Continuous aircraft validation to improve production build efficiency

Abstract

The present disclosure relates to continuous aircraft validation to improve production build efficiency. Systems, apparatuses, and methods can provide a validation system for an aircraft. The validation system includes a validation function subsystem to automatically validate operating conditions of one or more components of the aircraft based on airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances, and to present the operating conditions via a display. The airflow-related signals can be obtained from a plurality of airflow fittings, the hydraulic-related signals can be obtained from a plurality of hydraulic fittings, and the electrical signals and associated impedances can be obtained from a plurality of electrical connectors. At least two of the airflow fittings, at least two of the hydraulic fittings, and at least two of the electrical connectors can be positioned in different aircraft sections prior to assembly of additional aircraft sections.

Description

Technical Field

[0001] The implementation methods generally involve validating the operating conditions of aircraft systems. More specifically, the implementation methods involve continuous aircraft validation to improve production build-up efficiency. Background Technology

[0002] The process of building an aircraft typically involves assembling numerous complex systems located in different sections of the aircraft. Verifying the operability of the assembled systems can be limited to testing conducted only after the aircraft construction is nearing or fully complete. Consequently, correcting errors and / or faults detected late in the construction process can be costly and time-consuming. Summary of the Invention

[0003] According to one or more embodiments, a verification system for an aircraft includes: a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different adjacent aircraft sections, and wherein each airflow fitting is connected to an airflow duct section and includes one or more duct sensors to generate airflow-related signals with respect to the airflow duct section; a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections, and wherein each hydraulic fitting is connected to a hydraulic line section and includes one or more line sensors to generate hydraulic-related signals with respect to the hydraulic line section; a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections and connect wiring in the different aircraft sections; a line-replaceable unit that senses electrical signals and associated impedances corresponding to the plurality of electrical connectors; and a verification function subsystem that automatically verifies the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances, and presents the operating conditions via a display.

[0004] According to one or more embodiments, a method for operating a verification system after aircraft assembly includes: obtaining airflow-related signals for airflow duct sections from a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections adjacent to each other; obtaining hydraulic-related signals for hydraulic line sections from a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections; obtaining electrical signals and associated impedances associated with a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; automatically verifying the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances; and sending the operating conditions to a display associated with the aircraft.

[0005] According to one or more embodiments, a method for operating a verification system during aircraft assembly includes: obtaining airflow-related signals for airflow duct sections from a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections adjacent to each other; obtaining hydraulic-related signals for hydraulic line sections from a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections; obtaining electrical signals and associated impedances associated with a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; automatically verifying the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances; and presenting the operating conditions via a display. Attached Figure Description

[0006] The various advantages of these embodiments will become apparent to those skilled in the art from the following description and appended claims, and from the following drawings, in which:

[0007] Figure 1 This is a perspective view of an example of different adjacent aircraft sections according to the implementation method;

[0008] Figure 2 This is a perspective view of an example of an assembled aircraft according to the implementation method;

[0009] Figure 3A This is a block diagram of an example of an airflow accessory according to an embodiment;

[0010] Figure 3B yes Figure 3A A perspective view of an example of an airflow accessory;

[0011] Figure 4A This is a block diagram of an example of a hydraulic fitting according to an embodiment;

[0012] Figure 4B yes Figure 4A A perspective view of an example of a hydraulic component;

[0013] Figure 5 This is a block diagram of an example of a line replaceable unit (LRU) according to an implementation method;

[0014] Figure 6 This is a block diagram of an example of an aircraft construction architecture according to the implementation method;

[0015] Figure 7 This is a flowchart illustrating an example of a method for operating a verification system during aircraft assembly, according to an implementation method.

[0016] Figure 8 This is a flowchart illustrating an example of a method for communicating with a circuit breaker according to an implementation method;

[0017] Figure 9 This is a flowchart illustrating an example of a method for operating a verification system after aircraft assembly, according to an implementation method.

