European standard mating/demating device for in-orbit servicing, assembly, and refuelling — recognised as a standard building block for OSAM missions.
HOTDOCK Mating/Demating Device
European standard mating/demating device for in-orbit servicing, assembly, and refuelling — recognised as a standard building block for OSAM missions.
Description
HOTDOCK is a compact, flight-qualified mating/demating device developed by Space Applications Services, recognised by ESA as a standard European building block for on-orbit servicing, assembly, and manufacturing (OSAM) missions. The device enables two spacecraft or modules to mate, establish structural and/or electrical connections, and demate in orbit — a fundamental capability for servicing satellites, assembling space stations, and enabling modular spacecraft architectures.
HOTDOCK supports both passive and active mating configurations, provides robust latching with known preload, and allows controlled release for demating. Its design prioritises reliability, low mass, and compatibility with a wide range of spacecraft interfaces. The device has been developed through multiple iterations with European institutional support, including funded studies by ESA and the Belgian Space Agency (BELSPO).
Space Applications Services provides HOTDOCK as a product for integration into servicing vehicles, client spacecraft, and modular space infrastructure, with full engineering support, testing, and qualification services. HOTDOCK aligns with the growing OSAM market driven by satellite life extension, active debris removal, and in-space manufacturing programmes.
Specifications
| Type | Mechanical mating/demating device |
|---|---|
| Applications | In-orbit servicing (OSAM), assembly, refuelling, modular platforms |
| Configurations | Active and passive variants |
| Status | European standard building block (recognised by ESA) |
| Support | Full engineering, testing, and qualification services available |
| Diameter | 148.5 mm |
| Height | 92.4 mm |
| Mass | 1.28 kg |
| Operating temperature | -60…+125 °C |
| Power | 20-50 W |
| Supply voltage | 28-100 V |
| Life in LEO | 7+ (RT avionics) |
| Life in GEO | 15+ (RH avionics) |
| Linear mechanical load transfer | 3.0 kN |
| Bending mechanical load transfer | 300 Nm |
| Translational guidance tolerance | ± 15 mm |
| Angular guidance tolerance | ± 10 deg |
| Full Coupling Duration | <20 sec |
