Optical data transmission over aircraft window

Abstract

The invention relates to optical data transmission through an aircraft window, the data transmission system comprising a sensor attached to an exterior of the aircraft and configured to generate sensor data. The outer shell is attached to an outer portion of the aircraft window. The outer housing includes a digital optical converter configured to convert the sensor data into an optical signal. The outer housing further includes a transmission optical device configured to transmit an optical signal through the aircraft window. The inner shell is attached to an inner portion of the aircraft window. The inner housing includes an optical receiver configured to receive an optical signal transmitted through an aircraft window. The inner housing further includes an optical-to-digital converter configured to convert the optical signal received from the optical receiver to second sensor data. The second sensor data represents the detected condition. A data acquisition system inside the aircraft is configured to receive the second sensor data.

Description

Technical Field

[0001] The present disclosure relates generally to transmitting sensor data, and more particularly to transmitting sensor data from outside an aircraft to inside an aircraft. Background Art

[0002] This background description is provided for the purpose of generally presenting the context of the present disclosure. Unless otherwise indicated herein, the materials described in this section are neither explicitly nor implicitly admitted to be prior art to the present disclosure or the appended claims.

[0003] Aircraft often use external sensors to detect environmental conditions. After sensing a specific environmental condition, the sensor can provide sensor data indicating the specific environmental data to internal components of the aircraft (e.g., an internal computing system). Typically, in order to provide sensor data to the internal components of the aircraft, wires are routed through openings in a pressure vessel of the aircraft. As a non-limiting example, in order to provide sensor data to the internal components of the aircraft, wires can be routed under aircraft doors, through specialized aircraft windows, etc. If there are a relatively large number of sensors providing sensor data to internal aircraft components, routing multiple wires through the pressure vessel of the aircraft may become increasingly difficult and inefficient. For example, a pressure vessel would require multiple openings to support multiple wires connected to the sensors and the internal components of the aircraft. Summary of the invention

[0004] The present application relates to transmitting data through an aircraft window during flight using an optical signal. According to the present application, a sensor is attached to the exterior of an aircraft during flight. As non-limiting examples, the sensor may correspond to an accelerometer, a microphone, a temperature sensor, a camera, etc. The sensor may be used to detect a condition. As non-limiting examples, if the sensor corresponds to an accelerometer, the sensor may detect acceleration of the aircraft, if the sensor corresponds to a microphone, the sensor may detect noise outside the aircraft, etc. In response to detecting a condition, the sensor may generate sensor data indicating the detected condition.

[0005] An outer shell is attached to the outer part of the window of the aircraft using an adhesive capable of flying. Inside the outer shell is a digital-to-optical converter and a transmission optical device. The sensor uses an external data cable to provide sensor data to the digital optical converter in the outer shell, and the digital optical converter converts the sensor data into an optical signal having a frequency and amplitude indicating the sensor data. In particular, the digital optical converter can determine the frequency and amplitude of the optical signal based on the sensor data. As a non-limiting example, if the sensor is a temperature sensor, if the sensor data indicates that a first temperature is detected, the digital optical converter can generate a first optical signal with a first frequency and a first amplitude, if the sensor data indicates that a second temperature is detected, the digital optical converter can generate a second optical signal with a second frequency and a second amplitude, and so on. Therefore, for each detected condition, the digital optical converter can generate an optical signal with different frequencies and amplitudes. The transmission optical device can transmit an optical signal through the window of the aircraft.

[0006] The inner housing is attached to the inner portion of the window via an adhesive. Inside the inner housing is an optical receiver and an optical digital converter. The optical receiver is physically aligned with the transmission optical device so that the optical receiver receives an optical signal transmitted from the transmission optical device through the window of the aircraft. According to one embodiment, the optical receiver and the transmission optical device are aligned in such a way as to maximize the signal-to-noise ratio level of the optical signal. The optical digital converter converts the optical signal received from the optical receiver into second sensor data representing the detected condition. In particular, the optical digital converter can generate second sensor data representing the detected condition based on the frequency and amplitude of the signal received by the optical receiver. Therefore, the digital optical converter and the optical digital converter can use similar conversion algorithms to convert the sensor data into the frequency and amplitude of the optical signal, and vice versa. A data acquisition system (e.g., a computing device or a data recording device) in the aircraft can receive the second sensor data via an internal data cable.

