US Army ARDEC, AMSTA-AR-PC, Picatinny Arsenal, New Jersey 07806-5000

10 -- THRUSTER TECHNOLOGIES DUE 060297 POC Lawrence A. Visconti, Jr., Contracting Officer, (201) 724-3125 WEB: US ARMY TACOM-ARDEC Procurement Network, http://procnet.pica.army.mil/procacts.htm. E-MAIL: Kimberly M. Ritacco, kritacco@pica.army.mil. The US Army plans on pursuing technologies that will enhance the accuracy of gun launched projectiles to enable engagement at extended ranges. Proof of principle efforts are currently underway to prove out a concept that uses miniature accelerometers to measure lateral launch disturbances and then fires a radial thrust or combination of radial thrusts with a calculated impulse and orientation (depending on the magnitude and orientation of the measured disturbances). This diversion of the projectile occurs very shortly after sabot discard to achieve significant increases in hit probability at extended ranges. Evaluation of the accelerometer technology is underway for the high g tank fired ammunition environment. A general description of the system is as follows: The projectile is fired from the cannon and the accelerometers measure the lateral launch accelerations. The measured accelerations are integrated to obtain the change in flight path from the reference direction. The flight path data is processed to determine the required thrust magnitude and orientation needed to correct the flight path back to the reference direction. The US Army is requesting information from reputable designers and manufacturers who have the capabilities to provide state-of-the-art thruster systems and/or the data processing systems that can be integrated with the accelerometer packages. For the Proof -of- Principle demonstration, the following requirements apply: Thruster requirements: 10 lbf.sec maximum total impulse, duration of 5mSec or less desired. This may be obtained through firing of multiple small thrusters. A minimum impulse of no more than 0.5 lbf.sec and the same duration are desirable. System should be capable of producing intermediate values of impulse. Thruster package Outer Diameter: 3.00 inches maximum Thruster package Inner Diameter: 1.5 inches minimum Thruster package Length: 3 inches maximum Peak Launch Acceleration: Up to 55000 times gravity Velocity: Up to 1500 m/s at muzzle Temperature: -32c to 52c operational -40c t0 63c storage Shelf life: 20 years Time of flight: Up to 5 seconds The system data is acquired through telemetry and provisions for such an interface is required. Successful demonstration of the above will follow on to development for a tactical system whose requirements are listed below: Launch: Up to 70000 gravities Velocity: Typically 1500-1700 m/s at muzzle Temperature: -32c to 52c operational -40c t0 63c storage Shelf life: 20 years Available volume: 2 cubic inches Outer Diameter: Less than 1 inch Time of flight: Up to 5 seconds Companies possessing the requisite capabilities should submit information and data on the proof of principle to the above addressee no later than 23 May 97. Comments on the tactical configurations are also requested. THIS IS A SOURCES SOUGHT NOTICE ONLY. This is not a request for proposal, but only a request for information on available technologies. (0129)

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