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A verification system of a small magnetoelectric speed sensor for aero-engine

A technology of aero-engine and speed sensor, which is applied in the testing/calibration of speed/acceleration/shock measuring equipment, instruments, speed/acceleration/shock measurement, etc., to achieve high output speed accuracy, improve accuracy, ensure accuracy and reliability Effect

Active Publication Date: 2016-11-30
CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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Problems solved by technology

[0003] The purpose of the present invention is to provide a verification system for small-sized magnetoelectric speed sensors used in aero-engines, to solve the problems of verification and calibration of small and medium-sized magneto-electric speed sensors in the prior art, and to ensure the accuracy and reliability of aero-engine speed measurement

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  • A verification system of a small magnetoelectric speed sensor for aero-engine
  • A verification system of a small magnetoelectric speed sensor for aero-engine
  • A verification system of a small magnetoelectric speed sensor for aero-engine

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Embodiment Construction

[0015] Below in conjunction with accompanying drawing and embodiment the specific embodiment of the present invention is further described, but the claimed scope is not limited to described:

[0016] Such as figure 1 , 2 As shown, the verification system of the small-sized magnetoelectric speed sensor for an aero-engine provided by the present invention includes a DC motor standard speed control output system and a verification fixture 9, wherein: the DC motor standard speed control output system includes a single-chip microcomputer 2, and Small keyboard 1 connected to single chip microcomputer 2, display output A3, display output B4, D / A output control 5, A / D feedback control 6, said D / A output control 5 and A / D feedback control 6 are all connected with DC motor 8 A measurement sensor 7 is also connected between the A / D feedback control 6 and the DC motor 8 , and the output shaft of the DC motor 8 is connected to the threaded connection seat 12 fixed on the verification fixt...

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Abstract

The invention discloses a verification system of a small magnetoelectric speed sensor for an aero-engine, which comprises a DC motor standard speed control output system and a verification fixture, wherein: the DC motor standard speed control output system includes a single-chip microcomputer and a small keyboard connected with the single-chip microcomputer , display output A, display output B, D / A output control, A / D feedback control, D / A output control and A / D feedback control are all connected to the DC motor, A / D feedback control and DC motor are also connected There is a measuring sensor, and the output shaft of the DC motor is connected with the fixed threaded connection seat on the verification fixture. The system utilizes mature single-chip computer control technology and adopts closed-loop control to realize the verification and calibration of small magnetoelectric speed sensors, ensuring the accuracy and reliability of aero-engine speed measurement.

Description

technical field [0001] The invention belongs to the technical field of aero-engine testing, and in particular relates to a verification system for a small-sized magnetoelectric rotational speed sensor for an aero-engine. Background technique [0002] Due to the advantages of small size, high sensitivity, strong anti-interference ability, stability and reliability, and not easy to damage, magnetoelectric speed sensors have been widely used in domestic and foreign aero-engine industries. Special verification standard equipment and methods cannot verify this kind of small magnetoelectric speed sensor, but simply check the appearance, insulation performance and coil resistance of the small magnetoelectric speed sensor, but the real output signal of the sensor cannot be verified The corresponding relationship between frequency and speed, output voltage amplitude and other key parameters, so it is very necessary to develop a set of verification system equipment for this small magn...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01P21/02
Inventor 张华滕李虎任伟
Owner CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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