Publication Date:
2019-06-27
Description:
A general procedure for computing the region of influence of a maneuvering vehicle is described. Basic differential geometric relations, including the use of a general trajectory parameter and the introduction of auxiliary variables in the envelope theory are presented. To illustrate the application of the method, the destruct region for a maneuvering fighter firing missiles is computed.
Keywords:
AERODYNAMICS
Type:
NASA-TP-1648
,
L-13419
Format:
application/pdf