[0018] Figure 10 This is a flowchart illustrating an example of a method for constructing an operational aircraft architecture according to an implementation method; and

[0019] Figure 11 This is a block diagram of an example of a verification function subsystem according to an implementation method. Detailed Implementation

[0020] Turn now Figure 1 The diagram illustrates a partially assembled aircraft. In the illustrated example, a first front section 20 is adjacent to (e.g., connected to) a second front section 22. In an embodiment, the first front section 20 includes a plurality of electrical connectors 24, wherein the electrical connectors 24 connect to wiring in the first front section 20. The first front section 20 may also include a plurality of airflow fittings 26, which connect to airflow duct sections in the first front section 20. Furthermore, the illustrated first front section 20 includes a plurality of hydraulic fittings 28, which connect to hydraulic line sections on the first front section 20. Similarly, the second front section 22 may include a plurality of electrical connectors 34 connecting to wiring in the second front section 22, a plurality of airflow fittings 36 connecting to airflow duct sections in the second front section 22, and a plurality of hydraulic fittings 38 connecting to hydraulic line sections in the second front section 22.

[0021] In this implementation, each of the airflow fittings 26, 36 includes one or more duct sensors to generate airflow-related signals (e.g., pressure, air quality, and / or temperature signals) regarding the airflow duct segment. Additionally, each hydraulic fitting 28, 38 includes one or more line sensors to generate hydraulic-related signals (e.g., pressure, fluid level, contamination control, and / or temperature signals) regarding the hydraulic line segment. Furthermore, a line replaceable unit (LRU, not shown) senses electrical signals and associated impedances corresponding to electrical connectors 24, 34. As will be discussed in more detail, each of the plurality of avionics systems 30 may include electronic, hydraulic, and airflow system head-end LRUs and a validation function subsystem (e.g., a continuous aircraft validation / CAV function subsystem) that automatically validates and / or determines the operating conditions (e.g., pass / fail) of one or more aircraft components based on airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances. Validating operating conditions during aircraft assembly can save considerable time and costs. In an implementation, the verification function subsystem sends operating conditions to and / or presents them to displays, such as one or more cockpit displays 32, remote displays (not shown), etc.

[0022] Figure 2 An assembled aircraft 40 is shown. In the illustrated example, in addition to the first forward section 20 and the second forward section 22, the aircraft 40 also includes an intermediate body section 42, a first aft section 44, a second aft section 46, and a third aft section 48. In embodiments, the intermediate body section 42, the first aft section 44, and the second aft section 46 also include electrical connectors with sensors, airflow fittings, and hydraulic fittings to facilitate automated and continuous verification of the operating conditions of components in the aircraft 40. In practice, verification can also be performed after the aircraft 40 has been assembled (e.g., during final assembly, on-line, at delivery centers, and / or during service).

[0023] Figure 3A and Figure 3B Airflow accessory 50 is shown, which can easily replace the discussed airflow accessories 26, 36. Figure 1 One or more of the following. In the illustrated example, the airflow fitting 50 includes a pressure sensor 52, an air quality sensor 54, and a temperature sensor 56. In an embodiment, the airflow fitting 50 connects a first airflow duct section 58 to a second airflow duct section 60. The airflow fitting 50 may be coupled to an LRU 62 (e.g., the head end), which in turn communicates with a validation function subsystem 64 (e.g., CAF function / CAVF). In one example, the validation function subsystem 64 may readily replace the avionics system 30 discussed. Figure 1 The verification function subsystem 64 further includes a second airflow duct section 60 that can be coupled to the LRU 62 via a control valve 66. The control valve 66 receives analog control signals and generates discrete outputs representing the state of the control valve 66. In this embodiment, the verification function subsystem 64 automatically determines whether the duct sections 58 and 60 are operable based on signals from the airflow fitting 50 and the control valve 66.

[0024] Figure 4A and Figure 4B Hydraulic fitting 70 is shown, which can easily replace the hydraulic fittings 28 and 38 already discussed. Figure 1 One or more of the following: In the illustrated example, hydraulic fitting 70 includes a pressure sensor 72, a fluid level sensor 74, a contamination control sensor 76, and a temperature sensor 78. In an embodiment, the hydraulic fitting connects a first hydraulic line segment 80 (e.g., a pipe) to a second hydraulic line segment 82. Hydraulic fitting 70 may be coupled to an LRU 62, which in turn communicates with a verification function subsystem 64. In an embodiment, the verification function subsystem 64 automatically determines whether hydraulic line segments 80, 82 are operable based on signals from hydraulic fitting 70.

