For reasoas of design sizpliciry and for all stages of che vehicle. [sgistics, the same engine was used A malified LaCrosse exgise, IX-52, aanufactured by the Thiokol Chemical Corporatisa, was found ro best suit requirements. This engine delivers a toral of approximately 96,000 lb/sec izpulse and bas a bura- ing tise of 2.6 seconds. The second-stage units of the teo-stage carriers far Orange were fired 15 seconds after Launch; those for Tasc were fired 19 seconds after launch. The latter time was selected because it yields a matima of al- titude and mininzizes variation of apogee for any dewistian in secood-staze ignition tise. Also, this delay reduces the airlosds ani aerodynanic beating of the second stage. Tne carriers are ret2ted aerodynamically ia order to average out thrust malaligoment anc trim errors. To accooplish this the fins are sounted at an incidence angle of one-half degree. For the single-stsgse carriers this pro- duces a roll rate of approximately 6-1/2 revoiutions per second at burnout. Two spin rockets are attached to the booster of che two-stage carriers and serve to initiate a roll rate of 2-1/2 revolutions per second immediately beyoo the end of the launcher. The second stage reaches a maximm roll rate of & revolutions per second at burnout. Since it was necessary to retrieve a portion of the instrumentation for analysis, a system vas provided for recovery of the instrumented noses. The nose is joined to the midsection and motor assembly by a split-ring, clamptype connector. At a specified tine, an electrical ispulse fires two squibs which separate the two components. A l2-foot, solid-canopy parachute stowed in the nose is then deployed by a 10-foot static line attached to the midsection bulkhead. The same chute design was utilized in recovery of all the cartiers; thus, strength requirements were dictated by the 40,000-foot vehicle. For the single-stage carriers, separation occurs apprexiaately 5 to 15 seconds after apogee. For the two-stage carriers, it is necessary to allow che secood stage to descend to a lower altitude where the descent rate after deployment is near sonic speeds or less, yet not so low that the parachute could be over- Stressed. Therefore, altitudes in the region of 160,000 feet seemed to be the best choice. Descent tine of the recovery operation ranges from 11 minutes for the 40,000-foot nose unit to 25 aimites for the sazpler nose. Ispace ve- locities are 4h feec per second for the instrumented noses and 32 feet per second for the sampler noses.