21-05-2012, 05:03 PM
MODEL 1221T1 INDICATED LOW AIRSPEEDTRANSDUCER
[attachment=22625]
DESCRIPTION
The Model 1221T1 Indicated Airspeed Transducer is
designed to provide a high level DC output signal
proportional to indicated airspeed for low airspeed
vehicles. This transducer uses a solid state, flight proven
design and has a calibrated indicated airspeed range of 30
to 180 knots.
The capacitive pressure sensing capsule is used in the
transducer and provides infinite resolution, excellent
repeatability, and negligible hysteresis. These three major
parameters determine the inherent relative accuracy of the
transducer. The excellent relative accuracy of the Model
1221T1 transducer provides the capability to maintain
constant airspeed flight when the autopilot is engaged. It
also assures that the aircraft will return precisely to a preestablished
flight condition after completion of aprogrammed maneuver or if disturbed by turbulence.
SPECIFICATIONS
Operating Accuracy (–54°C to +71°C)
±(2.5 knots + 0.4% of reading)
Long-Term Stability (per 12 month period)
Initial error band limits will increase by no more than 0.5
times their initial limits.
Overpressure Effect
The transducer will withstand a differential input pressure of
4.541 in. Hg (300 knots) without subsequent damage or
performance degradation.
Vibration Effect
Operating accuracy errors will increase by no more than 0.15
times their initial limits.
Response Time (63% step pressure change): 20 msec
Electrical
Input Power: ±15 VDC ±0.75VDC @0.055
amperes maximum (each)
Output Voltage
Gradient and Range: 75 mV/knots from 30 to 180 knots
[attachment=22625]
DESCRIPTION
The Model 1221T1 Indicated Airspeed Transducer is
designed to provide a high level DC output signal
proportional to indicated airspeed for low airspeed
vehicles. This transducer uses a solid state, flight proven
design and has a calibrated indicated airspeed range of 30
to 180 knots.
The capacitive pressure sensing capsule is used in the
transducer and provides infinite resolution, excellent
repeatability, and negligible hysteresis. These three major
parameters determine the inherent relative accuracy of the
transducer. The excellent relative accuracy of the Model
1221T1 transducer provides the capability to maintain
constant airspeed flight when the autopilot is engaged. It
also assures that the aircraft will return precisely to a preestablished
flight condition after completion of aprogrammed maneuver or if disturbed by turbulence.
SPECIFICATIONS
Operating Accuracy (–54°C to +71°C)
±(2.5 knots + 0.4% of reading)
Long-Term Stability (per 12 month period)
Initial error band limits will increase by no more than 0.5
times their initial limits.
Overpressure Effect
The transducer will withstand a differential input pressure of
4.541 in. Hg (300 knots) without subsequent damage or
performance degradation.
Vibration Effect
Operating accuracy errors will increase by no more than 0.15
times their initial limits.
Response Time (63% step pressure change): 20 msec
Electrical
Input Power: ±15 VDC ±0.75VDC @0.055
amperes maximum (each)
Output Voltage
Gradient and Range: 75 mV/knots from 30 to 180 knots