[0025] Now go to Figure 5The LRU 62 is shown in more detail. In the example shown, the LRU 62 includes a first electrical connector 82 coupled to a digital wiring harness 84 (e.g., carrying Ethernet, ARINC / Aeronautical Radio Corporation, and / or CAN / Controller Area Network bus signals) and a second electrical connector 86 coupled to an analog wiring harness 88. The electrical connectors 82 and 86 provide proper grounding and engagement after installation. In an embodiment, the LRU 62 senses the electrical signals and associated impedances corresponding to the electrical connectors 82 and 86 when energized; these connectors 82 and 86 can readily replace the electrical connectors 24 and 34 discussed earlier. Figure 1 When the different aircraft sections to be evaluated include at least two adjacent sections of a production aircraft being assembled, the verification function subsystem can be configured at startup to further detect (via LRU) electrical signals from avionics or other electronic equipment already installed in at least two adjacent sections, and determine whether the correct electrical signal received via the electrical connector matches the signal expected from the avionics. Therefore, LRU 62 provides multi-level verification regarding electrical connectors 82, 86. First, LRU 62 determines whether the correct electrical signal is detected at the wiring physical layer. Second, LRU 62 determines whether the correct information is received at the application layer.

[0026] In addition, the airflow fitting 50 monitors a drop in flow pressure and detects upstream leaks or blockages, while the hydraulic fitting 70 prevents leaks after installation and detects dirt / contamination. When the different aircraft sections to be evaluated include at least two adjacent sections of a production aircraft being assembled, the verification function subsystem can be configured at startup to further detect (via duct sensors) signals from airflow or hydraulic equipment already installed in at least two adjacent sections and determine whether the signals received via duct sensors match the expected flow or pressure values ​​from the airflow or hydraulic duct lines. Therefore, operating conditions reported from LRU 62 to verification function subsystem 64 (e.g., as self-verification results) include failures, overheating, excessive vibration, power conditions, data corruption, safety event detection, fluid volume, etc. In an embodiment, verification function subsystem 64 further verifies operating conditions based on assembly condition (CoA) data. In practice, verification function subsystem 64 can automatically filter out false alarms based on CoA data (e.g., automatically ignoring faults associated with aircraft sections that have not yet been installed).

[0027] Figure 6The diagram illustrates an aircraft construction architecture in which a verification function subsystem 64 communicates with multiple aircraft systems 90 (systems "A"-"F"), circuit breakers 92, and a manufacturing operating system 94 (e.g., in the production system's ground infrastructure). In one example, the operating system 94 manages the installation operations for building the aircraft. Therefore, the operating system 94 can maintain the aircraft's current CoA and digital twin 96, which the verification function subsystem 64 uses to determine if any non-operational states (e.g., faults, failures) exist before or after the assembly of other aircraft sections. The verification function subsystem 64 can also query the status information (e.g., open, closed, locked) of the circuit breaker 92, where the circuit breaker 92 selectively maintains power to the aircraft systems 90, and the verification function subsystem 64 controls the circuit breaker 92 based on the query results. As will be discussed in more detail, the verification function subsystem 64 can correlate information obtained from systems 90, the manufacturing operating system 94, and the circuit breaker 92, and determine whether to assign "pass" or "fail" designations to systems 90 and the interfaces (e.g., buses) between systems 90.

[0028] Related Examples

[0029] For example, system A could have a "design-in-build" capability, detecting a lack of activity at the interfaces with systems B, C, and D. In this case, system A could report three faults (e.g., interface B fault, interface C fault, interface D fault) to the verification function subsystem 64. Upon power-up, the verification function subsystem 64 could obtain current CoA build progress information from the manufacturing operating system 94. The build progress information could indicate that system A is installed (e.g., including hardware part numbers, software part numbers, etc.), system B is installed (e.g., including hardware part numbers, software part numbers, etc.), system C is not installed, system D is installed (e.g., including hardware part numbers, software part numbers, etc.), etc.

[0030] The verification function subsystem 64 can also obtain status information from the manufacturing operating system 94 for circuit breaker 92. In this implementation, the status information is defined by the production organization to ensure the safety of individuals involved in the construction process. For example, the status information may indicate that the circuit of system A is unlocked, the circuit of system B is unlocked, the circuit of system C is locked, the circuit of system D is unlocked, and so on. In one instance, "locked" indicates that the circuit is disconnected (e.g., no power) and can only be unlocked by a person using a special tool to cut the lock tag.

