Quantcast Figure 1-4. AH-1S Low Airspeed Profile.

 

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Figure 1-3. Airflow Under the Rotor.
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TM-9-1270-219-13-P Fire and Flight Air Data Subsystem Helicopter Armament: XM 143 PN 03-004-02 Manual
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Figure 1-5. Air Data Subsystem Block Diagram.
TM 9-1270-219-13&P
Figure 1-4. AH-1S Low Airspeed Profile.
a . The AADS is a swiveling pitot-static probe which
error against lateral airspeed for discrete forward speeds,
samples local airflow pitot and static pressures, the angles
a complete picture of Iateral errors is obtained.
of that airflow relative to the helicopter and the free
j. Vertical airspeed errors are corrected in a similar
stream air temperature. Pneumatic pressure outputs are
fed via the helicopter plumbing to transducers in the EPU
way to the horizontal airspeed errors, using error curves
and
angle
airflow
signals representing
Electronic
and
techniques.
temperature are also fed to the EPU. The pneumatic
pressure outputs are converted into analog electronic
k.
Because
downwash
is
inconsistent
when
the
signals by the electrical force balance transducers in the
h e l i c o p t e r is in ground effect, the ADS utilizes the Radar
EPU.
A l t i t u d e signal to obtain the corrected airspeed at heights
of less than 30 feet.
b. Computation to convert the AADS outputs into
airspeed components and temperature and pressure output
System Description of the Air Data Subsystem
is accomplished by a microprocessor based computing unit
( A D S ) . A system block diagram is shown in figure 1-5 and
i n the EPU. The computing unit also controls input and
modular breakdown of the ADS is shown in figure 1-6.

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