Electromagnetic coil open circuit and short circuit detection circuit

Abstract

The invention discloses an electromagnetic coil open circuit and short circuit detection circuit which comprises a first dual operational amplifier U3A, a second dual operational amplifier U3B, first to thirteenth resistors R1-R13, first to fourth diodes D1-D4, a first triode U1, a second triode U2, a second capacitor C2 and a third capacitor C3. The circuit is divided into an open-circuit fault detection circuit, a short-circuit fault detection circuit and a fault indication circuit. The problem of high false alarm rate of output of the open and short circuit fault detection circuit caused by external signal interference or unreliable contact of the connector is thoroughly solved. The failure rate of the brake system is reduced by 90%, the qualified period of the brake system used in an external field is prolonged, the economic benefit is improved, and the public praise of the product in the external field is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft brakes, and in particular relates to an open-short circuit detection circuit. Background technique [0002] The aircraft digital fly-by-wire anti-skid brake system in the prior art is composed of a brake command sensor, an anti-skid brake control box, a wheel speed sensor, an electro-hydraulic pressure servo valve and an electromagnetic hydraulic lock, and undertakes the necessary anti-skid brake function during take-off and landing of the aircraft. [0003] According to the requirements of 3.11 Ergonomics in GJB2879A General Specification for Aircraft Wheel Anti-skid Brake Control System, the internal inspection device should not affect the normal function of the system, and the internal detection should be able to provide light or sound fault indication information. The self-testing function of the aircraft anti-skid brake system is a must. At present, the open-short circuit fault detection cir...

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Problems solved by technology

[0004] The invention with the notification number CN110562223A uses short RC charging time, which does not affect the rapid response capability of the system; at the same time, the RC discharge circuit has a long discharge time, which can shield the reference speed caused by vibration, electromagnetic interference, noise and temperature changes. Jumping leads to static braking protection; when the aircraft is in the static braking state, it can resist the interference of vibration, electromagnetic interference, noise and temperature changes and other interference signals, which improves the stability of static braking and the safety of the aircraft; however, This circuit is only used for aircraft static brake protection function, and cannot be used for fault detection of aircraft electro-hydraulic pressure servo valve and wheel speed sensor

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