DUSU-1-45AS

DUSU-1-45AS angular rate sensor

DUSU-1-45AS is an aviation angular rate sensor intended to convert rotation about its sensitive axis into an electrical signal for a compatible flight-control, stabilization or recording circuit. The exact designation is essential because related sensors can use a similar housing while having a different measuring range, zero-signal tolerance, electrical interface or calibration. The confirmed measuring range for this execution is ±45°/s. Published family data gives a sensitivity threshold not over 0.75% of range and a normal-temperature zero signal not over ±0.15 V. Selection must therefore be based on the full marking and approved installation documentation rather than on appearance alone.

Measurement function and output

The sensor detects angular motion and supplies a proportional signal to connected avionics. In a control loop, that signal can help the receiving equipment determine the direction and rate of rotation and form the required correction. It is a measuring element, not a complete autopilot or stabilization system. Supply voltage, phase sequence, connector pinout, polarity and permissible output error must match the passport for the exact suffix. A general explanation of this class of instrument is available in the rate gyro reference. Values published for another suffix must not be transferred automatically.

Designation and aircraft application

The original Cyrillic suffix “С”, represented as S in the Latin title, identifies use on manned aircraft; the exact platform still requires installation documentation. Commercial records may omit hyphens or transliterate the original Cyrillic letters, so Technical Details lists common search forms while preserving the original designation. A confirmed family relationship does not establish interchangeability. The mounting orientation, mating connector and receiving equipment must be checked in the aircraft illustrated parts catalogue, wiring diagram, maintenance manual or product passport. Other verified measuring units can be reviewed in the Sensors category.

Inspection and installation control

Before installation, inspect the body, mounting faces, connector, locking devices and legibility of the marking. Confirm that the sensor has been transported and stored within the limits stated by the manufacturer and that the aircraft circuit is isolated before connection. Bench testing should use the prescribed supply and approved harness. The test should verify zero output, response direction, scale factor and stability only against the acceptance values for this execution. Do not compensate for an unexplained deviation by adjusting another unit or by applying data from a visually similar sensor.

Ordering DUSU-1-45AS

An enquiry should state DUSU-1-45AS, quantity, required condition, documentation requirement and the equipment or aircraft reference in which the sensor will be installed. If available, include a clear photograph of the original marking and connector. Aviamisto can use that information to check the suffix and proposed delivery configuration. The DChV-2500 speed sensor is linked only for navigation within the same category and is not presented as a substitute.

For incoming inspection, compare the delivered marking, connector layout, mounting features and preservation status with the approved order. Confirm the availability of a passport or inspection record before shipment when those documents are mandatory. Any difference in suffix, electrical execution or installation interface should be resolved before the unit is connected to a test bench. Legacy aviation sensors often appear in commercial lists with shortened designations, so a procurement record should preserve both the exact marking and the verified alternative spellings. The final decision on installation remains with the responsible aviation maintenance organization using the documentation for the particular aircraft and system.

Product Type: Gyroscopic angular rate sensor

Function: Conversion of angular velocity into an electrical signal

Measuring Range: ±45°/s

Manufacturer / Developer: Arzamas Instrument-Making Plant (APZ), published family data

Potentiometer Supply: 5–30 V DC

Gyromotor Supply: 36 ±3.6 V three-phase AC, 400 ±8 Hz

Steady-State AC Consumption: Not more than 0.25 A per phase

Ready Time: Not more than 60 seconds

Full-Range Output: 13.5 V at nominal supply conditions

Sensitivity Threshold: Not more than 0.75% of range

Zero Signal: ≤ ±0.15 V normal; ≤ ±0.3 V over temperature

Operating Temperature: −60 to +60 °C

Atmospheric Pressure Range: (100 ±4) to 0.67 kPa

Primary Designation: DUSU-1-45AS

Original Cyrillic Designation: ДУСУ1-45АС

Alternative Designations: DUSU145AS; DUSU 1 45AS; ДУСУ1-45АС; ДУСУ-1-45АС

Aircraft / Equipment Application: Manned aircraft; exact platform by installation documentation

Installation Position: According to the approved equipment or aircraft manual

Connector / Pinout: According to the passport for the exact execution

Interchangeability: Not established by family name or external appearance

Documentation: Product passport and approved installation / maintenance documentation

Ordering Check: Full marking, range suffix, connector, condition and required documents

Acceptance Control: Compare designation, connector, mounting features and available test record with the approved requirement before installation

Data Verification: Values not listed for the exact suffix must be confirmed from its passport and must not be copied from an adjacent family execution

Related Products: Same-category links support catalogue navigation only and do not state interchangeability

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Warranty
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Extended warranty is available upon request and is agreed individually; it may affect the final product price.