Navigation systems requirement analysis for the Aeroassist Flight Experiment (AFE)Navigation requirements for Aeroassist Flight Experiment (AFE) spacecraft passing through the earth's atmosphere have been studied using a 6-DOF dynamics model, an Inertial Measurement Unit model, a baseline AFE aeropass flight guidance logic, and a baseline AFE aeropass control model. The goal of this study is to determine, in a statistical sense, how much flight path angle error can be tolerated at Entry Interface (EI) and still have acceptable delta-V requirements at exit to position the AFE spacecraft for recovery. Assuming there is fuel available to produce 370 ft/sec of delta-V at atmospheric exit, a 3-sigma standard deviation in flight path angle error of 0.04 degree at EI would result in a 98 percent probability of mission success. In addition to the required delta-V at exit, other aeropass parameters such as maximum aeroheating rate, fuel consumption, and the science requirements affecting mission success are also investigated.
Document ID
19900032810
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huang, K. H. (Teledyne Brown Engineering Huntsville, AL, United States)
Chang, Ho-Pen (Sverdrup Technology, Inc. Huntsville, AL, United States)
Wells, Eugene M. (Control Dynamics Co. Huntsville, AL, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking