View source for Engineering:Miura 5

{{short description|European orbital recoverable rocket of the company PLD Space}}
{{Infobox rocket
|logo        =  <!--logo filename (omit "Image:" prefix), required-->
|logo_size   =  <!--Size of logo (omit "px" suffix), optional, defaults to 270px-->
|image       = Prueba de reutilización, Miura 5, Huelva, España, 2019 06.png
|caption     =  A reuse test small-scale first stage of Miura 5 in El Arenosillo

<!----Core parameters (required)---->
|name           =  Miura 5
|function       =  partially [[Astronomy:Reusable launch system|reusable]] [[Engineering:Launch vehicle|launch vehicle]] to [[Astronomy:Low Earth orbit|low Earth orbit]] <!--Purpose of the rocket, required-->
|manufacturer   =  [[Company:PLD Space|PLD Space]]
|country-origin =  Spain

<!----Costs (optional)---->
|pcost    =  <!--project cost, optional-->
|cpl      =  <!--cost per launch, optional-->
|alt-cpl  =  <!--cost in alternative currency, optional-->
|cpl-year =  <!--year of stated cost per launch-->

<!----Dimensions (required)---->
|height       =  {{cvt|34.4|m|abbr=on}}<ref name="auto2">{{cite tweet|url=https://twitter.com/RaulTorresPLD/status/1483502909518229506|title=Thread 👉 Happy to give you accurate #MIURA5 figures: maximum payload mass to reference mission (500km SSO): 450kg . Maximum payload to orbit : 900kg (equatorial launch). Launch site is CSG in French Guiana.|number=1483502909518229506|user=RaulTorresPLD}}</ref>
|diameter     =  {{cvt|1.8|m}}<ref name="auto2"/> <!--core diameter in metres, use {{cvt|DIAMETER|m}}, required-->
|width        =  <!--width if not axisymmetric, use {{cvt|WIDTH|m}}, optional-->
|mass         = {{cvt|32000|kg}} <!--mass of rocket in kilograms, use {{cvt|MASS|kg}}, required-->
|stages       = 2–3 <!--number of stages, not including boosters-->

<!----Payloads (optional)---->
|capacities =  <!--insert one of the following templates for each payload:-->
{{Infobox rocket/payload
  |location =  [[Astronomy:Low Earth orbit|Low Earth orbit]] (LEO) <!--Target orbit/trajectory, required. Please use [[Astronomy:Geostationary transfer orbit|GTO]] or [[Astronomy:Low Earth orbit|LEO]] instead of just GTO or LEO.-->
  |kilos    =  {{convert|900|kg|abbr=on|round=5}}<ref name="auto2"/>
}}
{{Infobox Rocket/Payload
  | location     = [[Astronomy:Sun-synchronous orbit|SSO]]
  | kilos        = {{convert|450|kg|abbr=on|round=5}}<ref name="auto2"/>
}}

<!----Associated rockets (optional)---->
|family      =  <!--rocket family, optional-->
|derivatives =  <!--derived rockets, optional-->
|comparable  =  [[Engineering:Shavit 2|Shavit 2]], [[Engineering:Orbex#Prime|Prime]], [[Engineering:Electron (rocket)|Electron]]

<!----Launch history (required)---->
|status   =  under development <!--current status (eg. Active, Retired, etc), required-->
|sites    =  El Hierro Launch Centre (proposed)<br />
[[Organization:Guiana Space Centre|Guiana Space Centre]] (planned)<br />
Azores (proposed)
<!--launch centres and pads, required-->
|launches =  <!--total launches to date, optional-->
|success  =  <!--total successful launches, optional-->
|fail     =  <!--total failed launches, optional-->
|partial  =  <!--total number of launches resulting in partial failure (e.g. incorrect orbit but still usable), optional-->
|other_outcome =  <!--number of launches with unknown outcomes (or in progress), optional-->
|landings =  <!--total number of landings, optional-->
|first    =  Q1 2026 (planned)<ref name="reuters-20231020" />
|last     =  <!--date of latest or final flight, optional-->
|only     =  <!--launch date if only one was launched, optional-->
|payloads =  <!--notable payloads, optional-->

<!--Stages/boosters (optional)-->
|stagedata    =  <!--insert one of the following templates for each stage:-->