[0007] Thus, the present application enables sensor data to be transmitted from outside the aircraft to inside the aircraft while bypassing the use of openings in the aircraft's pressure vessels. For example, by transmitting an optical signal representing sensor data through a window of the aircraft, the use of physical wiring to transmit sensor data from outside the aircraft to inside the aircraft can be bypassed. In particular, the present application reduces the need to wire aircraft doors and aircraft windows to route cables from outside the aircraft to inside the aircraft. In addition, it should be understood that the optical signal transmitted through the aircraft's window will not interfere with the electrical and mechanical limitations of the aircraft. For example, the optical signal will not interfere with other communication frequencies used by the aircraft to communicate with other aircraft, controllers, and systems.

[0008] The present application may also achieve cost savings for flight testing and measurement because a reduced amount of material (e.g., wires) is required to transmit sensor data from the outside of the aircraft to the inside of the aircraft. Additionally, because outside-to-inside wiring may be bypassed, sensors may be placed in more locations (e.g., hard-to-reach locations) on the outside of the aircraft that are not near aircraft penetrations suitable for outside-to-inside wiring.

[0009] In one aspect, the present application discloses a data transmission system. The data transmission system includes a sensor attached to an external component of an aircraft. The sensor is configured to generate sensor data representing a detected condition. The data transmission system also includes an external housing attached to an external portion of an aircraft window of the aircraft. The external housing includes a digital optical converter configured to convert the sensor data into one or more optical signals. The external housing also includes a transmission optical device configured to transmit one or more optical signals through the aircraft window. The data transmission system also includes an internal housing attached to an internal portion of the aircraft window. The internal housing includes an optical receiver configured to receive one or more optical signals transmitted from the transmission optical device through the aircraft window. The internal housing also includes an optical digital converter configured to convert one or more optical signals received from the optical receiver into second sensor data. The second sensor data represents the detected condition. The data transmission system also includes a data acquisition system inside the aircraft. The data acquisition system is configured to receive the second sensor data.

[0010] In another aspect, the present application discloses a method. The method includes generating sensor data representing a detected condition by a sensor outside the aircraft. The method also includes converting the sensor data into one or more optical signals by a digital optical converter. The digital optical converter is in an external housing attached to an external portion of an aircraft window of the aircraft. The method also includes transmitting one or more optical signals through the aircraft window by a transmission optical device. The transmission optical device is in the external housing. The method also includes receiving one or more optical signals transmitted through the aircraft window by an optical receiver. The optical receiver is in an internal housing attached to an internal portion of the aircraft window. The method also includes converting one or more optical signals received from the optical receiver into second sensor data by an optical digital converter. The second sensor data represents the detected condition. The method also includes receiving the second sensor data by a data acquisition system.

[0011] In another aspect, the present application discloses an aircraft. The aircraft includes an aircraft exterior, an aircraft window, and a sensor attached to the aircraft exterior. The sensor is configured to generate sensor data representing a detected condition. The aircraft also includes an external housing attached to an external portion of the aircraft window. The external housing includes a digital optical converter configured to convert the sensor data into one or more optical signals. The external housing also includes a transmission optical device configured to transmit one or more optical signals through the aircraft window. The aircraft also includes an internal housing attached to an internal portion of the aircraft window. The internal housing includes an optical receiver configured to receive one or more optical signals transmitted from the transmission optical device through the aircraft window. The internal housing also includes an optical digital converter configured to convert one or more optical signals received from the optical receiver into second sensor data. The second sensor data represents the detected condition. The aircraft also includes a data acquisition system configured to receive the second sensor data.

[0012] The foregoing summary is illustrative only and is not intended to be limiting in any way. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] A more complete understanding of the embodiments of the present application may be obtained by referring to the detailed description and claims when considered in conjunction with the accompanying drawings, wherein like reference numerals may refer to similar elements throughout the drawings. The accompanying drawings are provided to facilitate understanding of the present disclosure and do not limit the breadth, scope, scale, or applicability of the present disclosure. The drawings are not necessarily drawn to scale.

