Valve condition detection system and assembly and method for aircraft fuel systems

Abstract

Directly identify and verify valve conditions present within aircraft fuel control valves in real time. [Solution] The aircraft fuel control valve incorporates an electromagnetic energy beam transmitter (42) and receiver (44) for transmitting and receiving an electromagnetic energy beam (42a) across an aircraft fuel control valve assembly chamber (32), allowing direct knowledge of the current "state" or "valve position" of a valve (34) within a valve assembly (24).

Description

[Technical Field]

[0001]

[0001] The present disclosure relates generally to the field of valve monitoring systems. In particular, the present disclosure relates to the field of monitoring aircraft fuel control valve systems. [Background technology]

[0002] Optimal operation of an aircraft may depend on the proper operating condition of fuel delivery systems and components. The ability to know the status of one or more valves in an aircraft fuel delivery system may be essential to ensure optimal operation of the aircraft and to comply with regulatory requirements.

[0003]

[0003] Typical methods for determining the orientation of a component part within an assembly may rely on indirectly monitoring the state of the component part of interest, for example, by measuring the properties and / or operation and / or orientation of a sub-component part within the assembly that is attached to the component part of interest. Malfunctioning of the sub-component part or deviation of the observed sub-component part from the actual component part of interest may result in an erroneous operational reading of the actual state of the component part of interest.

[0004]

[0004] Nothing in this specification is admitted to be prior art merely by virtue of its inclusion in the technical field and / or background art unless expressly stated to be prior art. Summary of the Invention

[0005]

[0005] This aspect is directed to an aircraft fuel control valve assembly including an aircraft fuel control valve housing. The aircraft fuel control valve housing includes a valve body with a valve body interior, a valve inlet, a valve outlet, and a valve chamber. The valve chamber is defined by an area within the valve body of the aircraft fuel control valve assembly. The valve body and the valve chamber are further defined between the valve inlet and the valve outlet. The valve body includes the valve chamber and a movable valve. The movable valve is substantially disposed within the valve chamber. The aircraft fuel control valve assembly further includes a primary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter configured to direct primary electromagnetic energy, which may be light (and may be a primary electromagnetic energy beam, which may be a primary electromagnetic energy ray), from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter further including an electromagnetic energy source. The aircraft fuel control valve assembly further includes a primary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the primary electromagnetic energy receiver is configured to receive primary electromagnetic energy, which may be a primary electromagnetic energy beam transmitted from the primary electromagnetic energy transmitter, where the primary electromagnetic energy receiver is configured to generate a primary valve state signal.

[0006]

[0006] In another aspect of this invention, the aircraft fuel control valve assembly further comprises a movable valve, wherein the movable valve is configured to include a range of motion between an open valve configuration and a closed valve configuration.

[0007]

[0007] In another aspect of the present invention, the aircraft fuel control valve assembly further includes an actuator, wherein the actuator is in communication with the movable valve, and wherein the actuator is configured to move the movable valve between an open valve configuration and a closed valve configuration.

[0008] In another present aspect, the aircraft fuel control valve assembly further comprises a secondary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, where the secondary electromagnetic energy transmitter is configured to direct secondary electromagnetic energy, which may be light (and may be a secondary electromagnetic energy beam, which may be a secondary electromagnetic energy ray), from the secondary electromagnetic energy transmitter into and across the valve chamber, where the secondary electromagnetic energy transmitter further comprises at least one of a primary electromagnetic energy source and a secondary electromagnetic energy source. The aircraft fuel control valve assembly further comprises a secondary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the secondary electromagnetic energy receiver is configured to receive at least one of the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and the secondary electromagnetic energy beam from the secondary electromagnetic energy transmitter, where the secondary electromagnetic energy receiver is configured to generate a valve-state secondary signal.

[0009]

[0009] In another aspect of the present invention, the primary and secondary electromagnetic energy sources are at least one of a laser and a light-emitting diode, in which case the primary and secondary electromagnetic energy sources are configured to generate light to form generated light, which may be a generated light beam.

[0010] In another present aspect, the generated light comprises wavelengths in the range of about 850 nm to about 1550 nm.

[0011]

[0011] In another aspect of the present invention, the secondary electromagnetic energy source comprises at least one of a laser and a light-emitting diode, in which case the secondary electromagnetic energy source is configured to generate a secondary electromagnetic energy beam to form the generated secondary light beam.

[0012] In another present aspect, the generated secondary light beam comprises wavelengths in the range of about 850 nm to about 1550 nm.

[0013]

[0013] In another aspect of the present invention, the generated light beam extends substantially along a straight line from the primary electromagnetic energy transmitter to the primary electromagnetic energy receiver, wherein the substantially straight line extends from the primary electromagnetic energy transmitter through the valve chamber to the primary electromagnetic energy receiver when the movable valve is in the open valve configuration.

[0014]

[0014] In another aspect of the present invention, the generated light beam is configured to extend from the primary electromagnetic energy transmitter diagonally through (e.g., across) the valve chamber to the primary electromagnetic energy receiver when the movable valve is in an open valve configuration.

[0015] Another present aspect is directed to an aircraft including an aircraft fuel control valve assembly including an aircraft fuel control valve housing. The aircraft fuel control valve housing includes a valve body with a valve body interior, a valve inlet, a valve outlet, and a valve chamber. The valve chamber is defined by an area within the valve body of the aircraft fuel control valve assembly. The valve body and the valve chamber are further defined between the valve inlet and the valve outlet. The valve body includes the valve chamber and a movable valve. The movable valve is substantially disposed within the valve chamber. The aircraft fuel control valve assembly further includes a primary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter configured to direct primary electromagnetic energy, which may be light (and may be a primary electromagnetic energy beam, which may be a primary electromagnetic energy ray), from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter further including an electromagnetic energy source. The aircraft fuel control valve assembly further includes a primary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the primary electromagnetic energy receiver is configured to receive the primary electromagnetic energy beam from the primary electromagnetic energy transmitter, where the primary electromagnetic energy receiver is configured to generate the valve-state primary signal.

[0016] Another present aspect is directed to an aircraft fuel control valve status detection system for identifying an aircraft fuel control valve status. The aircraft fuel control valve status detection system includes an aircraft fuel control valve assembly disposed in an aircraft fuel line. The aircraft fuel control valve assembly includes an aircraft fuel control valve housing. The aircraft fuel control valve housing includes a valve body with a valve body interior, a valve inlet, a valve outlet, and a valve chamber. The valve chamber is defined by an area within the valve body of the aircraft fuel control valve assembly. The valve body and the valve chamber are further defined between the valve inlet and the valve outlet. The valve body includes a valve chamber and a movable valve. The movable valve is substantially disposed within the valve chamber. The aircraft fuel control valve assembly further includes a primary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, where the primary electromagnetic energy transmitter is configured to direct primary electromagnetic energy, which may be light (and may be a primary electromagnetic energy beam, which may be a primary electromagnetic energy ray), from the primary electromagnetic energy transmitter into and across the valve chamber, where the primary electromagnetic energy transmitter further includes an electromagnetic energy source. The aircraft fuel control valve assembly further includes a primary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the primary electromagnetic energy receiver is configured to receive the primary electromagnetic energy beam from the primary electromagnetic energy transmitter, where the primary electromagnetic energy receiver is configured to generate a valve-status primary signal. The aircraft fuel control valve status detection system for identifying an aircraft fuel control valve status further includes a processor in communication with the primary electromagnetic energy receiver, where the processor is configured to receive the valve-status primary signal. Where the processor is further configured to interpret the valve-status primary signal generated by the primary electromagnetic energy receiver to form an interpreted fuel valve-status primary signal. In that case, the interpreted fuel valve status primary signal corresponds to the aircraft fuel control valve status.

