WP40

Full specification

The WP40 is a short-life turbojet developed for target drone users. Rated thrust is not less than 40 kgf at 91,500 rpm, with specific fuel consumption of 1.55 kg/kgf/h and a 25 h TBO. A ground start takes 45 s or less from a 3S battery; acceleration is within 18 s and deceleration within 25 s. The ECU talks to a flight controller over RS-232 at 115,200 bps and reports speed, exhaust temperature and fuel pressure. Mounting holes can be made to the airframe drawing. Fuel is RP-3 with 5% lubricant, fed through a 6×4 mm PU line at 20–40 kPa gauge.

Thrust class

Mid class

Fuel consumption

SFC 1.55 kg/kgf/h at maximum state

Fuel

RP-3 + 5% lubricant

Start

ECU automatic start sequence, 12 V (3S)

ECU

Integrated ECU, RS-232 at 115,200 bps

Service interval

25 h TBO

Max altitude

9,000 m and above

Temperature

-40 to 60 °C

Start altitude

4,000 m

Mach

0.7 and above

Ground start time

45 s

Acceleration

Within 18 s

Deceleration

Within 25 s

Exhaust temperature

850 °C maximum

Fuel supply pressure

20–40 kPa gauge

Electrical interface

XT60H-M power, DB15 RS-232

Starting power

Under 400 W for 5 s

Typical use

Target drone

Rated values from the model datasheet; factory test performance can vary by 2–3%. Altitude, Mach and temperature limits are operating limits, not guarantees of airframe performance.

Fitment notes

1. 01Fuel is aviation kerosene with the lubricant ratio stated above. Fit a 20–50 µm filter before the pump and keep supply pressure inside the datasheet range.
2. 02Ground starts follow the ECU's automatic ignition sequence. Stay within the stated start altitude and temperature limits; a start that times out is aborted by the controller.
3. 03Keep the intake and exhaust clear during runs. The manuals specify 3 m in front and 5 m to each side as a safety distance for ground operation.