Samiksha Jaiswal (Editor)

VLS 1

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Manufacturer
  
CTA

Height
  
19.5 m (63.9 ft)

Status
  
Cancelled

Failures
  
2

Stages
  
3

Mass
  
50,700 kg (111,700 lb)

Country of origin
  
Brazil

Diameter
  
1.01 m (3.31 ft)

Total launches
  
2

No. boosters
  
4

Function
  
Payload to LEO
  
380 kg (830 lb)

VLS-1 VLS1

Launch sites
  
Centro de Lançamento de Alcântara

Vls 1 v02


The VLS-1 (Portuguese: Veículo Lançador de Satélites) was the Brazilian Space Agency's main satellite launch vehicle. The launch vehicle was to be capable of launching satellites into orbit. The launch site was located at the Alcântara Launch Center due to its proximity to the equator.

Contents

VLS-1 BINACIONAL BRASIL e UCRNIA Histria do VLS1 Fabricante IAE

Associated vehicles include the Sonda I, Sonda II, Sonda III and Sonda IV, the VS-30, VS-40 and VSB-30.

The VLS was cancelled after decades of development and high expenditures with poor results and a failed association with Ukraine that slowed years the program.

VLS-1 BRAZILIAN SPACE A MECTRON e a Misso VLS1 VSISNAV

Vls 1


History

VLS-1 BRAZILIAN SPACE Conhea a Verdade Sobre o Projeto do VLS1

VLS-1 development started in 1984, after the first launch of the Sonda IV rocket. To date, three prototypes have been built and two launches attempted, departing from the Alcântara Launch Center. During the V1 and V2 prototype launches (VLS-1 V1 and VLS-1 V2) technical problems prevented mission success, but allowed the testing of several vehicle components. The V3 prototype exploded on the launch pad on 22 August 2003, two days before its intended launch date. The 2003 Alcântara VLS accident caused a considerable setback to the Brazilian space program. The V4 prototype was expected to be launched in 2016.

The project was terminated by Brazilian Space Agency in 2016.

The Departamento de Ciência e Tecnologia Aeroespacial (DCTA) (Department of Aerospace Science and Technology) and the Agência Espacial Brasileira (AEB) (Brazilian Space Agency) informed on public audience before the VLS-1 project ended by the Senado Federal (Federal Senate) on February 16, 2016.

Current schedule

VLS-1 IAE prope reviso do Programa VLS1 Tecnodefesa

The V04 prototype was originally scheduled for launch in 2006. Further testing has resumed in 2008. The final VLS-1 schedule was as follows:

VLS-R1 test vehicle

The VLS-R1 test vehicle had two stages, arranged in the following configuration:

  • Stage 1 - four S-20 rocket engines
  • Stage 2 - one dummy S-20 rocket engine
  • VLS-R2 test vehicle

    The VLS-R2 test vehicle had two stages, arranged in the following configuration:

  • Stage 1 - four S-20 rocket engines
  • Stage 2 - one S-20 rocket engine
  • VLS-XVI 01 sub-orbital test vehicle

    VLS-1 httpsuploadwikimediaorgwikipediacommonsthu

    The VLS-XVI 01 sub-orbital test vehicle has three solid fuel rocket stages and boosters, arranged in the following configuration:

    VLS-1 BRAZILIAN SPACE Sonho do VLS1 Virou Pesadelo

  • Stage 0 - four S-43 rocket engines
  • Stage 1 - one S-43TM rocket engine
  • Stage 2 - dummy S-40TM rocket engine
  • Stage 3 - dummy S-44 rocket engine
  • VLS-1 operational configuration

    The VLS-1 has three solid fuel rocket stages and boosters, arranged in the following configuration:


  • Stage 0 - four S-43 rocket engines
  • Stage 1 - one S-43TM rocket engine
  • Stage 2 - one S-40TM rocket engine
  • Stage 3 - one S-44 rocket engine
  • The rocket has four 400N RCS jets, located on the top of the third stage.

    VLM

    The VLM (Veículo Lançador de Microssatélites) based on the S50 rocket engine is being studied, with the objective of orbiting satellites up to 150 kg in circular orbits ranging from 250 to 700 km. It will be a three-stage rocket, expected to launch the SHEFEX III mission by the German Aerospace Center (DLR) in 2016.

    VLS Alfa

    In the framework of the proposed Cruzeiro do Sul program, the VLS-1 rocket is the basis of the VLS Alfa project.

    L5 rocket based configuration - three-stage rocket, with the upper stage being liquid-fuel, putting 200 to 400 kg satellites into low equatorial orbits:

  • Stage 0 - four S-43 rocket engines
  • Stage 1 - one S-43TM rocket engine
  • Stage 2 - one S-40TM rocket engine
  • Stage 3 - one L5 rocket engine
  • L75 rocket based configuration - two-stage rocket, with the upper stage being liquid-fuel, putting 500 kg satellites equatorial orbits up to 750 km:

  • Stage 0 - four S-43 rocket engines
  • Stage 1 - one S-43TM rocket engine
  • Stage 2 - one L75 rocket engine
  • VLS Beta

    The VLS Beta is another related project, intended to lift up to 800 kg payloads to an 800 km equatorial orbit.

    Three-stage rocket, with the upper two stages being liquid-fuel.

  • Stage 1 - one P40 solid rocket engine
  • Stage 2 - one L300 rocket engines
  • Stage 3 - one L75 rocket engine
  • Projected flights are:

    VLS Gama

    The VLS Gama is intended to carry up to 1000 kg payloads to an 800 km polar orbit. Three-stage liquid-fuel rocket.

    VLS Delta

    The VLS Delta is capable of placing 2000 kg payloads in a geostationary orbit. Three-stage liquid-fuel rocket (VLS BETA body) with two solid fuel boosters.

    VLS Epsilon

    The VLS Epsilon is capable of placing 4000 kg payloads in a geostationary orbit. Three-stage liquid-fuel rocket (VLS BETA body) with two liquid-fuel boosters.

    References

    VLS-1 Wikipedia