  {{Infobox rocket/stage
  |type       = stage <!--booster or stage (must be in lower case)-->
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    = First <!--position of stage in rocket, spelled out (eg. First, Second, etc), required if type = stage-->
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     = {{cvt|17.7|m}}<ref name="auto">{{Cite journal|url=https://digitalcommons.usu.edu/smallsat/2020/all2020/63/|title = MIURA 5: The European and Reusable Microlauncher for CubeSats and Small Satellites|journal = Small Satellite Conference|date = August 2020|last1 = Gallego|first1 = Pablo}}</ref> <!--length of a single booster/stage in metres, use {{cvt|LENGTH|m}}, optional-->
  |diameter   = {{cvt|1.8|m}} <!--diameter of a single booster/stage in metres, use {{cvt|DIAMETER|m}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{cvt|WIDTH|m}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{cvt|EMPTYMASS|kg}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{cvt|GROSSMASS|kg}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{cvt|PROPMASS|kg}}, optional--> 
  |engines    =  5 [[Engineering:TEPREL|TEPREL]]-C<!--number and type of engines used on each individual booster/stage, required-->
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     = {{cvt|950|kN}} <!--thrust provided by a single booster/stage in kN, use {{cvt|THRUST|kN}}, required-->
  |total      =  {{cvt|950|kN}} <!--total thrust for all boosters in kN, use {{cvt|THRUST|kN}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in seconds, use {{convert|ISP_IN_SECONDS|isp}}, optional-->
  |burntime   =  182 s.<ref name="auto2"/> <!--burn time, required-->
  |fuel       =  [[Physics:Liquid oxygen|LOX]] / [[Chemistry:RP-1|RP-1]]
  }}
  {{Infobox rocket/stage
  |type       = stage <!--booster or stage (must be in lower case)-->
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    = Second <!--position of stage in rocket, spelled out (eg. First, Second, etc), required if type = stage-->
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     = {{cvt|9|m}} <!--length of a single booster/stage in metres, use {{cvt|LENGTH|m}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{cvt|DIAMETER|m}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{cvt|WIDTH|m}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{cvt|EMPTYMASS|kg}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{cvt|GROSSMASS|kg}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{cvt|PROPMASS|kg}}, optional--> 
  |engines    =  1 [[Engineering:TEPREL|TEPREL]]-C vacuum<!--number and type of engines used on each individual booster/stage, required-->
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  {{cvt|50|kN}} <!--thrust provided by a single booster/stage in kN, use {{cvt|THRUST|kN}}, required-->
  |total      =  {{cvt|50|kN}} <!--total thrust for all boosters in kN, use {{cvt|THRUST|kN}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in seconds, use {{convert|ISP_IN_SECONDS|isp}}, optional-->
  |burntime   = 420 s.<ref name="auto2"/> <!--burn time, required-->
  |fuel       =  [[Physics:Liquid oxygen|LOX]] / [[Chemistry:RP-1|RP-1]]
  }}
  {{Infobox rocket/stage
  |type       = stage <!--booster or stage (must be in lower case)-->
  |diff       = optional <!--variant of rocket this is used on, optional-->
  |stageno    = Kick <!--position of stage in rocket, spelled out (eg. First, Second, etc), required if type = stage-->
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{cvt|LENGTH|m}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{cvt|DIAMETER|m}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{cvt|WIDTH|m}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{cvt|EMPTYMASS|kg}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{cvt|GROSSMASS|kg}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{cvt|PROPMASS|kg}}, optional--> 
  |engines    =  <!--number and type of engines used on each individual booster/stage, required-->
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  <!--thrust provided by a single booster/stage in kN, use {{cvt|THRUST|kN}}, required-->
  |total      =  <!--total thrust for all boosters in kN, use {{cvt|THRUST|kN}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in seconds, use {{convert|ISP_IN_SECONDS|isp}}, optional-->
  |burntime   =  <!--burn time, required-->
  |fuel       =  
  }}
}}
'''Miura 5''' is a two-stage European orbital [[Astronomy:Reusable launch system|recoverable launch vehicle]] currently under development by the Spanish company [[Company:PLD Space|PLD Space]]. In a standard two-stage configuration, it will have a length of 34 m, be capable of inserting 1000&nbsp;kg of payload into a [[Astronomy:Low Earth orbit|low Earth orbit]] (LEO), featuring an optional kick stage that can circularize the orbits of satellites.<ref name="double 2018"/>

Development of the Miura 5 has been sponsored by the [[Organization:European Space Agency|European Space Agency]] (ESA) via the agency's Future Launchers Preparatory Programme (FLPP); additional support has come from the French space agency [[Organization:CNES|CNES]] and the Spanish agency [[Organization:National Institute for Aerospace Technology|National Institute for Aerospace Technology]] (INTA). Work commenced during the mid-2010s under the name ''Arion 2'', the present name was adopted following a redesign that doubled the lift capacity of the launcher during 2018. On 11 April 2019, PLD Space carried out a successful drop and recovery test of the first stage of a Miura 5 demonstrator. As of December 2023, the first test flight of Miura 5 is expected to take place sometime in early 2026.<ref name="reuters-20231020"/>

== Design ==
[[File:Prueba_de_reutilización,_Miura_5,_Huelva,_España,_2019_03.jpg|thumb|left|Downscale testing vehicle used during drop test in 2019]]

The Miura 5 has been designed to reuse the majority of the technology developed for the preceding [[Engineering:Miura 1|Miura 1]]. However, many of these technologies will be refined substantially to incorporate lessons learnt with the earlier rocket.<ref name = "atalayar Oct2023"/><ref>{{cite web |url = https://interestingengineering.com/innovation/spain-rocket-launch-could-be-turning-point-for-european-spaceflight |title = Spain rocket launch could be turning point for European spaceflight |website = interestingengineering.com |first = Chris |last = Young |date = 12 October 2023 }}</ref> New design elements include the propellant tanks and engine; it remains a liquid fuel rocket.<ref>{{cite tweet |url = https://twitter.com/RaulTorresPLD/status/1432099445546569735 |title = Comenzaremos la fabricación del primer MIURA5 pero por supuesto necesitamos que vuele MIURA1 para validar y transferir muchas tecnologías. Otras, como los motores TEPREL-C o los tanques de propelente son nuevas. Esperamos tener a principios del próximo año hardware de ensayo |number = 1432099445546569735 |language = es |user = RaulTorresPLD}}</ref> Many elements of the Miura 5, including the propulsion system, structures, and avionics development, will be designed and produced in-house.<ref name = "satmagazine 2022">{{cite web |url = http://www.satmagazine.com/story.php?number=977671537 |title = PLD Space Secures The Next Steps for the MIURA Launches |first = Pablo Gallego |last = Sanmiguel |website = satmagazine.com |date = March 2022}}</ref><ref>{{cite web |url = https://www.euronews.com/next/2023/04/07/an-alternative-to-spacex-spanish-start-up-to-launch-first-european-reusable-rocket |title = SpaceX competitor? A Spanish start-up is ready to launch Europe’s first reusable rocket |publisher = euronews.com |first = Oceane |last = Duboust |date = 7 April 2023}}</ref>

The Miura 5 is to be propelled by a single [[Engineering:TEPREL#TEPREL-C|TEPREL-C]] [[Engineering:Turbopump|turbopump]] engine, unlike its predecessor, which used a [[Physics:Pressure-fed engine|pressurized tank cycle]] instead.<ref name="miura1-payloadusersguide">{{cite web |title=MIURA 1 - Payload User's guide |url=https://pldspace.com/images/MIURA_1/MIURA1_Payload_Users_Guide.pdf |publisher=Payload Aerospace S.L. |access-date=2 January 2024 |archive-url=https://web.archive.org/web/20231007111221/https://www.pldspace.com/images/MIURA_1/MIURA1_Payload_Users_Guide.pdf |archive-date=7 October 2023 |page=10 |date=13 November 2018 |url-status=live}}</ref>

A key feature of the Miura 5 is its reusable first stage. The recovery process shall employ a combination of engine thrust and [[Engineering:Parachute|parachute]]s.<ref name='SN Caleb June 2018'>{{cite web |url = https://spacenews.com/pld-space-raises-additional-10-million-for-reusable-smallsat-launchers/ |title = PLD Space raises additional $10 million for reusable smallsat launchers |first = Caleb |last = Henry |website = spacenews.com |date = 11 June 2018 |access-date = 3 March 2019}}</ref> While furnished with a larger parachute arrangement to account for the larger scale of the Miura 5, the various subsystems controlling the recovery are identical those used on the Miura 1.<ref name = "satmagazine 2022"/> The launcher's reuse capabilities have reportedly been scaled as to permit each rocket to be launched a maximum of three times.<ref name="esapres">{{cite web |url = http://esamultimedia.esa.int/docs/space_transportation/LAUNCHER_WS_Presentation_PLDSpace.pdf |title = ESA Microlaunch Services Workshop Presentation |language = en-gb |date = 6 November 2018}}</ref>

