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M10 (rocket engine)

MR10 (previously known as M10 and LM10-MIRA) is a liquid-fuel, upper-stage rocket engine in development 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 after the start of the…

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Explore the main themes, entities and connections around M10 (rocket engine). Start with the topic map, then use the sections below for research and deeper semantic analysis.

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Development

HydrazineKBKhAItalianRussianMoscow
18 related topics

Overview

Liquid-fuelUpper-stageAvioEuropean Space AgencyVega E
21 related topics

Comparable engines

Aeon 1TQ-11
2 related topics

Key facts & relationships

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Application
Upper stage
Associated LV
Vega
Chamber
1
Country of origin
Italy
Cycle
Expander, closed
Designer
Avio, KBKhA

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Overview

Development

Comparable engines

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Map overview Semantic statistics

M10 (rocket engine)

Nodes45
Edges44
Triples25
Avg. degree1.96
Density0.044444
Components1

How this topic connects Entity context

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M10 (rocket engine)

Top relations

Application · 1
M10 (rocket engine) → Upper stage
Associated LV · 1
M10 (rocket engine) → Vega
Chamber · 1
M10 (rocket engine) → 1
Country of origin · 1
M10 (rocket engine) → Italy
Cycle · 1
M10 (rocket engine) → Expander, closed
Designer · 1
M10 (rocket engine) → Avio, KBKhA
Diameter · 1
M10 (rocket engine) → 1.2 m (3 ft 11 in)
Dry mass · 1
M10 (rocket engine) → 250 kg (550 lb)
Gimbal range · 1
M10 (rocket engine) → ±10°
Length · 1
M10 (rocket engine) → 2.4 m (7 ft 10 in)

Important terminology Word statistics

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Important terminology

engine development avio thrust mr10 vega kbkha rocket collaboration space rd-0146 upper successfully 2022 testing started liquid m10 consequent russian

Entity relationships Subject–Predicate–Object triples

SubjectPredicateObjectConfidenceSrc
M10 (rocket engine)ApplicationUpper stage1.00infobox
M10 (rocket engine)Associated LVVega1.00infobox
M10 (rocket engine)Chamber11.00infobox
M10 (rocket engine)Country of originItaly1.00infobox
M10 (rocket engine)CycleExpander, closed1.00infobox
M10 (rocket engine)DesignerAvio, KBKhA1.00infobox
M10 (rocket engine)Diameter1.2 m (3 ft 11 in)1.00infobox
M10 (rocket engine)Dry mass250 kg (550 lb)1.00infobox
M10 (rocket engine)Gimbal range±10°1.00infobox
M10 (rocket engine)Length2.4 m (7 ft 10 in)1.00infobox
M10 (rocket engine)ManufacturerAvio1.00infobox
M10 (rocket engine)Mixture ratio3.41.00infobox
M10 (rocket engine)Nozzle ratio401.00infobox
M10 (rocket engine)PredecessorRD-01461.00infobox
M10 (rocket engine)PropellantLOX / .mw-parser-output .template-chem2-su{display:inline-block;font-size:80%;line-height:1;vertical-align:-0.35em}.mw-parser-output .template-chem2-su>span{display:block;text-a…1.00infobox
M10 (rocket engine)Pumps21.00infobox
M10 (rocket engine)Restarts71.00infobox
M10 (rocket engine)Specific impulse362 s (3.55 km/s)1.00infobox
M10 (rocket engine)StatusUnder development1.00infobox
M10 (rocket engine)Thrust98 kN (22,000 lbf)1.00infobox

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