[0014] Figure 1 A data transmission system operable to transmit an optical signal representative of sensor data through an aircraft window is shown in accordance with an exemplary embodiment;

[0015] Figure 2 A data transmission system operable to transmit an optical signal representative of sensor data through an aircraft window is shown in accordance with an exemplary embodiment;

[0016] Figure 3 illustrates an aircraft according to an exemplary embodiment; and

[0017] Figure 4 is a flow chart of an implementation example of a method according to an exemplary embodiment. DETAILED DESCRIPTION

[0018] The accompanying drawings and the following description illustrate specific exemplary embodiments. It should be understood that those skilled in the art will be able to design various arrangements that, although not explicitly described or shown herein, embody the principles described herein and are included within the scope of the claims preceding this specification. In addition, any examples described herein are intended to aid in understanding the principles of the present disclosure and should be interpreted as not limiting. Therefore, the present disclosure is not limited to the specific embodiments or examples described below, but is defined by the claims and their equivalents.

[0019] Particular implementations are described herein with reference to the accompanying drawings. In the specification, common features may be identified throughout the drawings by common reference numerals. In some of the drawings, multiple instances of a particular type of feature are used. Although the features are physically and / or logically distinct, the same reference numeral is used for each feature, and letters are added to the reference numerals to distinguish different instances. When features are referred to herein as a group or type (e.g., when no particular one is referred to), a reference numeral without a distinguishing letter is used. However, when a particular feature among multiple features of the same type is referred to herein, a reference numeral with a distinguishing letter is used. For example, with reference to Figure 1 , the alignment guides are shown and associated with reference numeral 194. When referring to a particular one of the alignment guides (e.g., alignment guide 194A), the distinguishing letter "A" is used. However, when referring to any one of the alignment guides or to the alignment guides as a group, reference numeral 194 may be used without a distinguishing letter.

[0020] As used herein, various terms are only used to describe the purpose of a specific implementation, and are not intended to be restrictive. For example, unless the context clearly indicates otherwise, the singular form "one", "an" and "said" are intended to also include plural forms. In addition, the terms "include", "comprise" and "contain" are used interchangeably. Additionally, the term "wherein" can be used interchangeably with the term "in...". As used herein, "exemplary" indicates examples, implementations and / or aspects, and should not be interpreted as restrictive or interpreted as indicating a preference or preferred implementation. As used herein, ordinal terms (e.g., "first", "second", "third", etc.) used to modify elements (e.g., structures, parts, operations, etc.) do not themselves indicate any priority or order of the element relative to another element, but only distinguish the element from another element with the same name (but for the use of ordinal terms). As used herein, the term "set" refers to the grouping of one or more elements, and the term "plurality" refers to multiple elements.

[0021] refer to Figure 1, shows a data transmission system 100 operable to transmit an optical signal representing sensor data through an aircraft window according to an exemplary embodiment. The data transmission system 100 includes a sensor 102, an outer housing 110, an inner housing 120, and a data acquisition system 130. The outer housing 110 is attached to an outer portion 152 of an aircraft window 150, while the inner housing 120 is attached to an inner portion 154 of the aircraft window 150. Thus, the outer housing 110 is attached to an outer portion 152 of an aircraft window 150, such as an aircraft window 150. Figure 3 , and the inner shell 120 is inside the aircraft 300.

[0022] The sensor 102 may be attached to an external component of the aircraft 300 or to the exterior 302 of the aircraft 300. The sensor 102 may be configured to detect one or more conditions and generate sensor data 104 indicating the detected conditions. As a non-limiting example, the sensor 102 may correspond to an accelerometer and may generate sensor data 104 indicating a detected acceleration of the aircraft 300. As another non-limiting example, the sensor 102 may correspond to a microphone and may generate sensor data 104 indicating noise detected near the aircraft 300. As another non-limiting example, the sensor 102 may correspond to a temperature sensor and may generate sensor data 104 indicating a detected temperature outside the aircraft 300. It should be understood that the above examples are for illustrative purposes only and should not be construed as limiting. In other embodiments, the sensor 102 may detect other conditions (e.g., radiation, velocity, pressure, etc.) and generate sensor data 104 indicating the detected conditions.

[0023] The sensor 102 may transmit the sensor data 104 to one or more components within the external housing 110 via the external data cable 190. For example, the external housing 110 includes a digital optical converter 112 and a transmission optical device 114. The external data cable 190 may be coupled to the sensor 102 and the digital optical converter 112 within the external housing 110. Thus, the sensor 102 may provide the sensor data 104 to the digital optical converter 112 via the external data cable 190.

