Microcosm, Inc.
Microcosm is a small, woman-owned space engineering company (founded 1984) focused on reducing space mission cost and enabling responsive, low-cost space systems. Its work spans mission and systems engineering, low-cost launch vehicle and propulsion development, composite spacecraft structures, small satellite design, autonomous guidance/navigation/control (GN&C) software, simulation tools, and training. The company publishes technical papers and has performed on-orbit demonstrations of autonomous orbit control and other flight-proven technologies.
Industries
N/A
Nr. of Employees
small (1-50)
Products
Attitude simulation framework with software-in-the-loop
Simulator for attitude control development that supports flight-like software modules, control verification, and subsystem sizing to accelerate flight code conversion and reduce verification time.
Autonomous on-board orbit control kit (flight-proven)
On-board orbit determination and absolute orbit control capability demonstrated in flight to maintain in-track position and reduce ground operations and propellant use.
Low-cost small satellite bus designs (NanoEye-class)
Design concepts for low-cost imaging and surveillance small satellites intended to deliver mission capability at reduced recurring cost.
Attitude simulation framework with software-in-the-loop
Simulator for attitude control development that supports flight-like software modules, control verification, and subsystem sizing to accelerate flight code conversion and reduce verification time.
Autonomous on-board orbit control kit (flight-proven)
On-board orbit determination and absolute orbit control capability demonstrated in flight to maintain in-track position and reduce ground operations and propellant use.
Low-cost small satellite bus designs (NanoEye-class)
Design concepts for low-cost imaging and surveillance small satellites intended to deliver mission capability at reduced recurring cost.
Services
Consulting for mission definition, system architecture, and trades to develop affordable, responsive space systems.
Development and provision of low-cost, responsive expendable launch vehicle capability for small payloads.
Design of integrated unibody pressurized composite structures that combine tank and structure to reduce mass and parts count.
Design and development of low-cost small satellite buses and mission systems for LEO, MEO, GEO and interplanetary applications.
Advanced mission engineering training provided to professionals and graduate students on topics such as low-cost mission design and reducing mission cost.
Consulting for mission definition, system architecture, and trades to develop affordable, responsive space systems.
Development and provision of low-cost, responsive expendable launch vehicle capability for small payloads.
Design of integrated unibody pressurized composite structures that combine tank and structure to reduce mass and parts count.
Design and development of low-cost small satellite buses and mission systems for LEO, MEO, GEO and interplanetary applications.
Advanced mission engineering training provided to professionals and graduate students on topics such as low-cost mission design and reducing mission cost.
Expertise Areas
- Space mission engineering
- Low-cost launch vehicle development
- Pressure-fed propulsion
- Composite spacecraft structures
Key Technologies
- Pressure-fed liquid propulsion
- LOX/kerosene engine technology
- All-composite propellant and pressurization tanks
- Autonomous guidance, navigation and control algorithms
News & Updates
Coverage highlighting the company's work on making launch affordable and its role in low-cost launch concepts.
Flight demonstration showing autonomous on-board orbit determination and control maintaining in-track position to approximately ±1 km while using less propellant than traditional methods.
Coverage highlighting the company's work on making launch affordable and its role in low-cost launch concepts.
Flight demonstration showing autonomous on-board orbit determination and control maintaining in-track position to approximately ±1 km while using less propellant than traditional methods.