DYNAMIC EQUATIONS FOR MISSILE STABILITY ANALYSIS,

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Abstract:

This report develops a method of presenting missile dynamics such that the equations may be easily adapted to any missile system configuration. Standardization of the missile dynamic equations is accomplished by combining the effects of propellant sloshing, flexible vehicle structure, and engine dynamics in a set of orthogonal coordinates. This approach is termed combined mode representation. The theory of combined mode representation is presented in general terms. The complete missile system dynamic equations are then derived using this representation. The derivation of the equations for obtaining the combined mode coordinates is followed by a description of the computer routine used to solve these equations. Finally an example control system problem is written in terms of combined modes. Author

Author(s):
Hieatt, J. L. ; Palmer, J. L.
Author Organization(s):
TRW SPACE TECHNOLOGY LABS LOS ANGELES CALIF
Supplementary Note:
Legibility of this document is in part unsatisfactory. Reproduction has been made from best available copy.
Annotation:
Dynamic equations for missile stability analysis.
Pagination:
0068

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
STL/TM-60-0000-00063
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*GUIDED MISSILES, *EQUATIONS, STABILITY, DYNAMICS, DEFLECTION, SLOSHING, CONFIGURATIONS, CONTROL SYSTEMS, MOTION, MASS, COMPUTER PROGRAMMING, BOUNDARY VALUE PROBLEMS, MATRICES(MATHEMATICS)
Report Date:
1960 Jul 01