[0031] For systems listed in the CoA build progress information, the verification function subsystem 64 queries circuit breaker 92 to confirm the status. For example, circuit breaker 92 may indicate that the circuit of system A is closed (e.g., energized), the circuit of system B is closed (e.g., energized), the circuit of system C is locked and open (e.g., de-energized), and the circuit of system D is open (e.g., de-energized, for other installation purposes).

[0032] Accordingly, the verification function subsystem 64 can correlate information obtained from system 90, manufacturing operating system 94, and circuit breaker 92, and determine whether to assign a "pass" or "fail" designation to system 90 and the interfaces between systems 90. In this example, system A is given a pass designation because it is installed, powered on, and reports design build verification data to the verification function subsystem 64. For system B, the verification function subsystem 64 can determine whether design build verification data has been received. If so, the verification function subsystem 64 can also assign a pass designation to system B (e.g., installation, power-on, and reporting build verification data), but assign a failure designation (e.g., wiring for possible reasons) to the interface between system A and system B.

[0033] On the other hand, if system B does not report design build verification data to verification function subsystem 64, verification function subsystem 64 can assign a failure designation to system B and ignore the interface B failure reported from system A. In this case, verification function subsystem 64 can query system B to determine the root cause. In one implementation, verification function subsystem 64 switches power to system B via circuit breaker 92 to confirm whether system B has actually failed.

[0034] Furthermore, since system C is not installed, verification function subsystem 64 can ignore the interface C fault reported from system A as a false alarm. Also, since system D is powered off, verification function subsystem 64 can ignore the interface D fault reported from system A as a false alarm.

[0035] In the event of a system B failure, a repair process can be initiated in response to a fault notification from the verification function subsystem 64. In this case, as a safety measure, the mechanic can disconnect the circuitry of system B. In this implementation, the verification function subsystem 64 detects an open circuit to system B via a query to circuit breaker 92 and reports system B offline to the manufacturing operating system 94. Once the repair or replacement of system B is completed, the verification function subsystem can automatically repeat the relevant process. This allows for the verification of components and / or the correction of non-operating parts on adjacent sections of the aircraft assembly before proceeding with the subsequent assembly of subsequent sections.

[0036] Figure 7This illustrates a method 100 for operating a verification system during aircraft assembly. Method 100 can typically be implemented in a verification functional subsystem, such as avionics system 30. Figure 1 The verification function subsystem and / or the verification function subsystem already discussed 64 ( Figure 5 More specifically, method 100 can be implemented in one or more modules as a set of logic instructions stored in a machine or computer-readable storage medium (such as random access memory (RAM), read-only memory (ROM), programmable ROM (PROM), firmware, flash memory, etc.), in configurable logic (such as, for example, a programmable logic array (PLA), a field-programmable gate array (FPGA), a complex programmable logic device (CPLD)), or in fixed-function hardware logic using circuitry techniques (such as, for example, application-specific integrated circuits (ASIC), complementary metal-oxide-semiconductor (CMOS), or transistor-transistor (TTL) technology, or any combination thereof).

[0037] The illustrated processing block 102 obtains multiple airflow-related signals regarding airflow duct segments from multiple airflow fittings, wherein at least two of the airflow fittings are located in different, adjacent aircraft segments. Furthermore, block 104 obtains hydraulic-related signals regarding hydraulic line segments from multiple hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft segments. In an embodiment, block 106 obtains electrical signals and associated impedances associated with multiple electrical connectors, wherein at least two of the electrical connectors are located in different aircraft segments. Blocks 102, 104, and 106 can obtain signals via push communication, pull communication, or any combination thereof.

[0038] Block 108 automatically verifies the operating conditions (e.g., pass or fail) of one or more aircraft components based on airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances. In one instance, block 108 further verifies the operating conditions based on CoA data. In this case, block 108 may also filter out and / or ignore false alarms based on CoA data. In an implementation, block 110 presents the operating conditions via a display (such as a cockpit display in the aircraft and / or (e.g., a remote display in a manufacturing operating system)).