[0017]

[0017] In another aspect of the present invention, the electromagnetic energy source is at least one of a laser and a light emitting diode configured to generate a beam of light, wherein the beam includes a wavelength in the range of about 850 nm to about 1550 nm.

[0018]

[0018] In a further aspect of this invention, the aircraft fuel control valve state detection system further comprises a reader in communication with the processor.

[0019]

[0019] In another aspect of the present invention, in the aircraft fuel control valve status detection system, the aircraft fuel control valve assembly further comprises a valve actuator, in which case the valve actuator is in direct communication with the movable valve, in which case the actuator is configured to move the movable valve between an open valve configuration and a closed valve configuration.

[0020] In another present aspect, in the aircraft fuel control valve status detection system, the aircraft fuel control valve assembly further comprises a secondary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, where the secondary electromagnetic energy transmitter is configured to direct secondary electromagnetic energy, which may be light (and may be a secondary electromagnetic energy beam, which may be a secondary electromagnetic energy ray), from the secondary electromagnetic energy transmitter into and across the valve chamber, where the secondary electromagnetic energy transmitter further comprises an electromagnetic energy source. The aircraft fuel control valve assembly further comprises a secondary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the secondary electromagnetic energy receiver is configured to receive at least one of the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and the secondary electromagnetic energy beam from the secondary electromagnetic energy transmitter, where the secondary electromagnetic energy receiver is configured to generate a valve status secondary signal.

[0021]

[0021] In another aspect of the present invention, in an aircraft fuel control valve status detection system, the secondary electromagnetic energy source is configured to generate a light beam, wherein the generated light beam includes a wavelength in the range of approximately 850 nm to approximately 1550 nm.

[0022]

[0022] A further present aspect is directed to a method for directly monitoring an aircraft fuel control valve status within an aircraft fuel control valve assembly. The method includes disposing the aircraft fuel control valve assembly in an aircraft fuel line. The aircraft fuel control valve assembly includes an aircraft fuel control valve housing. The fuel control valve housing includes a valve body interior, a valve inlet, a valve outlet, and a valve chamber. The valve chamber is defined by an area within the valve body of the aircraft fuel control valve assembly. The valve body and the valve chamber are further defined between the valve inlet and the valve outlet. The valve body includes the valve chamber in communication with a movable valve. The movable valve is substantially disposed within the valve chamber. The aircraft fuel control valve assembly further includes a primary electromagnetic energy transmitter integrated within the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter configured to direct primary electromagnetic energy, which may be light (and may be a primary electromagnetic energy beam, which may be a primary electromagnetic energy ray), from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter further comprising an electromagnetic energy source. The aircraft fuel control valve assembly further includes a primary electromagnetic energy receiver integrated within the aircraft fuel control valve assembly, where the primary electromagnetic energy receiver is configured to receive a primary electromagnetic energy beam from the primary electromagnetic energy transmitter, where the primary electromagnetic energy receiver is configured to generate a primary valve-state signal. The method further includes generating an electromagnetic energy beam at the primary electromagnetic energy transmitter, transmitting the primary electromagnetic energy beam from the primary electromagnetic energy transmitter into a valve chamber to form a transmitted primary electromagnetic energy beam, receiving the primary electromagnetic energy beam transmitted from the primary electromagnetic energy transmitter at the primary electromagnetic energy receiver, and directly monitoring the aircraft fuel control valve state based on at least one of reception and non-reception of the primary electromagnetic energy beam transmitted by the primary electromagnetic energy receiver.

[0023] In another present aspect, the method further includes generating a fuel valve state primary signal at the primary electromagnetic energy receiver when the primary electromagnetic energy receiver receives the transmitted primary electromagnetic energy beam, and interpreting the fuel valve state primary signal to form an interpreted fuel valve state primary signal, where the interpreted fuel valve state primary signal corresponds to an aircraft fuel valve state, where the aircraft fuel control valve state includes at least one of an aircraft fuel control valve open configuration and an aircraft fuel control valve closed configuration.

[0024]

[0024] In another present aspect, the method further includes transmitting the interpreted fuel valve status primary signal to a reader.

[0025]

[0025] Further in this aspect, in the method, reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver is configured to verify an aircraft fuel control valve open configuration.

[0026]

[0026] In a further aspect, the method is configured such that non-reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver indicates an aircraft fuel control valve closed configuration.

[0027]

[0027] The above-described features, functions, and advantages can be realized alone in various aspects or can be combined in further multiple aspects, details of which can be confirmed by referring to the following description and accompanying drawings.

[0028]

[0028] Having described variations of the present disclosure in general terms, reference is now made to the accompanying drawings, which are not necessarily drawn to scale, and in which: [Brief explanation of the drawings]

[0029] [Figure 1]

[0029] A diagram of a vehicle in the form of an aircraft that may include the aircraft fuel control valve assembly and the aircraft fuel control system according to this embodiment. [Figure 2]

[0030] FIG. 2 is a box diagram of a fuel control system in an aircraft, according to a present embodiment. [Figure 3A]

[0031] FIG. 2 is a cross-sectional side view of the aircraft fuel control valve assembly in a fuel line with a movable valve in an open valve position according to a present embodiment. [Figure 3B]

[0032] FIG. 3B is a cross-sectional side view of the aircraft fuel control valve assembly in a fuel line of the type shown in FIG. 3A with the movable valve in a closed valve position, according to a present embodiment. [Figure 4]

[0033] FIG. 2 is a flow diagram of a fuel control system that may incorporate the aircraft fuel control valve assembly, according to present aspects. [Figure 5A]

[0034] FIG. 2 is a cross-sectional side view of the aircraft fuel control valve assembly with primary and secondary electromagnetic energy beam transmitters and primary and secondary electromagnetic energy beam receivers in a fuel line with a movable valve in an open valve state according to present aspects. [Figure 5B]

[0035] FIG. 1 is a cross-sectional side view of the present fluid control valve assembly with primary and secondary electromagnetic energy beam transmitters and primary and secondary electromagnetic energy beam receivers in a fuel line with a movable valve in an open valve state according to present embodiments. [Figure 6]

[0036] 1 is a flowchart outlining the method, according to the present embodiment. [Figure 7]

[0037] 1 is a flowchart outlining the method, according to the present embodiment. [Figure 8]

[0038] 1 is a flowchart outlining the method, according to the present embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0030]

[0039] Several present aspects are directed to an aircraft fuel control valve state detection system. The system may be disposed in an aircraft fuel line incorporating at least one presently disclosed aircraft fuel control valve assembly. Further present aspects are directed to a method for directly monitoring, directly identifying, and directly verifying aircraft fuel control valve “states” (equivalently referred to herein as “aircraft fuel line control valve states”) in real time and on demand. The presently disclosed aircraft fuel control valve state detection system can directly monitor, directly detect, directly assess, and directly verify aircraft fuel line control valve “states” (equivalently referred to herein as “valve states” and / or “valve configurations” and / or “valve positions”) in real time and on demand to directly identify and / or directly verify the “state” of a movable valve in an aircraft fuel control valve assembly in either a “closed” state (e.g., closed valve state, closed valve configuration, closed valve position, etc.) or an “open” state (e.g., open valve state, open valve configuration, open valve position, etc.).

