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274
from soia may. For this mission,
where mamy roRl manoeuvres are
envisaged and speed is likely to
x
be
~~~OPBZIIIII~U, the approach corn ares
BWDUJIR~D~~~ wi~b the use of col gas
@hmtets whkb provide a finite life to the
told &isW.
The mP~anua e of this operational
pMw by is 8 at a$e manoeuvre enables
!
re 'QEU on eitber side of
the S AE US viw~
he nadir taaack. U& an o erational
philosophy requires that t E e wplolc
satellite indudinmg latforw, solar arrays,
md SAR muenma, L designed to form a
robust structure with no flimsy
pro~ism.
on the
oprauing duitpade, carrier frequency,
spatid ~esoi~uia~n, and possible antema
stmmres. Wwever, in OPdQP to linlit the
scope of he pap9 dl options Rave been
based on an asumed antenna area of
ha. This area is derived from
co~~ide~atic~~~i of viable payloads for
hglcmew~a~on onto a toroidal platform
within the TACSAT mass goal of <
7043.
The deadled domce of a SAR is
described in t 's section, specifically for
the single-lobk ca abilities whicb will
chauracuerise ins; pc 3 ommce in Spotlight
mode, by parameters which include;
sensitivity expressed in terms of noise
equivalent OQ) (PIIEOQ) and presented
foe the worst cases situation which is
&aased whh oh6 furthest edge of the
available ccvemge width
access croveqe width as that distance
from nadir beyond wEch ambiguities
rise to MI unacceptable level
available swath width for various
operauixlg mdep :
Jt
,,%? ';,
s atial re$&'hon' in azimuth and
evation fot$arious operating modes
e P