[0039] In this implementation, the verification function subsystem is configured upon startup to further detect the non-operational state of the identified component and generate information indicating the non-operational state of the identified component in a specific segment to the output of the cockpit display and / or other display devices. Furthermore, when different aircraft segments include at least two adjacent segments of a production aircraft being assembled, the verification function subsystem may be configured upon startup to further detect non-operational conditions of the component. For example, when different aircraft segments to be evaluated include at least two adjacent segments of a production aircraft being assembled, the verification function subsystem may be configured upon startup to further detect (via LRU) electrical signals from avionics equipment or other electrical equipment installed in at least two adjacent segments, determine whether the correct electrical signal received via the electrical connector matches the expected signal from the avionics equipment, and detect non-operational conditions where the sensing signal from the specific aircraft segment and / or electrical connector does not match the expected signal. In this case, the verification function subsystem generates information indicating the non-operational state of the component in the specific segment to the output of the display before the assembly of additional aircraft components. Therefore, the illustrated method 100 improves performance to at least some extent, namely, verifying operating conditions during aircraft assembly improves reliability and enables earlier detection of errors and / or faults during the construction process. In fact, method 100 significantly reduces time and cost.

[0040] Figure 8 A method 120 for communicating with a circuit breaker is shown. Method 120 can typically be used in verification functional subsystems (such as, for example, avionics system 30). Figure 1 The verification function subsystem and / or the verification function subsystem already discussed 64 ( Figure 5 The method 120 may be implemented in one or more modules as a set of logic instructions stored in a machine or computer-readable storage medium (such as RAM, ROM, PROM, firmware, flash memory, etc.), in configurable logic (such as, for example, PLA, FPGA, CPLD), or in fixed-function hardware logic using circuitry techniques (such as, for example, ASIC, CMOS, or TTL technology, or any combination thereof).

[0041] The illustrated processing block 122 provides a query for the circuit breaker coupled to the aircraft. In an embodiment, block 124 controls the circuit breaker based on the result of the query. For example, block 124 may include switching power to a component or system suspected of being faulty. Thus, method 120 further enhances performance by implementing automated fault diagnosis.

[0042] Figure 9 Method 130 for operating a verification system after aircraft assembly is shown. Method 130 can typically be used to verify functional subsystems (e.g., avionics system 30). Figure 1The verification function subsystem and / or the verification function subsystem already discussed 64 ( Figure 5 The method 130 may be implemented in one or more modules as a set of logic instructions stored in a machine or computer-readable storage medium (such as RAM, ROM, PROM, firmware, flash memory, etc.), in configurable logic (such as, for example, PLA, FPGA, CPLD), or in fixed-function hardware logic using circuitry techniques (such as, for example, ASIC, CMOS, or TTL technology, or any combination thereof).

[0043] The processing box is similar to method 100 ( Figure 7 The processing box, except for box 132 shown, explicitly sends the operating conditions to the display associated with the aircraft. Therefore, method 130 can be performed when the aircraft is on a flight line, route, delivery center, and / or in service.

[0044] Figure 10 A method 140 for operating an aircraft construction structure is shown. Method 140 can be implemented as a set of logic instructions in one or more modules, stored in a machine or computer-readable storage medium (such as RAM, ROM, PROM, firmware, flash memory, etc.), in configurable logic (such as, for example, PLA, FPGA, CPLD), or in fixed-function hardware logic using circuitry technologies (such as, for example, ASIC, CMOS, or TTL technology, or any combination thereof).

[0045] The illustrated aircraft block 142 is energized, triggering activation at CAVF block 144, LRU block 146, and sensor block 148. CAVF block 150 can request updates to the CoA (Condition of Assembly). In one implementation, operating system block 152 provides the CoA (e.g., a list of installed systems) in response to a request from block 150. In one example, CAVF block 154 requests the circuit breaker status of the installed systems listed in the CoA, wherein circuit breaker block 156 provides the circuit breaker status (e.g., open or closed) in response to a request from CAVF block 154. LRU block 160 continuously performs design verification processing. The illustrated LRU block 162 sends the published verification data to CAVF block 158, which continuously associates the installed LRU verification data with circuit breaker status information (e.g., limited to system "on").

[0046] More specifically, the illustrated CAVF block 164 determines whether additional LRU data is available. If so, CAVF block 166 requests LRU-related data, such as, for example, software configuration information, sensor data, and / or other parameters. In an implementation, sensor block 170 continuously monitors data and publishes data to the LRUs, wherein LRU block 168 sends additional LRU-related data to CAVF block 158. If it is determined in CAVF block 164 that no additional LRU data is available, method 140 bypasses CAVF block 166.

