Synchronized Modular Integrated Deployable Array (P-DoD12-003)

ABSTRACT: Conventional deployable arrays of rigid solar panels use cables or added external structures to provide synchronized deployment, adding mass, volume and limiting applicability, and are custom engineered for each application with unique assembly and integration processing and fixtures. This SBIR develops a novel Integrated Deployable Array which uses a multi-functional modular rigid solar panel that provides both panel structural support and synchronized deployment. The integrated system engineering approach uses multi-functionality to reduce total mass, improve stowed volume, and provide flexibility in application to variety of panel sizes and number of panels. The approach adopts the advantages of modularity and standardization of the MOSAIC modular solar panel developed in a prior SBIR, with easy life-cycle processing, standardizing interfaces to the array assembly fixture, the Ground Support Equipment, the shipping container, the Hold-Down and Release mechanism, and the spacecraft integration fixtures. The Phase I effort completes the conceptual design of an Integrated Deployable Array including deployment mechanism and drives, performs preliminary static, dynamic and kinematic analysis, and optimizes the design for mass and volume. A proof of concept multi-panel deployment test article is assembled to demonstrate ease of assembly, modularity, and synchronized deployment under ambient conditions, in multiple configurations. BENEFIT: The development of a standardized, modular approach to rigid deployable solar array will significantly reduce non-recurring engineering, and its associated schedule and cost, which represents a significant fraction of the total cost for deployable arrays. Ease of assembly and ability to integrate into arrays of different sizes and number of panels provides the greatest applicability of the design. With standardization also comes improved reliability from improved qualification traceability and manufacturing process control. Commercial application is particularly suitable to small spacecraft with prime power requirements of 500-5,000 Watts, where the non-recurring engineering costs and impacts of customized unique designs are a high fraction of total solar array costs.