VLS-1

For the naval missile-firing system, see Vertical launching system.

VLS-1
*Veículo Lançador de Satélites*
Size
VLS launch
Function	Orbital launch vehicle
Manufacturer	CTA
Country of origin	Brazil
Height	19.5 m (63.9 ft)
Diameter	1.01 m (3.31 ft)
Mass	50,700 kg (111,700 lb)
Stages	3
Capacity
Payload to LEO	380 kg (830 lb)
Launch history
Status	Cancelled
Launch sites	Centro de Lançamento de Alcântara
Total launches	2
Failures	2
First flight	2 November 1997
Boosters - S-43
No. boosters	4
Engines	1 Solid
Thrust	303 kN (68,100 lb_f)
Specific impulse	225 s (2.21 kN·s/kg)
Burn time	59 seconds
Fuel	Solid
First stage - S-43TM
Engines	1 Solid
Thrust	320.6 kN (72,074 lb_f)
Specific impulse	277 s (2.72 kN·s/kg)
Burn time	58 seconds
Fuel	Solid
Second stage - S-40TM
Engines	1 Solid
Thrust	208.39 kN (46,848 lb_f)
Specific impulse	275 s (2.70 kN·s/kg)
Burn time	56 seconds
Fuel	Solid
Third stage - S-44
Engines	1 Solid
Thrust	33.24 kN (7,473 lb_f)
Specific impulse	282 s (2.77 kN·s/kg)
Burn time	68 seconds
Fuel	Solid

The VLS-1 (Portuguese: Veículo Lançador de Satélites) is the Brazilian Space Agency's main satellite launch vehicle.^[1] The launch vehicle will be capable of launching satellites into orbit. The launch site is located at the Alcântara Launch Center^[2] due to its proximity to the equator.

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

History

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.^[3]

The project was terminated by Brazilian Space Agency in 2016.^[4]

VLS-1 schedule

Initial flight test schedule

#	Vehicle	Payload	Date	Place	Result
1	VLS-R1	-	1985 December 1	CLA	Failure, apogee of 10 km.
2	VLS-R2	-	1989 May 18	CLA	Apogee of 50 km.
3	VLS-1 V1	SCD-2A	1997 December 2	CLA	in flight failure
4	VLS-1 V2	SACI 2	1999 December 11	CLA	in flight failure
5	VLS-1 V3	SATEC	2003	CLA	pad explosion on 2003 August 22

Current schedule

The V04 prototype was originally scheduled for launch in 2006. Further testing has resumed in 2008. Current VLS-1 schedule is as follows:^[5]

#	Vehicle	Payload	Date	Place	Result
1	mockup	electrical tests with a mockup rocket^[6]^[7]	2012	CLA	- Success
2	VLS-1 XVT-01 VSISNAV	only first two stages active	2016	CLA	-
3	VLS-1 V-04	satellite launch	2018	CLA	-

VLS Configurations

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

The VLS-XVI 01 sub-orbital test vehicle 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 - 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.

Developments

VLM

Main article: VLM (rocket)

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.^[8]^[9]^[10]

"Cruzeiro do Sul" (Southern Cross) program

**VLS Alfa**
Size
Function	Orbital launch vehicle
Manufacturer	CTA
Country of origin	Brazil
Height	19.5 m (63.9 ft)
Stages	3
Capacity
Payload to LEO	600 kg
Launch history
Status	In development
Launch sites	Centro de Lançamento de Alcântara
Boosters - S-43
No. boosters	4
Engines	1 Solid
Thrust	303 kN (68,100 lb_f)
Specific impulse	225 s (2.21 kN·s/kg)
Burn time	59 seconds
Fuel	Solid
First stage - S-43TM
Engines	1 Solid
Thrust	320.6 kN (72,074 lb_f)
Specific impulse	277 s (2.72 kN·s/kg)
Burn time	58 seconds
Fuel	Solid
Second stage - L75
Engines	1 Liquid
Thrust	7.50 t
Burn time
Fuel	Liquid

**VLS Beta**
Size
Function	Orbital launch vehicle
Manufacturer	CTA
Country of origin	Brazil
Stages	3
Capacity
Payload to LEO	800 kg
Launch history
Status	In development
Launch sites	Centro de Lançamento de Alcântara
First stage - P40
Engines	1 Solid
Thrust	40 t
Burn time
Fuel	Solid
Second stage - L75
Engines	1 Liquid
Thrust	7.5 t
Burn time
Fuel	Liquid

