M10 (rocket engine)
{{Use dmy dates|date=March 2021}}
{{Infobox rocket engine
| name = MR10
| image = Moteur-fus%C3%A9e_italien_LOX_CH4_Mira_DSC_0023.JPG
| caption = LM-10 MIRA model at Le Bourget
| country_of_origin = Italy
European Union
| date =
| first_date =
| last_date =
| manufacturer = Avio
| purpose = Upper stage
| associated = Vega
| predecessor = RD-0146
| successor =
| status = Under development
| type = liquid
| fuel = {{chem2|CH4|link=liquid methane}}
| oxidizer = LOX
| mixture_ratio = 3.4
| cycle = Expander
| pumps = 1
| combustion_chamber = 1
| nozzle_ratio = 40
| thrust =
| thrust_at_altitude =
| thrust(Vac) = {{cvt|98|kN}}
| thrust(SL) = {{cvt|91|kN}}
| thrust_to_weight =
| chamber_pressure =
| specific_impulse =
| specific_impulse_vacuum = {{cvt|362|isp}}
| specific_impulse_sea_level = {{cvt|334|isp}}
| total_impulse =
| burn_time =
| gimbal =
| capacity =
| dimensions =
| length = Sea level: {{ubl| {{cvt|1.5|m}} }}Vacuum {{ubl| {{cvt|2.4|m}} }}
| diameter = Sea level: {{ubl| {{cvt|0.5|m}} }}Vacuum {{ubl| {{cvt|1.2|m}} }}
| dry_weight = Sea level: {{ubl| {{cvt|200|kg}} }}Vacuum {{ubl| {{cvt|230|kg}} }}
| used_in = Vega-E
}}
MR10 (previously known as M10) is a liquid-fuel upper-stage rocket engine {{as of|2021|March|alt=in development}} by Avio on behalf of European Space Agency for use on Vega E. The engine, initially known as LM10-MIRA, was a derivation of the existing Russian RD-0146 engine and result of a past collaboration between Avio and Chemical Automatics Design Bureau (KBKhA) ended in 2014{{cite web |url=http://www.cesmamil.org/wordpress/wp-content/uploads/2017/07/010_Italian-Contribution-to-Innovative-Space-Propulsion-Re-entry-Missions-Battiston.pdf |archive-url=https://web.archive.org/web/20181126093336/http://www.cesmamil.org/wordpress/wp-content/uploads/2017/07/010_Italian-Contribution-to-Innovative-Space-Propulsion-Re-entry-Missions-Battiston.pdf |url-status=usurped |archive-date=26 November 2018 |title=Italian Contribution to Innovative Space Propulsion & Re-entry missions |last=R. Battiston |date=2016-06-30 |publisher=CESMA, Centro Studi Militari Aeronautici "Giulio Douhet" |access-date=2021-03-24}} after the start of the Russo-Ukrainian War and consequent economic sanctions.{{Cite book |last1=Aliberti |first1=Marco |last2=Lisitsyna |first2=Ksenia |date=May 2018 |title=Russia's Posture in Space: Prospects for Europe |url=https://espi.or.at/publications/espi-public-reports/send/2-public-espi-reports/261-executive-summary-russia-s-posture-in-space |access-date=2022-05-10 |publisher=European Space Policy Institute |page=2 |doi=10.1007/978-3-319-78960-6 |isbn=978-3-319-90554-9|s2cid=187915217 }} On May 6, 2022 engine testing campaign started at Salto di Quirra, Sardinia,{{Cite web |last=Cozzi |first=Emilio |date=2018-11-13 |title=Il primo propulsore europeo a metano liquido ha passato il collaudo |url=https://www.wired.it/scienza/spazio/2018/11/13/m10-avio-test-motore/ |access-date=2022-05-10 |website=Wired Italia |language=it-IT}} with consequent maiden flight on a Vega-E launcher expected by 2026 from Guiana Space Centre.{{cite press release |url=https://www.avio.com/press-release/new-launch-service-contracts-vega-c-and-new-development-activities |title=New launch service contracts for Vega C and new development activities |date=20 January 2022 |access-date=20 January 2022 |work=Avio}}
Overview
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 {{convert|98|kN|lbf|abbr=on}} with a propellant mixture ratio of 3.4 and a minimum specific impulse of 362s.{{cite web |url=https://www.avio.com/it/m-10 |title=Motore M10 |publisher=Avio |language=Italian |trans-title=Engine M10 |access-date=2021-03-24}}{{cite web |url=https://aerospace.aicqpiemonte.it/wp-content/uploads/2023/05/AICQ_FBetti_.pdf |title=Le nuove sfide della propulsione e dei sistemi di lancio spaziali in Avio | publisher=Polytechnic University of Turin |language=Italian |trans-title=Avio's new challenges in propulsion and space launch systems |date=2023-05-05 |access-date=2025-02-16}}