[0024] The digital optical converter 112 may be configured to convert the sensor data 104 into one or more optical signals 118 that represent the detected condition indicated by the sensor data 104. For example, for each different detected condition indicated by the sensor data 104, the digital optical converter 112 may determine a frequency and / or amplitude of the one or more signals 118 that, when transmitted, represent the detected condition. As a non-limiting example, if the sensor 102 is a temperature sensor, if the sensor data 104 indicates that a first temperature is detected, the digital optical converter 112 may generate a first optical signal 118 having a first frequency and a first amplitude, if the sensor data 04 indicates that a second temperature is detected, the digital optical converter 112 may generate a second optical signal 118 having a second frequency and a second amplitude, and so on. Thus, the digital optical converter 112 may generate an optical signal 118 having a different frequency and amplitude for each detected condition.

[0025] Although different frequencies of the optical signals 118 may be used to transmit the detected conditions indicated by the sensor data 104, the frequency ranges of the optical signals 118 may fall within different light spectra. As non-limiting examples, one or more of the optical signals 118 may include visible light signals, ultraviolet signals, infrared signals, etc. Additionally, the optical signals 118 may be generated at a relatively high data rate. As a non-limiting example, the digital optical converter 112 may generate high-rate data (e.g., approximately 50,000 samples per second) and, as described below, transmit the high-rate data through the aircraft window 150.

[0026] The transmission optical device 114 can be configured to transmit one or more optical signals 118 through the aircraft window 150. According to one embodiment, the transmission optical device 114 includes one or more lasers configured to transmit the optical signal 118 through the aircraft window 150. According to another embodiment, the transmission optical device 114 includes one or more light emitting diodes (LEDs) configured to transmit the optical signal 118 through the aircraft window 150. It should be understood that the above examples of the transmission optical device 114 are for illustrative purposes only and should not be construed as limiting. In other embodiments, the transmission optical device 114 can correspond to any device that can transmit the optical signal 118.

[0027] The inner housing 120 includes an optical receiver 122 and an optical digitizer 124. The optical receiver 122 can be aligned to receive one or more optical signals 118 transmitted from the transmission optical device 114 through the aircraft window 150. In order to align the optical receiver 122 to receive the one or more optical signals 118, the position of the outer housing 110 on the outer portion 152 of the aircraft window 150 can be aligned with the position of the inner housing 120 on the inner portion 154 of the aircraft window 150. For example, the outer housing 110 can include a plurality of alignment guides 194A, 194B (e.g., alignment marks), and the inner housing 120 can include a plurality of alignment guides 94C, 194D. By aligning the alignment guides 194A, 194B of the outer housing 110 with the corresponding alignment guides 194C, 194D of the inner housing 120, the optical receiver 122 of the inner housing 120 is aligned with the transmission optical device 114 of the outer housing 110 to maximize (or substantially maximize) the signal-to-noise ratio level of the optical signal 118.

[0028] In response to aligning the outer housing 110 with the inner housing 120, the optical receiver 122 can be configured to receive one or more optical signals 118 transmitted from the transmission optical device 114 through the aircraft window 150. The optical receiver 122 can include a spectrometer, a photoelectric tube, a camera, etc. It should be understood that the above examples of optical receivers 122 are for illustrative purposes only and should not be construed as limiting. In other embodiments, the optical receiver 122 can be any photosensitive transducer capable of detecting (e.g., receiving) one or more optical signals 118.

[0029] The optical digitizer 124 may be configured to convert one or more optical signals 118 received from the optical receiver 122 into second sensor data 126. The second sensor data 126 may be similar to the sensor data 104 generated by the sensor 102. For example, the second sensor data 126 may represent a condition detected by the sensor 102. To generate the second sensor data 126, the optical digitizer 124 may identify a frequency and / or amplitude of the optical signal 118 and map the frequency and / or amplitude to the second sensor data 126. In some embodiments, the optical digitizer 124 converts the optical signal 118 into the second sensor data 126 using the same conversion algorithm as the digital optical converter 112. For example, the optical digitizer 124 may perform operations that are opposite to those performed by the digital optical converter 112.

