Systems and methods for landing identification

• US 9,688,389 B2
• Filed: 12/06/2011
• Issued: 06/27/2017
• Est. Priority Date: 12/06/2011
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cahill, Eric D., Shaw, Michael
• Primary Examiner(s): Vargas, Manuel Rivera
• Application Number:
  US13/312,495
• Publication Number:
  US 20130139590A1
• Time in Patent Office: 2,030 Days
• CPC Class Codes: B64C 25/00 Alighting gear air-cushion alighting gear B60V3/08
• CPC Class Codes: B64C 25/46 Brake regulators for preventing skidding or aircraft somersaulting
• CPC Class Codes: G01D 5/14 influencing the magnitude of a current or voltage
• CPC Class Codes: G01P 3/44 for measuring angular speed G01P3/56 takes precedence
• CPC Class Codes: H03K 3/0232 Monostable circuits

Abstract

Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.

Claims

1. A landing identification system comprising:

a wheel speed sensor that outputs a signal indicative of angular displacement;

a signal conditioner that receives the signal indicative of angular displacement and outputs a conditioned angular displacement signal;

a monostable multivibrator that receives the conditioned angular displacement signal,

wherein the monostable multivibrator is in electrical communication with a wheel angular displacement circuit,

a comparator in electrical communication with the wheel angular displacement circuit and configured to receive a reference voltage,

wherein the monostable multivibrator is configured to set a time period in response to receiving the conditioned angular displacement signal,

wherein the wheel angular displacement circuit changes state in response to angular displacement above a displacement threshold over a first time period,

wherein the comparator compares the reference voltage to a voltage output of the wheel angular displacement circuit, and

wherein a voting scheme determines a likelihood of a landing event based upon the comparison.

2. The landing identification system of claim 1, wherein the displacement threshold is indicative of a speed over 20 knots.

3. The landing identification system of claim 1, wherein the change of state of the wheel angular displacement circuit is provided to another aircraft component.

4. The landing identification system of claim 1, wherein the period is between 50 ms and 500 ms.

5. The landing identification system of claim 1, wherein the wheel speed sensor is a variable reluctance wheel speed sensor.

6. The landing identification system of claim 1, wherein the signal indicative of angular displacement is in AC form.