Wikipedia

Tronador (rocket)

(Redirected from Tronador I)

Tronador (Spanish for Thunderer) is a series of Argentine rockets, including the Tronador I and Tronador II vehicles, to develop a liquid-propellant rocket expendable launch system called ISCUL[1] (Inyector Satelital de Cargas Utiles Ligeras, Light-Payload Satellite Launcher).

The Tronador I is an unguided liquid-fueled rocket[2] used for sub-orbital test flights. Its development led to the larger VEx test rocket, testing technologies needed for the Tronador II, which has a guidance system and would be capable of reaching low Earth orbit.[2] Development of the satellite launch vehicle has cost more than 600 million dollars over several years.

Tronador I

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Tronador I

The Tronador I is an unguided liquid-fueled rocket[2] used for sub-orbital test flights.

Tronador I (T1)

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The Tronador I (T1) vehicle was flown successfully on June 6, 2007[3][4] from Puerto Belgrano Naval Base near Bahía Blanca,[3][5] in the south east of the Buenos Aires Province. This was the first flight of a technology demonstrator vehicle for the program.

Characteristics

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  • Length: 3,400 mm
  • Stages: 1
  • Total takeoff mass: 60 kg
  • Payload mass: 4 kg
  • Thrust (x 10 s): 500 kgf

Tronador Ib (T2)

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The Tronador Ib (T2) vehicle was flown successfully on August 5, 2008[3][4] from Puerto Belgrano Naval Base.[5] This was the second technology demonstrator vehicle flown for the program.

Characteristics

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  • Length: 3,400 mm
  • Stages: 1
  • Total takeoff mass: 60 kg
  • Payload mass: 4 kg
  • Apogee: 15–20 km
  • Thrust (10 s): 1,500 kgf

VS-30

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This was the first cooperative test flight between Comisión Nacional de Actividades Espaciales and Brazilian Space Agency; it was successfully flown in December 2007 (Operacion Angicos).[6][7][8][9] The payload built by CONAE, carried several experiments to validate subsystems for the program such as: IMU (Inertial Measurements Unit, that used IFOG's), GPS receptor (for navigation), all integrated into the on-board computer, and an attitude control system via cold-gas thrusters. The payload unit completed a suborbital flight carried by an AEB-built VS-30 solid-propellant rocket booster, and was then recovered from the sea after landing with parachutes.

Characteristics

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  • Length: 3,288 mm (Payload module)
  • Stages: 1 (VS-30 booster)
  • Total takeoff mass: 1,500 kg
  • Payload mass: 242.1 kg
  • Apogee: 120–160 km
  • Specific Impulse: 266 s (VS-30 booster)

Tronador II

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Tronador II
 
FunctionOrbital launch vehicle
ManufacturerCONAE
Country of originArgentina
Size
Height27 m (89 ft)
Diameter2.5 m (8 ft 2 in)
Mass72,000 kg (159,000 lb) (including propellant)
Stages2
Capacity
Payload to Polar
Mass600 kg (1,300 lb)
Launch history
StatusUnder development
Launch sitesManuel Belgrano Space Center
First flight2030
First stage
Powered by3 T30
Maximum thrust3 × 30,000 kg
PropellantLOX / RP-1
Second stage
Powered by1 other or T4R
Maximum thrust1400 to 4000 kg
PropellantMonomethylhydrazine (MMH) / N2O4
[edit on Wikidata]

As of 2020, Tronador II's maiden orbital launch is expected to fly in "the next 4 years", according to the National Commission for Space Activities.[10]

Early proposals

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The initial proposal was for a 3-stage rocket. In early 2015, an evolved configuration[11] was presented at the 52nd Committee on Peaceful Uses of Ultra-Terrestrial Space meeting[12] and at the Punta Indio (35°31′25″S 57°11′05″W / 35.523496°S 57.1846139°W / -35.523496; -57.1846139 (Centro Espacial Punta Indio - Sector L)) test launch pad:

  • First Stage: 90 t total thrust (3 x 30 t engines)
  • Second Stage: 30 t thrust
  • Third stage: 4 t thrust

Characteristics

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As of June 2016, the proposed Tronador II configuration was:[13]

  • Length: 27 m
  • Stages: 2
  • Diameter: 2.5 m
  • Total weight: 72,000 kg
  • Payload mass: 600 kg[14]
  • Apogee: 600 km
  • Lower Stage: 90 t total thrust (3x30 t engines) at sea level. Fuel: RP-1 / LOX
  • Upper stage: 1.4 t to 4 t thrust (single pressurized engine) at sea level (2 t to 5.5 t in vacuum). Fuel: Monomethylhydrazine (MMH) / N2O4
  •  
    Tronador II dimensions
  •  
    Tronador II mockup
  •  
    First stage tank of the Tronador rocket