[0030] Optical digitizer 124 may provide second sensor data 126 to data acquisition system 130 within aircraft 300. For example, optical digitizer 124 may use internal data cable 192 to provide second sensor data 126 to data acquisition system 130. Data acquisition system 130 may correspond to a computing device or a data recording device within aircraft 300.

[0031] therefore, Figure 1 The data transmission system 100 enables the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without having to run wiring through the pressure vessel of the aircraft 300. For example, by transmitting the optical signal 118 representing the sensor data 104 through the aircraft window 150, the use of physical wiring and cabling to transmit the sensor data 104 from outside the aircraft to inside the aircraft can be bypassed. In addition, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 will not interfere with the electrical and mechanical constraints of the aircraft 300. For example, the optical signal 118 will not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.

[0032] refer to Figure 2 , shows a data transmission system 200 operable to transmit an optical signal representing sensor data through an aircraft window according to an exemplary embodiment. The data transmission system 200 includes a sensor 102, an outer housing 110, an inner housing 120, and a data acquisition system 130. The outer housing 110 is attached to an outer portion of an aircraft window 150 using a flight-capable adhesive 210, while the inner housing 120 is attached to an inner portion of the aircraft window 150. Thus, the outer housing 110 is outside the aircraft 300, while the inner housing 120 is inside the aircraft 300.

[0033] About Figure 1 In a similar manner, the sensor 102 may be attached to an external component of the aircraft or to the exterior of the aircraft 300. The sensor 102 may be configured to detect one or more conditions and generate sensor data 104 indicative of the detected conditions. The sensor 102 may transmit the sensor data 104 to one or more components within the external housing 110 via the external data cable 190.

[0034] although Figure 2 Although not shown in the figure, the external housing 110 includes a digital optical converter 112 and a transmission optical device 114. The digital optical converter 112 and the transmission optical device 114 can be used in conjunction with Figure 1For example, digital optical converter 112 may be configured to convert sensor data 104 into one or more optical signals 118 , and transmission optical device 114 may be configured to transmit one or more optical signals 118 through aircraft window 150 .

[0035] although Figure 2 Although not shown in the figure, the internal housing 120 includes an optical receiver 122 and an optical digitizer 124. The optical receiver 122 and the optical digitizer 124 can be used in conjunction with Figure 1 For example, the optical receiver 122 may be configured to receive one or more optical signals 118 transmitted from the transmission optical device 114 through the aircraft window 150 , and the optical digitizer 124 may be configured to convert the one or more optical signals 118 received from the optical receiver 122 into the second sensor data 126 .

[0036] The position of the outer housing 110 on the outer portion 152 of the aircraft window 150 may be aligned with the position of the inner housing 120 on the inner portion 154 of the aircraft window 150. For example, the outer housing 110 may include a plurality of alignment guides 194A, 194B, 194E (e.g., alignment marks), and the inner housing 120 may include a plurality of alignment guides 194C, 194D, 194F. By aligning the alignment guides 194A, 194B, 194E of the outer housing 110 with the corresponding alignment guides 194C, 194D, 194F of the inner housing 120, the optical receiver 122 of the inner housing 120 is aligned with the transmission optical device 114 of the outer housing 110 to maximize (or substantially maximize) the signal-to-noise level of the optical signal 118.

[0037] Optical digitizer 124 may provide second sensor data 126 to data acquisition system 130 within aircraft 300. Thus, Figure 2 The data transmission system 200 enables the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without requiring wiring to penetrate the pressure vessel of the aircraft 300. For example, by transmitting the optical signal 118 representing the sensor data 104 through the aircraft window 150, the use of physical wiring and cabling to transmit the sensor data 104 from outside the aircraft to inside the aircraft can be bypassed. In addition, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 will not interfere with the electrical and mechanical constraints of the aircraft 300. For example, the optical signal 118 will not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.

[0038] refer to Figure 3, an aircraft 300 is shown in accordance with an exemplary embodiment.

[0039] exist Figure 3 , the sensor 102 is attached to an aircraft exterior 302 of the aircraft 300 near the aircraft window 150. The sensor 102 may be configured to detect one or more conditions and generate sensor data 104 indicative of the detected conditions. The sensor 102 may transmit the sensor data 104 to one or more components within the external housing 110 via the external data cable 190.

