Accession Number : AD0429015


Title :   SPACE LAUNCH VEHICLE FULL-SCALE DAMPING TESTS


Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA


Personal Author(s) : Miller, J G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/429015.pdf


Report Date : 21 Jun 1963


Pagination or Media Count : 54


Abstract : The wind study portion of testing showed that the SLV gantry tower is sufficiently stable to be used as a base for forced oscillation of the vehicle and that any measurement of relative motion between the vehicle and tower is of vehicle movement only. The structural damping ratio of the first cantilever mode of Atlas Agena 461 and 698 BJ varied between a high of 2.14 percent and a low of 0.57 percent, depending upon the axes and the tanking condition. It was not possible to determine a damping factor for all cases by the methods used because of the internal (liquid) movements, but for many conditions damping factors were determined with good accuracy. In general the theoretical frequencies were verified to an excellent degree. The experimental damping factors agreed reasonably well with the results of previous tests. Increased confidence in the recent SLV ground wind restrictions has been the direct result of this test.


Descriptors :   *LAUNCH VEHICLES , GUIDED MISSILE SAFETY , WIND , DAMPING , TEST METHODS , MOMENTS , REDUCTION , CONFIGURATIONS , TRANSDUCERS , OSCILLATION , FRICTION , SURFACE TO SURFACE MISSILES , LIQUID ROCKET PROPELLANTS , PROPELLANT TANKS , PAYLOAD , DEFORMATION


Subject Categories : Unmanned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE