guidance, flight mechanics and trajectory optimization

For the guidance technique which nulls the angular rage of the LOS, the
direction of thrust are along the range and normal and steering is achieved'
by determining the length of time each rocket motor is to operate. For this
situation, the link between the state estimation and the dynamics is rep-
resented as
ESTIMATE
OF
STATE
I
I
DETERMINE
DURATION
OF
NORMAL THRUST
I
*
I
* I DYJMucs
I
I
I
DETERMINE
DURATION -
OF
RADIAL THRUST
Still another representation is possible for the optimum guidance scheme of
Section 2.3.2 since this scheme determines the steering angles directly.
For this method, the two blocks of the first sketch can be combined as
I I
ESTIMATE
OF
STATE
I
I
e
COMPUTE
Q(t) I ,
OPTIMUM I-
THRUST PROGRAM
DYNAMICS *
I
I .
Although the sensors necessary to measure the quantities necessary for
a particular guidance scheme or the methods used to smooth the raw data have
been discussed in this Monograph, these portions of the guidance and navi-
gation process have been included in the above diagrams for completeness.
Both of these.subjects have been discussed in detail in previous monographs
of this series (Reference 1.1 and 2.22).
86
I