Accession Number : AD0437525


Title :   DERIVATION OF THE GUIDANCE EQUATIONS FOR THE USAF ATHENA


Corporate Author : AEROSPACE CORP EL SEGUNDO CA


Personal Author(s) : Herman, L K ; Allman, R M ; Katz, B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/437525.pdf


Report Date : 30 Mar 1964


Pagination or Media Count : 45


Abstract : The USAF ATHENA is a re-entry test vehicle which has four solid propellant stages. A midcourse correction type of guidance is used to compensate for boost dispersions by adjusting the third stage attitude and ignition time. The guidance computations are performed in a ground based digital computer using radar data obtained after second stage burnout. Because this is a re-entry test vehicle, the guidance system must cause the payload to meet various re-entry constraints as well as the usual impact point constraint. The complete derivation of the guidance equations and a description of the entire guidance loop are presented in this report.


Descriptors :   *HYPERSONIC TEST VEHICLES , MIDCOURSE GUIDANCE , GUIDED MISSILE TRAJECTORIES , REAL TIME , TAYLORS SERIES , RADAR TRACKING , MATHEMATICAL PREDICTION , NUMERICAL INTEGRATION , DIFFERENTIAL EQUATIONS , EQUATIONS , CORRECTIONS , COMMAND GUIDANCE , NOSE CONES , REENTRY VEHICLES , ATTITUDE CONTROL SYSTEMS


Subject Categories : Research and Experimental Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE