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US 12,092,495 B2Granted
Variable inductive displacement sensor, associated device, system and aircraft
AssigneeSafran Electronics & Defense
InventorMathieu Conq
Life of this patent
Estimating the term…
Abstract
A variable inductive displacement sensor includes a primary excitation coil, a first secondary coil, and a second secondary coil. The primary excitation coil is configured to generate a variable magnetic field, and the first and second secondary coils are configured to each generate a signal induced by the variable magnetic field. The primary coil and the first and second secondary coils each have one end which is intended to be connected to a common ground.
Claims5
An aircraft, comprising:
- a first monitoring system integrated into a cockpit of the aircraft, the first monitoring system having an aircraft monitoring device that includes:
- a throttle connected to a first processing unit, the throttle including a rotor connected to a lever, and a stator housing the rotor such that a thrust provided by a jet engine is selectively controlled by pushing and pulling the lever;
- and
- a rotary variable inductive displacement sensor, comprising a primary excitation coil, a first secondary coil, and a second secondary coil, the primary excitation coil being configured to generate a variable magnetic field, and the first and second secondary coils being configured to each generate a signal induced by the variable magnetic field, wherein adjacent ends of the first and second secondary coils are connected to each other at a common point connected to a first connection terminal of the primary coil, the first connection terminal being configured to be connected to a common ground, wherein the common point and a connection between the common point and the first connection terminal are disposed within the sensor, wherein the primary excitation coil, the first secondary coil and the second secondary coil form a torus, each of the coils defining an angular sector of the torus relative to a central axis of the torus, a magnetic core being disposed at a center of the torus and rotating about the central axis of the torus, the induced signals generated by the first and second secondary coils being indicative of a position of the core in the torus, the magnetic core being configured to be connected to a rotor and the torus being configured to be disposed on a stator housing the rotor, the magnetic core being connected to the rotor and the first and second secondary coils being disposed on the stator;
- and
- a second monitoring system integrated into the jet engine of the aircraft, the second monitoring system having:
- a second processing unit connected to the first processing unit;
- a servo valve including a fixed portion and a movable portion;
- and
- a linear variable inductive displacement sensor, comprising a primary excitation coil, a first secondary coil, and a second secondary coil, the primary excitation coil being configured to generate a variable magnetic field, and the first and second secondary coils being configured to each generate a signal induced by the variable magnetic field, wherein adjacent ends of the first and second secondary coils are connected to each other at a common point connected to a first connection terminal of the primary coil, the first connection terminal being configured to be connected to a common ground, wherein the common point and a connection between the common point and the first connection terminal are disposed within the sensor, the sensor further comprising a magnetic core including a magnetic rod, the primary excitation coil, the first secondary coil and the second secondary coil surrounding the rod and extending along the rod, the rod translating in the coils, the induced signals generated by the first and second secondary coils being indicative of the position of the rod in the coils, the magnetic core being connected to the movable portion,
- the second monitoring system being configured to manage the jet engine of the aircraft from a position of the lever via the first processing unit, the servo valve being configured to control a fuel metering device of the jet engine in order to monitor the thrust delivered by the jet engine,
- the second processing unit being configured to drive the movable portion of the servo valve and to determine the position of the movable portion relative to the fixed portion from signals emitted by the linear variable inductive displacement sensor.
9 more elements
An aircraft, comprising:
- a first monitoring system integrated into a cockpit of the aircraft, the first monitoring system having an aircraft monitoring device that includes:
- a throttle connected to a first processing unit, the throttle including a rotor connected to a lever, and a stator housing the rotor such that a thrust provided by a jet engine is selectively controlled by pushing and pulling the lever;
- and
- a resolver-type variable inductive displacement sensor, comprising a primary excitation coil, a first secondary coil, and a second secondary coil, the primary excitation coil being configured to generate a variable magnetic field, and the first and second secondary coils being configured to each generate a signal induced by the variable magnetic field, wherein adjacent ends of the first and second secondary coils are connected to each other at a common point connected to a first connection terminal of the primary coil, the first connection terminal being configured to be connected to a common ground, wherein the common point and a connection between the common point and the first connection terminal are disposed within the sensor, wherein the primary coil is configured to be disposed on a rotor, and the first and second secondary coils are configured to be disposed in a stator housing the rotor, the first and second secondary coils being perpendicular to each other such that induced signals generated by the first and second secondary coils are indicative of a position of the rotor relative to the stator;
- and
- a second monitoring system integrated into the jet engine of the aircraft, the second monitoring system having:
- a second processing unit connected to the first processing unit;
- a servo valve including a fixed portion and a movable portion;
- and
- a linear variable inductive displacement sensor, comprising a primary excitation coil, a first secondary coil, and a second secondary coil, the primary excitation coil being configured to generate a variable magnetic field, and the first and second secondary coils being configured to each generate a signal induced by the variable magnetic field, wherein adjacent ends of the first and second secondary coils are connected to each other at a common point connected to a first connection terminal of the primary coil, the first connection terminal being configured to be connected to a common ground, wherein the common point and a connection between the common point and the first connection terminal are disposed within the sensor, the sensor further comprising a magnetic core including a magnetic rod, the primary excitation coil, the first secondary coil and the second secondary coil surrounding the rod and extending along the rod, the rod translating in the coils, the induced signals generated by the first and second secondary coils being indicative of the position of the rod in the coils, the magnetic core being connected to the movable portion,
- the second monitoring system being configured to manage the jet engine of the aircraft from a position of the lever via the first processing unit, the servo valve being configured to control a fuel metering device of the jet engine in order to monitor the thrust delivered by the jet engine,
- the second processing unit being configured to drive the movable portion of the servo valve and to determine the position of the movable portion relative to the fixed portion from signals emitted by the linear variable inductive displacement sensor.
9 more elements
Dependencies are inferred from the claim text.