Optical data transmission through aircraft window
Patent Information
- Application Number
- JP2024135336
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-08-27
- Filing Date
- 2024-08-14
- Publication Date
- 2025-03-11
Smart Images
Figure 2025032063000001_ABST
Abstract
Description
[Technical field]
[0001]
[0001] The present disclosure relates generally to transmitting sensor data, and more specifically, to transmitting sensor data from outside an aircraft to inside the aircraft. [Background technology]
[0002]
[0002] This background description is provided generally for the purpose of providing a context for the present disclosure. Unless otherwise indicated herein, the material described in this section is not admitted, either expressly or impliedly, as prior art to this disclosure or the appended claims.
[0003]
[0003] Aircraft often use external sensors to detect environmental conditions. After sensing a certain environmental condition, the sensor may provide sensor data indicative of certain environmental data to an internal component (e.g., an internal computing system) of the aircraft. Typically, wires are threaded through openings in the aircraft's pressure vessel to provide the sensor data to the internal component of the aircraft. As a non-limiting example, wires may be threaded under the aircraft's door, through a special aircraft window, or the like to provide the sensor data to the internal component of the aircraft. When there are a relatively large number of sensors providing sensor data to the internal aircraft components, threading multiple wires through the aircraft's pressure vessel may become increasingly difficult and inefficient. For example, the pressure vessel may require multiple openings to support the sensors and multiple wires coupled to the internal component of the aircraft. Summary of the Invention
[0004]
[0004] The present application is directed to using optical signals to transmit data through windows of an aircraft during flight. According to the present application, sensors are mounted on the exterior of the aircraft during flight. By way of non-limiting example, the sensors may correspond to accelerometers, microphones, temperature sensors, cameras, etc. The sensors may be used to detect a condition. By way of non-limiting example, 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 the condition, the sensor may generate sensor data indicative of the detected condition.
[0005]
[0005] An external housing is attached to an exterior portion of the aircraft window using a flight-resistant adhesive. Within the external housing are a digital optical converter and a transmitting optics. The sensor uses an external data cable to provide sensor data to the digital optical converter within the external housing, which converts the sensor data into an optical signal having a frequency and amplitude indicative of the sensor data. Specifically, the digital optical converter may determine a frequency and amplitude of the optical signal based on the sensor data. As a non-limiting example, if the sensor is a temperature sensor, then if the sensor data indicates that a first temperature is detected, the digital optical converter may generate a first optical signal having a first frequency and a first amplitude, if the sensor data indicates that a second temperature is detected, the digital optical converter may generate a second optical signal having a second frequency and a second amplitude, etc. In this manner, the digital optical converter may generate an optical signal having a separate frequency and amplitude for each detected condition. The transmitting optics may transmit the optical signal through the aircraft window.
[0006]
[0006] An inner housing is attached to the inner portion of the window via adhesive. Within the inner housing is an optical receiver and an optical to digital converter. The optical receiver is physically aligned with the transmitting optical device such that the optical receiver receives the optical signal transmitted from the transmitting optical device through the window of the aircraft. According to one embodiment, the optical receiver and the transmitting optical device are aligned to maximize the signal / noise level of the optical signal. The optical to digital converter converts the optical signal received from the optical receiver into second sensor data representative of the detected condition. In particular, the optical to digital converter may generate the second sensor data representative of the detected condition based on the frequency and amplitude of the signal received by the optical receiver. Thus, the digital to optical converter and the optical to digital converter may use similar conversion algorithms to convert the sensor data to frequency and amplitude for the optical signal and vice versa. A data acquisition system (e.g., a computing device or a data recorder) within the aircraft may receive the second sensor data via the inner data cable.
[0007]
[0007] Thus, the present application avoids the use of openings in the aircraft pressure vessel while allowing sensor data to be transmitted from outside the aircraft to inside the aircraft. For example, by transmitting optical signals representing the sensor data through the aircraft windows, the use of physical wiring to transmit sensor data from outside the aircraft to inside the aircraft may be avoided. In particular, the present application reduces the need for aircraft doors and aircraft windows to be wired to pass cables from outside the aircraft to inside the aircraft. Furthermore, it should be appreciated that the optical signals transmitted through the aircraft windows are not interfered with by electronic and mechanical limitations of the aircraft. For example, the optical signals do not interfere with other communication frequencies used by the aircraft to communicate with other aircraft, controllers, and systems.
[0008]
[0008] The present application also provides cost savings for flight testing and flight measurements because a reduced amount of material (e.g., wires) is required to communicate sensor data from outside the aircraft to inside the aircraft. Furthermore, because wiring from the outside to the inside can be avoided, sensors can be placed in more locations (e.g., hard-to-reach locations) outside the aircraft that are not in close proximity to penetrations suitable for wiring from the outside to the inside.
[0009] In one aspect, the present application discloses a data transmission system. The data transmission system includes a sensor mounted on an exterior component of the aircraft. The sensor is configured to generate sensor data representative of the detected condition. The data transmission system also includes an exterior housing mounted on an exterior portion of the aircraft window of the aircraft. The exterior housing includes a digital-to-optical converter configured to convert the sensor data into one or more optical signals. The exterior housing also includes a transmitting optical device configured to transmit the one or more optical signals through the aircraft window. The data transmission system also includes an interior housing mounted on an interior portion of the aircraft window. The interior housing includes an optical receiver configured to receive the one or more optical signals transmitted from the transmitting optical device through the aircraft window. The interior housing also includes an optical-to-digital converter configured to convert the one or more optical signals received from the optical receiver into second sensor data. The second sensor data is representative of the detected condition. The data transmission system also includes a data acquisition system located 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 representative of the detected condition by an external sensor of the aircraft. The method also includes converting the sensor data to one or more optical signals by a digital-to-optical converter. The digital-to-optical converter is in an exterior housing attached to an exterior portion of the aircraft window of the aircraft. The method also includes transmitting the one or more optical signals through the aircraft window by a transmitting optical device. The transmitting optical device is in the exterior housing. The method also includes receiving the one or more optical signals transmitted through the aircraft window by an optical receiver. The optical receiver is in an interior housing attached to an interior portion of the aircraft window. The method further includes converting the one or more optical signals received from the optical receiver to second sensor data by an optical-to-digital converter. The second sensor data representative of 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 exterior of the aircraft, a window of the aircraft, and a sensor mounted on the exterior of the aircraft. The sensor is configured to generate sensor data representative of the detected condition. The aircraft also includes an exterior housing mounted on an exterior portion of the aircraft window. The exterior housing includes a digital-to-optical converter configured to convert the sensor data to one or more optical signals. The exterior housing also includes a transmit optical device configured to transmit the one or more optical signals through the aircraft window. The aircraft also includes an interior housing mounted on an interior portion of the aircraft window. The interior housing includes an optical receiver configured to receive the one or more optical signals transmitted from the transmit optical device through the aircraft window. The interior housing also includes an optical-to-digital converter configured to convert the one or more optical signals received from the optical receiver to second sensor data. The second sensor data is representative of the detected condition. The aircraft also includes a data acquisition system configured to receive the second sensor data.
[0012]
[0012] The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the exemplary aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description.
