TECHNOLOGY AREAS: Weapons

ACQUISITION PROGRAM: PMA-259, Air-to-Air Missile Systems

RESTRICTION ON PERFORMANCE BY FOREIGN CITIZENS (i.e., those holding non-U.S. Passports): This topic is "ITAR Restricted." The information and materials provided pursuant to or resulting from this topic are restricted under the International Traffic in Arms Regulations (ITAR), 22 CFR Parts 120 - 130, which control the export of defense-related material and services, including the export of sensitive technical data. Foreign Citizens may perform work under an award resulting from this topic only if they hold the "Permanent Resident Card", or are designated as "Protected Individuals" as defined by 8 U.S.C. 1324b(a)(3). If a proposal for this topic contains participation by a foreign citizen who is not in one of the above two categories, the proposal will be rejected.

OBJECTIVE: Develop and demonstrate a reliable low-cost ignition system for use in multi-pulse and high-volume-fraction end-burning solid rocket motors for tactical air-launched missile applications.

DESCRIPTION: To improve overall weapon performance, activities are ongoing to enhance the functionality of traditional volume-limited tactical solid rocket motors. These efforts have led to the evaluation of cutting-edge high-volume-fraction and multi-pulse solid rocket motors. Increasing the propellant volume loading and using multiple discrete pulses push the limit of, or even exceed the capabilities of, existing ignition systems. With higher volume fractions there is typically less propellant surface area available for ignition and significantly reduced free volume for hot ignition gases, making rapid and reliable ignition more difficult. Multiple discrete propellant grains require reliable and safe low-volume embedded igniters for each distinct pulse, all of which must work seamlessly together. The requisite level of integration and the parasitic weight penalties pose significant technical challenges. Each igniter must have a link to a remote safety-approved firing circuit that is accessed via an energy transmission line that is embedded inside and eventually transits the combustion chamber. In addition, each igniter must both rapidly ignite the discrete propellant pulse grain and fill the void volume left by burning previous pulses. Magnifying the complexity of achieving these objectives are stringent cost, space, size, and power parameters, as well as the requirements that the resultant system function reliably within the appropriate time frame and generate minimal debris. All new subsystems, both individually and in concert with the entire weapon system, must meet the performance, safety, and insensitive munitions requirements specified in MIL STD 1901A, MIL STD 2105C, and MIL STD-810F.

Realizing the ultimate goal for such a revolutionary ignition system entails developing advanced technologies for a multi-pulse initiation system, a pulse 1 igniter (main grain ignition), and a pulse 2 igniter (discrete grain ignition). Consideration will be given to innovative approaches that achieve one or more of these technologies. The ultimate objective is for all individual solutions to work flawlessly together. Finding the means to satisfy each of these disparate needs will be exceptionally difficult and will require unique and groundbreaking approaches. Even more challenging may be finding a way to integrate the resultant technologies so that they all work in concert. Extraordinary innovation and creativity, as well as the ability to push the state of the art, are required. The resultant system must function within the appropriate time frame and generate minimal debris.

PHASE I: Develop an innovative concept for an advanced ignition system for use in state-of-the-art end-burning solid rocket motors for tactical air-launched missiles. Demonstrate the feasibility of the technology and generate a plan to demonstrate functionality.

PHASE II: Devise and build a prototype ignition system for testing in a representative environment and determine the efforts required to bring the technology to the engineering and manufacturing development phase.

Note: The prospective contractor(s) must be U.S. Owned and Operated with no Foreign Influence as defined by DOD 5220.22-M, National Industrial Security Program Operating Manual, unless acceptable mitigating procedures can and have been be implemented and approved by the Defense Security Service (DSS). The selected contractor and/or subcontractor must be able to acquire and maintain a secret level facility and Personnel Security Clearances, in order to perform on advanced phases of this contract as set forth by DSS and NAVAIR in order to gain access to classified information pertaining to the national defense of the United States and its allies; this will be an inherent requirement. The selected company will be required to safeguard classified material IAW DoD 5220.22-M during the advance phases of this contract.

PHASE III: Integrate the ignition system into a full-scale analog rocket motor to be tested in firings at a designated site.

PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: The commercial Space sector has a need for modernized standard initiators and ignition systems for use in the next generation of launch vehicle boosters. The technologies demonstrated in this SBIR would have application to these commercial propulsion systems.

REFERENCES:
1. MIL-STD-1901A, Munition Rocket and Missile Motor Ignition System Design, Safety Criteria for, dated 6 June 2002

2. MIL-STD-2105C, Hazard Assessment Tests for Non-Nuclear Munitions, dated 14 July 2003

3. MIL-STD-810F, Environmental Engineering Considerations and Environmental Tests, dated 1 January 2000

KEYWORDS: Solid Propulsion Rocket Motors; Multi-Pulse Solid Rocket Motors; Air-Launched Rocket Motors, Ignition Systems; Multi-Pulse Ignition Systems; Ignition Safety Devices

** TOPIC AUTHOR (TPOC) **

DoD Notice:   Between November 10 and December 12, 2010, you may talk directly with the Topic Authors to ask technical questions about the topics. Their contact information is listed above. For reasons of competitive fairness, direct communication between proposers and topic authors is not allowed starting December 13, 2011, when DoD begins accepting proposals for this solicitation.

However, proposers may still submit written questions about solicitation topics through the DoD's SBIR/STTR Interactive Topic Information System (SITIS), in which the questioner and respondent remain anonymous and all questions and answers are posted electronically for general viewing until the solicitation closes. All proposers are advised to monitor SITIS (11.1 Q&A) during the solicitation period for questions and answers, and other significant information, relevant to the SBIR 11.1 topic under which they are proposing.

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