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