Aerial refueling coupling for in-flight operation parameter measuring

Abstract

The present disclosure refers an aerial refueling coupling for in-flight parameter measuring, including a body configured to receive and support a probe and a removable shell that covers at least part of the body. The aerial refueling coupling includes a sensor system for detecting at least one parameter related to in-flight refueling operation, a data processing device configured to provide a measure at least relative to parameters detected by the sensor system, a portable storage system, and a power supply system comprising at least on battery for supplying energy, and a ram air turbine for their activation when the aerial refueling coupling is in-flight. The data processing device, the storage system and the power supply system are mounted onto the body covered by the shell.

Claims

1. An aerial refueling coupling for in-flight parameter measuring, the aerial refueling coupling comprising: a body configured to receive and support a probe; a removable shell that covers at least part of the body; three latching pistons, at least one of which comprises a port for ground testing; a sensor system configured for detecting at least one parameter related to an in-flight refueling operation, the sensor system comprising a pressure sensor positioned on the port to detect fuel output pressure during the in-flight refueling operation; a data processing device configured to provide a measure relative to the at least one parameter detected by the sensor system; a portable storage system in communication with the data processing device for storing measurements of the at least one parameter; a power supply system comprising at least one battery, for supplying energy to the data processing device, the sensor system, and the portable storage system, and a ram air turbine for activation thereof when the aerial refueling coupling is in-flight, wherein the data processing device, the portable storage system, and the power supply system are mounted onto the body covered by the shell.

2. The aerial refueling coupling according to claim 1, comprising three latch levers configured to engage a probe, wherein the sensor system comprises at least one potentiometer positioned at each latch lever so as to detect a displacement of each of the latch levers.

3. The aerial refueling coupling according to claim 1, comprising a ball joint to allow rotatable movement of the aerial refueling coupling when the aerial refueling coupling is coupled to a probe for the in-flight refueling operation, wherein the sensor system comprises gauged screws that fix the ball joint to detect axial force exerted by or on the aerial refueling coupling during the in-flight refueling operation to compensate for a drag of the probe.

4. The aerial refueling coupling according to claim 1, wherein the pressure sensor is configured for detecting fuel pressure surges.

5. The aerial refueling coupling according to claim 1, wherein the sensor system comprises three-dimensional (3D) accelerometers and gyroscopes for detecting acceleration and positioning of the aerial refueling coupling.

6. The aerial refueling coupling according to claim 1, further comprising a video camera positioned at an outwards end of the aerial refueling coupling to record the in-flight refueling, the camera being in communication with the portable storage system to store a recording recorded by the video camera.

7. The aerial refueling coupling according to claim 6, wherein the data processing device is configured to provide a measure relative to an approach speed of a probe before entry of the probe into the aerial refueling coupling for the in-flight refueling operation.

8. The aerial refueling coupling according to claim 1, comprising a real time clock, which is synchronized with Coordinated Universal Time (UTC) and connected to the data processing device for synchronizing measures of the at least one parameter.

9. The aerial refueling coupling according to claim 1, wherein the data processing device is configured to measure electrical pulses generated by the ram air turbine when the aerial refueling coupling is in-flight and to calculate an air speed from the electrical pulses measured.

10. The aerial refueling coupling according to claim 1, wherein the power supply system comprises a battery configured to store energy and to supply energy to the data processing device, the sensor system, and the portable storage system, the battery being configured to withstand in-flight conditions.

11. The aerial refueling coupling according to claim 1, wherein the data processing device is configured to stop providing an energy to the sensor system, the portable storage system, and the data processing device itself from the power supply system when the ram air turbine stops generating sufficient electrical pulses.

12. The aerial refueling coupling according to claim 1, wherein the portable storage system is a removable memory card.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) For a better comprehension of the disclosure herein, the following drawings are provided for illustrative and non-limiting purposes, wherein:

(2) FIG. 1 shows a schematic view of a refueling operation between a tanker aircraft and a receiver aircraft using a hose-and-drogue system.

(3) FIG. 2 shows a schematic cross section view of the aerial refueling coupling that indicates the preferred emplacements of most of the elements that form the sensor system. Also, the figure shows the data processing device, the storage system and power supply system preferred emplacements, according to an embodiment of the disclosure herein.

(4) FIG. 3 shows a simplified block diagram illustrating most of the elements that form the sensor system, the data processing device, the storage system and the power supply system, according to an embodiment of the disclosure herein.

DETAILED DESCRIPTION

(5) FIG. 1 shows an in-flight refueling operation based on the use of a hose-and-drogue system. The in-flight refueling involves a tanker aircraft 15 and a receiver aircraft 16, wherein both are provisioned for the refueling operation. The tanker aircraft 15 is provided with a flexible hose 18 ended in a drogue. The drogue comprises an aerial refueling coupling 1 that is specially constituted for the operation. The receiver aircraft 16 is provided with a probe 18, which is a rigid arm placed on the receiver aircraft's nose or fuselage. The aerial refueling coupling 1 is configured for receiving and supporting the probe 18, and also for controlling the pass of fuel once the probe 18 is coupled. When the aerial refueling coupling 1 and the probe 18 are coupled, the valve that carries the probe 18 at its forward end opens, and the fuel passes from the tanker aircraft 15 to the receiver aircraft 16.

(6) The aerial refueling coupling 1 depicted in FIG. 2 shows the rigid body 13 configured to support and receive a probe 18 by its outwards conical end, opposite to its connection with the hose (not shown). After the ring-shaped coupling, to which the hose (not shown) is assembled, and the partial cylindrical section, the removable shell 14 is fixed to the body 13, covering at least part of it. The shell 14 has a conical-shaped and extends around the cone or bell-shaped portion of the aerial refueling coupling 1.

