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VLS Launch Vehicle
All-solid orbital launch vehicle. Country: Brazil. Status: Active. Other Designations: Veiculo Lancador de Satelites.

Brazilian satellite launcher building on successful family of sounding rockets.

Manufacturer: INPE. Launches: 7. Failures: 4. Success Rate: 42.86%. First Launch Date: 1985-12-01. Last Launch Date: 2003-08-22. Launch data is: continuing. LEO Payload: 380 kg (830 lb). to: 200 km Orbit. at: 5.00 degrees. Payload: 80 kg (176 lb). to a: sun synchronous, 800 km, 98.6 deg orbital trajectory. Associated Spacecraft: SACI, SCD. Liftoff Thrust: 1,048.900 kN (235,802 lbf). Total Mass: 49,609 kg (109,369 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 19.50 m (63.90 ft). Development Cost $: 300.000 million. in: 1990 average dollars. Flyaway Unit Cost $: 8.000 million. in: 1999 unit dollars. Version:

VLS-R1. All-solid test vehicle. Status: Retired 1989.

Single stage vehicle.

Launches: 2. Failures: 1. First Launch Date: 1985-12-01. Last Launch Date: 1989-05-18. Apogee: 50 km (31 mi). Liftoff Thrust: 300.000 kN (67,440 lbf). Total Mass: 9,000 kg (19,800 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 9.00 m (29.50 ft).

  • Stage0: 4 x S-43. Gross Mass: 8,550 kg (18,840 lb). Empty Mass: 1,328 kg (2,927 lb). Motor: 1 x S-43. Thrust (vac): 303.000 kN (68,117 lbf). Isp: 260 sec. Burn time: 59 sec. Length: 9.00 m (29.50 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage1: 1 x S-43TM. Gross Mass: 8,720 kg (19,220 lb). Empty Mass: 1,536 kg (3,386 lb). Motor: 1 x S-43TM. Thrust (vac): 320.600 kN (72,074 lbf). Isp: 277 sec. Burn time: 58 sec. Length: 8.10 m (26.50 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage2: 1 x S-40TM. Gross Mass: 5,664 kg (12,486 lb). Empty Mass: 1,212 kg (2,672 lb). Motor: 1 x S-40TM. Thrust (vac): 208.390 kN (46,848 lbf). Isp: 275 sec. Burn time: 56 sec. Length: 5.80 m (19.00 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage3: 1 x S-44. Gross Mass: 1,025 kg (2,259 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x S-44. Thrust (vac): 33.240 kN (7,473 lbf). Isp: 282 sec. Burn time: 68 sec. Length: 1.80 m (5.90 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
Version:

VS-40. Sounding rocket. Status: Retired 1998.

Two stage vehicle consisting of 1 x S-40TM + 1 x S-44

Launches: 2. First Launch Date: 1993-04-02. Last Launch Date: 1998-03-21. Apogee: 1,000 km (600 mi). Liftoff Thrust: 190.000 kN (42,710 lbf). Total Mass: 6,800 kg (14,900 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 9.50 m (31.10 ft).

  • Stage1: 1 x S-40TM. Gross Mass: 5,664 kg (12,486 lb). Empty Mass: 1,212 kg (2,672 lb). Motor: 1 x S-40TM. Thrust (vac): 208.390 kN (46,848 lbf). Isp: 275 sec. Burn time: 56 sec. Length: 5.80 m (19.00 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage2: 1 x S-44. Gross Mass: 1,025 kg (2,259 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x S-44. Thrust (vac): 33.240 kN (7,473 lbf). Isp: 282 sec. Burn time: 68 sec. Length: 1.80 m (5.90 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
Version:

VLM. Status: Development ended 1997. Other Designations: Veiculo Lancador de Microsatelites.

Brazilian satellite launcher using core of VLS only. Planned for launch of microsatellites. First launch 2002 or later.

LEO Payload: 100 kg (220 lb). to: 200 km Orbit. at: 5.00 degrees. Payload: 18 kg (39 lb). to a: sun synchronous, 800 km, 98.6 deg orbital trajectory. Liftoff Thrust: 262.200 kN (58,945 lbf). Total Mass: 15,900 kg (35,000 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 20.00 m (65.00 ft). Flyaway Unit Cost $: 4.000 million. in: 1999 unit dollars.

