Novel Ignition Systems for multi-pulse Solid Propellant Rocket Motors - STTR Topic MDA26TZ04-NV001

Funding Amount:

Phase I - $314,000

Deadline to Apply:

August 19th, 2026

ITAR:

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 a reliable, lightweight ignition system for solid propellant propulsion systems that is capable of multiple ignitions.

Description:

Solid propellant propulsion systems which utilize multiple pulses commonly use separate pyrotechnic or pyrogen igniters for each pulse. In recent years, alternative ignition methods have been conceptualized which could ignite rocket motors multiple times with the same ignition hardware. Alternative ignition methods may also eliminate the need for sensitive pyrotechnic initiators typically used in conventional igniters, reducing the danger of inadvertent initiation. Ignition systems which are capable of multiple ignitions facilitate the design of systems which provide more flexible use of propellant.

PHASE I:

Design an ignition system capable of generating combustion gases from reduced smoke propellant grains with mass flow rates adequate to achieve stable combustion with multiple ignitions. Proposed designs must consider attenuation from combustion products. Proposed ignition system should minimize use of novel subcomponents and maximize the use of commercially available subcomponents. Proposed work plans must include demonstration of combustion gases to validate models.

PHASE II:

Develop an ignition system which could ignite solid propellant propulsion systems in multiple ignitions with a single ignition system. The igniter should be applicable to several propellant compositions. The proposed ignition system must be demonstrated to achieve motor rise times with a wide range of motor free volumes, and the mass of the proposed ignition system should be lower than the mass of a conventional pyrogen or pyrotechnic igniter. Proposer should specify the energy requirements and energy source for the proposed igniter system. Required power should not exceed capabilities of existing commercially available thermal batteries and power supplies. Work with propulsion system supplier or system level integrator to further define performance attributes.

PHASE III DUAL USE APPLICATIONS:

Design and build an ignition system for solid propellant rockets capable of igniting rockets with free volumes and motor rise times specified by prime contractors. The proposed ignition system must be capable of multiple ignitions for multiple rocket pulses with the same hardware.

Who will win?

If you can achieve the objective above better than any other company on the market, you have a very high-likelihood of success and should apply.

Who is eligible to apply?

Any company that meets the following criteria:

• For-profit company

• U.S.-owned and controlled.

• 500 or fewer employees (including affiliates)

How Can BW&CO Help?

1) End-to-end support including, strategy, writing of the full proposal, and administrative & compliance support.

2) Proposal strategy and review.

3) Administrative & compliance support.

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