The Miura 5 was originally envisioned to have a lift capacity of 150 kilograms; in comparison to [[Engineering:Vega (rocket)|Vega]], [[Company:Arianespace|Arianespace]]’s smallest launcher, it was to be capable of carrying roughly one-tenth of the payload.<ref name='SN Caleb June 2018'/> It is specifically intended for the launching of [[Engineering:Small satellite|small satellite]]s into [[Astronomy:Low Earth orbit|low Earth orbit]] (LEO).<ref name='SN Caleb June 2018'/> However, mid-way through the design process, the Miura 5's lift capacity was doubled in response to formal recommendations produced by the ESA in 2018.<ref name = "double 2018"/> It will be typically operated as a two stage launcher, although provisions will be made for individual rockets to be expandable to three stages when a greater lift capacity or altitude is required.<ref>{{cite web |url = https://www.universetoday.com/161906/startup-pld-space-to-launch-europes-first-reusable-rocket/ |title = Startup PLD Space to Launch Europe’s First Reusable Rocket |website = universetoday.com |first = David |last = Dickinson |date = 12 June 2023}}</ref>

== Development==
===LPSR Program===
During October 2016, the [[Organization:European Space Agency|European Space Agency]] (ESA) announced the selection of the Spanish aerospace start-up [[Company:PLD Space|PLD Space]] as the main contractor of the LPSR ("Liquid Propulsion Stage Recovery") program, one part of the agency's Future Launchers Preparatory Programme (FLPP).<ref name = "satmagazine 2022"/> The company was allocated an initial contribution of €750,000 towards the early development of a reusable first stage of a future space launch system; the long-term objective is to provide the reusable first stage for what later became the Miura 5. Various options for recovery were examined, primarily involving the use of [[Engineering:Parachute|parachute]]s; other methods, such as the use of controlled paragliders or [[Engineering:Ballute|ballute]]s, were also explored at this stage. Some early testing of the system was performed using the smaller [[Engineering:Miura 1|Miura 1]] rocket.<ref>{{cite news |trans-title = PLD Space: the first European reusable rocket |title = PLD Space: el primer cohete reutilizable europeo |url = http://danielmarin.naukas.com/2016/11/02/pld-space-el-primer-cohete-reutilizable-europeos/#more-58088 |language = es |date = 2 November 2016 |first = Daniel |last = Marín |website = naukas.com}}</ref><ref name = "satmagazine 2022"/>

Early on in its development, the launch vehicle was referred to as ''Arion 2''; however, following the completion of a ten-month review conducted by the ESA and the decision to redesign the launcher to facilitate launches up to 300 kilograms to a 500-kilometer orbit, it was decided to adopt the name ''Miura 5''.<ref name = "double 2018">{{Cite web |url = https://spacenews.com/pld-space-after-esa-input-doubles-lift-capacity-of-smallsat-launcher/ |title = PLD Space, after ESA input, doubles lift capacity of smallsat launcher |date = 28 November 2018 |website = spacenews.com}}</ref><ref name='Rename Nov 2018'>{{cite press release |url = http://pldspace.com/new/2018/11/13/pld-space-miura/ |title = Since today, MIURA is the new PLD Space rocket's commercial brand |publisher = PLD Space |date = 13 November 2018 |access-date = 3 March 2019}}</ref>

===Test flights and partnerships===
On 11 April 2019, with the assistance of the Spanish Army, PLD Space performed a successful drop and recovery test of the first stage of a Miura 5 demonstrator at El Arenosillo Test Center.<ref>{{cite news |url = http://www.infoespacial.com/en/2019/04/15/news-space-army-land-exceeds-first-miura.html |title = PLD Space and the Spanish Army pass the first drop test of Miura 5 – Info-Space News Spain |last = info-space.com |date = 15 April 2019 |website = infoespacial.com |access-date = 2 August 2020}}</ref> This demonstration stage, which had a reduced 1.5 m diameter instead of 1.8 m, was dropped by a Boeing CH-47 Chinook helicopter from a height of 5&nbsp;km. It slowed its rate of descent using a total of three parachutes before performing a water landing, at which point it had been descending at a rate of roughly ten meters per second. The demonstrator was recovered by divers and brought back to Mazagón by a [[Engineering:Tugboat|tugboat]] to be thoroughly examined.<ref>{{Cite web |url = https://spacewatch.global/2019/04/spains-pld-space-successfully-completes-miura-5-reusable-booster-drop-test/ |title = Spain's PLD Space Successfully Completes Miura-5 Reusable Booster Drop Test |first = John |last = Sheldon |date = 17 April 2019 |website = spacewatch.global}}</ref><ref>{{cite web |url = https://www.esa.int/ESA_Multimedia/Videos/2019/04/Reusability_Drop_test_of_microlauncher_s_demonstration_first_stage/(lang) |title = Reusability: Drop test of microlauncher's demonstration first stage |publisher = European Space Agency |date = 15 April 2019}}</ref>

