FUNDAMENTALS FOR THE GENERATION OF A MATH MODEL FOR A MISSILE FLYING IN THREE-DIMENSIONAL SPACE WITH SIX DEGREES OF FREEDOM.

摘要

Methods are explained for deriving the differential equations describing a general missile airframe flying in three-dimensional space. All the forces and moments acting on the missile are written as vectors. These vectors are readily expressed in suitable coordinate systems. After they are so expressed,they are transformed to a common coordinate system where the solutions are carried out. The desired output information is then transformed to a fixed system on the ground and presented in terms of that system. A short exposition of vector analysis,to the extent required,is included,and matrix notation is emphasized throughout. Methods (utilizing vector analysis and coordinate system transformations) are presented for handling thrust misalignment,the general moment of inertia tensor,curvature of the earth,rotation of the earth,targets,etc. The methods,as employed,generate an exact representation of the flying missile;however,wherever possible,approximations are suggested which simplify the equations. Errors,not only from approximations,but from other sources,are pointed out when such situations arise. Since there are so many types of guidance philosophies,only very general statements are made concerning guidance. However,the guidance philosophies for two specific types of missiles are included as examples. (Author)