The IBDM development was initiated as a joint development programme with NASA JSC. The first application of the IBDM was intended to be the ISSCrew Return Vehicle. In the original Agency to Agency agreement, it was decided to develop an Engineering Development Unit to demonstrate the feasibility of the system and the associated technologies. NASA JSC were responsible for the system and avionics designs and ESA for the mechanical design. However, since the cancellation of the CRV program, the two Agencies have independently progressed with the docking system development. The IBDM is now designed to be compatible with the International Docking System Standard and is hence compatible with the future ISS International Docking Adapters on the US side of the ISS. The European Space Agency has now started a cooperation with SNC to provide the IBDM for attaching this new vehicle to the ISS in the future. After SNC was selected as a commercial contractor to resupply the International Space Station in January 2016, ESA decided to spend 33 million euros to complete the design of the IBDM and build a flight model for Dream Chaser’s first mission.
Design
The IBDM provides both docking and berthing capability. The docking mechanism comprises a Soft Capture Mechanism, and a structural mating system called the Hard Capture System, explained in more detail below. The IBDM avionics runs in hot redundancy.
Soft Capture System
The SCS utilizes active control using 6 servo-actuated legs from RUAG Space which are coordinated to control the SCS ring in its 6 degrees of freedom. The leg forces are measured to modify the compliance of the SCS ring to facilitate alignment of the active platform during capture. A large range of vehicle mass properties can be handled. Mechanical latches achieve soft capture.
Hard Capture System
The HCS uses structural hook mechanisms to close the sealed mated interface. QinetiQ Space has developed several generations of latches and hooks to come to the final hook design. SENER will be responsible for the further development and qualification of the HCS subsystem.
Features
The key feature of IBDM is that it is a fully computer controlled mechanism, and it is able to take part in smooth low impact docking and berthing, autonomous operations in case of failures, flexibility in vehicle mass making it suitable for applications ranging from explorations to resupply missions. A backup safe mode is also available in case of failure.
Application
The American company Sierra Nevada Corporation is developing the Dream Chaser, which is a small reusable spacecraft that is selected to transport cargo and/or crew to the ISS. The European Space Agency has started a cooperation with SNC to potentially provide the IBDM for attaching this new vehicle to the ISS in the future. The IBDM will be mounted to the unpressurised cargo module, which will be ejected before reentry.
Status
The IBDM development has successfully passed the Critical Design Review. An engineering model of the mechanism and its hot-redundant avionics has been developed and successfully tested. The performance of the system has been verified at the certified SDTS docking test facility at NASA JSC. The consortium has currently started the manufacturing of the full IBDM qualification model.