[0031]

[0040] The disclosed direct aircraft fuel control valve condition detection apparatus, systems, and methods can operate independently of, in addition to, and simultaneously in cooperation with existing indirect valve position measurement systems that operate indirectly, for example, by measuring the movement of components and / or subcomponents (e.g., parts, assemblies, etc. other than the valve itself) that are physically attached to or otherwise in communication with a movable valve within a valve assembly. When the present apparatus, systems, and methods are employed in addition to or simultaneously in cooperation with an indirect valve monitoring system, the present apparatus, systems, and methods for direct assessment of fuel control valve condition or valve "state" provide redundancy for independent, direct auxiliary fuel system monitoring critical to aircraft operation, which can have a significant impact on ensuring optimal aircraft performance and significantly improve flight safety.

[0032]

[0041] According to several present aspects, the aircraft fuel control valve assembly of the present disclosure comprises a movable valve that may be configured to move or otherwise operate to "move" on demand between a closed valve configuration (preventing fluid flow through the valve assembly) and an open valve configuration (facilitating or otherwise enabling fluid flow through the valve assembly), and further incorporates a valve state detection device incorporated or otherwise integrated within the aircraft fuel control valve assembly (equivalently referred to herein as the "valve assembly") that directly determines the current valve "state" or "valve position" within the valve assembly.

[0033]

[0042] 1 illustrates a vehicle in the form of an aircraft 10 including a fuselage 12 and wing structures 14. Each of the wing structures 14 may include a fuel supply system 20 (equivalently referred to herein as a "fuel system 20"), not specifically shown in FIG. 1, which may include a fuel supply (equivalently referred to herein as a fuel source), which may be, for example, a fuel supply housed within a fuel tank 16. In that case, the fuel tank is configured to be housed within the wing structure 14, and in that case, the fuel supply and fuel supply system are in communication with the engine 17.

[0034]

[0043] 2 , the aircraft 10 may include a fuel system 20 (equivalently referred to herein as an “aircraft fuel supply system”) for controlled delivery of a fuel supply from, for example, one or more fuel tanks 16 (which may be located within the wing assemblies of the wings 14) into fuel lines 22. In this case, the fuel lines 22 communicate with at least one aircraft fuel control valve assembly 24. The valve assembly 24 may communicate along the fuel lines with a fuel destination in, for example, the aircraft engines 17.

[0035]

[0044] 3A and 3B are cross-sectional side views of the present aircraft fuel control valve assembly 24 of a type that may be incorporated into the present aircraft fuel line control valve system. Figure 3A shows the presently disclosed aircraft fuel control valve assembly 24 with the movable valve 34 therein shown in an "open" position (equivalently referred to herein as an "open valve state," "open valve condition," or "open valve configuration"). This "open" position may facilitate, or otherwise conditionally selectively allow, fluid flow through the aircraft fuel control valve assembly and through an aircraft fuel line in which the aircraft fuel line valve assembly is disposed and positioned, according to present embodiments.

[0036]

[0045] 3B illustrates the aircraft fuel control valve assembly 24 of the present disclosure with the movable valve 34 within the assembly shown in a “closed” position (equivalently referred to herein as a “closed valve state,” “closed valve condition,” or “closed valve configuration”). This “closed” position may conditionally selectively impede or completely inhibit fluid flow through the aircraft fuel control valve assembly, and may similarly impede fluid flow through an aircraft fuel line in which the aircraft fuel line valve assembly is disposed and positioned.

[0037]

[0046] Although the fluid passing through the aircraft fuel control valve assembly is typically a liquid flow in the form of liquid aviation fuel, present aspects further contemplate the use of the valve assembly and the fuel line incorporating the valve assembly for purposes of venting aircraft fuel lines that may carry non-liquid fluids of air or other gases (e.g., nitrogen) through the aircraft fuel line and through the aircraft fuel control valve assembly.

[0038]

[0047] 3A , according to various present embodiments, the aircraft fuel control valve assembly 24 includes a fuel control valve housing 25. The housing 25 includes a valve body 26 having an internal valve chamber 32 bounded by an interior area within the valve body 26, where the valve chamber 32 is further bounded by a valve inlet 28 and a valve outlet 30, where the valve body 26 is disposed immediately adjacent to and positioned between the valve inlet 28 and the valve outlet 30. Depending on the configuration of the valve “state” within the aircraft fuel control valve assembly 24, the aircraft fuel control valve assembly 24 is configured to facilitate, inhibit, impede, terminate (e.g., completely “block”), or otherwise control fluid flow (e.g., liquid or gas flow) through an aircraft fluid line (which may be an aircraft fuel line) that includes the aircraft fuel control valve assembly.

[0039]

[0048] 3A further illustrates movable valve 34, shown in FIG. 3A as a non-limiting ball valve. Movable valve 34 as shown in FIG. 3A is configured with dimensions such that the ball valve includes the dimensions of an imperfect sphere around its three-dimensional spherical periphery. Through rotational motion of the ball valve (which may be back-and-forth rotational motion), a valve state within valve chamber 32 (in which the movable valve is disposed) can be established. The state is either an "open" valve state or a "closed" valve state, as the ball valve moves through a range of rotational motion between the "open" and "closed" valve states.

[0040]

[0049] In this “open” valve state, a fluid flow 23 from a fluid source (not shown in FIG. 3A ), which may be, for example, a fuel supply (equivalently referred to herein as a “fuel source”) that may be maintained in a fuel tank, proceeds or is otherwise directed from the fluid source through fluid flow line 22 to aircraft fuel control valve assembly 24. The fuel supply is then configured to enter aircraft fuel control valve assembly 24 at valve inlet 28 (equivalently referred to herein as “aircraft fuel control valve assembly inlet 28”). When movable valve 34 is in the “open” state, passage of fluid flow 23 through valve chamber 32 of aircraft fuel control valve assembly 24 is established, and fluid flow 23 proceeds into and through valve chamber 32 and then from valve chamber 32 and aircraft fuel control valve assembly 24 through (e.g., exits) valve outlet 30 (equivalently referred to herein as “aircraft fuel control valve assembly outlet 30”).