Development
A feasibility study on improving Vega began in 2004, when the rocket was still in development, with the aim of increase performance, reduce costs and move away from toxic hydrazine fuels. The study proposed a new three-stage version of the rocket named Lyra with a liquid oxygen-methane upper stage. In 2007 Avio and KBKhA started the collaboration for the development of such an engine under an agreement signed between Italian and Russian governments in Moscow on November 28, 2000. The first phase of the collaboration, ended in 2008, aimed at designing a concept for a 10t thrust LOx-LNG engine. The second phase of the collaboration focused instead on designing, manufacturing and testing a 7.5t thrust LM10-MIRA demonstrator engine. The engine was successfully tested in June 2014 in Voronezh, Russia.{{cite book |chapter-url=https://www.eucass-proceedings.eu/articles/eucass/abs/2019/01/eucass2019_447/eucass2019_447.html |chapter=Development of LM10-MIRA liquid oxygen – liquid natural gas expander cycle demonstrator engine |last1=P. Bellomi |last2=M. Rudnykh |last3=S. Carapellese |last4=D. Liuzzi |last5=G. Caggiano |last6=L. Arione |last7=A.A. Gurtovoy |last8=S.D. Lobov |last9=V. S. Rachuk |title=Progress in Propulsion Physics – Volume 11 |date=2019-02-08 |pages=447–466 |doi=10.1051/eucass/201911447 |isbn=978-5-94588-228-7 |s2cid=139531422 |access-date=2021-03-23}}
After the end of the collaboration with KBKhA, Avio continued the development of MR10 under the Vega-Evolution program returning to the original target thrust of 10t. Objectives were finalizing development of main subsystems such as turbopumps, valves, igniter, thrust vectoring and a new ALM 3D printed Thrust Chamber Assembly (TCA).{{Cite journal |last=Kajon |first=D. |last2=Liuzzi |first2=D. |last3=Boffa |first3=C. |last4=Rudnykh |first4=M. |last5=Drigo |first5=D. |last6=Arione |first6=L. |last7=Ierado |first7=N. |last8=Sirbi |first8=A. |date=2019 |title=Development of the liquid oxygen and methane M10 rocket engine for the Vega-E upper stage |url=https://www.eucass.eu/doi/EUCASS2019-0315.pdf |journal=8th European Conference for Aeronautics and Space Sciences |doi=10.13009/EUCASS2019-315 |access-date=2021-03-24}} A subscale model of the TCA was tested successfully on 13 November 2018 in Colleferro, Italy.{{cite web |url=https://www.esa.int/ESA_Multimedia/Images/2018/11/Hot_fire_test_of_prototype_engine_thrust_chamber_for_future_Vega_Evolution |title=Hot fire test of prototype engine thrust chamber for future Vega Evolution |date=2018-11-21 |publisher=ESA |author=Avio |access-date=2021-03-24}}
In February 2020 a full scale engine prototype with a 3D printed TCA was successfully tested at NASA Marshall Space Flight Center, firing 19 times for a total of 450 seconds.{{cite web |url=https://www.esa.int/Enabling_Support/Space_Transportation/3D-printed_thrust_chamber_passes_first_tests_for_Vega_evolutions |title=3D-printed thrust chamber passes first tests for Vega evolutions |date=2020-03-03 |publisher=ESA |access-date=2021-03-24}}
On May 6 2022, the engine test and qualification campaign started in Avio's new Space Propulsion Test Facility (SPTF) at the Salto di Quirra with a single firing of 20 seconds. The first series of testing concluded successfully in July 2022 with a total ignition time of more than 800 seconds.{{cite press release |url=https://www.avio.com/press-release/first-half-2022-results |title= First half 2022 results |date=9 September 2022 |access-date=16 September 2022 |work=Avio}}
See also
{{Portal |Spaceflight}}