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BR-102024018324-A2 - DEVICE AND METHOD FOR QUICK DISCONNECTION OF AN AIRCRAFT DOOR ACTUATING SYSTEM

BR102024018324A2BR 102024018324 A2BR102024018324 A2BR 102024018324A2BR-102024018324-A2

Abstract

The present invention discloses a device and method for the rapid disconnection of an aircraft door actuation system. The device comprises: a coupling element, with open ends, for coupling between a first shaft and a second shaft of the actuation system; and a locking element, engaged within at least one hole of the coupling element and disposed between the first shaft and the second shaft. The method comprises at least the steps of: accessing a device of the aircraft door actuation system, disengaging the locking element from within at least one hole of the device's coupling element, and performing an axial displacement of the coupling element until a disconnection configuration is achieved between a first shaft and a second shaft of the actuation system.

Inventors

  • DAVID MACHADO LOUREIRO
  • FABRÍCIO JOSÉ RODRIGUES FLORES
  • ROGÉRIO FIGUEREDO LACERDA
  • TAKAO NEWTON HATAKEYAMA
  • AZÉLIO PASQUINI
  • CAIO BROMONSCHENKEL PAES

Assignees

  • Embraer S.A.

Dates

Publication Date
20260317
Application Date
20240905

Claims (16)

  1. 1. Device (100) for quick disconnection of an aircraft door actuation system, characterized in that the quick disconnection device (100) comprises: a coupling element (110), with open ends, for coupling between a first shaft (130) and a second shaft (140) of the actuation system; and a locking element (120), engaged within at least one hole (111) of the coupling element (110) and disposed between the first shaft (130) and the second shaft (140).
  2. 2. Device (100), according to claim 1, characterized in that the locking element (120) restricts an axial displacement of the coupling element (110) while engaged.
  3. 3. Device (100), according to claim 1, characterized in that at least one orifice (111) of the coupling element (110) is designed so that the locking element (120) is adjacent to the second shaft (140).
  4. 4. Device (100), according to claim 1, characterized in that the first shaft (130) and the second shaft (140) are respectively retained, at least partially, within the coupling element (110) while the locking element (120) is engaged within at least one hole (111) of the coupling element (110).
  5. 5. Device (100), according to claim 1, characterized in that the coupling element (110) is capable of being displaced axially when the locking element (120) is disengaged from within at least one orifice (111) of the coupling element (110).
  6. 6. Device (100), according to claim 1, characterized in that the coupling element (110) is a mechanical sleeve, in the form of a hollow cylinder, with a grooved inner surface, and in which the first shaft (130) and the second shaft (140) comprise, respectively, at least one toothed interface for meshing with the respective grooved inner surface of the coupling element (110).
  7. 7. Device (100), according to claim 1, characterized in that the first shaft (130) is a driving shaft and the second shaft (140) is a driven shaft.
  8. 8. Device (100), according to claim 1, characterized in that the first axis (130) comprises a stop (131) configured to limit the axial displacement of the coupling element (110) in its direction.
  9. 9. Device (100), according to claim 1, characterized in that at least one orifice (111) of the coupling element (110) is composed of two holes, each of the holes being arranged diametrically opposite to each other, wherein the locking element (120) passes through both holes of the coupling element (110).
  10. 10. Device (100), according to claim 1, characterized in that the locking element (120) is any one of: a quick-disconnect pin, metal pin, shackle pin with locking ball, cotter pin or spring-loaded lever, indexing pin, engagement pin or quick-release magnetic pin.
  11. 11. Device (100), according to claim 1, characterized in that the coupling element (110) comprises another orifice (112).
  12. 12. Device (100), according to claim 1, characterized in that the aircraft door is an aircraft cargo door.
  13. 13. Device (100), according to claim 1, characterized in that access to the device (100) for a user is provided through a removable panel (200) of the aircraft; wherein, in operation, the locking element (120) is facing the removable panel (200).
  14. 14. Method for quick disconnection of an aircraft door actuation system, characterized in that it comprises at least the steps of: accessing a device (100) of the aircraft door actuation system, wherein the device comprises: a coupling element (110), with open ends, for coupling between a first shaft (130) and a second shaft (140) of the actuation system; and a locking element (120), engaged within at least one hole (111) of the coupling element (110) and disposed between the first shaft (130) and the second shaft (140); disengaging the locking element (120) from within at least one hole (111) of the coupling element (110); and performing an axial displacement of the coupling element (110) until a disengagement configuration is achieved between the first shaft (130) and the second shaft (140) of the actuation system.
  15. 15. Method according to claim 14, characterized in that it comprises accessing the device (100) through a removable panel (200) of the aircraft.
  16. 16. Method according to claim 14, characterized in that it further comprises the step of introducing a compatible standard tool or locking element into the other hole (112) of the coupling element (110) to facilitate axial displacement of the coupling element (110).