TII-250

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Infographic of the Tronador II-250 rocket

In late 2022 Tronador II was named TII-250, with the launch site being indicated as Centro Espacial Manuel Belgrano (CEMB), in Bahía Blanca.[15][16]

Tronador II prototypes

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T4000

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The T4000 (Tronador T4000 pathfinder rocket) test rocket is related to the project, as it is the basis of the 3rd stage of the Tronador II.[3] Specifically, it was intended to house the attitude control system (“Thrust Vector Control” - TVS).[17] The first launch attempt in 2011 failed.[18]

Characteristics
  • Diameter: 4.38 m [19]
  • Thrust: 4,000 kg (40 kN)
  • Burn time: 10 seconds[20]

VEx

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The recent strategy was to fly separately several suborbital experimental subsystems, called "VEx", before they are incorporated in the prototype of the Tronador II rocket.[2][17][20][21][22][23] After a few launches, it was decided in 2017 to stop the experimental VEx series as enough data was obtained to go ahead with a prototype rocket.[24] However, in November 2021, it was announced that the program were reactivated again.

VEx-1A
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VEx-1A at its launch pad, Punta Indio Spaceport

In March 2014, a suborbital prototype named VEx-1A failed during launch from Pipinas, Punta Indio Partido.[2][23][25][26] It had only one stage, weigh 2.8 tonnes, thrust of 4 ton, with an expectation of 60 seconds mission duration and expected apogee of 2 km. VEx-1A first launch attempt was postponed in December 2013 due to ground support equipment fail. The second attempt failed on February 26, 2014.[27][28] It was discovered that the failure was caused by interferences between the launch pad and the rocket, which prevented the vehicle from elevating more than 2m off the ground. The engine control mechanism shut off the fuel valve, preventing an explosion, and the rocket fell down next to the pad.

VEx-1B
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VEx-1b being rolled to its launch pad at the Punta Indio Space Center.

The first flight of this suborbital vehicle was on 15 August 2014 from Pipinas, Punta Indio Partido.[14] It successfully tested propulsion, control, and navigation subsystems. The mission concluded with 2,200 m apogee altitude and 27 seconds flight time. It landed in the sea assisted by the recovery parachutes. The vehicle was recovered and examined to determine whether further VEx-1 test rockets are required or if a VEx-2 flight should proceed.

VEx-5A
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The prototype of the Tronador II rocket, VEX-5A in its launch complex.

VEx-5A was a two-stage suborbital rocket that was destroyed upon launch. The T-10 first stage is capable of producing 11t of thrust, while the T-4 second stage is capable of 4t of thrust. The rocket was 18 meters long and 1.5 meters diameter, with a total launch weight (including fuel) of 8500 kg.[29][11] The rocket would have separated from the first stage (the propellants are liquid oxygen / RP-1) at 15 km altitude and the second stage would have continued, reaching up to 30 km altitude using hydrazine / nitric acid.[30] The vehicle would have tested several technologies, new fuels, and for the first time, the interstage separation (mechanical and automatic aspects), and the ignition of the second stage. The rocket was completed in mid 2015 and scheduled to launch in October 2015, but postponed to November 2016, before postponed again.[31] The test flight finally occurred on 21 April 2017, 18:00 local time from Pipinas, Punta Indio Partido. The rocket climbed up from its pad, but eight seconds later the first stage rocket engine shut down due to abrupt flow in its fuel lines. Several seconds later, the rocket fell and impacted the launch pad, causing a fiery explosion. The ill-fated launch was announced officially by CONAE several hours after the launch and footage from several angles were made available.[32][33][34][35]

VEx-5B
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Test flight - single stage 30t thrust engine rocket - it was projected for a 2018 launch from Pipinas, Punta Indio Partido. The mission was cancelled in 2017,[24] before were announced in November 2021 that the mission were reactivated again.

VEx-5C
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Test flight - two stage test rocket. First stage 30t thrust engine, second stage VEx-1 engine - it was projected for a 2019 launch from Puerto Belgrano Naval Base.[36][37][38][39] The mission was cancelled in 2017,[24] before were announced in November 2021 that the mission were reactivated again.