[0041]

[0050] According to some aspects, the aircraft fuel control valve assembly of the present disclosure is configured to directly, conclusively, and independently ascertain valve "state" (i.e., valve "condition") by directing primary electromagnetic energy, which may be, for example, a beam of electromagnetic energy in the form of "light," which may include, for example, a light beam, from an electromagnetic energy transmitter to an electromagnetic energy receiver, in real time, on demand, and / or continuously. According to some aspects, the transmitter and receiver are located, for example, at the end of a fiber optic cable. In this case, the transmitter assembly and / or receiver assembly further comprise electronics and support architecture (which may communicate with the fiber optic cable), which may be physically located outside the valve housing, including being physically located outside the valve chamber.

[0042]

[0051] According to this aspect, at least one electromagnetic energy transmitter is integrated into the valve assembly at a location outside one end of the valve body comprising the valve chamber (e.g., the inlet end or outlet end of the valve chamber), and disposed within the valve assembly, and at least one electromagnetic energy receiver is disposed at the other end of the valve body and the valve chamber (e.g., the inlet end or outlet end of the chamber linearly opposite the location of the electromagnetic energy transmitter). and disposed within the valve assembly at a location outside of the valve assembly, where at least one electromagnetic energy receiver is further disposed opposite and facing the electromagnetic energy transmitter, for example, for the purpose of receiving the electromagnetic energy beam transmitted from the electromagnetic energy transmitter.

[0043]

[0052] According to some present aspects, a primary electromagnetic energy transmitter configured to emit and direct a beam of electromagnetic energy is paired with a primary electromagnetic energy receiver positioned or otherwise configured to receive the beam of electromagnetic energy transmitted from the transmitter, the beam transmitted across and into the valve chamber in an open valve state. Because the transmitter and receiver are positioned opposite each other and across the valve chamber from each other (e.g., on opposite sides of the valve chamber from each other), the transmitted beam of electromagnetic energy (e.g., transmitted from the transmitter) can only be received when the valve is in an open “state” (because the transmitted beam can be “blocked” from successfully traversing the length and / or width of the valve chamber when the valve is in a “closed” position (e.g., closed state) (a valve position in which the beam cannot travel unrestricted into and / or through the valve chamber and cannot reach and be received by the receiver).

[0044]

[0053] 3A , according to some present embodiments, a primary electromagnetic energy transmitter 42 comprising or in communication with a primary electromagnetic energy source 41 is integrated into the valve outlet 30 so that a substantially linear beam of transmitted electromagnetic energy travels substantially across the chamber (e.g., from one end of the chamber to the other (equivalently referred to herein as the valve chamber length and / or the valve chamber width)). The primary electromagnetic energy transmitter 42 is shown positioned to provide a primary electromagnetic energy beam 42a into, through, and across the valve chamber 34 directly to a primary electromagnetic energy receiver 44.

[0045]

[0054] Because the primary electromagnetic energy beam 42a (which may be, for example, a collimated beam of light) may travel in a substantially linear direction, as shown in FIG. 3A, the primary transmitter may be positioned at an angle (represented by θ1 in FIG. 3A) relative to the horizontal axis of the flow path through the valve assembly. This allows a substantially linear beam (e.g., a linear ray of light) to travel across the valve chamber from the transmitter and be received by the receiver. The receiver may be located within the valve chamber or just outside the valve chamber, on the "opposite side" or "opposite" the transmitter, at a distance from the transmitter that may be approximately equal to or slightly longer than the length of the valve chamber. The orientation of the transmitted ray of light across the valve chamber may be determined by the angle of the primary transmitter relative to the horizontal axis of the flow path through the valve assembly. The movable valve therein (and ultimately the valve chamber itself) is shown in FIG. 3A as being oriented substantially diagonally across and through the valve chamber when configured to the "open" valve state.

[0046]

[0055] According to several present aspects, an aircraft fuel control valve assembly may include two or more integrated transmitter / receiver pairs for the purpose of providing integral redundancy to at least the valve assembly, such that, for example, if one transmitter or receiver temporarily malfunctions, a second transmitter / receiver pair may initiate and operate to continue direct assessment of the valve's "state," such as "open" or "closed," in the present aircraft fuel control valve assembly. For the present purposes, when two transmitter / receiver pairs are present in the system and assembly, the two transmitter / receiver pairs are described and designated as comprising "primary" and "secondary" electromagnetic energy transmitters configured to emit and otherwise direct corresponding "primary" and "secondary" electromagnetic energy beams to corresponding "primary" and "secondary" electromagnetic energy receivers.

[0047]

[0056] 3A and 3B illustrate a single transmitter / receiver pair designated, described, and listed therein as a “primary” electromagnetic energy transmitter 42 and a “primary” electromagnetic energy receiver 44. As described herein, for example, to provide system redundancy, FIGS. 5A and 5B illustrate two transmitter / receiver pairs designated, described, and listed as a “primary” electromagnetic energy transmitter 142 and a “primary” electromagnetic energy receiver 144, and a “secondary” electromagnetic energy transmitter 152 and a “secondary” electromagnetic energy beam receiver 154, integrated or otherwise incorporated into the aircraft fuel control valve assembly, where the secondary receiver 154 is configured to receive electromagnetic energy from a primary energy source via the primary energy transmitter 142 and / or receive electromagnetic energy from a secondary energy source via the secondary energy transmitter 152.

[0048]

[0057] As shown in Figures 3A and 3B and as described herein, even though one transmitter / receiver pair 42, 44 is integrated into the aircraft fuel control valve assembly 24 (a "secondary" transmitter / receiver pair is not present within the aircraft fuel control valve assembly 24), the electromagnetic energy transmitter 42 is equivalently referred to herein as a "primary" electromagnetic energy transmitter 42, and the electromagnetic energy receiver 44 is equivalently referred to herein as a "primary" electromagnetic energy receiver 44.

[0049]

[0058] In operation, according to some present embodiments, as shown in FIG. 3A , the movable valve 34 of the aircraft fuel control valve assembly 24 can be fixed into an aircraft fuel line. In that case, the movable valve 34 is configured to an open state, causing the aircraft fuel control valve assembly 24 to be in an open state. The open state allows controlled fluid flow 23 into, through, and out of the valve chamber 32 and valve outlet 30 of the aircraft fuel control valve assembly 24. The primary electromagnetic energy transmitter 42 is integrated into the fuel control valve housing 25 at the location of the valve outlet 30 and positioned at a selected angle to direct a primary electromagnetic energy beam 42 a substantially linearly and obliquely into a portion of the valve outlet 30, into and completely through the valve chamber 32, and into a portion of the valve inlet 28 where the electromagnetic energy receiver 44 is located.

[0050]

[0059] According to various present aspects, the primary electromagnetic energy transmitter 42 may be, comprise, or be in communication with an electromagnetic energy source. That is, the primary electromagnetic energy transmitter 42 may emit and / or transmit electromagnetic energy from the transmitter 42 into a flow path established within the aircraft fuel control valve assembly 24. The established flow path may include a valve inlet, a valve chamber (established within the valve body), and a valve outlet. In one embodiment, the transmitted electromagnetic energy transmitted from the primary energy transmitter 42 is transmitted as a primary electromagnetic energy beam 42a of light (equivalently referred to herein as a “primary light beam 42a”) in a wavelength range from about 850 nm to about 1550 nm. The primary light beam may be generated from, in communication with, or comprise a light source, which may be, for example, but is not intended to be limited to, a laser, a light-emitting diode (LED), or the like.