[0013] A more complete understanding of the embodiments of the present application may be obtained by reference to the Detailed Description and the Claims in conjunction with the following drawings, in which like reference numbers may refer to similar elements throughout the drawings. The numbers are provided to facilitate understanding of the disclosure and are not intended to limit the breadth, scope, scale, or applicability of the disclosure. The drawings are not necessarily drawn to scale. [Brief description of the drawings]
[0014] [Figure 1] According to an exemplary embodiment, a data transmission system is operable to transmit optical signals representative of sensor data through a window of an aircraft. [Diagram 2]
[0015] 1 is a data transmission system operable to transmit optical signals representative of sensor data through a window of an aircraft according to an illustrative embodiment. [Diagram 3]
[0016] 1 is an aircraft in accordance with an illustrative embodiment. [Figure 4]
[0017] 1 is a flowchart of an example implementation of a method according to an exemplary embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0015]
[0018] The drawings and the following description show specific and exemplary embodiments. It is understood that those skilled in the art can devise various configurations that embody the principles described herein and are included in the scope of the claims following the description of this specification, even if not explicitly described or shown in this specification. Furthermore, any examples described herein should be understood to be intended to assist in understanding the principles of the disclosure, and are not intended to be limiting. As a result, the disclosure is not limited to the specific embodiments or examples described below, but is limited by the claims and their equivalents.
[0016]
[0019] Certain embodiments are described herein with reference to the drawings. In the description, common reference numbers may refer to common features throughout the drawings. In some drawings, multiple instances of a particular type of feature are used. Although these features are physically and / or logically different, the same reference number is used for each, and the different instances are distinguished by adding a letter to the reference number. When features as a group or type are referred to herein (e.g., when no particular one of the features is referred to), the reference number is used without the distinguishing letter. However, when one particular feature of multiple features of the same type is referred to herein, the reference number is used with an identifying letter. For example, referring to FIG. 1, an alignment guide is shown and associated with reference number 194. When referring to a particular one of the alignment guides (e.g., alignment guide 194A), the identifying letter "A" is used. However, when referring to any one of the alignment guides or the alignment guides as a group, the reference number 194 may be used without the identifying letter.
[0017]
[0020] Various terms are used herein only to describe particular embodiments and are not intended to be limiting. For example, the singular forms "a / an" and "the" are intended to include the plural (unless the context clearly indicates otherwise). Additionally, the terms "comprise, comprises, and comprising" are used interchangeably with "include, includes, including." Additionally, the term "wherein" is used interchangeably with the term "where." As used herein, "exemplary" refers to examples, embodiments, and / or aspects and should not be construed as limiting or indicating a preference or preferred embodiment. As used herein, ordinal terms (e.g., "first," "second," "third," etc.) modifying elements such as structures, components, acts, etc. do not themselves indicate a preference or order of one element over another element, but merely distinguish between other elements having the same name (apart from their use as ordinal terms). As used herein, the term "set" refers to a grouping of one or more elements, and the term "plurality" refers to a plurality of elements.
[0018]
[0021] 1, a data transmission system 100 operable to transmit optical signals representing sensor data through an aircraft window is shown in accordance with an exemplary embodiment. Data transmission system 100 includes a sensor 102, an exterior housing 110, an interior housing 120, and a data acquisition system 130. Exterior housing 110 is attached to an exterior portion 152 of an aircraft window 150, and interior housing 120 is attached to an interior portion 154 of the aircraft window 150. Thus, exterior housing 110 is outside an aircraft (e.g., aircraft 300 in FIG. 3 ) and interior housing 120 is inside aircraft 300.
[0019]
[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 indicative of the detected condition. As a non-limiting example, the sensor 102 may correspond to an accelerometer and generate sensor data 104 indicative of a detected acceleration of the aircraft 300. As another non-limiting example, the sensor 102 may correspond to a microphone and generate sensor data 104 indicative of a detected noise proximate to the aircraft 300. As another non-limiting example, the sensor 102 may correspond to a temperature sensor and generate sensor data 104 indicative of a detected temperature on the exterior of 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., brightness, speed, pressure, etc.) and generate sensor data 104 indicative of the detected condition.
[0020]
[0023] The sensor 102 may transmit the sensor data 104 to one or more components within the external housing 110 via an external data cable 190. For example, the external housing 110 includes a digital to optical converter 112 and a transmitting optics 114. The external data cable 190 may be coupled to the sensor 102 and the digital to optical converter 112 within the external housing 110. Thus, the sensor 102 may provide the sensor data 104 to the digital to optical converter 112 via the external data cable 190.
