Attitude
Director Indicator
The commander's
and pilot's ADIs are supported throughout the mission, while the
aft ADI is active only during orbital operations. They give the
crew attitude information as well as attitude rate and attitude
errors, which can be read from the position of the pointers and
needles. Each ADI has a set of switches by which the crew can select
the mode or scale of the readout. The commander's switches are located
on panel F6, the pilot's on panel F8 and the aft switches on panel
A6.
The orbiter's
attitude is displayed to the flight crew by an enclosed ball (sometimes
called the eight ball) that is gimbaled to represent three degrees
of freedom. The ball, covered with numbers indicating angle measurements
(a zero is added as the last digit of each), moves in response to
software-generated commands to depict the current orbiter attitude
in terms of pitch, yaw and roll.
The ADI attitude
select switch determines the unit's frame of reference: inrtl (inertial),
LVLH (local vertical/local horizontal), and ref (reference). The
inrtl position allows the flight crew to view the orbiter's attitude
with respect to the inertial reference frame, useful in locating
stars. The LVLH position shows the orbiter's attitude from an orbiter-centered
rotating reference frame with respect to Earth. The ref position
is primarily used to see the orbiter's attitude with respect to
an inertial reference frame defined when the flight crew last depressed
the att ref push button. It is useful when the crew flies back to
a previous attitude or monitors a maneuvering system thrusting period
for attitude excursions. The two forward switches are active during
ascent, orbital and transition flight phases but have no effect
during entry, the latter part of a return to launch site or phases
when the backup flight system is driving the ADIs. The aft switch,
like the aft ADI, is operational only in orbit.
Each attitude
director indicator has a set of three rate pointers that provide
a continuous readout of vehicle body rotational rates. Roll, pitch
and yaw rates are displayed on the top, right and bottom pointers,
respectively. The center mark on the graduated scale next to the
pointers shows zero rates, while the rest of the marks indicate
positive or negative rates. The adi rate switch for each indicator
unit determines the magnitude of full-scale deflection. When this
switch is positioned to high (the coarsest setting), the pointer
at the end of the scale represents a rotation rate of 10 degrees
per second. When the switch is positioned to med, a full-range deflection
represents 5 degrees per second. In the low position (the finest
setting), a pointer at either end of the scale is read at a rate
of 1 degree per second. These pointers are ''fly to'' in the sense
that the rotational hand controller must be moved in the same direction
as the pointer to null a rate.
ADI rate readings
are independent of the selected attitude reference. During ascent,
the selected rates come directly from the solid rocket booster or
orbiter rate gyros to the ADI processor for display on the rate
pointers. During entry, only the pitch rate follows the direct route
to the ADI display. The selected roll and yaw rates first flow through
flight control, where they are processed and output to the ADI as
stability roll and yaw rates. (This transformation is necessary
because, in aerodynamic flight, control is achieved about stability
axes, which in the cases of roll and yaw differ from body axes.)
Three needles
on each attitude director indicator display vehicle attitude errors.
These needles extend in front of the ADI ball, with roll, pitch
and yaw arranged just as the rate pointers are. Like the rate indicators,
each error needle has a background scale with graduation marks that
allow the flight crew to read the magnitude of the attitude error.
The errors are displayed with respect to the body-axis coordinate
system and, thus, are independent of the selected reference frame
of the attitude display.
The ADI error
needles are driven by flight control outputs that show the difference
between the required and current vehicle attitude. These needles
are also ''fly to,'' meaning that the flight crew must maneuver
in the direction of the needle to null the needle. For example,
if the pitch error needle points down, the flight crew must manually
pitch down to null the pitch attitude error. The amount of needle
deflection indicating the number of degrees of attitude error depends
upon the adi error switch for each ADI. In the high position, the
error needles represent 10 degrees, med represents 5 degrees and
low represents 1 degree.
At the aft
flight station on panel A6, the aft sense switch allows the flight
crew to use the aft ADI, RHC and translational hand controller in
a minus X or minus Z control axis sense. These two options of the
aft ADI and hand controllers correspond to the visual data out of
the aft viewing (negative X) or overhead viewing (negative Z) windows.
Each ADI has
a single flag labeled off on the left side of the display whenever
any attitude drive signal is invalid. There are no flags for the
rate and error needles; these indicators are driven out of view
when they are invalid.
The ADI contractor
is Lear Siegler, Grand Rapids, Mich.
|