[0040] The outer shell 110 is attached to the outer portion of the aircraft window 150 using a flight-capable adhesive 210, while the inner shell 120 is attached to the inner portion of the aircraft window 150. Thus, the outer shell 110 is outside the aircraft 300, while the inner shell 120 is inside the aircraft 300.

[0041] although Figure 3 Although not shown in the figure, the external housing 110 includes a digital optical converter 112 and a transmission optical device 114. The digital optical converter 112 and the transmission optical device 114 can be used in conjunction with Figure 1 For example, digital optical converter 112 may be configured to convert sensor data 104 into one or more optical signals 118 , and transmission optical device 114 may be configured to transmit one or more optical signals 118 through aircraft window 150 .

[0042] although Figure 3 Although not shown in the figure, the internal housing 120 includes an optical receiver 122 and an optical digitizer 124. The optical receiver 122 and the optical digitizer 124 can be used in conjunction with Figure 1 For example, the optical receiver 122 may be configured to receive one or more optical signals 118 transmitted from the transmission optical device 114 through the aircraft window 150 , and the optical digitizer 124 may be configured to convert the one or more optical signals 118 received from the optical receiver 122 into the second sensor data 126 .

[0043] By transmitting the optical signal 118 representing the sensor data 104 through the aircraft window 150, the use of physical wiring and cabling to transmit the sensor data 104 from the aircraft exterior 302 to the aircraft interior may be bypassed. Furthermore, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 will not interfere with the electrical and mechanical limitations of the aircraft 300. For example, the optical signal 118 will not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.

[0044] Figure 4 4 shows a flow chart of a method 400 according to an exemplary embodiment. The method 400 may be performed by Figure 1 The data transmission system 100 and / or Figure 2 The data transmission system 200 is executed.

[0045] Method 400 includes generating sensor data representing a detected condition by a sensor external to the aircraft at block 402. For example, referring to Figure 1 , sensors 102 (external to aircraft 300 ) generate sensor data 104 representative of detected conditions.

[0046] The method 400 also includes converting the sensor data to one or more optical signals via a digital optical converter at block 404. The digital optical converter is within an external housing attached to an external portion of the aircraft window of the aircraft. For example, referring to Figure 1 , the digital optical converter 112 converts the sensor data 104 into one or more optical signals 118. The digital optical converter 112 is within an outer housing 110 attached to an outer portion 152 of an aircraft window 150 of the aircraft 300. According to one embodiment of the method 400, the one or more optical signals 118 include visible light signals, ultraviolet signals, or infrared signals.

[0047] The method 400 also includes transmitting one or more optical signals through the aircraft window by a transmission optical device at block 406. The transmission optical device is within the external housing. For example, referring to Figure 1 , the transmission optics 114 transmits one or more optical signals 118 through the aircraft window 150 . The transmission optics 114 is within the outer housing 110 .

[0048] The method 400 also includes receiving, at block 408, one or more optical signals transmitted through the aircraft window by an optical receiver. The optical receiver is within an inner housing attached to an inner portion of the aircraft window. For example, referring to Figure 1 The optical receiver 122 receives the one or more optical signals 118 transmitted through the aircraft window 150. The optical receiver 122 is within the inner housing 120 attached to the inner portion 154 of the aircraft window 150.

[0049] The method 400 also includes converting one or more optical signals received from the optical receiver into second sensor data by an optical digitizer at block 410. The second sensor data represents the detected condition. For example, referring to Figure 1The optical digitizer 124 converts the one or more optical signals 118 received from the optical receiver 122 into second sensor data 126. The second sensor data 126 represents the detected condition. According to one embodiment of the method 400, the second sensor data 126 is similar to the sensor data 104.

[0050] The method 400 also includes receiving second sensor data by the data acquisition system at block 412 . For example, the data acquisition system 130 receives the second sensor data 126 from the optical digitizer 124 .

[0051] According to one embodiment of the method 400, the transmission optics 114 include one or more lasers. According to one embodiment of the method 400, the transmission optics 114 include one or more LEDs. According to one embodiment of the method 400, the optical receiver 122 includes a spectrometer, a photoelectric tube, or a camera.