[0021]
[0024] The digital optical converter 112 may be configured to convert the sensor data 104 into one or more optical signals 118 representative of the detected condition indicated by the sensor data 104. For example, for each distinct detected condition indicated by the sensor data 104, the digital optical converter 112 may determine, upon communication, a frequency and / or amplitude for the one or more signals 118 representative of 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 104 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, etc. Thus, the digital optical converter 112 may generate an optical signal 118 having a distinct frequency and amplitude for each detected condition.
[0022]
[0025] Although distinct frequencies of the optical signals 118 may be used to communicate the detected conditions indicated by the sensor data 104, the frequency ranges of the optical signals 118 may fall within different optical spectra. By way of non-limiting example, the one or more 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. By way of non-limiting example, the digital-to-optical converter 112 may generate high-speed data (e.g., approximately 50,000 samples per second) and pass the high-speed data through the aircraft window 150, as described below.
[0023]
[0026] The transmitting optical device 114 may be configured to transmit one or more optical signals 118 through the aircraft window 150. According to one embodiment, the transmitting 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 transmitting 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 transmitting optical device 114 are for illustrative purposes only and should not be construed as limiting. In other embodiments, the transmitting optical device 114 may correspond to any device capable of emitting the optical signal 118.
[0024]
[0027] The inner housing 120 includes an optical receiver 122 and an optical to digital converter 124. The optical receiver 122 may be aligned to receive one or more optical signals 118 transmitted from the transmitting optics 114 through the aircraft window 150. To align the optical receiver 122 to receive the one or more optical signals 118, a position of the outer housing 110 on an outer portion 152 of the aircraft window 150 may be aligned with a position of the inner housing 120 on an inner portion 154 of the aircraft window 150. For example, the outer housing 110 may include a number of alignment guides 194A, 194B (e.g., alignment markers) and the inner housing 120 may include a number of alignment guides 194C, 194D. By aligning alignment guides 194A, 194B on the outer housing 110 with corresponding alignment guides 194C, 194D on the inner housing 120, the optical receiver 122 on the inner housing 120 is aligned with the transmitting optics 114 on the outer housing 110 to maximize (or substantially maximize) the signal / noise level of the optical signal 118.
[0025]
[0028] In response to aligning the outer housing 110 with the inner housing 120, the optical receiver 122 may be configured to receive one or more optical signals 118 transmitted from the transmitting optics 114 through the aircraft window 150. The optical receiver 122 may include a spectrometer, a photocell, a camera, etc. It should be understood that the above examples of the optical receiver 122 are for illustrative purposes only and should not be construed as limiting. In other embodiments, the optical receiver 122 may be any photosensitive transducer capable of detecting (e.g., receiving) the one or more optical signals 118.
[0026]
[0029] The optical to digital converter 124 may be configured to convert the 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 to digital converter 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 to digital converter 124 uses the same conversion algorithm as the digital-to-optical converter 112 to convert the optical signal 118 into the second sensor data 126. For example, the optical to digital converter 124 may perform an inverse operation with respect to the operation performed by the digital-to-optical converter 112.
[0027]
[0030] The optical to digital converter 124 may provide the second sensor data 126 to a data acquisition system 130 that is internal to the aircraft 300. For example, the optical to digital converter 124 may use an inner data cable 192 to provide the second sensor data 126 to the data acquisition system 130. The data acquisition system 130 may correspond to a computing device or a data recording device within the aircraft 300.
[0028]
[0031] 1 allows the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without penetrating the pressure vessel of the aircraft 300 for wiring. 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 avoided. Furthermore, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 is not interfered with by electronic and mechanical limitations of the aircraft 300. For example, the optical signal 118 does not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.
