AIRCRAFT REFUELING BOOM SYSTEM WITH NOZZLE SECURITY MEANS

Abstract

An Air Refueling Boom System comprising a boom joined to the tanker aircraft by means of a mechanical articulation with an inner fuel conduit and a nozzle at its distal end. The tip module of the boom includes a breakable section for separating the tip module in a first and a second portion for allowing a safe separation of tanker and receiver aircraft in a failure event of a refueling operation and linking means of its first and second portions to allow their separation in case of an overload on the nozzle when it is latched to the receptacle and to allow their separation in case of an overload on the nozzle when it is latched to the receptacle.

Claims

1. An Air Refueling Boom System for supplying fuel from a tanker aircraft to a receiver aircraft in flight comprising a boom joined to the tanker aircraft by means of a mechanical articulation with an inner fuel conduit and a nozzle at its distal end; the receiver aircraft having a receptacle to cooperate with the nozzle in a refueling operation; the nozzle and the receptacle of the receiver aircraft having cooperating latching means; the boom having a tip module joined to the nozzle that includes a breakable section for separating the nozzle in a first portion and a second portion to allow a safe separation of tanker and receiver aircraft in a failure event of a refueling operation, the nozzle being latched to the receptacle; the tip module further comprises linking means of its first and second portions configured for maintaining both portions mechanically linked in case of an overload on the nozzle when the nozzle is not latched to the receptacle and to allow the separation of both portions in case of overload on the nozzle when the nozzle is latched to the receptacle.

2. The Air Refueling Boom System according to claim 1, wherein the breakable section is a mechanical fuse.

3. The Air Refueling Boom System according to claim 1, wherein the linking means are configured to allow relative movement between the first and second portions of the tip module when the nozzle is not latched to the receptacle.

4. An Air Refueling Boom System according to claim 1, wherein the linking means are attached to at least an elastic element located on the second portion of the tip module so that both portions may be held together.

5. The Air Refueling Boom System according to claim 4, wherein the linking means are attached to an elastic element located inside the fuel conduit of the second portion of the tip module.

6. The Air Refueling Boom System according to claim 4, wherein the linking means are attached to at least an elastic element located outside the fuel conduit of the second portion of the tip module.

7. The Air Refueling Boom System according to claim 6, wherein the linking means are attached to two elastic elements.

8. The Air Refueling Boom System according to claim 5, wherein the linking means comprise a wire rope.

9. The Air Refueling Boom System according to claim 5, wherein the linking means comprise an ensemble of wire ropes.

10. A tanker aircraft comprising an Air Refueling Boom System according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0023] FIG. 1 is a schematic a side view of a refueling operation between a tanker aircraft and a receiver aircraft using an Aircraft Refueling Boom System.

[0024] FIG. 2 is a schematic partial view of an Aircraft Refueling Boom System before engaging its nozzle in the receptacle of the receiver aircraft.

[0025] FIG. 3 is a schematic side view of the engagement of the nozzle in the receptacle of the receiver aircraft.

[0026] FIGS. 4a and 4b are schematic side views of the nozzle joined to a tip module of the boom in two possible states in an embodiment of the invention.

[0027] FIGS. 5a and 5b are schematic side views of the nozzle joined to a tip module of the boom in two possible states according to another embodiment of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0028] The Aircraft Refueling Boom System of the invention comprises a boom 21 which is a telescoping beam fuel-tight unit attached by its forward end to the underside fuselage of a tanker aircraft 11 by means of a mechanical articulation 23. Integrally attached to the boom 21 are aerodynamic lift surfaces 25 called ruddevators which are used to aerodynamically control the position of the boom 21 in elevation and azimuth.

[0029] The outer end portion of boom 21 is a telescoping section 27 for inward and outward movement. A boom tip assembly 29 and a nozzle 31 are located on the distal end of the telescoping section 27. The receiver aircraft 13 is equipped with an aerial refueling receptacle 19 which engages with the nozzle 31 for the refueling operation.

[0030] A boom operator or an automatic system, not shown, located in the tanker aircraft 11 guides the boom 21 so as to line the nozzle 31 with the receptacle 19 of the receiver aircraft 13. When the boom nozzle 31 is dynamically aligned with the receiver receptacle, the boom operator extends the telescoping section 27 so that the nozzle 31 engages the receptacle 19 to complete the coupling, which must be accomplished and maintained within a predetermined refueling envelope to avoid a disconnection.

[0031] The nozzle 31 and the receptacle 19 of the receiver aircraft 13 are equipped with, respectively, latching means 32, 20 to control their engagement and disengagement.

[0032] Loads during engagement and contact are transferred from the nozzle 31 to the boom 21 through the boom tip assembly 29 which attenuates, alleviates and limits such loads while maintaining a fuel tight passage through the boom 21 to the nozzle 31.

[0033] In the Aircraft Refueling Boom System of the invention, the tip module 41 of the boom tip assembly 29, which is joined to the nozzle 31, comprises a breakable section 43 for dividing the tip module 41 in a first portion 45 joined to the nozzle 31, a second portion 47 and also linking means between both portions 45, 47.

[0034] In the embodiment illustrated in FIGS. 4a, 4b the linking means 51 are attached to an elastic element 53, such as a spring, located inside the fuel conduit of the second portion 47.

[0035] In the embodiment illustrated in FIGS. 5a, 5b the linking means 61, 61 are attached to, respectively, two elastic elements 63, 63, such as springs, placed inside two cylinders located outside the fuel conduit of the second portion 47.

[0036] The elastic elements 53; 63, 63 provide to the linking means 51; 61, 61 with extension and retraction functionalities to keep the first and second portions 45, 47 in a separated or in a joined relative position depending on the circumstances of the disconnection procedure.

[0037] The breakable section 43 is intended for keeping attached the ensemble of the nozzle 31 and the first portion 45 of the tip module 41 to the receptacle 19 of the receiver aircraft 13 in overloads events during the disconnection phase of a refueling operation, being the nozzle 31 latched to the receptacle 19. The breakable section 43 may be configured as a mechanical fuse that breaks when the loads on it reach a determined value.

[0038] The linking means 51, 61, 61 are intended as means for keeping the nozzle 31 attached to the boom tip assembly 29 in overload events during the disconnection phase of a refueling operation when the nozzle 31 is not latched to the receptacle 19, thus preventing a separation of the end of the boom 21 from the rest of it, after the nozzle 31 is from the receptacle 19, due to, for example, a contact of the nozzle 31 with the receptacle 19 (they are very close during the disconnection phase) that activates a breakage of the tip module 41 leaving the ensemble of the nozzle 31, and leaving the first portion 45 of the tip module 41 of the boom tip assembly 29 as a free body that may impact the receiver aircraft or the ground, producing catastrophic damages.

[0039] The linking means 51, 61, 61 are also intended as complementary means for keeping the nozzle 31 attached to the receptacle 19 of the receiver aircraft 13 in overload events during the disconnection phase of a refueling operation, the nozzle 31 being latched to the receptacle 19. The linking means 51, 61, 61 is thus configured to break at the same load as the breakable section 43.

[0040] The linking means 51, 61, 61 therefore give the Aircraft Refueling Boom System an additional degree of freedom that allows a disconnection operation without the risk of losing the boom end.

[0041] In one embodiment, the linking means 51, 61, 61 are either a wire rope or an ensemble of wire ropes joining the first and second portions 45, 47 of the tip module 41 in a manner that allows relative movement between them.

[0042] Although the present invention has been described in connection with various embodiments, it will be appreciated from the specification that various combinations of elements, variations or improvements therein may be made, and are within the scope of the invention as defined by the appended claims.

[0043] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.