[0047] In this implementation, CAVF block 172 determines whether the switching of the LRU circuit breaker is appropriate. If so, the illustrated CAVF block 174 commands the circuit breaker to perform an open / close transition for a specific LRU or associated sensor (e.g., causing an open / close state transition). In this case, circuit breaker block 173 operates the internal controller accordingly. If it is determined at CAVF block 172 that the switching of the LRU circuit breaker is inappropriate, method 140 can bypass CAVF block 174.

[0048] In one instance, CAVF box 176 notifies mechanical and / or quality experts of actual build issues, where operating system box 178 assigns mechanical and / or quality experts. In an implementation, CAVF box 180 updates the aircraft digital twin build verification data. Furthermore, digital twin box 182 can appropriately modify the aircraft verification status.

[0049] Figure 11 This demonstrates that it can easily replace avionics system 30 ( Figure 1 The verification function subsystem and / or the verification function subsystem already discussed 64 ( Figure 5 The verification function subsystem 190 includes a processor 192 (e.g., a microcontroller), a memory 194 (e.g., volatile memory such as RAM), a mass storage device 196 (e.g., non-volatile memory such as ROM and / or flash memory), and a network controller 198 (e.g., supporting wired and / or wireless communication).

[0050] Memory 194 and / or mass storage device 196 may include stored instructions 200, which, when executed by processor 192, cause processor 192 to implement method 100. Figure 7 Method 120 Figure 8 Method 130 Figure 9 ) and / or method 140 ( Figure 10One or more aspects of ). Therefore, execution of instruction 200 can cause subsystem 190 and / or processor 192 to obtain airflow-related signals regarding airflow duct sections from a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections adjacent to each other. Execution of instruction 200 can also cause processor 192 to obtain hydraulic-related signals regarding hydraulic line sections from a plurality of hydraulic fittings, wherein at least two hydraulic fittings are located in different aircraft sections. In an embodiment, execution of instruction 200 further causes processor 192 to obtain electrical signals and associated impedances associated with a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections.

[0051] In one instance, the execution of instruction 200 also enables processor 192 to automatically verify the operating conditions of one or more aircraft components based on airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances. Furthermore, the execution of instruction 200 can cause processor 192 to present the operating conditions via a display. Therefore, the verification function subsystem 190 improves performance at least to some extent—that is, it enhances reliability by verifying operating conditions during aircraft assembly and enables earlier detection of errors and / or faults during the build process. In fact, the verification function subsystem 190 can significantly reduce time and cost.

[0052] Additional notes and examples:

[0053] Example 1 includes a verification system for an aircraft, comprising: a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different adjacent aircraft sections, and wherein each airflow fitting is connected to an airflow duct section and includes one or more duct sensors to generate airflow-related signals with respect to the airflow duct section; a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections, and wherein each hydraulic fitting is connected to a hydraulic line section and includes one or more line sensors to generate hydraulic-related signals with respect to the hydraulic line section; a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections and connect wiring in the different aircraft sections; a line-replaceable unit that senses electrical signals and associated impedances corresponding to the plurality of electrical connectors; and a verification function subsystem that automatically verifies the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances, and presents the operating conditions via a display.

[0054] Example 2 includes the verification system of Example 1, wherein the verification function subsystem further verifies the operating conditions based on the conditions of the assembly data.

[0055] Example 3 includes the verification system of Example 2, wherein the verification function subsystem filters out false alarm information based on conditions of assembly data.

[0056] Example 4 includes the verification system of Example 1, wherein the verification function subsystem verifies operating conditions during aircraft assembly.

[0057] Example 5 includes the verification system of Example 1, wherein the verification function subsystem verifies the operating conditions after the aircraft has been assembled.

[0058] Example 6 includes the verification system of Example 1, wherein the verification function subsystem queries the circuit breakers coupled to the aircraft and controls the circuit breakers based on the query results.

[0059] Example 7 includes the verification system of Example 1, wherein one or more duct sensors include a pressure sensor, an air quality sensor, and a temperature sensor.

[0060] Example 8 includes the verification system of Example 1, wherein one or more line sensors include a pressure sensor, a fluid level sensor, a contamination control sensor, and a temperature sensor.

[0061] Example 9 includes the verification system of Example 1, wherein the operating conditions are presented via cockpit displays in the aircraft.

[0062] Example 10 includes the verification system of Example 9, wherein the verification function subsystem is configured upon startup to further detect non-operating conditions of the identified component and generate information indicating the non-operating conditions of the identified component in a specific section to the output of the cockpit display.