[0029]
[0032] 2, a data transmission system 200 operable to transmit optical signals representing sensor data through an aircraft window is shown in accordance with an exemplary embodiment. Data transmission system 200 includes sensor 102, exterior housing 110, interior housing 120, and data acquisition system 130. Exterior housing 110 is attached to an exterior portion of aircraft window 150 using flight-resistant adhesive 210, and interior housing 120 is attached to an interior portion of aircraft window 150. Thus, exterior housing 110 is outside aircraft 300 and interior housing 120 is inside aircraft 300.
[0030]
[0033] 1 , the sensors 102 may be mounted on an external component of the aircraft or on the outside of the aircraft 300. The sensors 102 may be configured to detect one or more conditions and generate sensor data 104 indicative of the detected conditions. The sensors 102 may transmit the sensor data 104 via an external data cable 190 to one or more components within the external housing 110.
[0031]
[0034] Although not shown in Figure 2, the exterior housing 110 includes a digital-to-optical converter 112 and a transmit optics 114. The digital-to-optical converter 112 and the transmit optics 114 may operate in a substantially similar manner as described with respect to Figure 1. For example, the digital-to-optical converter 112 may be configured to convert the sensor data 104 into one or more optical signals 118, and the transmit optics 114 may be configured to transmit the one or more optical signals 118 through a window 150 of the aircraft.
[0032]
[0035] Although not shown in Figure 2, inner housing 120 includes optical receiver 122 and optical-to-digital converter 124. Optical receiver 122 and optical-to-digital converter 124 may operate in a substantially similar manner as described with respect to Figure 1. For example, optical receiver 122 may be configured to receive one or more optical signals 118 transmitted from transmitting optics 114 through a window 150 of the aircraft, and optical-to-digital converter 124 may be configured to convert one or more optical signals 118 received from optical receiver 122 into second sensor data 126.
[0033]
[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 number of alignment guides 194A, 194B, 194E (e.g., alignment markers) and the inner housing 120 may include a number 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 transmitting optics 114 of the outer housing 110 to maximize (or substantially maximize) the signal / noise level of the optical signal 118.
[0034]
[0037] The optical to digital converter 124 may provide the second sensor data 126 to a data acquisition system 130 inside the aircraft 300. Thus, the data transmission system 200 of FIG. 2 allows the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without penetrating the pressure vessel of the aircraft 300 for wiring. 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 avoided. Furthermore, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 is not interfered with by electronic and mechanical limitations of the aircraft 300. For example, the optical signal 118 does not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.
[0035]
[0038] With reference to FIG. 3, an aircraft 300 is illustrated in accordance with an illustrative embodiment.
[0036]
[0039] 3 , the sensor 102 is mounted on the aircraft exterior 302 of the aircraft 300 proximate to an 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 via an exterior data cable 190 to one or more components within the exterior housing 110.
[0037]
[0040] The outer housing 110 is attached to an outer portion of the aircraft window 150 using a flight-resistant adhesive 210, and 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 and the inner housing 120 is inside the aircraft 300.
[0038]
[0041] Although not shown in Figure 3, the outer housing 110 includes a digital-to-optical converter 112 and a transmit optics 114. The digital-to-optical converter 112 and the transmit optics 114 may operate in a substantially similar manner as described with respect to Figure 1. For example, the digital-to-optical converter 112 may be configured to convert the sensor data 104 into one or more optical signals 118, and the transmit optics 114 may be configured to transmit the one or more optical signals 118 through a window 150 of the aircraft.
[0039]
[0042] Although not shown in Figure 3, inner housing 120 includes optical receiver 122 and optical-to-digital converter 124. Optical receiver 122 and optical-to-digital converter 124 may operate in a manner substantially similar to that described with respect to Figure 1. For example, optical receiver 122 may be configured to receive one or more optical signals 118 transmitted from transmitting optics 114 through a window 150 of the aircraft, and optical-to-digital converter 124 may be configured to convert one or more optical signals 118 received from optical receiver 122 into second sensor data 126.