VEx-6
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Test flight of the rocket. Investment of approximately $45 million in the Tronador SLV program was announced in 2022, including associated experimental rockets VEx-5 and VEx-6.[40]

TII-70 and TII-150

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Tronador II family with TII-70 and TII-150 prototypes

In late 2022, two Tronador II prototypes, with the goal of engine testing were announced:[15]

  • TII-70 (150 km apogee, 11 m length, 2.2 ton weight, launched from Punta Indio Space Center - CEPI)
  • TII-150 (400 km apogee, 20 m length, 23 ton weight, launched from Centro Espacial Manuel Belgrano - CEMB)

Tronador III

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The proposed Tronador III would have the same diameter as Tronador II, but would have a length of 34 metres (112 ft). The fueled rocket would weight 90 metric tons, and capable of delivering satellites with up to 750 kg to a 600 km orbit, or up to a ton if upper stages are used.[41][42][43][44]

Characteristics

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Proposed Tronador III configuration:[45][46]

  • Length: 35 m
  • Stages: 2
  • Diameter: 2.5 m
  • Empty mass: 6,600 kg
  • Total weight: 90,000 kg
  • Payload mass: 1000 kg
  • Apogee: 600 km
  • Lower Stage: 120t total thrust (4 × 30t engines) at sea level. Fuel: RP-1/LOX
  • Upper stage: 3t thrust (single engine). Fuel: MMH/NTO

VLE (Vehículo Lanzador Espacial)

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Tronador III will be preceded by the VLE (Vehículo Lanzador Espacial for Space Launch Vehicle) capable of placing a 80 kg payload on a 300 km orbit.[46][47][43][44] This would be a two stage rocket, with the first stage using 5 or more Karut engines with 2.5 t of thrust and burning RP-1/LOX.[46][47]