During July 2019, it was announced that PLD Space had reached an agreement with the French space agency [[Organization:CNES|CNES]] to study the launch of Miura 5 at the [[Organization:Guiana Space Centre|Guiana Space Centre]] (CSG) in French Guiana.<ref>{{cite tweet |number = 1145705155121287169 |user = PLD_Space |title = Today @PLD_Space and @CNES , and with the support of @CDTIoficial signed at #EUCASS2019 a preliminary Agreement to… |date = 1 July 2019}}</ref> Under a separate arrangement, the Spanish agency [[Organization:National Institute for Aerospace Technology|National Institute for Aerospace Technology]] (INTA) has also worked with PLD Space in securing a launch site at the El Hierro Launch Centre, which has been claimed by the company to be the optimal choice from a technical perspective.<ref>{{Cite web |url = https://www.defensa.com/en-abierto/entrevistamos-teniente-general-jose-maria-salom-director-general |title = Teniente general José María Salom, director general del INTA – Noticias Defensa En abierto |date = 14 April 2019 |website = defensa.com}}</ref> PLD Space has also publicly commented on the possibility of conducting launches from the planned spaceport in Azores, but the status of this proposal is presently uncertain.<ref name="auto"/> Company officials have estimated that the construction of a suitable ground facilities for launching will cost roughly €15 million.<ref name = "surinenglish oct2023"/>

During 2021, in light of the successful drop testing of the first stage, the ESA awarded a new contract to PD Space to continue with development of the Miura 5.<ref name = "satmagazine 2022"/> During mid 2023, an agreement was signed with CNES for the future maiden launch of the Miura 5 to be conducted at Guiana.<ref name = "surinenglish oct2023">{{cite web |url = https://www.surinenglish.com/spain/space-race-miura-rocket-20231009104947-nt.html |title = As Spain enters the space race, this is the successor to the Miura-1 rocket that will be three times taller and thirty times more powerful |website = surinenglish.com |first = Jon |last = Garay |date = 9 October 2023}}</ref><ref name = "atalayar Oct2023">{{cite web |url = https://www.atalayar.com/en/articulo/new-technologies-innovation/pld-wants-its-miura-5-rocket-to-take-off-from-french-guiana-in-early-2026/20231023123323192623.html |title = PLD wants its Miura 5 rocket to take off from French Guiana in early 2026 |first = Juan |last = Pons |date = 23 October 2023 |website = atalayar.com}}</ref>

==Launch schedule==
As of December 2023, the first test flight of Miura 5 is expected to take place sometime in early 2026.<ref name="reuters-20231020">{{cite web |last = Pinedo |first = Emma |url = https://www.reuters.com/technology/space/spains-pld-space-expects-first-orbital-launch-q1-2026-french-guiana-2023-10-20/ |title = Spain's PLD Space expects first orbital launch in Q1 2026 from French Guiana |work = {{wipe|Reuters}} |date = 20 October 2023 |access-date = 5 December 2023}}</ref> The initial model, which is planned to be used for the first two flights, will be entirely expendable. It will be superseded by an improved model of the Miura 5 that uses the recoverable first stage, which is intended to perform the planned commercial launches.<ref name = "satmagazine 2022"/>

==See also==
* {{annotated link|Engineering:Miura 1}}
* {{annotated link|Company:PLD Space}}
* {{annotated link|Engineering:List of orbital launch systems}}
* {{annotated link|Engineering:Zero 2 Infinity}}
* {{annotated link|Engineering:Capricornio (rocket)}}
* {{annotated link|Engineering:Themis programme}}

==References==
{{Reflist}}

==External links==
* [https://pldspace.com/en/miura-5 Official Miura 5 product website]

{{Reusable launch systems}}
{{European launch systems}}

[[Category:Partially reusable space launch vehicles]]

{{Sourceattribution|Miura 5}}