[0051]

[0060] The primary light beam 42a is selected to be generated and emitted from the primary transmitter at an intensity and wavelength sufficient for the primary light beam to travel from the primary transmitter and be received by the primary receiver, as disclosed more fully herein, i.e., the primary light beam is selected to travel the distance within the aircraft fuel control valve assembly from the primary transmitter to the primary receiver.

[0052]

[0061] Additionally, recognizing that when the valve assembly is in an open state, a flow of working fluid (e.g., liquid fuel, gas, etc.) traverses a flow path through the valve assembly in the valve open state, the primary light beam is further configured to have sufficient intensity and wavelength to pass through actively flowing materials that may simultaneously pass into, through, and out of the aircraft fuel control valve assembly.

[0053]

[0062] Furthermore, because the liquid flowing through the control valve assembly may be aviation fuel, some present aspects further contemplate that the electromagnetic energy beam (which may be, for example, a light beam) has an intensity and wavelength that does not generate substantial heat and does not adversely affect the flow of volatile aviation fuel or fuel vapor through the aircraft fuel control valve assembly. In this embodiment, the light beam may be generated by a transmitter and received by a receiver. In this case, the light beam may have an optical intensity including a maximum power level of 200 mW, with a minimum power level depending on, for example, the noise level of the receiver, and in this case, the electromagnetic energy may take the form of light, which may further take the form of an electromagnetic energy beam, having a wavelength in the range of about 850 nm to about 1550 nm.

[0054]

[0063] 3A , in the open valve assembly configuration, the aircraft fuel control valve assembly 24 includes a primary electromagnetic energy receiver 44. The receiver 44 is integrated within the fuel control housing 25 and is further configured to receive, for example, primary light beam 42a. Primary light beam 42a is directed from the primary electromagnetic energy transmitter 42 through the valve chamber 32. The primary electromagnetic energy receiver 44 (equivalently referred to herein as the “primary receiver”) may be a photodetector that may be linked by a fiber optic link to a photodetector (which may include a photodetector and a fiber optic link) selected to receive, sense, and otherwise detect the primary light beam 42a transmitted from the primary electromagnetic energy transmitter 42.

[0055]

[0064] Upon receiving the light beam transmitted from the transmitter, the photodetector may further generate a signal and transmit the signal from the receiver to verify receipt of the light beam from the transmitter and further verify that the movable valve in the aircraft fuel control valve assembly is in an "open" configuration. The photodetector may be and / or include, for example, but is not limited to, an MSM photodetector, a photodiode, an avalanche photodiode (APD), a phototransistor, a charge-coupled device (CCD), a CMOS imaging sensor (CIS), a photomultiplier tube (PMT), etc.

[0056]

[0065] According to various present aspects, when the movable valve 34 of the aircraft fuel control valve assembly is operably configured to a "closed" state, as shown in FIG. 3B, the fluid flow path 23 attempting to traverse or otherwise be directed along and through a fuel line incorporating the aircraft fuel control valve assembly is obstructed or otherwise completely "blocked," effectively terminating fluid flow through the control valve assembly. As shown in FIG. 3B, the movable valve 34 (shown as a movable ball valve) is now shown "moved" through a range of motion from an "open" movable valve configuration and / or position and / or "state" (which may facilitate fluid throughflow, as shown in FIG. 3A) to the "closed" movable valve configuration shown in FIG. 3B. This "closed" configuration may completely obstruct and effectively terminate fluid flow 23 (e.g., fluid flow through the fluid flow path) through the aircraft fuel control valve assembly 24. In addition to blocking the flow path of fluid through the valve assembly, in the "closed" valve configuration, primary light rays 42a emitted from a primary electromagnetic energy transmitter (located on one side of the valve chamber) are also "blocked" from entering and traversing the valve chamber 32. This prevents primary light rays 42a from reaching or otherwise being received by a primary electromagnetic energy receiver 44 (e.g., a primary receiver located beyond or at an opposite, outer location of the valve chamber relative to the transmitter location).

[0057]

[0066] FIG. 4 is a box diagram illustrating a present aircraft fuel control valve state detection system 40 (equivalently referred to herein as "valve state detection system 40"). As shown in FIG. 4, valve state detection system 40 includes an aircraft fuel control valve assembly 24 of the present disclosure. Assembly 24 includes a primary electromagnetic energy transmitter 42. Transmitter 42 includes, or is otherwise in communication with, an electromagnetic energy source 41. According to various present embodiments, when valve state detection system 40 is operating, primary electromagnetic energy transmitter 42 is configured to provide a primary electromagnetic energy beam 42a and direct beam 42a to primary electromagnetic energy receiver 44 (included within aircraft fuel control valve assembly 24).

[0058]

[0067] In one embodiment, in an “open” valve state, upon receiving the directed primary electromagnetic energy beam 42a, the primary electromagnetic energy receiver 44 generates a valve-state primary signal 44a (equivalently referred to as a “fuel control valve-state primary signal 44a,” “valve-state primary signal 44a,” and “fuel control valve-state signal 44a”). The generated valve-state primary signal 44a is then provided to a processor 46 (shown in FIG. 4 as being integrated into the aircraft fuel control assembly 24, but may also be located externally and / or remotely from the aircraft fuel control assembly 24). The processor 46 is then configured to interpret the valve-state primary signal 44a. In this embodiment, the processor 46 is further configured to generate and transmit a processor signal 48 to one or more readers 50. The readers 50 may be located, for example, within or external to the valve-state detection system 40. According to this embodiment, depending on the type of movable valve present in the aircraft fuel control valve assembly 24, an actuator 36 may be in communication with the movable valve.

[0059]

[0068] According to further present aspects, the aircraft fuel control valve condition detection system 40 of the present disclosure and the aircraft fuel control valve assembly 24 included therein (e.g., to provide at least selected device and system redundancy) may further include two or more electromagnetic energy transmitter / electromagnetic energy receiver “pairs” positioned or otherwise arranged within the aircraft fuel control valve assembly 24 for supplying and receiving additional electromagnetic energy beams. The present aspects illustrated in the drawings are not intended to limit the number of transmitter / receiver “pairs” or otherwise limit the number of transmitted and received electromagnetic energy (e.g., light) beams. FIGS. 5A and 5B illustrate this non-limiting example showing two (two) electromagnetic energy transmitter / electromagnetic energy receiver “pairs,” designated as “primary” and “secondary” electromagnetic energy transmitter / electromagnetic energy receiver “pairs” configured to transmit and receive primary and secondary electromagnetic energy beams, respectively.

[0060]

[0069] Figures 5A and 5B both show the present aircraft fuel control valve assembly 124 in an "open valve state." In Figure 5A, a primary electromagnetic energy beam 142a (which may be a light beam) is generated, transmitted, and received in a manner and operation similar to that described herein with respect to the present aircraft fuel control valve assembly 24 shown in Figure 3A. Furthermore, as shown in Figure 5A, a secondary electromagnetic energy transmitter and a secondary electromagnetic energy receiver are integrally disposed within a fuel control valve housing 125 of the aircraft fuel control valve assembly 124.

