Baltic Orbital Services
Orbital Transport & Service Vehicles
Why space tugs?
The core team has the flight experience of 5 successful missions with the proprietary propulsion system and innovative ballistic calculations
Launchers deploy small satellites at the base orbital points generally accepted for all cluster members with associated payloads ranking lower in priority;
Our space tugs would reliably and cost-efficiently enhance the individual and cluster orbital placement capabilities of the compatible launchers, both existing and nearing their flight testing (incl. several European projects), while
Our space tugs would reliably and cost-efficiently enhance the individual and cluster orbital placement capabilities of the compatible launchers, both existing and nearing their flight testing (incl. several European projects), while
- applied as the LVs’ kick-stages
- precisely placing small satellites into customer-determined orbits (altitude, inclination)
- meeting the space debris mitigation requirements: ECA (ISO 24113:2010) and NASA (2009, NPR 8715.6A) while programmed to safely maneuver to the mission orbits
Baseline space technologies reinforced
Can be equipped with the docking and manipulator systems to capture a spacecraft for its refueling, in-orbit correction, or de-orbiting
*to be developed at a later stage to provide more versatile orbital services
*to be developed at a later stage to provide more versatile orbital services
- Minimalistic design, embodied with new composites and alloys
- Use of standard navigation devices and modular control systems enabling the independent orientation, navigation and stabilization, with innovative energy-saving ballistic calculations
- Sufficiently energy armed with proprietary ion-plasma (LEO and MEO) or chemical (GEO and cislunar) multiply-ignitable propulsion systems
First in the row: enduring leo-tug
Heritage/COTS Systems and Operating Equipment
High-Thrust Propulsion System
- 1-3 Main HEET-85 (SPT-100) and 2-4 AOCS Thrusters HEET-40 (SPT-70)
- 8 Maneuvering cold (or warm, to heat the Gxe to increase Isp) thrusters
- Feeding gas and Flow Control sub-systems using Xe
- 150L capacity tanks
- 4 combustion chambers
Command & Data handling
- Distributed data handling architecture with 2:1 redundant RAD-750 central control processors
- MIL-STD-1553B serial data bus, lower-level RS-485 buses data architecture and RS-485 routers
- Serial Interface Modules
- Command and Telemetry capability
Electrical power subsystem
- 2x6.5kWh Lithium-Ion battery
- Direct energy transfer with single power bus regulated at 70 or 100V and/or 28V low voltage bus
- 2 three-panel solar-array wings; panels fully populated with Triple Junction GaArs cells and Radiators
Thermal control
- Standard passive system
- Dual-bore matrix heat pipes in communication panels
Altitude Control
- Heritage 3-axis momentum bias system with robust 4-wheel control
- Star Trackers for precise attitude determination
- Heritage suites of redundant Sun Sensors
LEO-Tug Development Project Stages
Immediate steps during the pre-seed stage with the partner
Designing the main frame and frame structures from aluminum alloys, machining their models, and testing (vibration, fatigue, strength...)
Mapping the potential subcontractors for works, services and materials in Poland
Mapping the potential compatible launch vehicles and customers (LOIs, NDAs to exchange technical information)
Optionally: developing the engineering blueprint of sensor placement and the list of necessary sensors (COTS): temperature (thermocouples) - up to 100, pressure - 8, solar - 2, startrackers - 2, 1 set of 4 flywheels, etc. Thermocouples and solar sensors could be developed in-house
Our business strategy
Immediate: Soft landing in Poland, obtaining a proper R&D base
Pre-seed: piloting the materiel solutions, mapping the supply chain (PL, Ua, De)
Seed: Develop the bus, overall construction design, tech documentation issuance
A-Round/Short-term: obtaining the production facilities; building the Flight Model,
AA-Round - Qualification Orbital Mission [with European light launcher developers]
Possible Exits: merger of the start-up with the mission integrator or launching company OR selling the tug to a company pursuing cluster launches to LEO/MEO
B-Round/Mid-term: developing the high-orbit transport and service spacecraft
Possible Exits: selling it to a company delivering spacecraft into MEO and GEO, (e,g. telecom operators), OR establishing the JV to serially produce the spacecraft and/or merge with orbital mission managers
C-Round/Long-term: developing the cislunar tug to participate in the international Moon exploration programs
D-Round: set up of a fully-fledged orbital servicing company, enabled with own orbital fleet and mission control center
Pre-seed: piloting the materiel solutions, mapping the supply chain (PL, Ua, De)
Seed: Develop the bus, overall construction design, tech documentation issuance
A-Round/Short-term: obtaining the production facilities; building the Flight Model,
AA-Round - Qualification Orbital Mission [with European light launcher developers]
Possible Exits: merger of the start-up with the mission integrator or launching company OR selling the tug to a company pursuing cluster launches to LEO/MEO
B-Round/Mid-term: developing the high-orbit transport and service spacecraft
Possible Exits: selling it to a company delivering spacecraft into MEO and GEO, (e,g. telecom operators), OR establishing the JV to serially produce the spacecraft and/or merge with orbital mission managers
C-Round/Long-term: developing the cislunar tug to participate in the international Moon exploration programs
D-Round: set up of a fully-fledged orbital servicing company, enabled with own orbital fleet and mission control center
Our Team’s Track-Record in the Development of Orbital Transport Systems and Flight Experience
Technical proposals for the atmosphere re-entry manoeuvring spacecraft, including a micro-launcher supporting the suborbital flight of the USC-50-X micro-orbiter weighing 50 kg with a payload, to an altitude of 150 km
Lunar Mobile Platform of the Solar Power Plant (collaboration with JAXA, 2000-02)
Rocket remote control on pasty fuel (2007-10, for MT Aerospace)
Plasma remote control for the Singaporean satellite TELEOS-1 (2012-15) and Australian-Canadian communications satellite (2017-20), including orbital flight mission experience
