Wing fold controller

Patent metadata

Field	Value
Publication number	US-9499252-B2
Application number	US-201414335625-A
Country	US
Kind code	B2
Filing date	Jul 18, 2014
Priority date	Oct 1, 2011
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and an on-ground position by an actuator of the wing fold system in response to commands from the wing fold controller.

First claim

What is claimed is:

1. A system configured to limit a force at a wing fold actuator output, the system comprising:
a power drive unit connected to the wing fold actuator;
a control module connected to and configured to control power to: the power drive unit, and a lock actuator configured to lock a latch configured to secure an unfixed portion of a wing to a fixed portion of the wing;
an aircraft system sensor;
an environment sensor; and
a flight controls computer configured to, based upon information from the sensors and a determination in real time of an actual moment, caused by actual loads on the unfixed portion, about a centerline axis of the wing fold actuator, limit power to the wing fold actuator.

2. The system of claim 1 , further comprising the flight control computer comprising a processor comprising an algorithm configured to vary an output of the power drive unit across a range based upon the actual loads on the unfixed portion.

3. The system of claim 2 , further comprising the algorithm configured to determine actual loads on the unfixed portion and the output for the power drive unit based upon inputs from aircraft sensors.

4. The system of claim 3 , further comprising the algorithm configured to limit, to approximately one-seventh of a maximum force available from the wing fold actuator to move the unfixed portion toward an on-ground position, a force from the power drive unit, based upon the output determined, that moves the wing fold actuator in a direction that moves the unfixed portion toward a flight position.

5. The system of claim 1 , further comprising the latch comprising a fixed lug and an unfixed lug, each lug configured such that a centerline axis of the fixed lug substantially aligns with a centerline axis of the unfixed lug and a centerline axis of the lock such that the lock may transition between an engaged position and a disengaged position such that no more than 6,000 pounds force is needed to insert the lock through the fixed lug and the unfixed lug and into the engaged position.

6. The system of claim 5 , further comprising the unfixed lug configured to contact a stop device located on the fixed portion via a force from the wing fold actuator moving the unfixed portion toward a flight position.

7. The system of claim 5 , further comprising the unfixed lug comprising a beveled corner on an opening through the lug such that the force from the wing fold actuator moving the unfixed portion toward a flight position may be overcome, by a force that acts in an opposite direction of the force from the wing fold actuator, applied against the unfixed portion by a corner of the lock as the lock actuator moves the lock, such that the lock moves through the latch and into the engaged position, the corner of the lock being beveled.

8. A system configured to regulate a power supplied to a wing fold actuator, the system comprising:
a control module in communication with a flight control computer in communication with sensors on an aircraft, the flight control computer configured such that based upon a real time determination of an actual moment about a central axis of the wing fold actuator, the flight control computer commands the control module to reduce, from a maximum power available from a power system, the power supplied to the wing fold actuator to a level required to move, at a specified rate, an unfixed portion of a wing of the aircraft.

9. A system configured to regulate a power supplied to a wing fold actuator, the system comprising:
a control module in communication with a flight control computer in communication with sensors on an aircraft, the flight control computer configured such that based upon a real time determination of an actual alignment of a centerline of an unfixed lug in a latch, a centerline of a fixed lug in the latch, and a centerline of a lock for the latch, the flight control computer commands the control module to vary the power supplied to the wing fold actuator to a level and a direction required to maintain the alignment of the fixed lug, the unfixed lug, and the lock, such that during insertion and retraction of the lock, with the latch, that forces upon the lock from the fixed lug and the unfixed lug are at a minimum level.

Assignees

• Boeing Co

Inventors

• Lassen Matthew August
• Good Mark Steven

Classifications

• Y02T50/145

  Cross-Sectional Technologies · mapped topic

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title

• Y02T50/54

  Cross-Sectional Technologies · mapped topic

• Y02T50/10

  Drag reduction · CPC title

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title