[0040]
[0043] By transmitting optical signals 118 representing sensor data 104 through aircraft windows 150, the use of physical wiring and cabling to transmit sensor data 104 from the exterior of the aircraft 302 to the interior of the aircraft may be avoided. Additionally, it should be appreciated that optical signals 118 transmitted through aircraft windows 150 are not interfered with by electronic and mechanical limitations of the aircraft 300. For example, optical signals 118 do not interfere with other communication frequencies used by aircraft 300 to communicate with other aircraft, controllers, and systems.
[0041]
[0044] 4 shows a flowchart of a method 400 according to an example embodiment. The method 400 may be performed by the data transmission system 100 of FIG. 1 and / or the data transmission system 200 of FIG.
[0042]
[0045] The method 400 includes generating sensor data representative of the detected conditions by a sensor external to the aircraft, at block 402. For example, with reference to Figure 1, a sensor 102 (external to the aircraft 300) generates sensor data 104 representative of the detected conditions.
[0043]
[0046] Method 400 also includes converting the sensor data 104 to one or more optical signals by a digital optical converter at block 404. The digital optical converter is in an exterior housing attached to an exterior portion of the aircraft window of the aircraft. For example, referring to FIG. 1 , digital optical converter 112 converts sensor data 104 to one or more optical signals 118. Digital optical converter 112 is in an exterior housing 110 attached to an exterior portion 152 of the aircraft window 150 of aircraft 300. According to one embodiment of method 400, one or more optical signals 118 include visible light signals, ultraviolet signals, or infrared signals.
[0044]
[0047] The method 400 also includes transmitting, at block 406, one or more optical signals through a window of the aircraft with the transmit optical device. The transmit optical device is within the exterior housing. For example, referring to FIG. 1 , the transmit optical device 114 transmits one or more optical signals 118 through a window 150 of the aircraft. The transmit optical device 114 is within the exterior housing 110.
[0045]
[0048] The method 400 also includes receiving, at block 408, by an optical receiver, the one or more optical signals transmitted through the aircraft window. The optical receiver is within an interior housing mounted to an interior portion of the aircraft window. For example, with reference to FIG. 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 an interior housing 120 mounted to an interior portion 154 of the aircraft window 150.
[0046]
[0049] The method 400 further includes converting, by an optical to digital converter, the one or more optical signals received from the optical receiver to second sensor data at block 410. The second sensor data is representative of the detected condition. For example, with reference to FIG. 1, the optical to digital converter 124 converts the one or more optical signals 118 received from the optical receiver 122 to second sensor data 126. The second sensor data 126 is representative of the detected condition. According to one embodiment of the method 400, the second sensor data 126 is similar to the sensor data 104.
[0047]
[0050] The method 400 also includes receiving, by the data acquisition system, the second sensor data, at block 412. For example, the data acquisition system 130 receives the second sensor data 126 from the optical-to-digital converter 124.
[0048]
[0051] According to one embodiment of the method 400, the transmitting optics 114 includes one or more lasers. According to one embodiment of the method 400, the transmitting optics 114 includes one or more LEDs. According to one embodiment of the method 400, the optical receiver 122 includes a spectrometer, a photocell, or a camera.
[0049]
[0052] According to one embodiment of method 400, the outer housing 110 is attached to the outer portion 152 of the aircraft window 150 via a flight-resistant adhesive 210. According to one embodiment of method 400, the location of the outer housing 110 on the outer portion 152 of the aircraft window 150 is aligned with the location of the inner housing 120 on the inner portion 154 of the aircraft window 150.
[0050]
[0053] 4 allows the sensor data 104 to be transmitted from outside the aircraft to inside the aircraft without penetrating the pressure vessel of the aircraft 300 for wiring. 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 avoided. Furthermore, it should be appreciated that the optical signal 118 transmitted through the aircraft window 150 is not interfered with by electronic and mechanical limitations of the aircraft 300. For example, the optical signal 118 does not interfere with other communication frequencies used by the aircraft 300 to communicate with other aircraft, controllers, and systems.
