‑5% turbine lubricant mixing ratio, while peak fuel consumption is controlled under 780 g/min under full‑thrust working status.
All R&D, manufacturing and bench‑test specifications are confined exclusively to non‑military civilian commercial, educational and hobby‑aviation scenarios. The full set of supporting accessories is shipped alongside the main engine body to shorten assembly and commissioning cycles for global buyers.
Unified Integrated Technical Parameter Table
| Parameter Category | Item Name | Specific Parameter Value |
|---|---|---|
| Main Engine Body | Product Model | SW240B |
| Main Engine Body | Maximum Static Thrust | 24kg / 240N |
| Main Engine Body | Outer Diameter | 115.5mm |
| Main Engine Body | Overall Length | 278.5mm |
| Main Engine Body | Net Dry Weight | 1740g |
| Main Engine Body | Usable Rotational Speed Range | 38000 ~ 116000 rpm |
| Main Engine Body | Stable Idle Speed | 38000 rpm |
| Main Engine Body | Rated Maximum Exhaust Temperature | 750℃ |
| Main Engine Body | Maximum Fuel Consumption | ≤780g/min |
| Main Engine Body | Applicable Fuel | Aviation Kerosene |
| Main Engine Body | Standard Lubricating Oil Mix Ratio | 3% ~ 5% |
| Main Engine Body | Standard Maintenance Cycle | 25 Flight Hours |
| Brushless Starter Motor | Rated Operating Speed | 97000 rpm |
| Brushless Starter Motor | Pop‑Up Time | 0.5S |
| Brushless Starter Motor | Pop‑Up Working Voltage | 4V |
| Brushless Starter Motor | Stable Running Voltage | 4V |
| Brushless Starter Motor | Cooling Rotational Speed | 5000 rpm |
| ECU Control System | Main Chip Specification | 32‑bit High‑Speed Processor |
| ECU Control System | Data Transmission Mode | Single Bus Telemetry Signal |
| ECU Control System | Fuel Pump Startup Voltage Range | 0.5–1.2V |
| ECU Control System | RPM Acceleration Slope Coefficient | 100 |
| ECU Control System | Fuel Pump Output Slope Coefficient | 3 |
| ECU Control System | Ignition Fuel Valve Opening Value | 40 |
| ECU Control System | Ignition Trigger Rotational Speed | 3000 rpm |
| ECU Control System | Preheating Rotational Speed | 5000 rpm |
| ECU Control System | Clutch Separation Rotational Speed | 20000 rpm |
| ECU Control System | Acceleration Curve Parameter | 25 |
| ECU Control System | Deceleration Curve Parameter | 25 |
| ECU Control System | Real‑Time Temperature Limit | ≤1000℃ |
| ECU Control System | Minimum Working Voltage | ≥10V |
| ECU Control System | Fuel Pump Voltage Protection Limit | 13V |
| ECU Control System | Auto Restart After Shutdown | Switchable On / Off |
| Standard Full Kit Accessories | Complete Matching Parts | Main Engine Unit, SWP50D Four‑Eye Fuel Pump, V3 ECU, GSU Display Terminal, Aviation Fuel Filter, Fuel Ball Valve, Power Line, Throttle Line, Telemetry Signal Line |
Core Independent Technical Highlights
Self‑Developed Integrated Brushless Starter Motor
This UAV gasoline engine is fitted with an in‑house engineered brushless starter motor rated at 97000 rpm. Its compact integrated layout will not occupy extra airframe installation space and can generate dependable starting torque under low‑temperature as well as high‑altitude operating environments to reduce cold‑start failure risks. The motor housing receives specialized heat‑dissipation coating treatment to sustain stable performance amid frequent repeated startup cycles and prolong the overall service life of this drone gasoline engine.
Four‑Eye Double‑Inlet Anti‑Bubble Fuel Pump System
The bundled SWP50D fuel pump adopts proprietary dual‑inlet dual‑outlet pipeline architecture with a 6 mm fuel inlet and 4 mm fuel outlet. Its multi‑layer internal flow‑splitting structure thoroughly breaks air bubbles mixed within aviation kerosene, fundamentally removing flameout hazards originating from fuel‑line air blockage during steep climbing and high‑speed cruise. The pump housing is fabricated from corrosion‑resistant aluminum alloy to withstand long‑duration fuel contact and lower component replacement frequency for commercial users.
Simplified Single‑Bus Communication Architecture
Different from multi‑cable discrete‑signal micro‑jet engines on the marketplace, this drone gasoline engine utilizes merely one single‑bus channel to finish full data exchange covering rotational speed, exhaust temperature and throttle commands between ECU, ground display terminal and flight controller. This solution drastically simplifies internal aircraft wiring layouts, decreases wiring‑related fault sources and elevates anti‑interference performance for the whole onboard electrical network.
V3 32‑Bit Intelligent ECU Control Unit
The supporting V3 ECU runs on a high‑speed 32‑bit computing chip, delivering two key practical capabilities: fixed‑RPM hold and switchable automatic restart after unexpected shutdown. When transient fuel‑supply fluctuation or momentary power loss occurs in‑flight, the ECU can activate re‑ignition sequences autonomously without manual ground intervention, greatly enhancing operational safety over long‑range civilian aerial missions. Reserved expansion ports support real‑time telemetry data feedback toward ground‑station monitoring hardware.