[0063] Example 11 includes the verification system of Example 10, wherein operating conditions are presented via a remote display.

[0064] Example 12 includes the verification system of Example 10, wherein different aircraft sections include at least two adjacent sections of a production aircraft being assembled, and wherein, upon startup, the verification function subsystem is configured to further detect non-operating conditions of components and generate information indicating non-operating conditions of components in a particular section to the output of a display before assembling additional aircraft sections.

[0065] Example 13 includes a method for operating a verification system after aircraft assembly, the method comprising: obtaining airflow-related signals for airflow duct sections from a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections adjacent to each other; obtaining hydraulic-related signals for hydraulic line sections from a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections; obtaining electrical signals and associated impedances associated with a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; automatically verifying the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances; and sending the operating conditions to a display associated with the aircraft.

[0066] Example 14 includes the method of Example 13, wherein the operating conditions are further verified based on the conditions of the assembly data.

[0067] Example 15 includes the method of Example 14, and also includes conditional filtering of false alarm information based on assembly data.

[0068] Example 16 includes the method of Example 13, and further includes querying the circuit breakers coupled to the aircraft and controlling the circuit breakers based on the results of the query.

[0069] Example 17 includes the method of Example 13, and further includes presenting operating conditions via one or more cockpit displays or remote displays in the aircraft.

[0070] Example 18 includes a method for operating a verification system during aircraft assembly, the method comprising: obtaining airflow-related signals for airflow duct sections from a plurality of airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections adjacent to each other; obtaining hydraulic-related signals for hydraulic line sections from a plurality of hydraulic fittings, wherein at least two of the hydraulic fittings are located in different aircraft sections; obtaining electrical signals and associated impedances associated with a plurality of electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; automatically verifying the operating conditions of one or more components of the aircraft based on the airflow-related signals, hydraulic-related signals, and electrical signals and associated impedances; and presenting the operating conditions via a display.

[0071] Example 19 includes the method of Example 18, wherein the operating conditions are further verified based on the conditions of the assembly data.

[0072] Example 20 includes the method of Example 19, and also includes conditional filtering of false alarm information based on assembly data.

[0073] Example 21 includes the method of Example 18, and further includes querying the circuit breakers coupled to the aircraft and controlling the circuit breakers based on the results of the query.

[0074] Example 22 includes the method of Example 18, wherein operating conditions are presented via one or more cockpit displays or remote displays in the aircraft.

[0075] The implementation is applicable to all types of semiconductor integrated circuit (“IC”) chips. Examples of these IC chips include, but are not limited to, processors, controllers, chipset components, programmable logic arrays (PLAs), memory chips, network chips, system-on-a-chip (SoC), SSD (Solid State Drive) / NAND controller ASICs, etc. Furthermore, in some figures, signal lines are represented by lines. Some may differ to indicate more component signal paths, have numerical markings to indicate multiple component signal paths, and / or have arrows at one or more ends to indicate the primary direction of information flow. However, this should not be interpreted in a limiting manner. Rather, such added details may be used in conjunction with one or more exemplary implementations to facilitate a more readily understood understanding of the circuit. Any signal line represented (whether or not it carries additional information) may substantially comprise one or more signals that can travel in multiple directions and can be implemented using any suitable type of signaling scheme, such as digital or analog lines implemented with differential pairs, fiber optic lines, and / or single-ended lines.

[0076] Example sizes / models / values / ranges may have been given, but implementations are not limited thereto. As manufacturing technologies (e.g., photolithography) mature over time, it is expected that smaller devices can be manufactured. Furthermore, to simplify description and discussion, and to avoid obscuring certain aspects of the implementation, well-known power / ground connections to the IC chip and other components may or may not be shown in the figures. Further, arrangements may be shown in block diagram form to avoid obscuring the implementation, also taking into account the fact that the details of the implementation of such block diagram arrangements are highly dependent on the platform in which the implementation will be carried out; that is, such details should be entirely within the capabilities of those skilled in the art. In the context of illustrating specific details (e.g., circuitry) to describe exemplary implementations, it will be apparent to those skilled in the art that implementations can be practiced without these specific details or with variations thereof. Therefore, the description is considered illustrative rather than restrictive.

