SBIR-STTR Award

M-DOT Inc. proposes to conduct a trade study and design a low- cost hot-gas turbine driven fuel pump/hydraulic power supply for use on an advanced missile system. When design is complete, a cost analysis of a proposed production version will be conducted. The unit will be capable of the following: Delivering 0.5 lbm/sec of jet fuel against a back pressure of 100 psia and providing 1 hp of hydraulic power at turbine inlet conditions of 1200 Of/20 psia and 1 psia exit pressure. Delivering 10.0 lbm/sec jet fuel against a back pressure of 500 psia and providing 5 hp of hydraulic power at turbine-inlet conditions of 1200 Of/100 psia and 14.7 psia exit pressure. The Phase I program will be subdivided as follows: 1. Initial establishment of system requirements. 2. Thermodynamic analysis of the required system. 3. Feasibility study and survey of off-the-shelf commercially- available components. 4. Detailed thermodynamic performance study of the system using models of selected components. 5. System cost analysis to ensure cost objectives are met. 6. Detailed design of system components. 7. Creation of a Phase II program plan for fabrication and test of two test units.

M-DOT INC. propses to refine the design of a low-cost hot-gas-turbine driven fuel pump/hydraulic power supply for use on the Navy Fasthawk cruise missile and produce eight development units for ground and flight test by the Navy. The unit will consis of turbocharger-based ram-air-driven turbine wheel with shaft mounted high-speed centrifugal pump and pressure multiplier for hydraulic power. The unit will be self starting and capable of providing all required fuel and hydraulic power to the missile while using less than 1% of main engine airflow. The Phase II program will be divided into Base and Option as follows: Base: 1. Update of mission and system requirements. 2. Bench test of the Phase I turbopump design. 3. Refinement of the turbine flowpath design 4. Refinement of the fuel pump flowpath design. 5. Refinement of the bearing and lubrication system. 6. Design and analysis of a turbine speed control. 7. Detailed design of system components 8. Preliminary design review 9. Fabrication and bench test of a prototype Option: 1. Final Design Review 2. Fabrication of 8 development units 3. Ground testing of development units 4. Flight test support

Benefits:
The proposed turbopump power supply will facilitate development of the Fasthawk low-cost, high-speed, ramjet-powered missile. This unit can also be used in modified form to provide drive accessories on tactical missiles where bleed air from an engine or hot gases from a pyrotechnic gas generator are available. Such a unit could be used as an emergency back-up power source or as a pump on military or commercial aircraft. This unit also has application on future hypersonic scramjet missiles and on ultra-low-cost orbital launch vehicles.

Keywords:
Turbopump Cruise Missile Turbocharger Missile Accessories High-Speed-Pump