High‑Temperature‑Resistant Integrated Turbine Main Body
Turbine rotor, combustion chamber and exhaust nozzle of this UAV gasoline engine are all cast from premium aviation superalloy. These components continuously tolerate 750 ℃ exhaust temperature under full‑load working status without structural deformation or power decay. Streamlined outer casing cuts aerodynamic drag during flight, while symmetric standardized mounting lugs are pre‑reserved to fit most mainstream large‑size civilian fixed‑wing UAV and RC‑jet
Civilian Commercial Application Scenarios
The SW240B micro turbojet drone gasoline engine is designed exclusively for non‑military civilian industrial, educational and recreational aviation‑related projects:
- High‑speed aerial survey & mapping: long‑distance mountain‑range terrain scanning, highway infrastructure inspection, large‑scale land‑resource general‑survey assignments
- Civilian environmental monitoring: full‑basin river water‑quality patrol, wide‑area forest vegetation growth tracking, wild ecological‑resource investigation
- Agricultural industrial UAV equipment: rapid large‑orchard patrol operations, high‑speed farm‑crop growth inspection tasks
- University aerospace laboratory research platforms: aerodynamic test aircraft, miniature turbine‑power R&D prototypes
- Premium large‑scale RC jet aircraft, commercial aviation‑exhibition demonstration aircraft models
Packaging, Delivery & Downloadable Technical Files
Standard Export Packaging: Custom shock‑absorbing aluminum inner box with thermal‑insulation foam lining + fumigated heavy‑duty wooden outer crate. All precision turbine assemblies and electronic accessories get individual wrapping using anti‑rust grease paper plus anti‑static film to prevent collision damage throughout cross‑border sea and air logistics.
Supported International Trade Terms: EXW, FOB, CIF, DDP door‑to‑door worldwide delivery; we cooperate with specialized aerospace‑focused freight providers.
Bulk Customized Packaging: Reinforced impact‑proof wooden crates are available for large‑volume wholesale orders, with isolated partition protection for every single accessory.
Delivery Lead Time: Single‑sample full‑kit shipments within 12 working days; mass‑production batch orders are fulfilled within 22‑28 working days after deposit confirmation.
Free Downloadable Documents After Order Confirmation: SW240B technical‑specification PDF, SW240B dimension‑drawing PDF, official installation‑and‑operation‑manual PDF.
Factory R&D & Strict Quality Inspection Flow
The manufacturer maintains complete in‑house micro‑turbine R&D laboratories, CNC intelligent manufacturing workshops and full‑function turbine bench‑test facilities. Every finished SW240B UAV gasoline engine must complete six critical inspection procedures before factory dispatch:
- Incoming raw‑material verification: material‑composition analysis plus dimensional calibration for high‑temperature‑alloy rotor, ECU chip, fuel‑pump hardware and all sealing components.
- Ultra‑high‑speed rotor dynamic‑balancing calibration and real‑time vibration‑magnitude detection.
- Three‑hour uninterrupted full‑load bench test; thrust value, rotational speed, exhaust temperature and fuel‑consumption metrics are logged synchronously.
- Low‑temperature and high‑altitude simulation cold‑start testing for startup‑reliability validation under harsh environmental conditions.
- Full‑kit accessory matching inspection plus functional verification covering wiring harnesses, fuel‑system parts and data‑display hardware.
- Finished‑unit anti‑rust protection, anti‑static handling and final packaging quality audit.
Each drone gasoline engine receives a unique independent serial number. All bench‑test logs and manufacturing records are permanently archived to deliver traceable quality assurance for global civilian UAV integrators and resellers.
Frequently Asked Questions
FAQ 1 What fuel and lubrication mixing ratio should I use for SW240B UAV gasoline engine? Are ethanol‑blended fuels allowed?
Answer: This UAV gasoline engine must utilize pure aviation kerosene blended with dedicated turbine lubricating oil at a mixing ratio of 3%‑5%. Any ethanol‑containing fuel is strictly forbidden. Ethanol will generate heavy carbon accumulation inside combustion chambers, clog four‑eye fuel‑pump pipelines and inflict permanent damage upon high‑temperature turbine rotors. Please clean the fuel filter before every refueling event to stop particulate matter from obstructing fuel circuits. Perform full‑disassembly maintenance strictly complying with the 25‑flight‑hour service cycle.
FAQ 2 Is the single‑bus V3 ECU compatible with third‑party autopilot hardware? How should operators respond to unexpected in‑flight engine flameout events?
Answer: The single‑bus communication interface of V3 ECU works with mainstream civilian‑grade industrial autopilot products available on global markets; matching communication‑protocol documents are supplied free‑of‑charge. This drone gasoline engine comes equipped with built‑in automatic restart capability. If unplanned flameout takes place mid‑flight, the ECU will trigger ignition procedures within several seconds to restart the engine. In the event of multiple unsuccessful restart attempts, cut throttle power supply and execute comprehensive ground inspection after completing safe gliding landing. Our engineering team offers remote ECU‑parameter‑tuning technical support upon request.
Inquiry & Global Cooperation Guide
Should you require sample bench‑testing services, bulk‑wholesale quotations, airframe‑matching technical consulting, ECU‑parameter tuning, or wish to acquire downloadable SW240B technical‑spec and dimension PDF documents, submit your inquiry via website contact‑form or official business email. Our specialized aerospace‑power sales‑engineering team replies to all consultation submissions within 24 working hours and provides complimentary global after‑sales‑policy documents plus detailed installation‑operation guidance materials.
