Attachment_1-_Statement_of_Objectives.pdf

STATEMENT OF OBJECTIVES (SOO)

COMPACT STRATEGIC-GRADE GYROSCOPE (CSG)

14 February 2019

REQUIREMENT DESCRIPTION:

The Air Force Research Laboratory (AFRL) is soliciting White Paper in Compact Strategic- Grade Gyroscope (CSG) under subparagraph letter of the ROSET Broad Agency Announcement (BAA) Topic Area #11, Precision timing, inertial sensor, and atom interferometry concepts and techniques. See the following for detailed information:

CSG Subparagraph:

AFRL is soliciting White Paper for the acquisition of innovative gyroscope technology capable of performing in space and strategic environments as identified in the technical objectives and key performance parameters below. Offerors shall address all listed objectives in the SOO.

Technical Objective 1:

Development of size-constrained gyroscope technology for strategic applications with a technical path to hostile radiation hardness. The requirements analysis and system trade studies for this objective shall be based on the Key Performance Parameters (KPPs) in Table 1. Gyroscope technology developed for this task is required to meet the KPPs while operating in high dynamic ranges with minimal degradation over a service live commensurate with strategic systems. Initial gyroscope technology must show path to hostile radiation tolerance. Execution of this objective includes building and testing four (4) prototype-engineering units for compliance with KPPs to support performance verification.

Parameter Units Threshold Goal Sensor Volume inch3 30 15

Angle Random Walk µdeg/hour1/2 * *

Bias Stability µdeg/hour * *

Scale Factor ppm * *

* See Classified Appendix Table 1: Compact Strategic-Grade Gyroscope Key Performance Parameters

Technical Objective 2:

Based on testing and performance verification results from Technical Objective 1, conduct iterative development of gyroscope technology for integrated testing and development. Iterations shall improve and refine requirements analysis and system trade studies based on the KPPs listed in Table 1. Execution of this objective includes building and testing six (6) strategic grade units to support inertial navigation development, test and evaluation.

Technical Objective 3:

Resulting iterations of gyroscope technology and supporting electronics shall be harden for hostile radiation environments while retaining performance parameters from Technical Objective

2. This objective will require Application Specific Integrated Circuit (ASIC) technology trade studies; Very High Speed Integrated Circuit Hardware Description Language (VHDL) code development; and the development of a mixed signal, radiation hardened ASIC for the strategic gyroscope. Execution of this objective includes building and radiation testing two (2) radiation-hardened gyroscopes.

Technical Objective 4:

Gyroscope technology from Technical Objective 3 shall be matured for hostile radiation environments and integration into experimental space vehicles. Gyroscope units must be capable of operating during launch and a minimum of one year at Low Earth Orbit (LEO). Execution of this objective includes: building, testing, and delivering four (4) strategic radiation hardened gyroscopes for demonstration on a space vehicle; building, testing and performing upgrades on up to nine (9) strategic radiation hardened units to support inertial navigation development, test, and evaluation; and providing engineering support for space vehicle integration of radiation hardened gyroscopes and support the 1 year space flight demonstration.

Technical Objective 5:

Additional development of size de-constrained space-rated gyroscopes configured as an attitude reference system for demonstration aboard a space vehicle. The attitude reference system must operate within the KPPs specified in Table 2 during launch and for a minimum of one year at LEO. Execution of this objective includes building, testing, and delivering four (4) space-rated gyroscopes; and providing engineering support for space vehicle integration of space-rated gyroscopes and support the 1-year space flight demonstration.

Parameter Units Threshold Goal Sensor Volume inch3 65 65

Angle Random Walk µdeg/hour1/2 * *

Bias Stability µdeg/hour * *

Scale Factor ppm * *

* See Classified Appendix Table 2: Space-Rated Gyroscope Key Performance Parameters

White Papers: acceptable white papers will include summary of the current state of the art strategic grade gyroscopes to demonstrate an understanding of current technologies and relevant experience in this field. White papers will identify a conceptual plan to improve on the state of the art through either improvement of current technologies or the introduction of new ones.

Phenomenologies of interest should be ranked by highest likelihood of success.

Proposed work should include an iterative approach and focus on radiation hardening for space and strategic applications early in the design process.