[0052] According to one embodiment of the method 400, the outer shell 110 is attached to the outer portion 152 of the aircraft window 150 via the flight-capable adhesive 210. According to one embodiment of the method 400, the position of the outer shell 110 on the outer portion 152 of the aircraft window 150 is aligned with the position of the inner shell 120 on the inner portion 154 of the aircraft window 150.

[0053] Figure 4 The method 400 enables the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without requiring wiring to be run through the pressure vessel of the aircraft 300. For example, by transmitting the optical signal 118 representing the sensor data 104 through the aircraft window 150, the use of physical wiring and cabling to transmit the sensor data 104 from outside the aircraft to inside the aircraft may be bypassed. Furthermore, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 will not interfere with the electrical and mechanical constraints of the aircraft 300. For example, the optical signal 118 will not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.

[0054] Although the systems are described herein with specific reference to space systems or aerospace vehicles, in other embodiments the systems may be vehicles other than spacecraft without departing from the essence of the present disclosure.

[0055] Additionally, examples of an element being "coupled" to another element in this specification may include direct and indirect coupling. Direct coupling may be defined as an element being coupled to another element and making some contact with the other element. Indirect coupling may be defined as a coupling between two elements that are not in direct contact with each other but have one or more additional elements between the coupled elements. Furthermore, as used herein, fixing an element to another element may include direct fixing and indirect fixing. Additionally, as used herein, "adjacent" does not necessarily mean contact. For example, an element may be adjacent to another element without being in contact with the element.

[0056] As used herein, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specified function is actually capable of performing the specified function without any changes, rather than merely having the potential to perform the specified function after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specified function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing the specified function. As used herein, "configured to" means existing features of a system, device, structure, article, element, component, or hardware that enable the system, device, structure, article, element, component, or hardware to perform the specified function without further modification. For the purposes of this disclosure, a system, device, structure, article, element, component, or hardware that is described as "configured to" perform a particular function may additionally or alternatively be described as "suitable for" and / or "operable to" perform that function.

[0057] The flowchart diagrams included herein are generally described as logical flow charts. Therefore, the depicted order and the marked steps indicate an embodiment of the method presented. Other steps and methods that are equivalent to one or more steps or parts thereof of the method shown in terms of function, logic or effect can be envisioned. Additionally, the format and symbols adopted are provided to explain the logical steps of the method, and are understood to not limit the scope of the method. Although various arrow types and line types can be adopted in the flowchart diagram, they are understood to not limit the scope of the corresponding method. In fact, some arrows or other connectors can be used to indicate only the logical flow of the method. For example, an arrow can indicate a waiting or monitoring period of an unspecified duration between the enumerated steps of the depicted method. Additionally, the order in which a particular method occurs may or may not strictly comply with the order of the corresponding steps shown.

[0058] Unless otherwise indicated, the terms "first", "second", etc. are used herein merely as labels and are not intended to impose order, position, or hierarchy requirements on the items to which these terms refer. Furthermore, reference to an item, such as a "second", does not require or preclude the existence of an item, such as a "first" or lower numbered item and / or an item, such as a "third" or higher numbered item.

[0059] Although the systems and methods of operation have been described with reference to certain examples, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the scope of the claims. Therefore, it is intended that the methods and systems are not limited to the particular examples disclosed, but that the disclosed methods and systems include all embodiments falling within the scope of the appended claims.

Claims

1. A data transmission system (100), comprising: a sensor (102) attached to an external component of the aircraft (300), the sensor (102) being configured to generate sensor data (104) representative of a detected condition; an outer shell (110) attached to an outer portion (152) of an aircraft window (150) of the aircraft (300), the outer shell (110) comprising: a digital optical converter (112) configured to convert the sensor data (104) into one or more optical signals (118); and a transmission optical device (114) configured to transmit the one or more optical signals (118) through the aircraft window (118); An inner shell (120) attached to an inner portion (154) of the aircraft window (150), the inner shell (120) comprising: an optical receiver (122) configured to receive the one or more optical signals (118) transmitted from the transmission optical device (114) through the aircraft window (150); and an optical digitizer (124) configured to convert the one or more optical signals (118) received from the optical receiver (122) into second sensor data (126), wherein the second sensor data (126) is representative of the detected condition; and A data acquisition system (130) inside the aircraft (300) is configured to receive the second sensor data (126).

2. The data transmission system (100) according to claim 1, wherein: The second sensor data (126) is similar to the sensor data (104).

