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SMA-2

Shown below is our new family of SMA-2 launch vehicles, which will begin flying in late 2021. The SMA-2 family features highly efficient first and second stage solid rocket motors which use a proprietary fuel developed by Space Mission Architects. Our third stages use a high Isp liquid propellant for finer maneuverability.
The SMA-2 is a family of launch vehicles which range from as low as 15 kg. up to 7,859 kg. payload capacity to LEO. All SMA-2 rockets, including the smallest (the Micro) are capable of inserting a payload anywhere from low earth orbit to a Mars transfer insertion.
SMA-2’s are designed with simplicity and reliability in mind. Each version of the SMA-2 family is scaled off of the other. Many components are the same for all rockets which provides flexibility and interchangeability on the assembly line.
The solid stage motors can be warehoused indefinitely and then delivered to the launch site within days. The third stage needs only to be fueled at the launch site. All SMA-2’s third stages utilize fuels which are non-cryogenic and therefore do not have to be off-loaded in case of a launch delay. Being hypergolic, the third stage motor can be restarted multiple times as needed for the mission without having to rely on an igniter, thereby adding one more element of reliability.
To get in on the ground floor with our groundbreaking and reliable technology and one of the lowest launch costs per kg. in the industry, please see our “Launch With Us” page.
(Hover mouse to see individual rocket statistics.)
config leo text
SMA-2 Micro
FunctionOrbital launch vehicle
ManufacturerSpace Mission Architects
Country of originUnited States
Project costUS $5.3 million
Size
Height8.5 m (27.9 ft.)
Diameter.42 m (1.39 ft.)
Rocket Mass1,164 kg. (2,561 lb.)
Stages3
Payload capacity
LEO15 kg.(33 lb.)
SSO11 kg.(24 lb.)
GTO7 kg.( 15 lb.)
TLI5 kg(11 lb.)
TMI4 kg.(9 lb.)
GSO3 kg.(7 lb.)
First stageSolid propellant
Engines1
Thrust
78.2 kN (17,579 lbf)
Specific impulse318 s (sea level)
Burn time30 seconds
Second stageSolid propellant
Engines1
Thrust19.5 kN (4384 lbf)
Specific impulse318 s (sea level)
Burn time30 seconds
Third stageLiquid propellant (hypergolic)
Engines1
Thrust19.4 kN (4,361 lbf)
Specific impulse339 s (vacuum)
Burn time30 seconds
SMA-2 Mini
FunctionOrbital launch vehicle
ManufacturerSpace Mission Architects
Country of originUnited States
Project costUS $15.9 million
Size
Height10.9 m (35.9 ft.)
Diameter.55 m (1.79 ft.)
Rocket Mass2,769 kg. (6,092 lb.)
Stages3
Payload capacity
LEO188 kg.(260 lb.)
SSO86 kg.(190 lb.)
GTO57 kg.( 125 lb.)
TLI40 kg(88 lb.)
TMI32 kg.(70 lb.)
GSO25 kg.(55 lb.)
First stageSolid propellant
Engines1
Thrust
195.0 kN (43,869 lbf)
Specific impulse318 s (sea level)
Burn time30 seconds
Second stageSolid propellant
Engines1
Thrust48.8 kN (10,973 lbf)
Specific impulse318 s (sea level)
Burn time30 seconds
Third stageLiquid propellant (hypergolic)
Engines1
Thrust16.2 kN (3,650 lbf)
Specific impulse339 s (vacuum)
Burn time30 seconds
SMA-2
FunctionOrbital launch vehicle
ManufacturerSpace Mission Architects
Country of originUnited States
Project costUS $31.6 million
Size
Height23.8 m (78 ft.)
Diameter1.21 m (3.96 ft.)
Rocket Mass2,769 kg. (6,092 lb.)
Stages3
Payload capacity
LEO1,277 kg.(2,609 lb.)
SSO932 kg.(2,050 lb.)
GTO613 kg.( 1,349 lb.)
TLI434 kg(955 lb.)
TMI345 kg.(759 lb.)
GSO268 kg.(590 lb.)
First stageSolid propellant
Engines1
Thrust
1,121.1 kN (252,247 lbf)
Specific impulse318 s (sea level)
Burn time60 seconds
Second stageSolid propellant
Engines1
Thrust280.4 kN (63,095 lbf)
Specific impulse318 s (sea level)
Burn time60 seconds
Third stageLiquid propellant (hypergolic)
Engines1
Thrust93.3 kN (20,987 lbf)
Specific impulse339 s (vacuum)
Burn time60 seconds

SMA-2 Booster Augmented
FunctionOrbital launch vehicle
ManufacturerSpace Mission Architects
Country of originUnited States
Project costUS $10.5 million
Size
Height23.8 m (78 ft.)
Diameter1.21 m (3.96 ft.)
Rocket Mass2,769 kg. (6,092 lb.)
Stages3
Payload capacity
(varies with booster configuration)
LEO1,870-7,859 kg.(4,114-17,283 lb.)
SSO1,365-5,737 kg.(3,003- 12,621 lb.)
GTO898-3,772 kg.(1,976-8,298 lb.)
TLI636-2,672 kg.(1,399-5,878 lb.)
TMI505-2,122 kg.(1,111-4,668 lb.)
GSO393-1,650 kg.(865-3,630 lb.)
First stageSolid propellant
Engines1
Thrust (total)1,121.1 kN (252,247 lbf)
Specific impulse318 s (sea level)
Burn time60 seconds
Second stageSolid propellant
Engines1
Thrust280.4 kN (63,095 lbf)
Specific impulse318 s (sea level)
Burn time60 seconds
Third stageLiquid propellant
(hypergolic)
Engines1
Thrust93.3 kN (20,987 lbf)
Specific impulse339 s (vacuum)
Burn time60 seconds
Each booster
(6 max.)
Solid propellant
Engines1
Thrust (total)1,121.1 kN (252,247 lbf)
Specific impulse318 s (sea level)
Burn time60 seconds