LAUNCH SYSTEM

Leo Aerospace is developing a high-altitude launch system to enable the next wave of innovation in space.  Our launch platform is built specifically for dedicated launch of small satellites.  Leo Aerospace's vehicle is designed for a typical mission of placing 25 kg to 550 km sun-synchronous orbit but can service a range of missions with payload capacity up to 57 kg.   

Our fully reusable, autonomous aerostat carries a rocket to 60,000 feet in altitude prior to launch.  By launching at this altitude, aerodynamic and gravitational losses are reduced for the rocket, cutting energy requirements to orbit by over 10% and the overall size of the rocket by more than 50%.  

Aerostats are also uniquely capable as robust platforms for heavy lift operations at high altitudes, enabling numerous missions aside from launch.  Our multi-mission modular payload system can carry up to 3,500 kg to 18 km or up to 23,000 kg to lower altitudes as illustrated on our Mission Profiles page.  

Moreover, Leo Aerospace's orbital launch system requires zero fixed-site launch infrastructure and is entirely mobile.  With this architecture, we can provide on-demand, flexible, and low-cost small satellite launch facilitating access to space.

REGULUS

ORBITAL

Regulus Orbital is Leo Aerospace's premier high-altitude orbital launch platform.  A fully and rapidly reusable craft, Regulus requires minimal refurbishment over lifetime operations.  Autonomous flight control provides optimized flight capabilities in a range of weather and mission envelopes. Additionally, its on-board, autonomous, command and control infrastructure continuously assesses system health.  Regulus is equipped with a rotational control system, comprised of a series of bipropellant thrusters.  This system is capable of controlling the entire platform’s yaw and roll profiles.  Regulus Orbital is designed for a typical mission of placing 25 kg to 550 km sun-synchronous orbit but can service a range of missions with payload capacity up to 57 kg with no fixed ground infrastructure.

INSULATED COMPOSITE BODY

LIGHTWEIGHT SHELL WITH OPTIMIZED

AERODYNAMICS FOR A RANGE OF ALTITUDES

ROTATIONAL CONTROL THRUSTERS

4 BIPROPELLANT, SECONDARY COMBUSTION AUGMENTED THRUSTERS

PROVIDE FULL CONTROL OF YAW AND ROLL PROFILES

BURNERS

HIGH AND LOW ALTITUDE BURNERS

IN STAGGERED CONFIGURATION FOR REDUNDANCY

HIGH STRENGTH ACTUATOR

SPACE GRADE ALUMINUM

AEROSTAT MOUNTS

6 MOUNTS CONFIGURABLE FOR VARIOUS LIFT PLATFORMS

PROPRIETARY RAIL LAUNCHER

ENABLES SMOOTH TRANSITION FROM

CAPTIVE CARRY TO ORBITAL FLIGHT

10.0 m
0.838 m
 
 

FULLY MOBILE SOLUTION

ENTIRE ORBITAL LAUNCH SYSTEM FITS WITHIN 40 FOOT ISO CONTAINER

Containers can be placed on semi-trucks, ships at sea or air-deployed.  Uniflated aerostat and inflation infrastructure also contained within this single unit.  Structure designed for sustained storage or global pre-positioning.  Trailer cab serves as initial communications station for launch.

REGULUS

MULTI-MISSION

Regulus Multi-Mission is Leo Aerospace's premier high-altitude suborbital launch, loiter, and testing platform.  A fully and rapidly reusable craft, Regulus requires minimal refurbishment over lifetime operations.  Autonomous flight control provides optimized flight capabilities in a range of weather and mission envelopes.  Its on-board, autonomous, command and control infrastructure continuously assesses system health.  Regulus is equipped with a rotational control system, comprised of a series of bipropellant thrusters.  This system is capable of controlling the entire platform’s yaw and roll profiles.  Mission profiles include suborbital launch, remote delivery, high-altitude loiter, experimental testing, surveillance, and emergency extract, among others. 