(7) The data processing device 4, the storage system 5 and the power supply system 2 are mounted onto the body 13 covered by the shell 14. In this emplacement, the shell 14 allows covering and protecting the mentioned elements, at the same time that the elements can be securely attached to the rigid body 13. Besides, the emplacement avoids the need of modifying conventional aerial refueling couplings for their colocation.

(8) The sensor system of the disclosure herein is suitable for detecting at least one parameter related to the in-flight refueling operation, and its emplacement depends on the parameter to be detected. This enables a quick, accurate, and reliable detection.

(9) As known, conventional aerial refueling couplings comprise three latch levers configured to engage a probe and latched it to prevent the probe from disengaging during the refueling. This way, a latching force is applied to latch the probe and the aerial refueling coupling together with a desired resistance, at least resistant to support the fuel pressure, and conveniently variable by adjustment to adequate it to particular cases. According to this, in a preferred embodiment of the disclosure herein, the sensor system comprises at least one potentiometer 10 positioned at each latch lever so as to detect the displacement of the latch levers. Thereby, the sensor system detects exact positions, rather than latching states (non-latched state, intermediate latching state and a latched state), as currently known by the state of the art.

(10) Also, conventional aerial refueling couplings comprise a ball joint to allow rotatable movement of the aerial refueling coupling, when the aerial refueling coupling is coupled to a probe for the in-flight refueling. According to another preferred embodiment, the sensor system comprises gauged screws 9 that fix the ball joint to detect the axial force exerted by the aerial refueling coupling 1 during the in-flight refueling to compensate the drag of the probe 18 when it is coupled with the aerial refueling coupling 1.

(11) Also, conventional aerial refueling couplings comprise three circumferentially spaced latching pistons 21. The fuel pressure within the coupling is admitted to the latching pistons 21, through respective ports 19, to assist springs 22 in the pistons 21 in urging the toggle links 23 outwardly of the pistons 21 so as to flex the toggle link 23 and urge the rollers 24 into a groove of the probe. At this point, the latching force should be applied to latch the probe and the aerial refueling coupling together.

(12) Conventionally, one of the three latching pistons 21 comprises a port for ground testing purposes. According to this, in another preferred embodiment, the sensor system comprises a pressure sensor 7 positioned on a port of one of the three latching pistons 21 to detect fuel output pressure during the in-flight refueling. Preferentially, the pressure sensor 7 shall be suitable for detecting fuel pressure surges.

(13) Additionally, according to another preferred embodiment, the sensor system comprises 3D accelerometers and gyroscopes 8 for detecting data of acceleration and positioning of the aerial refueling coupling 1.

(14) According to another preferred embodiment, the aerial refueling coupling 1 further comprises a video camera 11 positioned, as shown in FIG. 2, at the outwards end of the aerial refueling coupling 1 to record the in-flight refueling. The camera 11 is in communication with the storage system 5 to store the recording.

(15) Preferentially, the data processing device 4 is configured to provide a measure relative to the approach speed (closure rate) of a probe 18 before entering the aerial refueling coupling 1 for the in-flight refueling. The data processing device will be able to obtain this measure from the recording provided by the video camera 11. Alternatively, the receiver closure rate measure may be provided by post-processing from the information stored in the aerial refueling coupling 1.

(16) Additionally, according to another preferred embodiment, the aerial refueling coupling 1 comprises a Real Time Clock (RTC) 6 synchronized with the Universal Coordinated Time (UTC) and connected to the data processing device 4 for synchronizing the measures. This way, the aerial refueling coupling 1 is able to count with an organized collection of measures, which facilitates the post-processing of the recorded data. Also, enables recording and storing the video captured by the video camera 11 with real time information.

(17) According to another preferred embodiment, the data processing device 4 is configured to measure the electrical pulses generated by the ram air turbine 12 when is in-flight, and to calculate the air speed from the measure.

(18) In addition, according to another preferred embodiment, the power supply system 2 might comprise a battery 20 to store energy for supplying energy to the data processing device 2 and to the sensor and storage 5 systems. The battery 20 is suitable for withstanding flight conditions. An algorithm based on the RAT inputs allows managing the energy supply, saving energy when the drogue is not deployed.

(19) According to another preferred embodiment, the data processing device 4 is configured to switch off all the systems: the sensor system, the storage system 5 and the data processing device itself by stopping feeding them from the power supply system 2 when the ram air turbine 12 stops generating electrical pulses. Thus, the aerial refueling coupling is a well-managed energy device, since the sensor system, the storage system 5 and the data processing device 4 are only powered when the aerial refueling coupling 1 is in-flight and the detecting and/or measuring can take place.

(20) In another preferred embodiment, the power supply system 2 may comprise a relay 3, so that as soon as aerial refueling coupling 1 is deployed and the ram air turbine 12 starts turning, the ram air turbine 12 feeds the relay 3, which switch on whole system (the data processing device, the sensor system and the storage system 5), fed by the power supply system 2.

(21) According to another preferred embodiment, the storage system 5 is a removable memory card. Thereby, the disclosure herein enables a post-processing of the data stored in the storage system 5 during the whole in-flight refueling process operation.

(22) FIG. 3 shows a simplified block diagram illustrating the architecture of the preferential elements that form the sensor system, the data processing device 4, the storage system 5, and the power supply system 2.

(23) Preferentially, all the hardware formed by the elements that constitute the sensor system, the data processing device 4, the storage system 5 and the power supply system 2 are packaged within boxes in order to support the environmental qualification tests applicable for these applications. Likewise, enclosing the mentioned elements in boxes, the disclosure herein provides a more compact and robust solution, which in addition, facilitates their mounting.

(24) While at least one exemplary embodiment of the 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.