[0061]

[0070] As shown in FIG. 5A , a secondary electromagnetic energy beam is not generated by the secondary electromagnetic energy transmitter. In FIG. 5B , a secondary electromagnetic energy beam 152 a (which may be a light beam) is shown generated and transmitted by the secondary electromagnetic energy transmitter 152. The secondary electromagnetic energy beam 152 a is then received by the secondary electromagnetic energy receiver 154. The secondary beam 152 a is then directed into the valve chamber 132 in an opposite beam direction from that of the primary beam 142 a (shown in FIG. 5A ). Additionally, according to some present embodiments, the secondary beam 152 a from the secondary electromagnetic energy transmitter 152 can be detected by the primary receiver 144 to provide built-in-test (BIT) functionality for the primary receiver system. Similarly, as described herein, the secondary receiver 154 can “BIT check” the proper operating status of the primary electromagnetic energy transmitter 142. Such “BIT checking” of the present system provides additional system redundancy to ensure: That is, in the event that the valve assembly is detected as malfunctioning, it is not the detection system that is malfunctioning.

[0062]

[0071] 5A , according to various present embodiments, aircraft fuel control valve assembly 124 includes a fuel control valve housing 125. Housing 125 includes a valve body 126 that includes an internal valve chamber 132 therein. Valve body 126 is then positioned immediately adjacent to and between valve inlet 128 and valve outlet 130. Depending on the configuration of the valve “state” within aircraft fuel control valve assembly 124, aircraft fuel control valve assembly 124 is configured to facilitate, inhibit, impede, terminate (e.g., completely “block”), or otherwise control fluid flow (e.g., liquid or gas flow) through an aircraft fluid line (which may be an aircraft fuel line) that includes the aircraft fuel control valve assembly.

[0063]

[0072] FIG. 5A further illustrates, without limitation, movable valve 134, shown in FIG. 5A as a ball valve. Movable valve 134 as shown in FIG. 5A is configured with dimensions such that the ball valve's three-dimensional periphery includes the dimensions of an incomplete sphere, such that an "open" state of valve chamber 132 (in which the movable valve is located) can be established via rotational movement of the ball valve. In this "open" state, fluid flow 23 (e.g., from a fluid source (e.g., a fuel supply maintained in a fuel tank, not shown in FIG. 5A )) travels from the fluid source through fluid flow line 22 to aircraft fuel control valve assembly 124 and enters aircraft fuel control valve assembly 124 at valve inlet 128. When movable valve 134 is in the "open" state, fluid passage through valve chamber 132 of aircraft fuel control valve assembly 124 is established, with fluid flow 23 traveling into and through valve chamber 132 and then from chamber 132 through valve outlet 130.

[0064]

[0073] 5A , according to some present embodiments, a primary electromagnetic energy transmitter 142 comprising a primary electromagnetic energy source 141 is integrated into the valve outlet 130 of the valve housing 125 so that a substantially linear beam of transmitted electromagnetic energy travels into and across the chamber (e.g., from one “end” or “side” of the chamber to the other). In that case, the primary electromagnetic energy transmitter 142 is shown positioned to provide an electromagnetic energy beam 142 a into and across the valve chamber 132 and directly toward the primary electromagnetic energy receiver 144. Because the primary electromagnetic energy beam 142a (which may be, for example, a collimated beam of light) may travel in a substantially linear direction, as shown in FIG. 5A, the primary transmitter may be positioned at an angle of approximately 180 degrees (e.g., in a straight line or "rectilinearly") across the valve chamber from the primary receiver in a direction that may be diagonal across and through the valve chamber when the movable valve 134 is within the valve chamber 132 and the valve chamber itself is configured in an "open" state.

[0065]

[0074] In operation, according to some present embodiments, as shown in FIG. 5A , the movable valve 134 of the aircraft fuel control valve assembly 124 may be fixed into and otherwise disposed in communication with an aircraft fuel line. In that case, the movable valve 134 is configured in an open state, causing the aircraft fuel control valve assembly 124 to be in an open state. This open state allows controlled fluid flow 23 into, through, and out of the valve chamber 132 of the aircraft fuel control valve assembly 124. The primary electromagnetic energy transmitter 142 is integrated into the fuel control valve housing 125 and positioned to direct a primary electromagnetic energy beam 142a substantially linearly and obliquely into a portion of the valve outlet 130, into and completely through the valve chamber 132, and into a portion of the valve inlet 128. Within the portion of the valve inlet 128, the beam arrives at and is received by the primary electromagnetic energy receiver 144.

[0066]

[0075] 5A further illustrates aircraft fuel control valve assembly 124 including a secondary electromagnetic energy transmitter 152 positioned at and / or adjacent and / or proximate to primary electromagnetic energy receiver 144. As shown in FIG. 5A, aircraft fuel control valve assembly 124 further includes a secondary electromagnetic energy receiver 154 positioned at and / or adjacent and / or proximate to primary electromagnetic energy transmitter 142.

[0067]

[0076] Figure 5B illustrates an aircraft fuel control valve assembly 124 of the type shown in Figure 5A, except that primary transmitter 142 is inactive and does not emit or direct primary light beam 142a. Instead, as shown in Figure 5B, according to this embodiment, secondary electromagnetic energy transmitter 152 is shown generating and providing a secondary electromagnetic energy beam, for example, in the form of secondary electromagnetic energy beam 152a, to secondary electromagnetic energy receiver 154. Secondary light beam 152a is shown traveling in a secondary beam direction opposite to the direction of primary light beam 142a (shown in Figure 5A).

[0068]

[0077] 5A and 5B, according to some present embodiments, the primary and secondary transmitter / receiver pairs may be located at different positions relative to one another, such that the primary and secondary light beams (which could potentially travel in opposite directions along the same beam path) will not occupy or travel along the same beam path (albeit in generally opposite directions). For example, in one present embodiment, the primary and secondary transmitter / receiver pairs may generate the primary and secondary beams simultaneously (both the primary and secondary beams are generated and operating simultaneously).

[0069]

[0078] In another embodiment, the primary and secondary transmitter / receiver pairs may generate the primary and secondary beams one at a time. In that case, the primary or secondary transmitter / receiver pair generates its respective primary and secondary beams only in the event that one component of the primary or secondary transmitter / receiver pair fails. That is, according to several present aspects, the presently disclosed aircraft fuel control valve assembly and the present valve state detection system incorporating the present aircraft fuel control valve assembly provide elements of system safety and redundancy with respect to conclusively monitoring valve “state” or status through its ability to directly monitor and directly assess valve status, independent of and in addition to existing valve monitoring systems and devices that may indirectly assess valve status by measuring components attached to or otherwise communicating with the valve itself (e.g., actuators attached to or communicating with the valve itself). As described herein, such typical indirect valve monitoring operations may inaccurately assess valve “state” in the event, for example, that a physical actuation device becomes detached from the valve or is otherwise unable to drive valve movement. In such indirect valve state monitoring systems, physical and / or mechanical disengagement of the monitored element connected to the valve can result in the system not accurately reflecting the current position of the valve within the fuel line valve assembly.

