# Masquito M80

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Belgian ultralight helicopter

M80 General information Type Ultralight helicopter National origin Belgium Manufacturer Masquito Aircraft Number built 4 History First flight May 1996 (M58) Developed from Maschelin M58 Masquito

The **Masquito M80** was a [Belgian](/source/Belgium) two-seat ultralight [helicopter](/source/Helicopter) designed and built by [Masquito Aircraft](https://en.wikipedia.org/w/index.php?title=Masquito_Aircraft&action=edit&redlink=1).[1]

## Design and development

The prototype was designated the **Maschelin M58 Masquito**. It was a conventional pod and boom design and was powered by a 64 hp (48 kW) [Rotax 582](/source/Rotax_582) engine driving a two-bladed main rotor and a two-bladed tail rotor.[1] It had two side-by-side seats and was fitted with two fixed skids as a [landing gear](/source/Landing_gear).[1] The M58 first flew in May 1996; it was later modified to the proposed production standard with a [Jabiru 2200](/source/Jabiru_2200) engine and re-designated the M80.[1] Three further M80 prototypes were built but the type failed to gain the appropriate certification and no others were produced.

A Belgian company, [D-Motor](/source/D-Motor) was set up to design and build a suitable motor for the M80. Two engines with a high power-to-weight ratio were produced: first, the [D-Motor LF26](/source/D-Motor_LF26) (a 92 hp (69 kW) [flat four](/source/Flat_four)) and, later, the [D-Motor LF39](/source/D-Motor_LF39) (a 125 hp (93 kW) [flat-six](/source/Flat-six)). Unlike the Jabiru motor, these Belgian [horizontally-opposed](/source/Horizontally-opposed) engines have [fuel-injection](/source/Fuel-injection), [liquid-cooling](/source/Radiator_(engine_cooling)) and, having [side-valves](/source/Flathead_engine), are ultra-compact, .

## Variants

**Maschelin M58 Masquito**
- Prototype with a [Rotax 582](/source/Rotax_582) engine.[1]

**Masquito M80**
- Production variant with a [Jabiru 2200](/source/Jabiru_2200) engine.[1]

## Specifications (M80)

*Data from* [1]

**General characteristics**

- **Crew:** 2

- **Length:** 5.80 m (19 ft 0.25 in)

- **Height:** 2.25 m (7 ft 4.5 in)

- **Empty weight:** 170 kg (375 lb)

- **Gross weight:** 390 kg (859 lb)

- **Powerplant:** 1 × [Jabiru 2200](/source/Jabiru_2200) flat-four piston , 60 kW (80 hp)

- **Main rotor diameter:** 4.60 m (15 ft 1 in)

- **Main rotor area:** 16.62 m2 (178.9 sq ft)

**Performance**

- **Maximum speed:** 180 km/h (112 mph, 97 kn)

- **Cruise speed:** 148 km/h (92 mph, 80 kn)

- **Range:** 680 km (422 mi, 367 nmi)

- **Service ceiling:** 3,050 m (10,000 ft)

- **Rate of climb:** 5.6 m/s (1,100 ft/min)

## See also

**Related lists**

- [List of rotorcraft](/source/List_of_rotorcraft)

## References

### Notes

1. ^ [***a***](#cite_ref-Janes_1-0) [***b***](#cite_ref-Janes_1-1) [***c***](#cite_ref-Janes_1-2) [***d***](#cite_ref-Janes_1-3) [***e***](#cite_ref-Janes_1-4) [***f***](#cite_ref-Janes_1-5) [***g***](#cite_ref-Janes_1-6) Jackson 1999, pp. 13-14

### Bibliography

- Paul Jackson, ed. (1999). *Jane's All the World's Aircraft 1999-2000*. Jane's Information Group Limited. [ISBN](/source/ISBN_(identifier)) [0-7106-1898-0](https://en.wikipedia.org/wiki/Special:BookSources/0-7106-1898-0).

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