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DESIGN FOR REMOVAL - PASSIVE MECHANICAL AND RENDEZVOUS INTERFACE FOR CAPTURE AFTER END-OF-LIFE (PRINCE) - EXPRO PLUS

ESA Open Invitation to Tender AO9578
Open Date: 23/10/2018
Closing Date: 04/12/2018 13:00:00

Status: ISSUED
Reference Nr.: 18.138.07
Prog. Ref.: CSC Ev.Instr.Mod.
Budget Ref.: E/E101-E5 - CSC Ev.Instr.Mod.
Special Prov.: BE+DK+FR+DE+IT+NL+ES+SE+CH+GB+IE+AT+NO+FI+PT+GR+LU+CZ+RO+PL+EE+CA+SI
Tender Type: C
Price Range: 100-200 KEURO
Products: Satellites & Probes / Mechanisms / Mechanisms / Other
Techology Domains: Automation, Telepresence & Robotics / Applications and Concepts / Orbital Systems
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Systems Department
Division: Systems Engineering Division
Contract Officer: Seynaeve, Christophe Rene R.
Industrial Policy Measure: N/A - Not apply
Last Update Date: 23/10/2018
Update Reason: Tender issue

The main objective of this activity is to design a mechanical interface with integrated rendezvous / navigation supports (PRINCE) which enables the capture of a non-operational satellite. PRINCE should reduce the risk, cost and/or complexity of a chaser, which will perform the capture of the non-operational satellite after end-of-life. Therefore, the design shall take into account degradation due to long-term exposure to the space environment.Therefore, the contractor shall:1. Identify the key features required from a mechanical interface to enable / simplify capture via a robotic arm and gripper. This should include all aspects of the robotic arm and gripper that need to be supported e.g. kinematic design, contact geometry, motion profile and loads transferred through the capture operation. 2. Identify, through analysis, the rendezvous supports that can simplify the image processing which is required toperform visual servoing of the robotic arm. Different rendezvous supports shall be evaluated e.g. 2D markers 3D markers. 3. Derive a conceptual design of the mechanical interface with integrated rendezvous supports, including justification for the design.4. Verify the functionality of the full system through simulation 5. Identify the interface requirements for the device on the hosted satellite e.g. accessibility, load support.6. Evaluate the benefits / disadvantages of the system in support of an ADR mission e.g. in terms of derisking, reduction of costs.7. Develop the required work plan / roadmap for the assembly, integration and testing of the mechanical unit.For the purpose of this activity, it is not possible to consider the launch adapter ring as the capture interface.

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