MONITORING SYSTEM FOR AIRCRAFT LANDING SYSTEM

• US 20080033607A1
• Filed: 06/01/2007
• Published: 02/07/2008
• Est. Priority Date: 06/01/2006
• Status: Abandoned Application

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Lin, Chuang-Chia, Harris, Neil, Walsh, Andy, Cepic, Adnan, Zeliff, Bob
• Application Number:
  US11/756,891
• Publication Number:
  US 20080033607A1
• Time in Patent Office: Days
• US Class Current: 701/29
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear

Abstract

A monitoring system for a landing gear system comprising a plurality of sensors for monitoring respective parameters of the aircraft landing system, and a monitor which receives the outputs of the sensors.

Claims

1. A monitoring system for a landing gear system comprising a plurality of sensors for monitoring respective parameters of the aircraft landing system, and a monitor which receives the outputs of the sensors.

2. A system as set forth in claim 1, wherein at least one of the sensors communicates wirelessly with the monitor.

3. A system as set forth in claim 1, wherein the monitor includes a processor for processing the outputs of the sensors to provide diagnostic information that can displayed, stored and/or further processed to provide operational information regarding the aircraft landing system.

4. A system as set forth in claim 3, wherein the operational information includes one or more of a hard landing indication, high ground load indication, brake usage, landing cycle counting, and fatigue.

5. A system as set forth in claim 1, wherein the sensed parameter include one or more of the following:

tire pressure;

strut oil level;

strut pressure;

strut position;

strut temperature;

brake wear measurement;

wheel temperature;

brake temperature;

wheel bearing temperature;

actuator temperature;

brake vibration, wheel shimmy and other vibrations;

component strain and/or stress;

brake torque;

corrosion;

weight on wheels;

landing gear states;

component temperature and/or loading in general;

ambient conditions such as temperature and humidity.

6. A monitoring method for a landing gear system comprising monitoring a plurality of sensors to sense respective parameters of the aircraft landing system.