Opening device common to two adjacent aircraft engine nacelle covers

• US 6,227,485 B1
• Filed: 06/21/1999
• Issued: 05/08/2001
• Est. Priority Date: 12/03/1997
• Status: Expired due to Term

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Porte, Alain
• Primary Examiner(s): Eldred, J. Woodrow
• Application Number:
  US09/297,887
• Time in Patent Office: 687 Days
• Field of Search: 244/54, 244/53 B, 244/55, 244/62, 60/39.31
• US Class Current: 244/54
• CPC Class Codes: B64D 29/08 Inspection panels for power plants

Abstract

A single actuator (35) is controlled so as to successively open two covers (4 and 5) on an aircraft engine nacelle which are adjacent, successively forming two hinges (40 and 47).

Claims

1. An aircraft engine nacelle comprising:

two adjacent covers, which are special in that a first one of the covers partially overlaps a second cover, imposing an order of opening and closing; and

an opening actuator connected to the first cover in a position where the first cover is closed by a first hinge and articulated by a second hinge on the engine, wherein by rotation about the second hinge, the actuator can be successively connected to the first cover or to the second cover without being disconnected from the second hinge and without disconnecting a control system of the actuator, and wherein the actuator is controlled by a control element concealed by the first cover, when the first cover is in the locked position.

2. An aircraft engine nacelle according to claim 1, wherein the control element is made accessible to an operator by flexing the first cover.

3. An aircraft engine nacelle according to claim 1, wherein the actuator comprises a stem provided with two stepped hinge elements respectively forming the first hinge and a removable hinge.

4. An aircraft engine nacelle according to claim 1, further comprising a system of controlling the actuator including a pump, a liquid reservoir and a valve allowing passage of liquid from the reservoir to the actuator through the pump and a direct passage of liquid from the actuator to the reservoir.

5. An aircraft engine nacelle according to claim 4, wherein the system controlling the actuator also comprises an auxiliary pressurised liquid reservoir.

6. An aircraft engine nacelle according to claim 1, wherein the actuator is an electrical actuator controlled by a switch constituting the control element.

7. An aircraft engine nacelle according to claim 1, wherein the actuator can rotate in a plane about the second hinge.

8. An aircraft engine nacelle according to claim 1, wherein the actuator can rotate in several planes, the second hinge being produced as a swivel.

9. An aircraft engine nacelle according to claim 1, wherein the hinges for connecting the actuator to the covers comprise fork elements fixed to the covers.

10. An aircraft engine nacelle according to claim 1, wherein the hinges for connecting the actuator to the covers comprise simple pivots, establishing cantilever connections, fixed to the covers.

11. An aircraft engine nacelle according to claim 1, wherein the covers each have an edge articulated on a suspension mast on the nacelle.

12. An aircraft engine nacelle according to claim 1, wherein the covers each have an edge articulated on a fixed element secured to the mast and engine.

13. An aircraft engine nacelle according to claim 1, wherein the covers are positioned adjacent to one another along the axial axis of the engine.

14. An aircraft engine nacelle according to claim 1, wherein the control element is made accessible to an operator by means of free travel obtained by the fact that the actuator comprises a stem formed in two segments.

15. An aircraft engine nacelle according to claim 1, wherein the first of the two segments is engaged in a cylinder of the actuator and the second of the two segments carries the first hinge and the first and second segments which enables the segments to move in an axial direction with respect to each other.