Your Partner
In Space

We Create the
Future

YOUR PARTNER
IN SPACE

WE CREATE THE
FUTURE

SMA-2

Shown below is our new family of SMA-2 launch vehicles, which will begin flying in late 2023. 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 with payload capacities to LEO from as low as 22 kg. up to 7,803 kg. 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
configuration payload to LEO
SMA-2 Micro
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $5.8 million
Size
Height 9.4 m (30.7 ft.)
Diameter .46 m (1.5 ft.)
Rocket Mass 1,010 kg. (2,223 lb.)
Stages 3
Mass Fraction 2.2
Payload capacity
LEO 22 kg. (48.4 lb.)
SSO 16.1 kg. (35.3 lb.)
GTO 10.6 kg. (23.2 lb.)
TLI 7.5 kg. (16.5 lb.)
TMI 5.9 kg. (13.1 lb.)
GSO 4.6 kg. (10.2 lb.)
First stage Solid propellant
Engines 1
Thrust
7.7 kN (1731 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Second stage Solid propellant
Engines 1
Thrust 1.6 kN (360 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Third stage Liquid propellant (hypergolic)
Engines 1
Thrust .4 kN (89.9 lbf)
Specific impulse 339 s (vacuum)
Burn time 30 seconds
SMA-2 Micro
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $5.8 million
Size
Height 9.4 m (30.7 ft.)
Diameter .46 m (1.5 ft.)
Rocket Mass 1,010 kg. (2,223 lb.)
Stages 3
Mass Fraction 2.2
Payload capacity
LEO 22 kg. (48.4 lb.)
SSO 16.1 kg. (35.3 lb.)
GTO 10.6 kg. (23.2 lb.)
TLI 7.5 kg. (16.5 lb.)
TMI 5.9 kg. (13.1 lb.)
GSO 4.6 kg. (10.2 lb.)
First stage Solid propellant
Engines 1
Thrust
7.7 kN (1731 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Second stage Solid propellant
Engines 1
Thrust 1.6 kN (360 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Third stage Liquid propellant (hypergolic)
Engines 1
Thrust .4 kN (89.9 lbf)
Specific impulse 339 s (vacuum)
Burn time 30 seconds
SMA-2 Mini
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $15.9 million
Size
Height 10.9 m (35.9 ft.)
Diameter .55 m (1.79 ft.)
Rocket Mass 2,769 kg. (6,092 lb.)
Stages 3
Mass Fraction 4.4
Payload capacity
LEO 188 kg. (260 lb.)
SSO 86 kg. (190 lb.)
GTO 57 kg. ( 125 lb.)
TLI 40 kg (88 lb.)
TMI 32 kg. (70 lb.)
GSO 25 kg. (55 lb.)
First stage Solid propellant
Engines 1
Thrust
195.0 kN (43,869 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Second stage Solid propellant
Engines 1
Thrust 48.8 kN (10,973 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Third stage Liquid propellant (hypergolic)
Engines 1
Thrust 16.2 kN (3,650 lbf)
Specific impulse 339 s (vacuum)
Burn time 30 seconds
SMA-2 Mini
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $15.9 million
Size
Height 10.9 m (35.9 ft.)
Diameter .55 m (1.79 ft.)
Rocket Mass 2,769 kg. (6,092 lb.)
Stages 3
Mass Fraction 4.4
Payload capacity
LEO 188 kg. (260 lb.)
SSO 86 kg. (190 lb.)
GTO 57 kg. ( 125 lb.)
TLI 40 kg (88 lb.)
TMI 32 kg. (70 lb.)
GSO 25 kg. (55 lb.)
First stage Solid propellant
Engines 1
Thrust
195.0 kN (43,869 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Second stage Solid propellant
Engines 1
Thrust 48.8 kN (10,973 lbf)
Specific impulse 318 s (sea level)
Burn time 30 seconds
Third stage Liquid propellant (hypergolic)
Engines 1
Thrust 16.2 kN (3,650 lbf)
Specific impulse 339 s (vacuum)
Burn time 30 seconds
SMA-2
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $31.6 million
Size
Height 23.8 m (78 ft.)
Diameter 1.21 m (3.96 ft.)
Rocket Mass 2,769 kg. (6,092 lb.)
Stages 3
Mass Fraction 4.2
Payload capacity
LEO 1,277 kg. (2,609 lb.)
SSO 932 kg. (2,050 lb.)
GTO 613 kg. ( 1,349 lb.)
TLI 434 kg (955 lb.)
TMI 345 kg. (759 lb.)
GSO 268 kg. (590 lb.)
First stage Solid propellant
Engines 1
Thrust
1,121.1 kN (252,247 lbf)
Specific impulse 318 s (sea level)
Burn time 60 seconds
Second stage Solid propellant
Engines 1
Thrust 280.4 kN (63,095 lbf)
Specific impulse 318 s (sea level)
Burn time 60 seconds
Third stage Liquid propellant (hypergolic)
Engines 1
Thrust 93.3 kN (20,987 lbf)
Specific impulse 339 s (vacuum)
Burn time 60 seconds
SMA-2 Booster Augmented
Function Orbital launch vehicle
Manufacturer Space Mission Architects
Country of origin United States
Project cost US $10.5 million
Size
Height 23.8 m (78 ft.)
Diameter 1.21 m (3.96 ft.)
Rocket Mass 30,100 kg. (66,219 lb.)
Small Boosters 5,635 kg. (12,296 lb.)
Large Boosters 22,098 kg. ea. (48,615 lb.)
Stages 3
Mass Fraction 4.3-4.8
Payload capacity
(varies with booster configuration)
LEO 1,791-7,803 kg. (3,940-17,167 lb.)
SSO 1,365-5,737 kg. (3,003- 12,621 lb.)
GTO 860-3745 kg. (1890-8240 lb.)
TLI 636-2,672 kg. (1,399-5,878 lb.)
TMI 505-2,122 kg. (1,111-4,668 lb.)
GSO 393-1,650 kg. (865-3,630 lb.)
First stage Solid propellant
Engines 1
Thrust (total) 1,121.1 kN (252,247 lbf)
Specific impulse 318 s (sea level)
Burn time 60 seconds
Second stage Solid propellant
Engines 1
Thrust 280.4 kN (63,095 lbf)
Specific impulse 318 s (sea level)
Burn time 60 seconds
Third stage Liquid propellant
(hypergolic)
Engines 1
Thrust 93.3 kN (20,987 lbf)
Specific impulse 339 s (vacuum)
Burn time 60 seconds
Each booster
(6 max.)
Solid propellant
Engines 1
Thrust (total) 1,121.1 kN (252,247 lbf)
Specific impulse 318 s (sea level)
Burn time 60 seconds