TEPREL#TEPREL-B
{{short description|Family of rocket engines designed and built by Spanish company PLD Space}}
{{Infobox rocket engine
|name = TEPREL-C
|image =
|image_size = 240px
|caption =
|country_of_origin= Spain
|date =
|first_date =
|last_date =
|designer = PLD Space
|manufacturer = PLD Space
|purpose = {{plainlist|
- Booster stage engines
- Upper stage engine
}}
|associated =
|predecessor = TEPREL-B
|successor =
|status = Testing
|type =liquid
|oxidiser = LOX
|fuel = RP-1
|mixture_ratio =
|cycle = Gas-generator{{cite tweet|number=1483502909518229506|user=RaulTorresPLD|title=@Astro_Danyboy @isaraerospace @rfa_space @PLD_Space Thread 👉 Happy to give you accurate #MIURA5 figures: maximum pa…|date=18 January 2022}}
|pumps =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust =
|thrust_at_altitude=
|thrust(Vac) = {{cvt|50|kN|lbf|lk=in}}
|thrust(SL) = {{cvt|190|kN|lbf|lk=in}}{{cite tweet|number=1565269345915248640|user=RaulTorresPLD|title=MIURA5 first stage engines|date=1 September 2022}}
|throttle_range =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time =
|restarts =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in = Miura 5
|references =
|notes =
}}
{{Infobox rocket engine
|name = TEPREL-B
|image =
|image_size =
|caption =
|country_of_origin= Spain
|date =
|first_date =
|last_date =
|designer = PLD Space
|manufacturer = PLD Space
|purpose =
|associated =
|predecessor = TEPREL-A
|successor =
|status = Active
|type =liquid
|oxidiser = LOX
|fuel = Jet-A1
|mixture_ratio = 2.35
|cycle = Pressure-fed engine
|pumps =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust = {{cvt|30.2|kN|lbf|lk=in}} kN
|thrust_at_altitude=
|thrust(Vac) =
|thrust(SL) =
|throttle_range =
|thrust_to_weight=
|chamber_pressure= 22 bar
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time = 240 seconds
|restarts =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in = Miura 1
|references =
|notes =
}}
TEPREL is a family of rocket engines designed and built by the Spanish aerospace company PLD Space for their Miura 1 and Miura 5 launch vehicles. The TEPREL engine, named after the Spanish reusable engine program that is financing its development, uses kerosene and liquid oxygen as propellants.{{cite news|title=The Spanish Government supports PLD Space launchers development with a $1.56M TEPREL program|url=http://www.pldspace.com/blog/en/2016/04/07/spanish-government-teprel-program-aprroved/|accessdate=27 May 2018|agency=pldspace.com|date=27 April 2016|archive-date=28 May 2018|archive-url=https://web.archive.org/web/20180528052453/http://www.pldspace.com/blog/en/2016/04/07/spanish-government-teprel-program-aprroved/|url-status=dead}} So far, several versions of this engine, intended to propel Miura 1, have been developed and tested on the company's own liquid propulsion test facilities located in Teruel, Spain.{{cite news|title=PLD Space completes static-fire tests of Miura 1|first=Jeff |last=Foust|date=September 16, 2022|url=https://spacenews.com/pld-space-completes-static-fire-tests-of-miura-1/|publisher=Space News|access-date=November 28, 2022}}
Revisions
In the first versions of the engine the propellants are driven to the engine by using a pressure-fed cycle with helium.{{cite web|url=https://pldspace.com/images/MIURA_1/MIURA1_Payload_Users_Guide.pdf|title=MIURA 1 – Payload User's guide |date=November 2018|publisher=pldspace.com|access-date=November 28, 2022}} Later versions of the engine (TEPREL-C) incorporate a turbopump.
