In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components
An in-flight refueling system and method are provided for facilitating the emergency separation of the components of a probe and drogue in-flight refueling. The in-flight refueling system and method provides a fuse device capable of being installed between, for instance, an elongate hose configured to trail from a tanker aircraft, and a drogue connected to, and in fluid communication with, the elongate hose. The fuse device may be configured to separate in response to a separating force such that the drogue may separate from the elongate hose prior to the exertion of a damaging force, a non-certified force, or an unknown aerodynamic force on the elongate hose, on a probe carried by a second receiver aircraft, or on the tanker aircraft.
1. An in-flight refueling system comprising:
a tanker aircraft;
an elongate hose having a first end carried by the tanker aircraft and a drogue operably engaged with and in fluid communication with an opposing second end thereof;
a fuse device operably engaged between the second end of the elongate hose and the drogue so as to allow fluid communication therebetween, the fuse device being configured to disengage the drogue from the elongate hose in response to a separating force experienced thereby, such that the elongate hose is separable from the drogue in response to the separating force; and
a valve device disposed between the tanker aircraft and the first end of the elongate hose, the valve device prevents a fluid flow though the elongate hose when the drogue is disengaged from the elongate hose.
2. An in-flight refueling system according to claim 1 , wherein the fuse device is further configured to be separable into a first segment operably engaged with a first portion of the elongate hose and a second segment operably engaged with the drogue in response to a separating force experienced thereby, such that the first portion of the elongate hose is separable from the drogue in response to the separating force.
3. An in-flight refueling system according to claim 1 , wherein the fuse device is operably engaged between the second end of the elongate hose and the drogue such that the fuse device is further configured to be separable into a first segment operably engaged with the second end of the elongate hose and a second segment operably engaged with the drogue in response to a separating force experienced thereby, such that the drogue is separable from the second end of the elongate hose in response to the separating force.
4. An in-flight refueling system according to claim 1 , wherein the fuse device is further configured such that the separating force is less than a breakage force required to damage the elongate hose.
5. An in-flight refueling system according to claim 1 , wherein the fuse device is selected from the group consisting of:
at least one shear bolt;
a cylindrical conduit; and
combinations thereof.
6. An in-flight refueling system according to claim 1 , wherein the fuse device further comprises:
a first threaded portion configured to be capable of operably engaging a first threaded surface disposed on the second end of the elongate hose; and
a second threaded portion configured to be capable of operably engaging a second threaded surface disposed on the drogue.
7. An in-flight refueling system adapted to be carried by a tanker aircraft, comprising:
an elongate hose having a first end carried by the tanker aircraft and a drogue operably engaged with and in fluid communication with an opposing second end thereof;
a fuse device operably engaged between the second end of the elongate hose and the drogue so as to allow fluid communication therebetween, the fuse device being configured to disengage the drogue from the elongate hose in response to a separating force experienced thereby, such that the elongate hose is separable from the drogue in response to the separating force; and
a valve device disposed between the tanker aircraft and the first end of the elongate hose, the valve device prevents a fluid flow though the elongate hose when the drogue is disengaged from the elongate hose.
8. An in-flight refueling system according to claim 7 , wherein the fuse device is further configured to be separable into a first segment operably engaged with a first portion of the elongate hose and a second segment operably engaged with the drogue in response to a separating force experienced thereby, such that the first portion of the elongate hose is separable from the drogue in response to the separating force.
9. An in-flight refueling system according to claim 7 , wherein the fuse device is operably engaged between the second end of the elongate hose and the drogue such that the fuse device is further configured to be separable into a first segment operably engaged with the second end of the elongate hose and a second segment operably engaged with the drogue in response to a separating force experienced thereby, such that the drogue is separable from the second end of the elongate hose in response to the separating force.
10. An in-flight refueling system according to claim 7 , wherein the fuse device is further configured such that the separating force is less than a breakage force required to damage the elongate hose.
11. An in-flight refueling system according to claim 7 , wherein the fuse device is selected from the group consisting of:
at least one shear bolt;
a cylindrical conduit; and
combinations thereof.
12. An in-flight refueling system according to claim 7 , wherein the fuse device further comprises:
a first threaded portion configured to be capable of operably engaging a first threaded surface disposed on the second end of the elongate hose; and
a second threaded portion configured to be capable of operably engaging a second threaded surface disposed on the drogue.