Patent Application
20180178924
This application claims the benefit of the European patent application No. 16382666.2 filed on Dec. 28, 2016, the entire disclosures of which are incorporated herein by way of reference.
The present invention relates generally to Aircraft Refueling Boom Systems and, more specifically, to Aircraft Refueling Boom Systems with security means for avoiding damages to the receiver aircraft.
An aircraft refueling boom is a beam fuel-tight unit attached by its forward end to a tanker aircraft having aerodynamic lift surfaces called ruddevators used to aerodynamically control the position of the boom in elevation and azimuth that provides a fuel passage from the tanker to the boom nozzle.
The outer end portion of the boom is a telescoping section for inward and outward movement.
The receiver aircraft is equipped with a refueling receptacle which engages with the boom nozzle in an in-flight refueling operation.
The boom is guided by an operator or a system located in the tanker aircraft so as to line the boom nozzle with the receiver aircraft receptacle. When the boom nozzle is aligned with the receiver receptacle, the telescoping portion is extended so that the nozzle engages the receptacle to complete the coupling which must be accomplished and maintained within a predetermined refueling envelope to avoid a disconnection.
During tanker to receiver contacts, mechanical contact loads are built up and stresses are placed on the boom as well as on the receiver. These stresses can result in boom or receptacle failure.
EP 1 894 840 A1 describes a refueling apparatus for interconnecting a tanker aircraft with 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 refueling nozzle at its distal end, having control means including a central computer station, being its tip region arranged by the assembly of a first module having load sensing means, a second module having load alleviation means and a third module, joined to the nozzle, having a mechanical fuse for allowing the safe separation of tanker and receiver aircraft in the event of overloads.
EP 2 343 240 A2 describes a system for disconnecting the nozzle of a boom from a receptacle to which the nozzle is connected for fuel transfer, comprising latches which are situated in the nozzle and engage with latch-pins arranged in the receptacle. The system comprises a receptacle disconnection sub-system which operates the latch-pins of the receptacle and a nozzle disconnection sub-system which operates the latches of the nozzle such that, when an operator performs a normal disconnection of the nozzle, the system sends a first signal to the receptacle so that its latch-pins are retracted in order to release the latches of the nozzle and, in parallel, sends a second signal to the nozzle so that the latches of the nozzle are retracted and release the nozzle.
After a refueling operation, during the disconnection phase, it may happen that the end of the boom is not connected to the receiver aircraft but is still very close to the receiver aircraft receptacle or even still inside the receptacle. In that situation, there is a big risk of contact between boom end and receptacle or of jamming of the nozzle inside the receptacle. In some cases, these events may lead to a separation of the nozzle from the boom.
A free nozzle flying freely towards the receiver aircraft can damage it causing a catastrophic event.
A free nozzle descending from a very high altitude can also cause significant damage when it hits the ground.
The present invention is intended to solve these problems.
The invention refers to 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 has a receptacle to cooperate with the nozzle in a refueling operation that takes place when the nozzle is latched to the receptacle. The boom comprises a tip module that includes a breakable section (such as a mechanical fuse) for separating it in a first portion and a second portion for allowing a safe separation of tanker and receiver aircraft in a failure event of a refueling operation, being the nozzle latched to the receptacle.
The invention provides an Air Refueling Boom System that additionally comprises linking means of the first and second portions of the tip module with a double functionality:
Breaking at the same time as the breakable section in an overload event when the nozzle is latched to the receptacle.
Keeping linked the first and second portions of the tip module when the nozzle is not latched to the receptacle and an overload occurs.
Moreover, the linking means of the Air Refueling Boom System are adapted to allow relative movements between the first and second portions of the tip module when the nozzle is not latched to the receptacle.
Moreover, the linking means of the Air Refueling Boom System are attached to at least one elastic element of the second portion of the tip module so that both portions may be held together. The elastic element or elements can be located inside or outside the fuel conduit.
Moreover, the Air Refueling Boom System comprises either a wire rope or an ensemble of wire ropes attached to the first and second portions of the tip module as linking means.
In another aspect, the invention provides a tanker aircraft comprising the Air Refueling Boom System.
Other desirable features and advantages of the invention will become apparent from the subsequent detailed description of the invention and the appended claims, in relation with the enclosed drawings.
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.
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.
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.
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.
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.
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.
In the embodiment illustrated in
In the embodiment illustrated in
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.
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.
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.
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.
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.
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.
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.
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.
| Number | Date | Country | Kind |
|---|---|---|---|
| 16382666.2 | Dec 2016 | EP | regional |