[0051]
[0054] Although the system is described herein with particular reference to a space system or aerospace vehicle, in other embodiments the system may be a vehicle other than a spacecraft without departing from the essence of the present disclosure.
[0052]
[0055] In addition, in this specification, an instance where an element is "coupled" to another element may include direct and indirect coupling. A direct coupling may be defined as an element being coupled to another element and having some contact with the other element. An 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, in this specification, fixing an element to another element may include direct fixing and indirect fixing. In addition, as used herein, "adjacent" does not necessarily mean contact. For example, an element may be adjacent to another element without contacting the other element.
[0053]
[0056] As used herein, a system, device, structure, article, element, component, or hardware that is "configured" to perform a particular function is not in fact capable of performing that particular function without any changes, but rather may perform that particular function after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured" to perform a particular function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing the particular function. In this specification, the phrase "configured to" means that there are characteristics of the system, device, structure, article, element, component, or hardware that enable the system, device, structure, article, element, component, or hardware to perform the particular function without further modification. In 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 "adapted to" and / or "operative to" perform that function.
[0054]
[0057] The schematic flow diagrams contained herein are generally defined as logical flow diagrams. As such, the illustrated order and numbered steps are indicative of one embodiment of the presented method. Other steps and methods may be envisioned that are equivalent in function, logic, or effect to one or more steps or portions of steps of the illustrated method. It is further understood that the format and symbols used are provided to describe the logical steps of the method and are not intended to limit the scope of the method. Although various types of arrows and lines may be used in the flowchart diagrams, these are understood not to limit the scope of the corresponding method. In fact, some arrows or other connectors may be used only to indicate the logical flow of the method. For example, arrows may indicate an unspecified amount of waiting or monitoring time between the listed steps of the illustrated method. Furthermore, the order in which a particular method is performed may or may not strictly follow the order of the corresponding steps shown.
[0055]
[0058] Unless otherwise indicated, the terms "first," "second," etc. are used herein merely as labels and are not intended to impose any sequential, positional, or hierarchical requirements on the items they refer to. Moreover, a reference to, for example, a "second" item does not require or preclude the presence of, for example, a "first" or lower numbered item and / or, for example, a "third" or higher numbered item.
[0056]
[0059] Although the system and method of operation have been described with reference to specific examples, those skilled in the art will recognize that various changes may be made and equivalents may be substituted without departing from the scope of the claims. Accordingly, it is not intended that the method and system be limited to the particular examples disclosed, but rather that the disclosed method and system include all embodiments falling within the scope of the appended claims.
Claims
1. A data transmission system (100), a sensor (102) mounted on an external component of the aircraft (300), the sensor (102) configured to generate sensor data (104) representative of a detected condition; An outer housing (110) attached to an outer portion (152) of an aircraft window (150) of the aircraft (300), the outer housing (110) comprising: a digital-to-optical converter (112) configured to convert the sensor data (104) into one or more optical signals (118); and a transmitting optical device (114) configured to transmit the one or more optical signals (118) through a window (118) of the aircraft; an outer housing (110) comprising: An inner housing (120) attached to an inner portion (154) of a window (150) of the aircraft, the inner housing (120) comprising: an optical receiver (122) configured to receive the one or more optical signals (118) transmitted from the transmitting optical device (114) through a window (150) of the aircraft; and an optical to digital converter (124) configured to convert the one or more optical signals (118) received from the optical receiver (122) into second sensor data (126), the second sensor data (126) being indicative of the detected condition; an inner housing (120) comprising: a data acquisition system (130) within the aircraft (300), the data acquisition system (130) configured to receive the second sensor data (126); A data transmission system (100) comprising:
2. The data transmission system (100) of claim 1, wherein the second sensor data (126) is similar to the sensor data (104).