  • Stage1: 1 x S-43TM. Gross Mass: 8,720 kg (19,220 lb). Empty Mass: 1,536 kg (3,386 lb). Motor: 1 x S-43TM. Thrust (vac): 320.600 kN (72,074 lbf). Isp: 277 sec. Burn time: 58 sec. Length: 8.10 m (26.50 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage2: 1 x S-40TM. Gross Mass: 5,664 kg (12,486 lb). Empty Mass: 1,212 kg (2,672 lb). Motor: 1 x S-40TM. Thrust (vac): 208.390 kN (46,848 lbf). Isp: 275 sec. Burn time: 56 sec. Length: 5.80 m (19.00 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage3: 1 x S-44. Gross Mass: 1,025 kg (2,259 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x S-44. Thrust (vac): 33.240 kN (7,473 lbf). Isp: 282 sec. Burn time: 68 sec. Length: 1.80 m (5.90 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage4: 1 x VLM-4. Gross Mass: 377 kg (831 lb). Empty Mass: 57 kg (125 lb). Motor: 1 x S-30. Thrust (vac): 20.490 kN (4,606 lbf). Isp: 275 sec. Burn time: 43 sec. Length: 1.25 m (4.10 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.
Version:

VLS-1. Status: Active.

Launches: 3. Failures: 3. First Launch Date: 1997-11-02. Last Launch Date: 2003-08-22. LEO Payload: 120 kg (260 lb). Apogee: 750 km (460 mi). Liftoff Thrust: 1,172.000 kN (263,476 lbf). Total Mass: 50,700 kg (111,700 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 19.50 m (63.90 ft).

  • Stage0: 4 x S-43. Gross Mass: 8,550 kg (18,840 lb). Empty Mass: 1,328 kg (2,927 lb). Motor: 1 x S-43. Thrust (vac): 303.000 kN (68,117 lbf). Isp: 260 sec. Burn time: 59 sec. Length: 9.00 m (29.50 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage1: 1 x S-43TM. Gross Mass: 8,720 kg (19,220 lb). Empty Mass: 1,536 kg (3,386 lb). Motor: 1 x S-43TM. Thrust (vac): 320.600 kN (72,074 lbf). Isp: 277 sec. Burn time: 58 sec. Length: 8.10 m (26.50 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage2: 1 x S-40TM. Gross Mass: 5,664 kg (12,486 lb). Empty Mass: 1,212 kg (2,672 lb). Motor: 1 x S-40TM. Thrust (vac): 208.390 kN (46,848 lbf). Isp: 275 sec. Burn time: 56 sec. Length: 5.80 m (19.00 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
  • Stage3: 1 x S-44. Gross Mass: 1,025 kg (2,259 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x S-44. Thrust (vac): 33.240 kN (7,473 lbf). Isp: 282 sec. Burn time: 68 sec. Length: 1.80 m (5.90 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.
VLS Chronology

1985 December 1 - Natal -. VLS-R1 VLS-R1 FAILURE: Failure. Test mission Agency: IAE. Apogee: 10 km (6 mi).

1989 May 18 - Natal -. VLS-R1 VLS-R2 Test mission Agency: IAE. Apogee: 50 km (31 mi).

1993 April 2 - 10:34 GMT - Alcantara -. VS-40 PT-01 Test mission Agency: INPE. Apogee: 950 km (590 mi).

1997 November 2 - 12:25 GMT - Alcantara VLS. VLS-1 V01 FAILURE: Destroyed during launch. SCD-2A Mass: 115 kg (253 lb). Spacecraft: SCD. Agency: Instituto Nacional de Pesquisas Espacias, Sao Jose dos Campos. Apogee: 3.00 km (1.80 mi). The SCD-2A (Data Collection Satellite 2A) was a Brazilian satellite designed for the collection of meteorological data relayed by data collection platforms spread throughout the Brazilian territory.

1998 March 21 - Alcantara -. Test mission Agency: INPE. Apogee: 900 km (550 mi).

1999 December 11 - 18:25 GMT - Alcantara VLS. VLS-1 V02 FAILURE: Second stage failed to ignite; destroyed by range safety. SACI-2 Mass: 80 kg (176 lb). Spacecraft: SACI. Agency: Instituto Nacional de Pesquisas Espacias, Sao Jose dos Campos. Apogee: 10 km (6 mi). Second attempted launch of Brazil's indigenous launcher.

2003 August 22 - 16:30 GMT - Alcantara VLS. VLS-1 V03 FAILURE: Failure - Exploded on pad during final prelaunch processing. 21 people were killed, with none injured. SATEC Mass: 57 kg (125 lb). Agency: INPE. Launch was due on August 25. Was to have been on third qualification flight after two previous failures. The launch had already been delayed from October 2002, then May 7 and June 20 2003. It appeared that one of the strapon boosters ignited by accident. The two satellite payloads were also destroyed in the blast, as was the launch pad.

Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
  • Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
  • NASA/GSFC Orbital Information Group Website, Web Address when accessed: http://oig1.gsfc.nasa.gov/.
  • Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: http://www.orbireport.com/Log.html.
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