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A summary of the state-of-the-art in determining captive flight loads and separation trajectories of airborne stores is presented. The summary is based largely on a recent survey of appropriate aerospace concerns and government installations. Responses to the survey indicate that the present state-of-the-art does not allow an accurate general analytical solution to the problem except under the most idealized situations. Testing of the specific aircraft/store combination is therefore recommended unless the combination closely matches a previously tested combination for which data are available. (Author).
Design loads computations for airborne stores is such a recurrent need that it became worthwhile to program the tedious task for digital computers. Two hanger configurations are treated: (1) the two-lug, four-sway-brace bomb rack common to U.S. stores, and (2) a statically determinate configuration often used for rail-launched missiles. Procedures recommended by MIL-A-8591 are used where applicable. Component hanger loads for stores subjected to arbitrary load conditions in captive flight are printed, and shear-moment distributions are plotted. (Author).
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Tests were conducted on a four-finned, ogive-cylinder store model which was mounted on the von Karman Gas Dynamics Facility (VKF) Captive Trajectory System (CTS) in the Arnold Engineering Development Center (AEDC) Supersonic Wind Tunnel A. The purpose of these tests was to provide information necessary for an independent check on the VKF CTS trajectory mode results. Grid and trajectory data were obtained for the store, both in the free stream and in the interference flow field of a generalized parent-aircraft model. The Mach number was 1.63, with Reynolds numbers per foot of 5.0 and 3.8 million. Grid data from these tests were used in conjunction with the Air Force Flight Dynamics Laboratory (AFFDL) Six-Degree-of-Freedom Computer Program (SDFCP) to simulate the trajectories obtained by the VKF CTS. These SDFCP simulations compared favorably with the CTS trajectories, providing an important compared favorably with the CTS trajectories, providing an important independent verification of the VKF CTS trajectory mode results. This report documents this validation effort and provides a general description of the VKF CTS as well as guidelines for potential users of this system. (Author).