DOD SBIR 24.1 BAA

Active
No
Status
Closed
Release Date
November 29th, 2023
Open Date
January 3rd, 2024
Due Date(s)
February 21st, 2024
Close Date
February 21st, 2024
Topic No.
MDA241-011

Topic

Non-eroding Nozzle Materials for High Temperature Combustion Gases

Agency

Department of DefenseN/A

Program

Type: SBIRPhase: BOTHYear: 2024

Summary

The Department of Defense (DOD) is seeking proposals for the development of non-eroding nozzle materials for high temperature combustion gases. The research topic falls under the Missile Defense Agency and is focused on developing rocket nozzle materials that are resistant to ablation, erosion, and thermal shock, while also having high temperature strength and compatibility with highly oxidizing propellant combustion gases. In Phase I, the goal is to develop nozzle material solutions with predicted high temperature strength and resistance to oxidizing species. Thermo-structural and chemical reaction modeling can be used to demonstrate the desired properties. The material solution must also be manufacturable. Phase II involves demonstrating the survivability of the material solutions under representative loads and temperatures. The mechanical and thermal material properties should be characterized, and thermal shock resistance must be demonstrated. Additionally, potential applications beyond the Missile Defense Agency should be identified. In Phase III, the focus shifts to dual-use applications. The objective is to produce nozzle components that meet the requirements of a propulsion system supplier and demonstrate their performance through static testing. The quality, reproducibility, and production requirements for a developing prime contractor system should also be demonstrated. The project duration and funding specifics are not provided in the document. For more information and to submit a proposal, interested parties can visit the DOD SBIR 24.1 BAA solicitation page on the Defense SBIR/STTR website.

Description

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics; Advanced Materials

 

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 ablation resistant, non-eroding, rocket nozzle materials with high temperature strength and compatibility with highly oxidizing propellant combustion gases.

 

DESCRIPTION: Maximizing missile range requires higher propellant combustion temperatures without nozzle erosion. Controllable solid propellant rockets use a variety of propellants based on their application, and many propellants used for controllable solids produce highly oxidizing combustion gases. While some propellants are seen as reducing, this topic is specifically asking for solutions for highly oxidized propellants. Besides high temperature strength, successful nozzle materials must also be capable of surviving the thermal shock experienced during ignition.

 

PHASE I: Develop nozzle material solutions with predicted high temperature strength and resistance to high partial pressures of oxidizing species such as oxygen, carbon dioxide, and water. If no testing is performed in Phase I, thermo-structural and chemical reaction modeling should demonstrate ablation and erosion resistance, high temperature strength, and thermal shock resistance for use in rocket motors with combustion temperatures up to 2800°C. Manufacturability of the material solution must be demonstrated.

 

PHASE II: Demonstrate the survivability of the material solutions developed in Phase I with loads and temperatures representative of those experienced by solid propellant rocket nozzles. High temperature mechanical and thermal material properties of the material solution should be characterized by the end of this effort. Testing must demonstrate thermal shock resistance under temperature rises experienced by rocket nozzles. Identify additional applications for the proposed technology beyond MDA applications.

 

PHASE III DUAL USE APPLICATIONS: Produce nozzle components that meet the requirements of a propulsion system supplier and demonstrate performance of the nozzle components through static testing. Demonstrate the quality, reproducibility, and production requirements for a developing, prime contractor system.

 

REFERENCES:

Non-eroding nozzle throat material for rocket motors with AP-based propellant https://arc.aiaa.org/doi/abs/10.2514/6.1998-3972 
Chemical Erosion of Refractory-Metal Nozzle Inserts in Solid-Propellant Rocket Motors https://arc.aiaa.org/doi/abs/10.2514/1.37922 
Status of army pintle technology for controllable thrust propulsion https://arc.aiaa.org/doi/abs/10.2514/6.2001-3598

 

KEYWORDS: Hypersonics; Materials; High Temperature; Propulsion; Nozzle