FORWARD PLATFORM DOOR

FULLY SEALS TO MAINTAIN OPERATING ENVIRONMENT

HOUSES CAMERA FOR REMOTE REAL-TIME VIDEO

DROPDOWN BAY DOOR

SUBORBITAL ROCKET ILLUSTRATED

PREPARED FOR LAUNCH

LAUNCH RAIL

HEAT RESISTANT STRUCTURE

LOW FRICTION INTERFACE

 
 

MISSION CONFIGURATIONS

GLIDER

ORBITAL ROCKET

SUBORBITAL ROCKET

MODULAR PAYLOAD

DRONE

 

ORBITAL ROCKET

Orbital rocket features solid motor first and second stages, and bipropellant third stage. High manufacturability supports high production rates and economies of scale. Minimal infrastructure requirements allow truly flexible launch operations.

SECOND STAGE

EXPENDED FIRST AND SECOND STAGES

RECOVERED UNDER PARACHUTE

ROCKET VARIANTS

  THIRD STAGE

ENABLES HIGH ACCURACY FOR

CUSTOMIZED ORBITAL INSERTION

FIRST STAGE

HIGH ALTITUDE OPERATION REDUCES AMBIENT

PRESSURE VARIANCE IN FLIGHT ENVELOPE

ENABLES GREATER EFFICIENCY FOR FIXED NOZZLE GEOMETRY

PAYLOAD

STANDARDIZED PAYLOAD INTEGRATION VARIANTS

TAILORED TO CUSTOMER REQUIREMENTS

10.05 m
0.838 m
25 kg to 550 km SSO

ORBITAL ROCKET SPECIFICATIONS

HEIGHT
DIAMETER
10.05 meters
0.838 meters
PAYLOAD

PAYLOAD CAPACITIES 

1U = x18
2U = x9
3U = x8
6U = x4
12U = x2
Design Point for Commercial Offering:
25 kg to 550 km SSO
Maximum SSO Payload:
33 kg to 550 km SSO
Maximum Circular Payload:
57 kg to 300 km circular
 

SUBORBITAL ROCKET

Suborbital rocket uses a high performance solid motor to support high manufacturability and streamlined operations.  Motor size can be customized to satisfy mission requirements for apogee and duration in micro gravity.

SUB-ORBITAL ROCKET SPECIFICATIONS

HEIGHT
DIAMETER
PAYLOAD
3 meters
0.31 meters
100 kg to 400 km altitude
3 m
0.31 m

EO/IR

COMMUNICATIONS

TECH DEMONSTRATION

CONTROLLED DROP TESTING

EMERGENCY EXTRACTION

MODULAR PAYLOAD PACKAGES

MODULAR PAYLOAD SPECIFICATIONS

HEIGHT
2.0 meters
WIDTH
1.7 meters
LENGTH
9.0 meters
PAYLOAD
3,500 kg to 18 km or up to 23,000 kg to lower altitudes
TEMPERATURE
Controlled to Client Requirements
ATMOSPHERE
Controlled to Client Requirements

MULTI-MISSION PLATFORM CONFIGURATION

 

PRIMARY LIFT AEROSTATS

HELIUM

ILLUSTRATED SIZE PROFILE AS INFLATED AT 60,000 FEET

HYDROGEN

ILLUSTRATED SIZE PROFILE AS UNINFLATED AT SEA LEVEL

91.5 m

HOT AIR

CONSISTENT SIZE PROFILE THROUGHOUT MISSION

48.75 m

AEROSTAT CHARACTERISTICS

VEHICLE
HOT AIR
HELIUM
HYDROGEN
MATERIAL
STABILITY
LOITER TIME
LIFE CYCLE
ripstop nylon
polyethylene
polyethyene
highly stable
inert gas
highly reactive
*
200+ missions
14+ days
single use
8 days
single use
PRIMARY MISSION
rocket launch | module payload
extended loiter operations
defense and emergency operations
*
Hours to weeks depending on payload.  Infinite loiter time with proprietary in-flight drone refueling.