Motorless Array Deployment (MAD) Energy

Dynovas Motorless Array Deployment Energy System prototype will demonstrate the deployment of a 10 kW, ~180 W/kg, ~60 kW/m3 array using entirely motorless actuation of bi-stable composite structures at TRL 6. The prototype will be prepared for a 2023 lunar demonstration with potential integration partner, Intuitive Machines. The proposed prototype will consist of two (2) bi-stable composite beams (targeted thickness of 0.66 mm). On the surface of the beams will be integrated piezoelectric or smart material motorless actuators (as demonstrated in Phase I). The actuators will be spaced along the length of the beam to control the vertical deployment and retraction of the MAD Energy system. During deployment and once deployed, the c-shaped bi-stable composite MAD Energy booms deliver the necessary stiffness and area moment of inertia for stable operation on the Lunar surface. The far end of the booms will connect directly to the array roll mandrel. The array roll mandrel includes a central rotation axis, composite ribs, outer mandrel surface, and axially mounted constant force springs. The membrane of the MAD Energy array will provide its own inherent stiffness. The semi-rigid membrane will consist of an approximately 2-ply, unidirectional glass substrate (0.15 mm). In Phase II, Dynovas will focus the development on the MAD Energy system and not on the solar cells and/or electrical circuits themselves. However, a detailed understanding of the array power module and circuitry is required to design the multi-functional membrane and the MAD Energy booms with the force necessary to deploy and retract 10+ kW arrays. The MAD Energy structure mounts to the array stowage box. The seal on the box works in concert with piezo vibration and the Lunar Electrostatic Array Deflector Shield (LEADS) to mitigate dust effects. The Dynovas delivers to the market an agile, independent, small business supplier of solar array structures and system. Motorless Array Deployment (MAD Energy System Overview -Power per weight and power per volume efficient -Multi-cycle deployable/retractable -Piezoelectric deploy/retract actuation -Modular 10 m extension, tilt, and rotation -Multifunctional membrane -Self-powered deployment/retraction -Structural health monitoring integrated Significance and Benefits of MAD Energy System Scalable deployed area from initial lunar testing to solar farms for habitation Minimized solar parasitic weight to achieve specific mass >180 W/kg Coiled/rolled stowed geometry to achieve a packing volume > 60 kW/m3 Cost minimized structures and systems for a structural cost of <$15/W Interface agnostic for deployment on spaceraft, landers, rovers, and habitats Leveraging existing high TRL baselines to accelerate maturation Overall SBIR (Phase II, IIE, and III): Scalable from test to 10 kW to 40 kW Motorless, controlled deployment and retraction Specific mass >180 W/kg Specific volume > 60 kW/m3 Structural cost <$15/W Self-cleaning via electro-repulsive acutation and piezo vibratory compensation Interface agnostic for deployment on landers, rovers, habitats, and spacecraft Up to 10 deg leveling and 360 deg sun tracking 10 m height extension 15 year, 10+ cycle lifetime Specific Phase II Objectives: Prototype MAD energy structure for 10 kW array, demonstrated at TRL 6, deployed, and retracted Detailed design of buckling resistant boom for vertical deployment of 10-40 kW array in lunar gravity Custom actuator design and acquisition for reliable, repeatable deployment/retraction Minimize parasitic weight to ~0% via optimized actuator-structure integration procedures Demonstrate 10+ deploy/retract cycles of MAD Energy prototype Physical weight measurement validating specific mass greater than 150 W/kg Physical coiled volume measurement validating specific volume greater than 60 kW/m3 Power generation functional demonstration through deploy/retract cycles Detailed design of leveling, rotation, and vehicle tilt interface Detailed design of self-cleaning via electro-repulsive actuation and piezo vibratory compensation
Benefits: The MAD Energy system aligns with the NASA taxonomy category TX03.1.1 Photovoltaic sub-group, which includes 25-150 kW class solar arrays and reliably retractable solar arrays, which are directly applicable to the MAD energy system. Furthermore, the Lunar surface missions are an explicit mission plan on the Technology Area 3 – Space Power and Energy Storage Roadmap enabling technologies. Specific NASA missions include: Artemis Asteroid Redirect Luna Surface Exploration Mars Moons Mars Orbit/Surface Exploration Power generation for networks of satellites and/or cube satellites for global communication networks; operation on spacecraft for orbiting debris removal, experimentation satellites, etc; non-space-based markets could include remotely operated electrically driven vehicles or deployment with Special Operators or forward deployed military facilities for on-demand power.