Low Cost Actuators

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: Develop new technologies or designs for linear actuators to decrease cost and improve performance. DESCRIPTION: The Government desires improvements in linear actuators to decrease cost and improve design space for future interceptor systems. In particular, linear actuators with fast response times and high accuracy requirements that are used in applications such as pintle valves are significant cost drivers. Electro-mechanical actuators are the typical state-of-the-art technology for these applications. Solutions could focus on improved designs, improved actuator components, or completely new type of linear actuators. In addition to decreasing actuator cost, solutions should also seek to minimize mass, volume, and power usage. While this topic focuses on actuators for pintle valves, additional missile defense applications could include thrust vector control and aero control surfaces. Proposers are strongly encouraged to work with a controllable solid propulsion system manufacturer, prime contractor, or actuator manufacturer for requirements definition and transition planning. This topic does not seek to design actuators for a specific system, but rather seeks to improve technologies for future systems. For purposes of the Phase I, proposers are encouraged to obtain requirements from an industry partner or may utilize the following ballpark performance objectives if requirements are not available: -Capable of operating at temperatures above 150 C -Stall load requirements vary significantly depending on application, proposers may select 5000 N -Minimal position error of 2% -Maximum stroke length: 5 cm -Velocity achieved within commanded stroke: > 0.1 m/s PHASE I: Evaluate feasibility of proposed actuator concept by modeling and simulation and/or proof of concept testing. Component or breadboard fabrication is recommended to provide evaluation of critical properties or to validate new manufacturing techniques. Work with solid propulsion system developers to understand environments and to further define requirements. PHASE II: Continue actuator development through design, analysis, and experimentation. Optimize parameters for cost and performance. Actuator testing should be conducted to validate models and generate performance databases. Demonstration in a representative environment is desired. Phase II should identify an insertion opportunity and conclude with a reasonable manufacturing strategy. PHASE III DUAL USE APPLICATIONS: Work with a solid propulsion system manufacturer to iteratively design and fabricate prototype components for high-fidelity testing in a relevant solid rocket motor for current or future missile defense applications. A successful Phase III would provide the necessary technical data to transition the technology into a missile defense application. REFERENCES: 1) https://ieeexplore.ieee.org/document/7137666/ 2) https://ieeexplore.ieee.org/document/8658303 3) https://ieeexplore.ieee.org/document/9495524 4) https://pdfpiw.uspto.gov/.piw?PageNum=0&docid=03948042 KEYWORDS: Actuators; Propulsion; Pintle Valves