Modular High Power Solar Array for BioSentinel

This technology will provide advanced capabilities for future small satellite based missions for NASA, DoD, commercial and academic space applications. Background: The BioSentinel Mission was selected in 2013 as one of three secondary payloads to fly on the Space Launch System�s first Exploration Mission (EM-1) planned for launch in December 2017. This will be one of the first demonstrations of Cubesats in a deep space mission environment. The primary objective of BioSentinel is to develop a biosensor using a simple model organism to detect, measure and correlate the impact of space radiation to living organisms over long durations beyond Low Earth Orbit (LEO). This project and payload were selected to help fill the HEOMD Strategic Knowledge Gaps. Major application objectives: NASA Ames Research Center BioSentinel will be one of the first nano-satellites to operate beyond Low Earth Orbit (LEO). The fact that that satellite will be operated up to 18 months continuously in interplanetary space exposes the electronics and solar cells to the high energy particle radiation environment. The highly energetic proton/helium ion flux from the Sun and the even higher energy proton/heavier ion flux from cosmic sources degrades the solar cells over time, lowering the power available to the spacecraft. With the limited mass and space available for this 6-U satellite, upsizing the solar arrays to overcome this power loss is not an option. This effort not only addresses the need for increased power, but also addresses improved reliability for use in high radiation environments. Due to the real estate constrains of this low-cost mission, a deployable solar array with an active control mechanism is required to maintain power positive. Expected Benefits: 1. New capabilities: Enhanced power generation in high radiation environments specially deep space missions. 2. Improved performance: up to 130% increase in specific power; 70% increase in peak power;up to 300% increase in orbital aver power 3. Improved reliability: Radiation mitigation to protect solar cells and electronic components will be implemented.Decreasing performance risk in deep space. 4. Cost savings: leveraging from existing LEO designs, reduces cost and schedule to mature the product to support Deep Space applications. Anticipated Value: Maturation of the MMA Deployable Solar Array Panels will enable Cubesat spacecraft to be utilized for more complex missions in LEO and Interplanetary missions. This technology will provide greatly improved reliable power for nanosatellites, allowing them to perform significantly more complex missions. This effort will result in a commercially produced deployable solar array system for Cubesats that will be readily available to government, commercial companies and academia. The end product that NASA will receive is a deployable solar array system with single-axis gimbal controlling capability. The expected beginning of life power is 36W and the end of life power should be greater than 32W. NASA also expects to receive the end item at a TRL=6~7, while the product will be qualified and proven through the BioSentinel mission reaching TRL=8~9. Proposed Statement of Work: Milestone 1: Preliminary Design for NASA Ames 6U Spacecraft Deployable Solar Panel � Provide review & analysis of proposed NASA BioSentinel Mission and Spacecraft Requirements o Review & Analyze following mission parameters: o Top Level Mission Requirements o System Power Requirements o Bus Interface Requirements o Spacecraft power requirements � Provide BioSentinel Deployable Solar Panel design definitions and specifications that meet requirements from the analyses performed in Task 1. Definition and Specification include but are not limited to following systems, subsystems and components: o Spacecraft Deployable Solar Panel Subsystem Design o Mechanical Interface Control Definition o Electrical Interface Control Definition Milestone 2: Engineering Development Unit (EDU) Deployable Array Development o Provide Engineering Development Unit(s) (EDU) for spacecraft development, integration and testing. The EDU must have the ability to support the following activities o Mechanical/Electrical Interface Model � test and evaluate interfaces for flight design o Hi-fidelity functional model � fully integrated unit to conduct functional and preliminary environmental testing. Milestone 3: Flight Unit Deployable Array Development o Provide Flight Units/Models as necessary. Flight units will incorporate modifications and updates identified during EDU testing and evaluation, o Qualification Model o Flight Unit o Flight Spare (TBD) Technical Outcome: MMA Design�s High Watts per Kilogram (HaWK) solar array is a compact system that provides significantly improved power for cubesat based flight projectss. The high performance solar panel array will have the following benefits: � Up to 130% increase in specific power (W/kg) � Up to 70% increase in peak power � Up to 300% increase in orbital average power (OAP) Additionally, there is a controllable single-axis gimbal assembly that allows the two-wing solar arrays to face the sun throughout the entire mission. This feature ensures the arrays provide the power needed for the system. Finally, the integrated deployable system allows the panels to be stowed prior to separation. . This technology will enable this mission thereby supporting AES as well as SSTP mission goals and provide the needed input to NASA Strategic Knowledge Gaps. In addition to the HEOMD and SMD goals that will be realized with this technology development, STMD goals will be accomplished in the following roadmap areas. TA 03 - Space Power & Engergy Storage TA 04 � Robotics, Telerobotics and Autonomous Systems TA 05 � Communication and Navigation

This is a mature technology (TRL 7) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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