Orbital Transportation
Strong demand for Orbital Transportation Systems
Light / medium launchers shall be enhanced with SSO placement capabilities (kick-stages/ deployers).
Service growing orbit population (extend life-span, re-profile, etc.)
Central&Eastern European Region shall posess its satellite constellation to solve economic and security issues, while it is impossible to build a ground-based cosmodrome on the territory of 3Seas States.
Our OTSs:
Innovative Space Technology Capitalizing on the Space Heritage
Standard navigation devices and modular control systems enable the independent orientation and stabilization.
Sufficiently energy armed with proprietary ion-plasma (LEO) and/or chemical (GEO and LLO) multiple-ignitable propulsion systems.
Minimalistic design, embodied with new composites and alloys.
Energy-saving ballistic calculations.
Equipped with the scanner, docking port and manipulator enabling versatile orbital use cases.
Minimal time&expense to operation.
First in the row: Light SUV
| LEO Tug’s mass | 270 kg |
| Maximal payload mass | 500 kg |
| Thrust | P = 200N |
| Specific impulse | Is=300 s |
| Max. change of the orbit inclination (with refueling) | 4° |
| Time of the altitude rise from 500 to 1000 km (dispensing step | 12000 s |
| 20 km) | |
| Maximal orbit altitude | 1400 km |
| Max number of propulsion system ignitions | Up to 24 |
Milestones Achieved
SUV Development Status
| Light SUV Subsystem | Current TRL | Delivery, ms | Suppliers |
|---|---|---|---|
| Overall construction design, tech documentation issuance | 3 | 8 | UA, PL, D |
| Electric\plasma propulsion | 7 | 14 | D, UA |
| Automatic Flight Control and Telemetry | 5 | 8 | UA, PL |
| Attitude Determination& Control | 4 | 8 | UA |
| Power Generation and Supply | 5 | 10 | Germ |
| SUV Communication and Operating Control | 5 | 12 | D |
| Thermal control and regulation | 5 | 8 | UA, PL |
| TOTAL | null | 24 | Integration PL |
Estimated Development Cost over Time
| Year | LSUV-300 |
|---|---|
| 2023 | 1.1 |
| 2024 | 4.4 |
| 2025 | 2.7 |
| 2026 | 5.5 (DM1) |
| 2027 | 0 |
| 2028 | 0 |
| 2029 | 0 |
| Total, $M | 13.7 |
Forecasted ARR, $M
| Year | LEO | In-Orbit | Total ARR |
|---|---|---|---|
| 2025 | 36 | 8 | 44 |
| 2026 | 54 | 12 | 66 |
| 2027 | 72 | 24 | 96 |
| 2028 | 90 | 30 | 120 |
| 2029 | 108 | 60 | 168 |
| 2030 | 108 | 60 | 168 |
| Total, $M | 468 | 194 | 662 |
Light SUV Laboratory Model (LM) MAIT
LM cost is ~USD 300 k (1.25 Mio PLN)
| Subsystem | Size | Mass | Materials | Function |
|---|---|---|---|---|
| Structures | yes | no | partly | partly |
| Electric Propulsion System | yes | yes | partly | partly |
| Cold Gas Propulsion System | yes | yes | yes | yes |
| Propellant Tanks | yes | yes | yes | yes |
| Solar Panels (SP) | yes | no | partly | partly |
| SP Deployment Mechanism | yes | no | no | partly |
| Batteries | yes | no | no | partly |
| Flight Computer | yes | yes | yes | yes |
| ADCS | yes | no | no | no |
| Thermal Control System | yes | no | no | no |
| Star Sensors | yes | no | no | partly |
| Sun Sensors | yes | yes | yes | partly |
| GPS Antennas | yes | yes | yes | yes |
| S-Band Antennas | yes | yes | yes | yes |
| Payload Separation System | yes | no | no | no |
LSUV-300 Engineering Model (EM) MAIT
EM total cost is ~USD 1.05 Mio
| Subsystem | Size | Mass | Materials | Function |
|---|---|---|---|---|
| Structures | yes | yes | yes | yes |
| Electric Propulsion System | yes | yes | partly | partly |
| Cold Gas Propulsion System | yes | yes | yes | yes |
| Propellant Tanks | yes | yes | yes | yes |
| Solar Panels (SP) | yes | yes | partly | partly |
| SP Deployment Mechanism | yes | yes | yes | yes |
| Batteries | yes | yes | partly | yes |
| Flight Computer | yes | yes | yes | yes |
| ADCS | yes | yes | yes | partly |
| Thermal Control System | yes | yes | yes | no |
| Star Sensors | yes | no | no | partly |
| Sun Sensors | yes | yes | yes | partly |
| GPS Antennas | yes | yes | yes | partly |
| S-Band Antennas | yes | yes | yes | yes |
| Payload Separation System | yes | yes | yes | yes |