3. The data transmission system (100) according to claim 1, wherein: The transmission optics (114) include one or more lasers.

4. The data transmission system (100) according to claim 1, wherein: The transmission optics (114) include one or more light emitting diodes (LEDs).

5. The data transmission system (100) according to claim 1, wherein: The optical receiver (122) includes a spectrometer, a photoelectric tube or a camera.

6. The data transmission system (100) according to claim 1, wherein: The outer shell (110) is attached to the outer portion (152) of the aircraft window (150) via a flight-capable adhesive (210).

7. The data transmission system (100) according to claim 1, wherein: The one or more optical signals (118) include a visible light signal, an ultraviolet light signal, or an infrared light signal.

8. The data transmission system (100) according to claim 1, wherein: The position of the outer shell (110) on the outer portion (152) of the aircraft window (150) is aligned with the position of the inner shell (120) on the inner portion (154) of the aircraft window (150).

9. A method (400), comprising: generating (402) sensor data (104) representing a detected condition by a sensor (102) external to the aircraft (300); converting (404) the sensor data (104) into one or more optical signals (118) via a digital optical converter (112), wherein the digital optical converter (112) is within an external housing (110) attached to an external portion (152) of an aircraft window (150) of the aircraft (300); transmitting (406) the one or more optical signals (118) through the aircraft window (150) via a transmission optical device (114), wherein the transmission optical device (114) is within the outer housing (110); receiving (408) the one or more optical signals (118) transmitted through the aircraft window (150) via an optical receiver (122), wherein the optical receiver (122) is within an interior housing (120) attached to an interior portion (154) of the aircraft window (150); converting (410) the one or more optical signals (118) received from the optical receiver (122) into second sensor data (126) via an optical digitizer (124), wherein the second sensor data (126) represents the detected condition; and The second sensor data (126) is received (412) by a data acquisition system (130).

10. The method (400) of claim 9, wherein: The second sensor data (126) is similar to the sensor data (104).

11. The method (400) of claim 9, wherein: The transmission optics (114) include one or more lasers.

12. The method (400) of claim 9, wherein: The transmission optics (114) include one or more light emitting diodes (LEDs).

13. The method (400) of claim 9, wherein: The optical receiver (122) includes a spectrometer, a photoelectric tube or a camera.

14. The method (400) of claim 9, wherein: The outer shell (110) is attached to the outer portion (152) of the aircraft window (150) via a flight-capable adhesive (210).

15. The method (400) of claim 9, wherein: The one or more optical signals (118) include a visible light signal, an ultraviolet light signal, or an infrared light signal.

16. The method (400) of claim 9, wherein: The position of the outer shell (110) on the outer portion (152) of the aircraft window (150) is aligned with the position of the inner shell (120) on the inner portion (154) of the aircraft window (150).

17. An aircraft (300), comprising: Aircraft exterior (302); Aircraft windows (150); a sensor (102) attached to the aircraft exterior (302), the sensor (102) being configured to generate sensor data (104) representative of a detected condition; An outer shell (110) attached to an outer portion (152) of the aircraft window (150), the outer shell (110) comprising: a digital optical converter (112) configured to convert the sensor data (102) into one or more optical signals (118); and a transmission optical device (114) configured to transmit the one or more optical signals (118) through the aircraft window (150); An inner shell (120) attached to an inner portion (154) of the aircraft window (150), the inner shell (120) comprising: an optical receiver (122) configured to receive the one or more optical signals (118) transmitted from the transmission optical device (114) through the aircraft window (150); and an optical digitizer (124) configured to convert the one or more optical signals (118) received from the optical receiver (122) into second sensor data (126), wherein the second sensor data (126) is representative of the detected condition; and A data acquisition system (130) is configured to receive the second sensor data (126).

18. The aircraft (300) according to claim 17, wherein: The position of the outer shell (110) on the outer portion (152) of the aircraft window (150) is aligned with the position of the inner shell (120) on the inner portion (154) of the aircraft window (150).

19. The aircraft (300) of claim 17, wherein: The one or more optical signals (118) include a visible light signal, an ultraviolet light signal, or an infrared light signal.

20. The aircraft (300) of claim 17, wherein: The transmission optics (114) include one or more light emitting diodes (LEDs).

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