[0070]

[0079] Additionally, within the aircraft fuel control valve assemblies of the present disclosure, multiple electromagnetic energy beam transmitter / receiver pairs may be incorporated to provide redundancy for continuous monitoring of the valve condition or “state” in the event that an element of one electromagnetic energy beam transmitter / receiver pair malfunctions.

[0071]

[0080] As described herein, the intensity of the light beam and the wavelength of the light are selected to ensure that the beam can traverse the distance from the transmitter to the receiver, can traverse a flow path simultaneously occupied by a fluid flow, and will not chemically or otherwise disturb the liquid flow, which may be a fuel flow. The distance traveled by the light beam between the transmitter and receiver is affected by the dimensions of the valve chamber and the overall dimensions of the aircraft fuel control valve assembly. In one embodiment, the valve chamber can have a width ranging from about 2 inches to about 4 inches. In another embodiment, the oblique light beam path from the transmitter to the receiver can have a distance ranging from about 4 inches to about 5 inches. In a further embodiment, the valve chamber can be about 2 inches in diameter. In that case, the valve chamber further includes a length measured from the inlet to the outlet of about 5 inches (e.g., a valve body length of about 5 inches).

[0072]

[0081] According to some present aspects, the electromagnetic energy transmitter and electromagnetic energy receiver, which may be integrated into the fuel control valve housing, may be removable from the housing, for example, to facilitate maintenance, replacement, inspection, etc. of the transmitter and / or receiver. In one embodiment, the transmitter and receiver are both configured to be built into the fuel control valve housing. In another embodiment, the transmitter and receiver may be fixedly mounted within the fuel control valve housing.

[0073]

[0082] 6, 7, and 8 are flowcharts outlining the present method for directly and independently monitoring aircraft fuel valve status within an aircraft fuel control valve assembly in real time and on demand. FIG. 6 outlines the present embodiment, directed to the present method 200 for directly monitoring aircraft fuel valve status within an aircraft fuel control valve assembly. In that case, method 200 includes disposing 202 a presently disclosed aircraft fuel control valve assembly of a type disclosed herein within an aircraft fuel line. In that case, the aircraft fuel control valve assembly includes an aircraft fuel control valve housing. Method 200 further includes generating 204 electromagnetic energy, which may be a primary electromagnetic energy beam. The electromagnetic energy may be a light beam (and may be a primary electromagnetic energy beam) at a primary electromagnetic energy transmitter. Method 200 further includes transmitting 206 a primary electromagnetic energy beam from a primary electromagnetic energy transmitter into the valve chamber to form a transmitted primary electromagnetic energy beam, receiving 208 the transmitted primary electromagnetic energy beam from the primary electromagnetic energy transmitter at a primary electromagnetic energy receiver, and directly monitoring 210 the aircraft fuel control valve status based on at least one of reception and non-reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver.

[0074]

[0083] 7 outlines this aspect directed to method 300, which includes elements of method 200, and further includes a primary electromagnetic energy receiver receiving 210 the transmitted primary electromagnetic energy beam, generating 302a a fuel valve state primary signal at the primary electromagnetic energy receiver, and interpreting 304 (e.g., via a processor configured to interpret the fuel control valve state primary signal transmitted from the receiver to the processor) to form an interpreted fuel control valve state primary signal, where the interpreted fuel control valve state primary signal corresponds to an aircraft fuel control valve state, where the aircraft fuel control valve state includes at least one of an aircraft fuel control valve open configuration and an aircraft fuel control valve closed configuration.

[0075]

[0084] 8 outlines this aspect directed to method 400, which includes elements of both methods 200 and 300, and further includes transmitting the interpreted fuel control valve status primary signal to a reader 402. This includes transmitting the interpreted fuel control valve status primary signal, interpreted by a processor, to at least one reader.

[0076]

[0085] In a further aspect, in the method 200, 300, 400, reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver verifies an aircraft fuel control valve open configuration.

[0077]

[0086] In a further aspect of the present method 200, 300, 400, non-reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver evidences an aircraft fuel control valve closed configuration.

[0078]

[0087] According to various present aspects, methods 200, 300, and 400 shown in FIGS. 6, 7, and 8, respectively, and disclosed herein, may employ the presently disclosed aircraft fuel control valve assembly and the presently disclosed aircraft fuel control valve status detection system disclosed herein and shown in one or more of FIGS. 1, 2, 3A, 3B, 4, 5A, and 5B, as described herein.

[0079]

[0088] As used herein, the term "substantially" means that a particular physical element, physical arrangement, and / or physical shape, orientation, etc. is almost completely or nearly realized. That is, for example, according to various present aspects, an angle value described as "substantially 180 degrees" is intended to include "approximately" 180 degrees. Similarly, a "substantially linear direction" is intended to include "approximately" linear or "linear" directions. Furthermore, an element "substantially" disposed within a valve chamber means that the element is almost entirely and / or almost completely contained within the valve chamber.

[0080]

[0089] The present aspects can, of course, be practiced in other ways than those specifically set forth herein without departing from the essential characteristics of the disclosure. The present aspects are to be considered in all respects as illustrative and not restrictive, and all changes that come within the meaning and range of equivalency of the claims are intended to be embraced therein.

Claims

1. An aircraft fuel control valve assembly (24), comprising: A fuel control valve housing (25) is provided, the fuel control valve housing comprising: a valve body (26); a valve inlet (28); a valve outlet (30); a valve chamber (32) defined by an area within the aircraft fuel control valve assembly and further defined between the valve inlet and the valve outlet; a movable valve (34) disposed substantially within the valve chamber (32); The aircraft fuel control valve assembly further comprises: a primary electromagnetic energy transmitter (42) integrated into the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter (42) configured to direct a primary electromagnetic energy beam (42 a) from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter (42) further comprising an electromagnetic energy source; and 1. An aircraft fuel control valve assembly comprising: a primary electromagnetic energy receiver (44) integrated within the aircraft fuel control valve assembly, the primary electromagnetic energy receiver (44) configured to receive the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and to generate a primary valve state signal (44a).

2. The aircraft fuel control valve assembly of claim 1 , wherein the movable valve is configured to include an operable range between an open valve configuration and a closed valve configuration.

3. 3. The aircraft fuel control valve assembly of claim 2, further comprising an actuator (36), said actuator in communication with said movable valve, said actuator configured to move said movable valve between said open valve configuration and said closed valve configuration.

4. a secondary electromagnetic energy transmitter (152) integrated into the aircraft fuel control valve assembly (124), the secondary electromagnetic energy transmitter (152) configured to direct a secondary electromagnetic energy beam (152 a) from the secondary electromagnetic energy transmitter into the valve chamber (132), the secondary electromagnetic energy transmitter (152) further comprising an electromagnetic energy source; and 3. The aircraft fuel control valve assembly of claim 2, further comprising: a secondary electromagnetic energy receiver (154) integrated within the aircraft fuel control valve assembly, the secondary electromagnetic energy receiver (154) configured to receive at least one of the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and the secondary electromagnetic energy beam from the secondary electromagnetic energy transmitter, and configured to generate a valve state secondary signal (154a).

