Abstract: Methods of producing a plurality of particle aggregates having a specified number of member particles are provided according to embodiments of the present invention. Specific methods include stimulating a plurality of particles with an aggregation stimulus to form a plurality of particle aggregates and then quenching the aggregation stimulus in order to inhibit further particle aggregation. An individual particle aggregate of the produced plurality of particle aggregates has member particles including at least a first member particle and a second member particle. Member particles of particle aggregates are optionally subjected to fusion to stabilize the particle aggregates. Produced particle aggregates having a specified number of member particles may be purified to enrich for particular aggregates.

Abstract: Methods of producing a plurality of particle aggregates having a specified number of member particles are provided according to embodiments of the present invention. Specific methods include stimulating a plurality of particles with an aggregation stimulus to form a plurality of particle aggregates and then quenching the aggregation stimulus in order to inhibit further particle aggregation. An individual particle aggregate of the produced plurality of particle aggregates has member particles including at least a first member particle and a second member particle. Member particles of particle aggregates are optionally subjected to fusion to stabilize the particle aggregates. Produced particle aggregates having a specified number of member particles may be purified to enrich for particular aggregates.

Abstract: A device for altering the after body shape of a missile configuration so as o reduce the ballistic flight drag coefficient after booster burnout and including linear shaped charge cutting device for severing a portion of a nozzle exit cone just aft of a fixed boattail configuration on the outer surface of the missile to allow boundary layer air flow to flow smoothly over the boattail and thereby reduce the base drag on the missile during the coast phase thereof.

Abstract: A spin nozzle system for imparting a thrust to pre-spin a missile prior to aunching. This system includes locating the spin nozzles within the outside diameter of the main missile motor. Also the nozzle exhaust gases are exited into the main motor exhaust cone to thereby augment the total missile thrust.