=TEPREL-DEMO=
The TEPREL-DEMO engine, originally called NetonVac1, was first tested in 2015. It is a calorimetric engine model, intended to demonstrate combustion stability as well as to acquire relevant information such as ignition and shut-down sequences, pressures and temperatures along the engine, thrust and propellant mass flow rates at different thrust profiles. Additionally, the engine served to test all associated hardware and software at PLD Space Propulsion Test Facilities. The engine is capable to produce a thrust of 28 kN at sea level.{{cite news|title=PLD Space ready to test its new engine|url=http://www.pldspace.com/blog/en/2017/07/10/2562/|accessdate=27 May 2018|agency=pldspace.com|date=10 Jul 2017|archive-date=18 June 2018|archive-url=https://web.archive.org/web/20180618175347/http://www.pldspace.com/blog/en/2017/07/10/2562/|url-status=dead}}{{cite news|last1=Marín|first1=Daniel|title=Europa apuesta por PLD Space para alcanzar el espacio|url=http://danielmarin.naukas.com/2018/02/16/europa-apuesta-por-pld-space-para-alcanzar-el-espacio/|accessdate=27 May 2018|date=16 Feb 2018}}
=TEPREL-A=
With the TEPREL-A engine, first tested in 2017, the company included several design upgrades, such as a new combustion chamber design,{{cite tweet |author=PLD Space |user=PLD_Space |number=882519746125680641 |date=5 July 2017 |title=Hoy tenemos el honor de presentar la nueva cámara de combustión de TEPREL-A,nuevo motor cohete regenerativo de @PLD_Space #GoPLD #GoARION1 https://t.co/SSi7uJJVRN |language=es |access-date=31 December 2020}} an improved injector geometry and a regenerative cooling system. The later enables the engine to fire for nearly 2 minutes, which is the envisaged nominal functioning duration for the suborbital launch vehicle Miura 1. At sea level, the engine produces a thrust of 32 kN.
=TEPREL-B=
TEPREL-B is the first flight version of the TEPREL engine. Several design improvements have been implemented to reduce the overall weight of the engine. It is equipped with a thrust vector control system{{Cite web|url=https://spacenews.com/pld-space-completes-critical-testing-of-its-teprel-b-rocket-engine/|title = PLD Space completes critical testing of its Teprel-B rocket engine|date = 31 August 2020}} and a convergent-divergent nozzle, all regeneratively cooled.{{cite tweet |author=Raúl Torres🇪🇸 |user=RaulTorresPLD |number=1301132303297519616 |date=2 September 2020 |title=@CarCamMar @PLD_Space Yes, to all. #TEPREL-B has convergent-Divergent nozzle, all regeneratively cooled, providing 32.3kN (SL) at full thrust and designed to work more than 1000s accumulated. |language=en |access-date=31 December 2020}} In May 2019 the first unit of this model was destroyed during a test. After a long investigation PLD Space concluded that the problem was due to excess pressure during engine start at ignition. PLD Space addressed the issue through a combination of improvements to the launch site infrastructure and procedural improvements.{{Cite web|url=https://spacenews.com/pld-space-books-first-suborbital-flight-nears-resolution-of-engine-setback/|title = PLD Space books first suborbital flight, nears resolution of engine setback|date = 5 February 2020}} It is currently fully operational. In February 2020, PLD Space successfully completed a 122-second test that allowed it to achieve flight rating.{{cite web|url=https://www.defensa.com/aeronautica-y-espacio/exito-ensayo-motor-cohete-para-lanzador-reutilizable-pld-space|title=Éxito en el ensayo del motor cohete para el lanzador reutilizable de PLD Space|date=February 27, 2020|publisher=defensa.com|access-date=November 28, 2022}}
On August 28, 2020, PLD Space completed required tests for the thrust vector control system on the Teprel-B rocket engine.
=TEPREL-C=
Flight version of the TEPREL engine{{Cite web|url=https://danielmarin.naukas.com/2017/01/09/pld-space-mas-cerca-del-espacio/|title = PLD Space más cerca del espacio|date = 9 January 2017}} to be used in the Miura 5 rocket. Initially it was expected to produce 105.5 kN{{Cite web|url=https://danielmarin.naukas.com/2021/11/26/la-guia-definitiva-del-cohete-miura-1-de-pld-space/|title=La guía definitiva del cohete Miura 1 de PLD Space|date=26 November 2021}} of thrust at sea level.{{cite web|url=https://esamultimedia.esa.int/docs/space_transportation/LAUNCHER_WS_Presentation_PLDSpace.pdf |title=PLDSpace|date=November 6, 2018|publisher=ESA Microlaunch Services Workshop|access-date=November 28, 2022}} Later expected thrust was increased to 190 kN.
=TEPREL-C vacuum=
Version of TEPREL-C adapted to vacuum, and capable of re-ignition in microgravity conditions.{{cite tweet |author=Raúl Torres🇪🇸 |user=RaulTorresPLD |number=1290394275230883840 |date=3 August 2020 |title=@Eurekablog @PLD_Space Arriba a la derecha, en otro palé se ve la cuaderna que hay entre el tanque de oxígeno y la interetapa de MIURA5, también sometida a ensayo destructivo. Al fondo de la imagen, se aprecia uno de los laterales del "erector" de MIURA 1, en el foso de ensamblaje. |language=es |access-date=31 December 2020}} Capable of 45 kN of thrust.