See also

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References

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  1. ^ "La Facultad de Ingeniería participará en el desarrollo del" (PDF). Proyectarse. 15 (71): 20–22. December 2008. Archived from the original (PDF) on 2014-08-21. Retrieved 2014-08-20.
  2. ^ a b c d e "Comisión Nacional de Actividades Espaciales - Tronador II". Conae.gov.ar. Archived from the original on 2015-09-05. Retrieved 2015-12-20.
  3. ^ a b c d "Comisión Nacional de Actividades Espaciales - Tronador". Conae.gov.ar. Archived from the original on 2015-09-23. Retrieved 2015-12-20.
  4. ^ a b "Tronador". Argentina.gob.ar (in Spanish). 2018-04-04. Retrieved 2023-12-08.
  5. ^ a b "free forum : grandprix". Grandprix.forochile.org. Retrieved 2015-12-20.[permanent dead link‍]
  6. ^ "Argentina y Brasil lanzan cohete con experimentos GPS". MundoGEO. 21 December 2007.
  7. ^ "CELPA 1 Chamical on Facebook". Facebook. Archived from the original on 2022-04-30.[user-generated source][self-published]
  8. ^ Aicke. "Desarrollo Argentino de instrumental aeroespacial" (PDF). AviaciónArgentina.net.
  9. ^ De Dicco, Ricardo (2008). "Acceso al Espacio". 1library.co.
  10. ^ "Argentina Aspires to Have its Own Pitcher in Four Years". infoespecial.com. Retrieved 2021-04-28.
  11. ^ a b Brügge, Norbert. "Tronador LSA". Space Launch Vehicles. Retrieved 2017-10-04.
  12. ^ Alvarez, Pablo (8 February 2015). "¿Nuevo diseño para el Tronador II?". Argentina en el Espacio. Retrieved 2015-12-20.
  13. ^ "Comisión Nacional de Actividades Espaciales - Tronador II". Archived from the original on 2015-09-05. Retrieved 2014-08-12.
  14. ^ a b "Comisión Nacional de Actividades Espaciales - 2014". Conae.gov.ar. Archived from the original on 2015-09-07. Retrieved 2015-12-20.
  15. ^ a b "Argentina desarrolla el primer prototipo de lanzador de satélites". Argentina.gob.ar (in Spanish). 2022-10-03. Retrieved 2023-12-08.
  16. ^ "Facilidades auxiliares". Argentina.gob.ar (in Spanish). 2018-04-04. Retrieved 2023-12-08.
  17. ^ a b "Escalera al cielo, peldaño a peldaño (Serie Tronador II)". Portinos.com. 2015-03-18. Retrieved 2015-12-20.
  18. ^ Falcão, Duda (December 11, 2011). "Informação Extraoficial Confirma Falha do Foguete T-4000". BRAZILIAN SPACE. Retrieved 2015-12-20.
  19. ^ Brügge, Norbert. "T-4000, Gallery". Space Launch Vehicles. Retrieved 2015-12-20.
  20. ^ a b "Argentina's SLV development". Forum.nasaspaceflight.com. Retrieved 2015-12-20.
  21. ^ "Proyecto de Inversión Pública. Secretaría de Política Económica". Mecon.gov.ar. 2015-11-30. Retrieved 2015-12-20.
  22. ^ "Argentina's SLV development". Forum.nasaspaceflight.com. Retrieved 2015-12-20.
  23. ^ a b Rey, Patricia (2013-10-14). "Argentina To Put First Satellite In Space Using Own Launch Technology By 2015". Ibtimes.com. Retrieved 2015-12-20.
  24. ^ a b c Bruno Massare. "Varotto: "A fines del año que viene deberíamos tener un lanzador satelital"" (in Spanish). TSS. Retrieved 2018-01-31. Decidimos interrumpir el desarrollo de los vehículos experimentales (la serie VEX) porque consideramos que con lo ya hecho no íbamos a aportar mucho más con otro experimental que lo que aportaría el modelo tecnológico.
  25. ^ "Cohete Tronador II: más que un monumento de Tecnópolis". Colonbuenosaires.com.ar. Retrieved 2015-12-20.
  26. ^ "Argentina lanzará un cohete de diseño nacional que pondrá en órbita satélites de observación". Infobae.com. Retrieved 2015-12-20.
  27. ^ "El cohete despegó y explotó". Punta Indio Web. 2014-02-26. Retrieved 2015-12-20.
  28. ^ "Un despegue fallido - 07.03.2014 - LA NACION". La Nación. 7 March 2014. Retrieved 2015-12-20.
  29. ^ Farre, Cecilia (March 14, 2016). "Planean más pruebas para el lanzador de satélites argentino". Perfil. Archived from the original on 2016-06-02.
  30. ^ Clarín.com (2016-11-22). "Vex 5-A: lanzan el tercer cohete experimental argentino". Clarín (in Spanish). Retrieved 2023-10-02.
  31. ^ "Página/12 :: Economía :: Una foto junto al cohete heredado". www.pagina12.com.ar. Retrieved 2016-09-30.
  32. ^ Clarín.com (2017-04-22). "Video: un cohete lanzado en Punta Indio tuvo problemas y se estrelló". Clarín (in Spanish). Retrieved 2023-10-02.
  33. ^ Digital, Redacción (2017-04-29). "Un vehículo experimental argentino se estrella nada más despegar". Ultima Hora (in Spanish). Retrieved 2023-10-02.
  34. ^ "Exclusivo: el Gobierno ocultó la explosión de un cohete lanzado por CONAE". www.politicargentina.com. Retrieved 2023-10-02.
  35. ^ "Видео взрыва ракеты VEX-5 при запуске в Аргентине появилось в Сети". РЕН ТВ (in Russian). 2017-04-29. Retrieved 2023-10-02.
  36. ^ "El INVAP de Bariloche ya prepara el Arsat 2 y 3 para 2015 y 2017". Energypress.com.ar. Retrieved 2015-12-20.
  37. ^ "VEX1 - Machtres Aeronautica y Espacio". Machtres.com. 2014-09-25. Retrieved 2015-12-20.
  38. ^ Krebs, Gunter D. "VEx-5". Gunter's Space Page.
  39. ^ "Argentina's SLV development". Forum.nasaspaceflight.com. Retrieved 2015-12-20.
  40. ^ "Space Programs - The World Factbook". www.cia.gov. Retrieved 2023-10-02.
  41. ^ Conrado Varotto (27 August 2015). "Plan Espacial Nacional - 27 de Agosto de 2015 - Seminario DAR" (PDF). Archived from the original (PDF) on 2016-03-04. Retrieved 2018-02-01.
  42. ^ Abel (2020-09-17). ""Es fundamental que se materialice el Proyecto Tronador III"". AgendAR (in Spanish). Retrieved 2020-11-24.
  43. ^ a b Pugliese, Pablo (2020-10-12). "El Plan de Acceso al Espacio y la importancia de que Argentina cuente con un lanzador". Escenario Mundial (in Spanish). Retrieved 2023-12-08.
  44. ^ a b "Reactivación espacial – Agencia TSS" (in European Spanish). Retrieved 2023-12-08.
  45. ^ García, Javier (2 September 2015). "CONAE proyecta el Tronador III". Argentina en el Espacio.
  46. ^ a b c "VLE, Nuevo Enfoque de CONAE". VLE, Nuevo Enfoque de CONAE. Retrieved 2020-11-24.
  47. ^ a b "VLE, nuevo enfoque de CONAE". Latam Satelital (in Spanish). 2020-07-19. Retrieved 2023-12-08.
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