VLM (rocket)

VLM-1
Veículo Lançador de Microssatélites

VLM-1 configuration
Function	Orbital launch vehicle
Manufacturer	Institute of Aeronautics and Space
Country of origin	Brazil
Size
Height	19.6 m (64 ft)
Diameter	1.45 m (4 ft 9 in)
Mass	28,000 kg (62,000 lb)
Stages	3
Capacity
Payload to LEO
Mass	150 kg (330 lb) to 300 km[1]
Launch history
Status	In development
Launch sites	Alcântara Space Center
First flight	NET March 2027[2]
First stage – S-50
Powered by	1 Solid
Maximum thrust	450 kN (100,000 lbf)[3]
Specific impulse	~277 s (2.72 km/s)
Burn time	82 seconds[3]
Propellant	Solid
Second stage – S-50
Powered by	1 Solid
Maximum thrust	450 kN (100,000 lbf)[3]
Specific impulse	~277 s (2.72 km/s)
Burn time	82 seconds[3]
Propellant	Solid
Third stage – S-44
Powered by	1 Solid
Maximum thrust	33.24 kN (7,470 lbf)
Specific impulse	282 s (2.77 km/s)
Burn time	68 seconds
Propellant	Solid
[edit on Wikidata]

The VLM (Veículo Lançador de Microsatélites) is a proposed three-stage satellite launcher being developed by the Brazilian General Command for Aerospace Technology in collaboration with Germany. The project originated in 2008 as a simplified version of the VLS-1 rocket, using only the core stages. The first launch is currently planned for no earlier than 2027.^[4]

A version based on the S-50 rocket motor is being developed, with the objective of launching satellites of up to 150 kg into equatorial circular orbits at 300 km altitude.^[5]