C-Tower: A scalable, deployable/retractable, and mobile truss mast to commission relocatable 50-kW class vertical solar arrays on the lunar surface

Ceres C-Tower is a self-contained novel solution which includes a central mast deployed 23.5m high to commission 60kW solar arrays near lunar poles. It is capable of multiple deployment and retraction cycles, relocation, and remote operations with a long system life of at least 10 years. It has a Specific Mass 85 W/kg Specific Packing Volume 22 kW/m3.C-Tower is adaptable to multiple launch vehicles, mission architectures, and landers. The mechanisms are robust under lunar dust and thermal environments. Key structural and mechanical innovations include: Central mast with innovative bearing assembly and unique internal cable-rigging to enable low-mass, high reliability multiple deployment, locking (without need of physical locks), and retraction under lunar gravity, dust, and extreme temperature environment. It is scalable to 50 m. Innovative Solar Array Deployment Arms allows for independent deployment of all solar arrays providing fault tolerance against multiple solar array deployment failures. Leg Mechanism provides stability and leveling with innovative footpad hinge design to minimizes stowed volume. Sun-Tracking Mechanism ensures optimal power generation. During Phase I, Ceres baseline technically feasible C-Tower by performing (i) multiple system component level trade studies, (ii) design space analysis to determine a feasible design boundary to meet the technical goals, (iii) baseline design and verification using finite element analysis of the C-Tower mechanical systems. For Phase II, Ceres will perform detailed design, finite element analysis, and simulations for the four C-Tower mechanisms and the integrated structure which will include analysis for lunar surface thermal cycling. Ceres will perform multiple sub-scale and scale prototype tests and simulations under relevant environments, including testing of the full scale central mast prototype under lunar gravity environment (1/6 g) which will mature the structures and mechanisms to TRL 5. Ceres C-Tower Solar Array System consists of central truss mast which deploys to 23.5m height to commission solar arrays > 60kW peak power near lunar poles. Substantial capacity increase ( > 5x) compared to 10 kW systems being developed under NASA GCD. The system has Specific Mass > 85 W/kg, Specific Packing Volume > 22 kW/m3, and is compatible with NASA CLPS class Landers.   Central mast uses innovative bearing assembly and unique internal cable-rigging to enable low-mass, high reliability multiple deployment, locking (without need of physical locks), and retraction under lunar gravity, dust, and extreme temperature environment. Innovative Solar Array Deployment Arms allows for independent deployment of all solar arrays and fault tolerance against multiple deployment failures. Leg Mechanism provides stability and leveling. Innovative footpad hinge design minimizes stowed volume. Sun-Tracking Mechanism ensures optimal power generation Key objective of this Phase II is to mature the technically feasible C-Tower structures and mechanisms baseline developed during Phase I to TRL 5 and verify that the detailed designs for the integrated C-Tower assembly and its individual components meet the 50-kW class vertical array requirements. Objectives for Phase II: Detailed Design and verification using FEA Development and testing of multiple sub-scale and scale prototypes of critical mechanisms: Full scale demonstration of multiple deployment, locking, and retraction of central mast as well as its loading under simulated lunar gravity environment (1/6 g) Sub-scale proof of concept of innovative bearing assembly, sliding mechanism using cable rigging, rotating mechanism using cable rigging, and of leveling mechanism High level full system analysis including avionics, power, communications, and other subsystems. Key Risks and their Mitigations Phase II Deliverables: Hardware demonstration of the mast under 1/6 g Test Reports Preliminary Design Summary Report  Detailed Design Summary Report Quarterly Status Reports Phase II Final Report Plan for Phase III mission infusion  

Extend life of missions and maximize science output for polar missions. Potential overnight survival and revival of NASA assets Support Human Missions and Habitats. Meet power needs for ISRU, lunar bases, infrastructure, landers, and rovers. Driver for keeping overall systems costs lower for future missions. Towers are used on lunar surface to provide communication, illumination, and observation services.   Power, communications, & imaging services for commercial customers like Lander, Rover, Infrastructure, and ISRU companies, Payload Providers, International Space Agencies to meet surface demands & extended mission life. In-orbit applications include solar array deployment for large satellites, commercial space stations. Terrestrial - emergency remote deployable power, comm, and imaging tower.  

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