VLS Alfa

In the framework of the proposed Cruzeiro do Sul program,^[11] 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^[12]

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^[5]

#	Vehicle	Payload	Date	Place	Result
1	VLS Alfa XVT-01	-	2015	-	-
2	VLS Alfa XVT-02	-	2016	-	-
3	VLS Alfa V-01	-	2017	-	-
4	VLS Alfa V-02	SARA Orbital	2018	-	-
5	VLS Alfa V-03	-	2020	-	-

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^[13]
Stage 3 - one L75 rocket engine^[5]

Projected flights are:^[8]

#	Vehicle	Payload	Date	Place	Result
1	VLS Beta XVT-01	-	2018	-	-
2	VLS Beta XVT-02	-	2019	-	-
3	VLS Beta V-01	-	2020	-	-

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.

Gallery

Engine
Engine test

References

↑ "Veículo Lançador de Satélites (VLS)". Brazilian Space Agency. Retrieved 2011-12-12.
↑ CLA - Centro de Lançamento de Alcântara Alcântara Launch Center. Retrieved on 2012-03-06. (Portuguese).
↑ Saiba como está o projeto Veículo Lançador de Satélite (VLS) Brazilian Air Force. Retrieved on 2012-03-06. (Portuguese).
↑ "VLS". space.skyrocket.de. Retrieved 2016-05-07.
1 2 3 http://www.aeb.gov.br/wp-content/uploads/2013/01/PNAE-Portugues.pdf
↑ Revista AEB 10 Brazilian Space Agency. Retrieved on 2012-03-06. (Portuguese).
↑ http://www.parabolicarc.com/2011/10/11/brazil-iae-conducts-vls-qualification-tests/
1 2 Brazilian space plans: 2011-2015 nasaspaceflight.com. Retrieved on 2012-03-06.
↑ "Brazilian Space". Brazilianspace.blogspot.com. Retrieved 2011-12-12.
↑ "VLM: veículo lançador de microsatélites, launch vehicle for SHEFEX-3". German Aerospace Center (DLR). Retrieved 2013-05-24.
↑ http://www.iae.cta.br/?action=cruzeirodosul
↑ http://www.aeb.gov.br/download/revista/RevistaAEB_n13.pdf
↑ http://www.iae.cta.br/?action=vlsbeta

External links

Wikimedia Commons has media related to VLS-1.

Brazilian space program

Satellites

Active	SCD CBERS

In development	Amazônia SGDC Flora Hiperspectral SABIA-Mar SARA LATTES GEOMET CLE SAR AST

Sounding
rockets

Active	Sonda VS-30 VSB-30 VS-40 Fogtrein

Canceled	VS-15

Launch
vehicles

In development	VLM

Canceled	VLS-1 "Cruzeiro do Sul" launcher family

Launch sites

Organisation

Orbital launch systems

Current	Angara 1.2 A5 Antares Ariane 5 Atlas V Delta II IV Dnepr-1 Epsilon Falcon 9 full thrust GSLV GSLV Mk III H-IIA H-IIB Kuaizhou Long March 2C 2D 2F 3A 3B 3C 4B 4C 6 11 Minotaur I IV V C Pegasus Proton-M PSLV Rokot Safir Shavit Strela Soyuz U FG 2 2.1a 2.1b 2-1v Unha Vega Zenit 2M 3SL 3SLB 3F

In development	Angara A5P A5V Ariane 6 Athena Ic IIc III Ausroc IV Electron Falcon Heavy Firefly α FT-1 H3 Haas KZ-11 Long March 5 7 8 9 LauncherOne Mayak Naga-1 Naro-2 OREL RPS (420, 550) Simorgh SLS Southern Cross Soyuz-5 SPARK Tronador II ULV VLM Vulcan

Retired	Ariane 1 2 3 4 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able Agena Centaur Black Arrow Conestoga Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 III Diamant Energia Europa Falcon 1 Falcon 9 v1.0 v1.1 Feng Bao 1 H-I H-II Juno I Juno II Kaituozhe-1 Kosmos 1 2I 3 3M Lambda 4S Long March 1 2A 2E 3 4A Mu 4S 3C 3H 3S 3SII V N1 N-I N-II Naro-1 Paektusan Pilot Proton UR-500 K R-7 Luna Molniya M L Polyot Soyuz L M U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna Saturn I IB V INT-21 Scout SLV Space Shuttle Sparta Start-1 Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon 2 3 Vanguard Zenit-2

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