Description

Field of invention: [001] The present invention is situated in the field of electromechanical systems that are subject to the mechanical locking failure mode. More particularly, the present invention relates to a device and method for the rapid disconnection of an aircraft door actuation system. Fundamentals of the invention: [002] The application of electromechanical solutions introduces a mechanical locking failure mode into the system. In the context of an aircraft cargo door actuation system, a locking event prevents the door from being moved. Therefore, the door's operation becomes impossible. [003] Considering a cargo aircraft operation, there is the aggravating factor that the interior of the aircraft is normally occupied with cargo, making access to the components of the cargo door actuation system from the inside impossible. Therefore, a situation arises where the door is closed, unable to be opened due to the locking mechanism, and it is not possible to access the system components to perform a maintenance task. [004] Normally, this situation is circumvented by providing a way to access the cargo door actuation system components from outside the aircraft. Such access may be a design feature, such as a panel that must be removed, or a tear in the structure that requires subsequent repair. [005] Once access to the system components has been granted, to resolve the jamming, it is still necessary to have a means to uncouple the locked system's loading door. Uncoupling is commonly done by removing fastening components such as screws, therefore access to the components must provide sufficient space to allow the mechanic to use the necessary tools. [006] Alternatively, this situation can be circumvented by introducing jam-tolerant actuators into the system. These actuators incorporate devices that considerably reduce the probability of a jam occurring, although they do not eliminate it completely. [007] A jam-tolerant actuator is a more expensive solution and may require a larger dimensional envelope to enable its installation compared to a conventional actuator. Its application is advantageous when inserted in the context of systems in which jamming can have severe safety implications. However, when dealing with a load door actuation system, the impact is merely operational. [008] Additionally, it is necessary to take into consideration that jamming is already a low-frequency event. Therefore, the use of jamming-tolerant actuators in load door actuation systems may end up increasing the project cost without providing an equivalent advantageous return in terms of operation. [009] Furthermore, the state of the art introduces the concept of a sliding sleeve for uncoupling door mechanisms. However, known solutions use complex manual actuation mechanisms that require a larger dimensional envelope. Moreover, they are geared towards other applications, such as cockpit doors and aircraft interiors. [0010] Therefore, there is a need for advances in solutions for decoupling actuation systems and aircraft doors in order to achieve a low-cost, reduced-complexity, easy-to-handle solution that speeds up the resolution of a mechanical jamming case. [0011] Thus, the features and advantages of the present invention will become clear from the detailed description below and with reference to the accompanying drawings. Brief description of the invention: [0012] The present invention discloses a device and method for quickly disconnecting an aircraft door actuation system. The device comprises: a coupling element, with open ends, for coupling between a first shaft and a second shaft of the actuation system; and a locking element, engaged within at least one hole of the coupling element and disposed between the first shaft and the second shaft. The method comprises at least the steps of: accessing a device of the aircraft door actuation system, disengaging the locking element from within at least one hole of the device's coupling element, and performing an axial displacement of the coupling element until a disconnection configuration is achieved between a first shaft and a second shaft of the actuation system. Brief description of the figures: [0013] In order to complement the present description and obtain a better understanding of the characteristics of the present invention, the following figures are presented, these being provided as preferred and not limiting embodiments. [0014] Figure 1 illustrates a front perspective view of an aircraft cargo door. [0015] Figure 2 illustrates a rear perspective view of an aircraft cargo door revealing a cargo door actuation system. [0016] Figure 3 illustrates an enlarged view of the load door actuation system with the device of the present invention. [0017] Figure 4 illustrates an enlarged view of the device of the present invention. [0018] Figure 5 illustrates an exploded view of the device of the present invention. [0019] Figure 6 illustrates a cross-sectional view of the device of