Tronador (rocket)

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 (''Inyector Satelital de Cargas Utiles Ligeras'', Light-Payload Satellite Launcher).

The Tronador I is an unguided liquid-fueled rocket 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. Development of the satellite launch vehicle has cost more than 600 million dollars over several years.

Tronador I

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

Tronador I (T1)

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

Characteristics

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

Tronador Ib (T2)

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

Characteristics

* 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

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). 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

* 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

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.

Early proposals

The initial proposal was for a 3-stage rocket. In early 2015, an evolved configuration was presented at the 52nd Committee on Peaceful Uses of Ultra-Terrestrial Space meeting and at the Punta Indio () test launch pad:

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

File:Cohete Tronador II.JPG
File:Maqueta del Tronador II en el Puerto espacial de Punta Indio.jpg
File:Tronador II.jpg
File:Piramidetronador-tecnópolis.JPG
File:Tecnópolis cohete Tronador II.JPG
File:TronadorIMPTecnopolis.JPG
File:Tronador2B.jpg

Characteristics

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

* Length: 27 m
* Stages: 2
* Diameter: 2.5 m
* Total weight: 72,000 kg
* Payload mass: 600 kg
* 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) /

File:Newmockup.png, Tronador II dimensions
File:Stand Soberanía Espacial en Técnopolis Octubre 2022 02.jpg, Tronador II mockup
File:Visita Alberto Fernández a CEPI 05.jpg, First stage tank of the Tronador rocket

TII-250

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

Tronador II prototypes

T4000

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. Specifically, it was intended to house the attitude control system (“Thrust Vector Control” - TVS). The first launch attempt in 2011 failed.

;Characteristics
* Diameter: 4.38 m
* Thrust: 4,000 kg (40 kN)
* Burn time: 10 seconds

VEx

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. 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. However, in November 2021, it was announced that the program were reactivated again.

=VEx-1A

=

In March 2014, a suborbital prototype named VEx-1A failed during launch from Pipinas, Punta Indio Partido. 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. 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

=

The first flight of this suborbital vehicle was on 15 August 2014 from Pipinas, Punta Indio Partido. 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

=

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. 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. 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. 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.

=VEx-5B

=
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, before were announced in November 2021 that the mission were reactivated again.

=VEx-5C

=
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. The mission was cancelled in 2017, before were announced in November 2021 that the mission were reactivated again.

=VEx-6

=
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.

TII-70 and TII-150

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

* 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

The proposed Tronador III would have the same diameter as Tronador II, but would have a length of . 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.

Characteristics

Proposed Tronador III configuration:

* 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)''

Tronador III will be preceded by the VLE (''Vehículo Lanzador Espacial'' for Space Launch Vehicle) capable of placing an 80 kg payload on a 300 km orbit. 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.

See also

* List of rockets
* Comparison of orbital launch systems

References

External links

Rocket.com.br
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{{Orbital launch systems

Sounding rockets of Argentina
Space programme of Argentina