Tronador (rocket)

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Tronador II
Cohete Tronador II.JPG
Tronador II rocket
Function Orbital launch vehicle
Manufacturer CONAE
Country of origin Argentina
Size
Height 33 m (108ft)
Diameter 2.5m - 1.5m
Mass 64000 kg
Stages 3
Capacity
Payload to LEO 200 - 400 kg
Launch history
Status In development
Launch sites Puerto Belgrano Naval Base
First flight 2014
First stage
Engines 3
Thrust 3 x 30000 kg
Burn time
Fuel Monomethyl-Hydrazine/N2O4
Second stage
Engines 1
Thrust 30000 kg
Burn time
Fuel Monomethyl-Hydrazine/N2O4
Third stage - T4000
Engines 1
Thrust 4000 kg
Burn time
Fuel

Tronador (Thunderer) is a series of Argentine rockets, including the Tronador II, a liquid propellant expendable launch system which is under development.

The Tronador I rocket is an unguided liquid-fueled rocket,[citation needed] used for suborbital test flights. It will lead to the larger Tronador II, which will have an guidance system and be capable of reaching low Earth orbit.[1] It is expected to make its maiden flight in 2014.[2]

Tronador I[edit]

One Tronador I (T1) vehicle was flown, on the June 6, 2007[3] from the Puerto Belgrano Naval Base.

Characteristics[edit]

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

Tronador Ib[edit]

One Tronador Ib (T2) vehicle was flown, on the August 5, 2008[3] from the Puerto Belgrano Naval Base.

Characteristics[edit]

  • Length: 3,400 mm
  • Stages: 1
  • Total takeoff mass: 60 kg
  • Payload mass: 4 kg
  • Apogee: 15~20 km
  • Thrust: 1,500 kgf x 10 sec

Tronador II[edit]

Tronador2B.jpg

In 2013 a prototype named VEX1 will be launched from Pipinas, Punta Indio Partido,[4] followed by five more.[5] The full Tronador II is expected to launch in 2015 from the Puerto Belgrano Naval Base[4] (near Bahía Blanca).

Program[edit]

The "Vex" prototipe plan is as follows:[6][7][8][9][10]

Demonstrator missions:

  • Vex1 - [11][10] only one stage, 2.8 tonnes, 4t engine, 60 seconds mission, apogee of 16 km.

Vex1B and Vex1C are expected to be launched one and two months after Vex1A.[12] Vex1A failed two launch attempts on January and February 2014.[13][14]

  • Vex2 - first stage 3 x 4t engines, second stage single 4t engine
  • Vex3 - 30t engine
  • Vex4 - 30t engine
  • Vex5 - first stage 3 x 30t, second stage 1 x 30t with RCS control and separation at 80 km

Orbital capable Tronador II:

  • First flight - 2015[10]

Characteristics[edit]

The projected Tronador II rocket has the following configuration:[15]

Tronador2.2b.jpg
  • Length: 33,000 mm
  • Stages: 3
  • Diameter: 2.5m - 1.5m
  • Empty mass: 8,000 kg
  • Total weight: 64,000 kg
  • Payload mass: 200-400 kg[1]
  • Apogee: 600-700 km
  • 1st stage thrust: 90t (3x30t)
  • 2nd stage thrust: 30t
  • 3rd stage engine: 4t thrust, 60 seconds burn, 2,800 kg of fuel

T4000[edit]

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 rest the attitude control system (“Trans Vector Control” - TVS).[7] The first launch attempt in 2011 failed.[16]

Characteristics[edit]

  • Diameter: 438 mm[17]
  • Thrust: 40 kN
  • Impulse time: 10 seconds[6]

External links[edit]

See also[edit]

References[edit]