3. The data transmission system (100) of claim 1, wherein the transmitting optics (114) include one or more lasers.
4. The data transmission system (100) of claim 1, wherein the transmitting optics (114) comprises one or more light emitting diodes (LEDs).
5. The data transmission system (100) of claim 1, wherein the optical receiver (122) comprises a spectrometer, a photocell, or a camera.
6. 2. The data transmission system of claim 1, wherein the outer housing is attached to the outer portion of the aircraft window via a flight-resistant adhesive.
7. The data transmission system (100) of claim 1, wherein the one or more optical signals (118) comprise a visible light signal, an ultraviolet signal, or an infrared signal.
8. 2. The data transmission system of claim 1, wherein a position of the outer housing on the outer portion of the aircraft window is aligned with a position of the inner housing on the inner portion of the aircraft window.
9. 1. A method (400), comprising: generating (402) sensor data (104) representative of conditions detected by sensors (102) external to the aircraft (300); converting (404) the sensor data (104) into one or more optical signals (118) by a digital to optical converter (112), the digital to optical converter (112) being within an exterior housing (110) attached to an exterior portion (152) of an aircraft window (150) of the aircraft (300); transmitting (406) the one or more optical signals (118) through a window (150) of the aircraft with a transmitting optical device (114), the transmitting optical device (114) being within the exterior housing (110); receiving (408) the one or more optical signals (118) transmitted through a window (150) of the aircraft with an optical receiver (122), the optical receiver (122) being 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) by an optical to digital converter (124), the second sensor data (126) being indicative of the detected condition; receiving (412) the second sensor data (126) by a data acquisition system (130); The method (400).
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 transmitting optics (114) comprises one or more lasers.
12. 10. The method (400) of claim 9, wherein the transmitting optics (114) comprises one or more light emitting diodes (LEDs).
13. The method of claim 9 , wherein the optical receiver comprises a spectrometer, a photocell, or a camera.
14. 10. The method (400) of claim 9, wherein the outer housing (110) is attached to the outer portion (152) of the aircraft window (150) via a flight-resistant adhesive (210).
15. 10. The method of claim 9, wherein the one or more optical signals include a visible light signal, an ultraviolet signal, or an infrared signal.
16. 10. The method of claim 9, wherein a position of the outer housing on the outer portion of the aircraft window is aligned with a position of the inner housing on the inner portion of the aircraft window.
17. An aircraft (300), An exterior of the aircraft (302); A window (150) of an aircraft; a sensor (102) mounted on an exterior of the aircraft (302), the sensor (102) configured to generate sensor data (104) representative of a detected condition; An outer housing (110) attached to an outer portion (152) of a window (150) of the aircraft, the outer housing (110) comprising: a digital-to-optical converter (112) configured to convert the sensor data (102) into one or more optical signals (118); and a transmitting optical device (114) configured to transmit the one or more optical signals (118) through a window (150) of the aircraft; an outer housing (110) comprising: An inner housing (120) attached to an inner portion (154) of a window (150) of the aircraft, the inner housing (120) comprising: an optical receiver (122) configured to receive the one or more optical signals (118) transmitted from the transmitting optical device (114) through a window (150) of the aircraft; and an optical to digital converter (124) configured to convert the one or more optical signals (118) received from the optical receiver (122) into second sensor data (126), the second sensor data (126) representing the detected condition; an inner housing (120) comprising: a data acquisition system (130) configured to receive the second sensor data (126); An aircraft (300).
18. 20. The aircraft (300) of claim 17, wherein a position of the outer housing (110) on the outer portion (152) of the aircraft window (150) is aligned with a position of the inner housing (120) on the inner portion (154) of the aircraft window (150).
19. 20. The aircraft (300) of claim 17, wherein the one or more optical signals (118) comprise a visible light signal, an ultraviolet signal, or an infrared signal.
20. The aircraft (300) of claim 17, wherein the transmitting optics (114) include one or more light emitting diodes (LEDs).