M10 (rocket engine)
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 LM-10 MIRA model at Le Bourget | |
| Country of origin | Italy |
|---|---|
| Designer | Avio, KBKhA |
| Manufacturer | Avio |
| Application | Upper stage |
| Associated LV | Vega |
| Predecessor | RD-0146 |
| Status | Under development |
| Liquid-fuel engine | |
| Propellant | LOX / CH4 |
| Mixture ratio | 3.4 |
| Cycle | Expander, closed |
| Pumps | 2 |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 40 |
| Performance | |
| Thrust | 98 kN (22,000 lbf) |
| Specific impulse | 362 s (3.55 km/s) |
| Restarts | 7 |
| Gimbal range | ±10° |
| Dimensions | |
| Length | 2.4 m (7 ft 10 in) |
| Diameter | 1.2 m (3 ft 11 in) |
| Dry mass | 250 kg (550 lb) |
| Used in | |
| Vega-E | |
| References | |
| Notes | [1][2][3] |
MR10 (previously known as M10 and LM10-MIRA) is a liquid-fuel, upper-stage rocket engine in development[update] by Avio on behalf of European Space Agency for use on Vega E. The engine is a derivative of the Russian RD-0146 engine and result of a past collaboration between Avio and Chemical Automatics Design Bureau (KBKhA) ended in 2014[4][5] after the start of the Russo-Ukrainian War and consequent economic sanctions.[6] On May 6, 2022 engine testing campaign started at Salto di Quirra, Sardinia,[7] with consequent maiden flight on a Vega E launcher expected by 2026 from Guiana Space Centre.[8] The designation "M10" reflects key characteristics of the motor: "M" stands for "methane", referencing its liquid methane fuel; and "10" denoting the original target of 10 tonnes of thrust. The engine was renamed the MR10 in September 2024 in honour of the late Mikhail Rudnykh, who had served as Avio's head of cryogenic propulsion systems and led the engine's development.[9]
The MR10 engine is the first operational European methane rocket engine, conceived for use on upper stages of future Vega-E and Vega-E Light launchers, in which will replace both the solid-fueled Zefiro 3rd stage and hydrazine-fueled AVUM 4th upper stage. An industrial team directed by Avio with companies of Austria, Belgium, France, Czech Republic, Romania and Switzerland will manufacture the engine. The MR10 minimum thrust requirements are a thrust of 98 kN (22,000 lbf) with a propellant mixture ratio of 3.4 and a minimum specific impulse of 362s.[1][10]
