VS-40

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VS-40 (Foguete Suborbital VS-40)
VS-40 rocket on display in Brazil
FunctionSounding rocket
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).Brazil
Size
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).9.5 m (31 ft)
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).1.01 m (3 ft 4 in)
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).6,800 kg (15,000 lb)
Stages2
Capacity
Payload to sub-orbital flight
Altitude650 km (400 mi)
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).500 kg (1,100 lb)
Launch history
StatusActive
Launch sitesAlcântara Space Center, Andøya Space, Barreira do Inferno Launch Center
Total launches3
Failure1[1]
First flight2 April 1993
First stage – S40TM
Gross mass4,200 kg (9,300 lb)
Specific impulse275 seconds (2.70 km/s)
Burn time56 seconds
Second stage – S44M
Gross mass810 kg (1,790 lb)
Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value).33.24 kN (7,470 lbf)
Specific impulse282 seconds (2.77 km/s)
Burn time68 seconds
[[[d:Lua error in Module:WikidataIB at line 2822: attempt to index field 'wikibase' (a nil value).|edit on Wikidata]]]

The VS-40 (Foguete Suborbital VS-40) is a Brazilian sounding rocket using solid fuel and stabilized aerodynamically.

The original version, VS-40, uses the S-40TM (4,200 kg) first stage engine and the S-44M (810 kg) second stage engine.[2][3][4] This configuration corresponds to the upper stages of the VLS-1 rocket.[5]

Version VS-40M used a S-40M engine for the first stage.[4]

Flights

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VS40 performed the following flights:[4][6][7][8][9][10][1][11]

Date Version Flight Site Mission
1993/04/02 VS-40 V01 Alcântara Operação Santa Maria - Qualifying flight for the S44 engine. 760 seconds in micro-gravity.[4]
1998/03/21 VS-40 V02 Alcântara Operação Livramento - VAP-1 (Fokker) payload.[12]
2012/06/22 VS-40M V03 Andøya SHEFEX (Sharp Edge Flight Experiment) II payload.[9][10]
2015/11/13 VS-40M Alcântara Operação São Lourenço - SARA Suborbital 1 (reentry experiment) – Failure (exploded on pad) [6][7][8][1][12]

A flight of VS-40M carrying "SARA Suborbital 2" was planned but eventually cancelled. A future flight of VS-40M carrying HIFiRE 8 is in development.[4]

Characteristics

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VS-40
  • Length (mm) 6725
  • Payload Mass (kg) 500
  • Diameter (mm) 1000
  • Total takeoff mass (kg) 6,737
  • Mass of propellant (kg) 5,054
  • Structural mass (kg) 1,028
  • Apogee (km) 650
  • Microgravity time (s) 760

S-40 rocket engine

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The S-40 is a solid-propellant rocket motor developed and manufactured by Avibras Aeroespacial, a Brazilian aerospace company, primarily for use in sounding rockets. Different versions were used on several rockets:[4]

  • S-40 - first stage of Sonda-4;
  • S-40TM - first stage of VS-40; third stage of VLS-1;[5][13]
  • S-40M - first stage of VS-40M; second stage of VLM.

S-40TM specifications:[13]

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  • Total mass: 5664 kg
  • Unfueled mass: 1212kg
  • Thrust: 208.39 kN
  • SI: 275 seconds
  • Burn time: 56 s

S-44 rocket engine

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The S-44 is a solid-propellant rocket motor developed by the Instituto de Aeronáutica e Espaço (IAE), part of Brazil’s Departamento de Ciência e Tecnologia Aeroespacial (DCTA).[14] It was used as second stage of VS-40 and VS-40M; the third stage of VLM and the fourth stage of VLS-1.[4]

S-44 specifications:[14]

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  • Total mass: 1025 kg
  • Unfueled mass: 190 kg
  • Thrust: 33.24 kN
  • SI: 282 seconds
  • Burn time: 68 s

References

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  10. ^ a b [1][dead link]
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  14. ^ a b Lua error in Module:Citation/CS1/Configuration at line 2172: attempt to index field '?' (a nil value).
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