SBIR-STTR Award

In this Phase I program, ISP, Inc. proposes to design, develop, and deliver a low cost hot gas valve to MICOM for testing in their advanced tactical missile propulsion program. The proposed valve is designed to provide continuous throttling of 2000 degrees F. fuel-rich solid propellant gas over a mass flow ratio of 5:1 with a maximum flow rate of 1 lbm/sec. The valve design is based on the axially translating pintle which controls flow by varying nozzle throat ara. To achieve the desired low cost, the valve comprises commercially-available control components such as the actuator and the servovalve and features a unique hydraulic power supply that derives its power from gas generator chamber pressure. The concept is scaleable over the desired 0.1 to 50 lbm/sec mass flow rate range and is compatible with conventional nozzle materials as evidenced by previous pintle nozzle development which has demonstrated a flow rate range of less than 0.1 to over 1000 lbm/sec and gas temperatures up to 6000 degrees F. ISP, Inc. is proposing a six-month program at the conclusion of which a heavyweight hot gas valve will be delivered to MICOM with sufficient spare parts to support a minimum of five advanced propulsion tests. Prior to delivery, ISP, Inc. will verify valve survivability and operability with a fullscale hot fire test.

The need for a tactical motor energy management system that will provide multi-mission capability is apparent given the continuing trend of reduced DoD spending that will limit the number of future missile systems. The U.S. Army must focus its limited resources on those endeavors that make maximum utilization of Horizontal Technology Integration (HTI) and Planned Product Improvement (P3I). In Phase II, ISF, Inc. with Aerojet as the principal subcontractor, proposes to develop and demonstrate an on-command axial pintle system (ALPS) that will provide variable thrust control for conventional solid propellant tactical rocket motors. The incorporation of an ALPS will improve missile performance and range, enhance target set flexibility, increase lethality, and improve warfighter survivability without the cost or time of developing a new missile system. The proposed ALPS will be demonstrated in both subscale and full-scale propulsion configurations that are directly applicable to current Army tactical missile systems. Before contract award, ISP and Aerojet will use company funding to complete the design of axial pintle hardware and tooling. Phase II contractual effort will include ISP fabricating and/or procuring all APS hardware, and manufacturing subscale propellant grains. Sufficient test hardware and grains will be produced to allow one subscale ALPS test at Aerojet and five subscale tests at MICOM. After successful completion of subscale testing, ISP and Aerojet will conduct a full-scale ALPS static firing with a U.S. Army HAWK motor cast with Advanced Medium Range Air-to-Air Missile (AMAMM) rocket motor propellant. Aerojet will contribute all HAWK motor materials including case, insulation, liner, propellant ingredients, and igniter. Successful demonstration of the proposed ALPS will validate the technology and provide the first step to incorporate "smart" propulsion into operational and future missile systems. Successful development of an on-command APS for tactical rocket motors will allow the U.S. military to significantly reduce procurement and operational costs. This will be achieved by retrofitting existing assets with APS'S that enable the missile system to achieve improved performance, mission flexibility, and greater lethality. Commercial application includes satellite station keeping and orbital transfer propulsion systems that would utilize a throttling pintle with solid prope