External Queuing Navigation Correction

RT&L FOCUS AREA(S): Hypersonics; Space TECHNOLOGY AREA(S): Air Platform; Sensors; Space Platform 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 section 3.5 of 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: Analyze best method and implementation for external inputs to navigation systems for course correction in global positioning system (GPS) denied environments. DESCRIPTION: Currently, most navigation systems must either have inputs from GPS to correct course, or have very accurate Inertial Measurement Units (IMUs) to ensure angular random walk (ARW) error is low. The former are susceptible to GPS jamming and the latter are expensive, large and can be very sensitive to environmental factors. The government desires non-jammable external queueing systems for constant error correction to allow less expensive IMUs to be used in GPS contested environments on multiple platforms. Application to hypersonic platforms is desired. Current external queuing systems such as star trackers are used for initial position, but not used for constant error correction. Also, star trackers historically have poor performance in direct sunlight. PHASE I: Design and develop innovative solutions, methods, and concepts to introduce external inputs into a navigation system. The solutions should capture the key areas for new development, suggest appropriate methods and technologies to minimize the time intensive processes, and incorporate new technologies researched during the design and development. PHASE II: Complete a detailed prototype design incorporating government performance goals. Coordinate with the government during prototype design and development to ensure that the delivered products will be relevant to an ongoing missile defense architecture and data types and structures. PHASE III DUAL USE APPLICATIONS: Scale-up the capability from the prototype utilizing the new technologies developed in Phase II into a mature, full scale, field-able capability. Work with missile defense integrators to integrate the technology into a missile defense system level test-bed and test in a relevant environment. REFERENCES: 1. I. Hrvoic, G.M. Hollyer, Brief Review of Quantum Magnetometers, 2009. https://www.gemsys.ca/pdf/GEM_Brief_Review_of_Quantum_Magnetometers.pdf ; 2. D.J. Pines, X-ray NAVigation for Autonomous Position Determination, National Academies 1. Panel on Robotics, Communication and Navigation, Mar. 29, 2011. 2. https://sites.nationalacademies.org/cs/groups/depssite/documents/webpage/deps_063592.pdf ; 3. J.E. Hanson, Principles of X-ray Navigation, SLAC-R-809, 1996. https://www.slac.stanford.edu/pubs/slacreports/reports16/slac-r-809.pdf