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DoW/USAF · DoW SBIR 2027 BAA

DAF27BZ02-NV015 — Solid Propellant Environmental Effects Digital Twin

Pre-Release | released 2026-11-04 | opens 2026-12-02 | closes 2027-01-06 | CMMC Level 2 (Self), SBIR

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TPOC: J Shelley <[email protected]>; Farid Rafla <[email protected]>

Keywords: Solid Rocket Propellant aging, viscoelastic fracture mechanics, temperature effects in elastomers, elastomer environmental effects

Technology areas: Air Platform, Materials, Nuclear, Space Platforms, Weapons

Objective

The objective of the proposed effort is twofold: 1) Model and simulate the combined effects of thermal, temporal, chemical, and geometric changes to solid propellants that occur over time for in rocket motor grains, and 2) integrate predictive behavior tools into solid rocket motor design tools for decision-quality models and simulations. The intended result is a solid propellant aging and environmental process digital twin.

Description

Solid Rocket Motors (SRMs) provide propulsion for many critical defense applications including surface launched, air launched, ballistic, and space vehicles. The propellant that creates acceleration through these SRMs is a complex active material that can be sensitive to environmental effects from thermal loads, exposure to air or humidity, chemical changes, pressure, or vibration loads due to time or ingredient changes. Both mechanical response characteristics and ballistic properties can be affected. This topic requests projects that will combine computational modeling and design capability from several sources to simulate aging responses due to environmental effects. The framework must follow Modular Open Systems Approach standards mandated in 10 U.S.C. § 4401 for compatibility with several commercially available computational tools such as ANSYS, ABAQUS, Python, MatLab, SysML, and others.

Phase I

Define a ballistic or structural degradation mechanism in solid propellent that can be implemented in a damage tolerant design process for solid rocket motors. Develop the technical argument for transitioning non-continuum mechanisms to a continuum-based analysis techniques. Develop a Digital Engineering plan to create the desired capability to model Solid Rocket Propellant and predict behavior over extended periods of time and environmental conditions.

Phase II

Phase 2 will build out the combined moderate fidelity predictive models of at least two environmental effects and anchor predictions to historical propellant aging data implemented through Cameo, OMG, or other SysML 2.0 platform. Performance predictions including both ballistic degradation and structural reactions should be included. Analytical techniques must be compatible with a MBSE enabled design threads.

Phase III / dual use

Phase 3 is intended to create a “digital twin” of the solid propellant aging process that can be integrated into solid rocket motor design tools and SySML – based predictive and systems engineering tools. Models and tools have three opportunities for transition and commercialization: 1) transition to Government Refence Architectures for SRM design and vehicle integration, 2) incorporation into commercial SRM design capabilities through the SRM industry, or 3) transition or reuse into other commercially viable polymer-dependent industries such as rubber tires, automotive components, in-vivo medical devices, hazardous response Personal Protective Equipment (PPE), and sporting goods.

References

  1. Yılmaz, Kuran, Ozgen ; Reliability Assessment of Solid-Propellant Rocket Motors Under Storage and Transportation Loads
  2. AIAA Aerospace Research Central, Published Online:1 Aug 2017 https://doi.org/10.2514/1.A33777. Kelley, Trout; Elements of solid rocket service life prediction
  3. Published Online:16 Aug 2012 https://doi.org/10.2514/6.1972-1085

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