5. 3. The aircraft fuel control valve assembly of claim 2, wherein the electromagnetic energy source is at least one of a laser and a light emitting diode, the electromagnetic energy source configured to generate the light beam to form a generated light beam, the generated light beam including a wavelength in a range from about 850 nm to about 1550 nm.

6. 5. The aircraft fuel control valve assembly of claim 4, wherein the primary electromagnetic energy transmitter is in communication with a primary electromagnetic energy source (41), the primary electromagnetic energy source including at least one of a laser and a light emitting diode, the primary electromagnetic energy source configured to generate the light beam to form a generated light beam, the generated light beam having a wavelength in a range from about 850 nm to about 1550 nm.

7. 6. The aircraft fuel control valve assembly of claim 5, wherein the generated light beam extends along a substantially straight line from the primary electromagnetic energy transmitter to the primary electromagnetic energy receiver, the substantially straight line extending from the primary electromagnetic energy transmitter through the valve chamber to the primary electromagnetic energy receiver when the movable valve is in the open valve configuration.

8. 6. The aircraft fuel control valve assembly of claim 5, wherein the generated light beam is configured to extend from the primary electromagnetic energy transmitter diagonally through the valve chamber to the primary electromagnetic energy receiver when the movable valve is in the open valve configuration.

9. An aircraft (10) comprising the aircraft fuel control valve assembly of claim 1.

10. An aircraft (10) comprising an aircraft fuel control valve assembly according to claim 4.

11. 1. An aircraft fuel line control valve assembly status detection system (40) for identifying an aircraft fuel control valve assembly status, comprising: An aircraft fuel control valve assembly (24) disposed in an aircraft fuel line (22), the aircraft fuel control valve assembly comprising: A fuel control valve housing (25) is provided, the fuel control valve housing comprising: a valve body (26); a valve inlet (28); a valve outlet (30); a valve chamber (32) defined by an area within the aircraft fuel control valve assembly and further defined between the valve inlet and the valve outlet; a movable valve (34) disposed substantially within the valve chamber (32); The aircraft fuel control valve assembly further comprises: a primary electromagnetic energy transmitter (42) integrated into the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter (42) configured to direct a primary electromagnetic energy beam (42 a) from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter (42) further comprising an electromagnetic energy source; and a primary electromagnetic energy receiver (44) integrated within the aircraft fuel control valve assembly, the primary electromagnetic energy receiver (44) configured to receive the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and configured to generate a primary valve state signal (44a); The aircraft fuel line control valve assembly status detection system further comprises: a processor (46) in communication with the primary electromagnetic energy receiver, the processor configured to receive the valve state primary signal, the processor further configured to interpret the valve state primary signal generated by the primary electromagnetic energy receiver to form an interpreted movable valve state primary signal, the interpreted movable valve state primary signal corresponding to the aircraft fuel control valve assembly state.

12. 12. The aircraft fuel line control valve assembly condition detection system of claim 11, wherein the electromagnetic energy source is at least one of a laser and a light emitting diode configured to generate a beam of light, the beam of light having a wavelength in a range from about 850 nm to about 1550 nm.

13. 12. The aircraft fuel line control valve assembly condition detection system of claim 11, further comprising a reader in communication with the processor.

14. 12. The aircraft fuel line control valve assembly condition detection system of claim 11, further comprising a valve actuator, the valve actuator in direct communication with the movable valve, the valve actuator configured to move the movable valve between an open valve configuration and a closed valve configuration.

15. a secondary electromagnetic energy transmitter (152) integrated into the aircraft fuel control valve assembly (124), the secondary electromagnetic energy transmitter (152) configured to direct a secondary electromagnetic energy beam (152 a) from the secondary electromagnetic energy transmitter into the fuel valve chamber (132) and across the fuel valve chamber, the secondary electromagnetic energy transmitter (152) further comprising a secondary electromagnetic energy source; and 14. The aircraft fuel line control valve assembly status detection system of claim 13, further comprising a secondary electromagnetic energy receiver (154) integrated within the aircraft fuel control valve assembly, the secondary electromagnetic energy receiver (154) configured to receive at least one of the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and the secondary electromagnetic energy beam from the secondary electromagnetic energy transmitter, and configured to generate a valve status secondary signal (154a).

16. 16. The aircraft fuel line control valve assembly condition detection system of claim 15, wherein the secondary electromagnetic energy source is configured to generate a light beam, the light beam having a wavelength in a range from about 850 nm to about 1550 nm.

17. 1. A method (200) for directly monitoring an aircraft fuel control valve assembly condition in an aircraft fuel control valve assembly, comprising: Disposing (202) the aircraft fuel control valve assembly in an aircraft fuel line, the aircraft fuel control valve assembly comprising: A fuel control valve housing (25) is provided, the fuel control valve housing comprising: a valve body (26); a valve inlet (28); a valve outlet (30); a valve chamber (32) defined by an area within the fuel control valve housing and further defined between the valve inlet and the valve outlet; a movable valve (34) disposed substantially within the valve chamber (32); The aircraft fuel control valve assembly further comprises: a primary electromagnetic energy transmitter (42) integrated into the aircraft fuel control valve assembly, the primary electromagnetic energy transmitter (42) configured to direct a primary electromagnetic energy beam (42 a) from the primary electromagnetic energy transmitter into the valve chamber and across the valve chamber, the primary electromagnetic energy transmitter (42) further comprising an electromagnetic energy source; and disposing the aircraft fuel control valve assembly (202) in an aircraft fuel line, the primary electromagnetic energy receiver (44) being integrated into the aircraft fuel control valve assembly, the primary electromagnetic energy receiver (44) being configured to receive the primary electromagnetic energy beam from the primary electromagnetic energy transmitter and to generate a primary valve state signal (44a); generating an electromagnetic energy beam at the primary electromagnetic energy transmitter (204); transmitting (206) a primary electromagnetic energy beam from the primary electromagnetic energy transmitter into the valve chamber to form a transmitted primary electromagnetic energy beam; receiving (208) the primary electromagnetic energy beam transmitted from the primary electromagnetic energy transmitter at the primary electromagnetic energy receiver; and directly monitoring (210) the aircraft fuel control valve assembly status based on at least one of reception and non-reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver.

18. Upon receiving the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver, the method further comprises: generating a fuel control valve state primary signal at the primary electromagnetic energy receiver (302); and 20. The method (300) of claim 17, comprising interpreting (304) the fuel control valve state primary signal to form an interpreted fuel control valve state primary signal, the interpreted fuel control valve state primary signal corresponding to the aircraft fuel control valve assembly state, the aircraft fuel control valve assembly state comprising at least one of an aircraft fuel control valve open configuration and an aircraft fuel control valve closed configuration.

19. 20. The method (400) of claim 18, further comprising directing (402) the interpreted fuel control valve status primary signal to a reader.

20. The method of claim 18 , wherein reception of the transmitted primary electromagnetic energy beam by the primary electromagnetic energy receiver verifies the aircraft fuel control valve open configuration.

Images