[0077] Furthermore, this disclosure includes embodiments according to the following:

[0078] Item 1. A verification system for an aircraft, comprising:

[0079] Multiple airflow fittings (26, 36), wherein at least two of the airflow fittings are located in different aircraft sections (20, 22) adjacent to each other, and wherein each airflow fitting is connected to an airflow duct section (58, 60) and includes one or more duct sensors (52, 54, 56) to generate airflow-related signals with respect to the airflow duct section;

[0080] Multiple hydraulic fittings (28, 38), wherein at least two of the hydraulic fittings are located in different aircraft sections, and wherein each hydraulic fitting is connected to a hydraulic line segment (80, 82) and includes one or more line sensors (72, 24, 76, 78) to generate information about the hydraulic pressure.

[0081] Hydraulic-related signals for pipeline sections;

[0082] Multiple electrical connectors (24, 34), wherein at least two of the electrical connectors are located in different aircraft sections and connect wiring (84, 88) in different aircraft sections;

[0083] The line-replaceable unit (62) senses electrical signals and associated impedances corresponding to multiple electrical connectors; and

[0084] The verification function subsystem (64) automatically verifies the operating conditions of one or more aircraft components based on airflow-related signals, hydraulic-related signals, electrical signals, and associated impedances.

[0085] The operating conditions are displayed on the screen.

[0086] Item 2. The verification system according to Item 1, wherein the verification function subsystem further verifies the operating conditions based on the assembly data.

[0087] Item 3. The verification system according to Item 2, wherein the verification function subsystem filters out false alarm information based on conditions of the assembly data.

[0088] Item 4. The verification system according to Item 1, wherein the verification function subsystem verifies operating conditions during aircraft assembly.

[0089] Item 5. The verification system according to Item 1, wherein the verification function subsystem verifies operating conditions after the aircraft is assembled.

[0090] Item 6. The verification system according to Item 1, wherein the verification function subsystem queries the circuit breaker coupled to the aircraft and controls the circuit breaker based on the query result.

[0091] Item 7. The verification system according to Item 1, wherein one or more duct sensors include a pressure sensor, an air quality sensor, and a temperature sensor.

[0092] Item 8. The verification system according to Item 1, wherein one or more pipeline sensors include a pressure sensor, a fluid level sensor, a contamination control sensor, and a temperature sensor.

[0093] Item 9. The verification system according to Item 1, wherein the operating conditions are presented via cockpit displays in the aircraft.

[0094] Item 10. The verification system according to Item 9, wherein the verification function subsystem is configured upon startup to further detect non-operating conditions of the identified component and generate information indicating the non-operating conditions of the identified component in a specific section to the output of the cockpit display.

[0095] Item 11. The verification system according to Item 1, wherein the operating conditions are presented via a remote display.

[0096] Item 12. The verification system according to Item 1, wherein different aircraft sections include at least two adjacent sections of a production aircraft being assembled, and wherein, upon startup, the verification function subsystem is configured to further detect the non-operating state of components and generate information indicating the non-operating conditions of components in a particular section to the output of a display before assembling additional aircraft sections.

[0097] Item 13. A method (130) for operating a verification system after aircraft assembly, the method comprising:

[0098] (102) Airflow-related signals about the airflow duct section are obtained from multiple airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections that are adjacent to each other;

[0099] (104) Hydraulic related signals for hydraulic pipeline segments are obtained from multiple hydraulic components, wherein at least two of the hydraulic components are located in different aircraft sections;

[0100] Obtain (106) electrical signals and associated impedances associated with multiple electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections;

[0101] Automatically verify the operating conditions of one or more components of the aircraft based on airflow-related signals, hydraulic-related signals, electrical signals, and associated impedances; and

[0102] Send the operating conditions (132) to the display associated with the aircraft.

[0103] Item 14. The method according to Item 13, wherein the operating conditions are further verified based on the assembly data.

[0104] Item 15. The method according to Item 14 further includes conditionally filtering false alarm information based on assembly data.

[0105] Item 16. The method according to item 13 further includes:

[0106] Inquire about the circuit breakers coupled to the aircraft; and

[0107] Control the circuit breaker based on the query results.

[0108] Item 17. The method according to item 13 further includes presenting operating conditions via one or more cockpit displays or remote displays in the aircraft.

[0109] Item 18. A method (100) for operating a verification system during aircraft assembly, the method comprising:

[0110] (102) Airflow-related signals about the airflow duct section are obtained from multiple airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections that are adjacent to each other;

[0111] (104) Hydraulic related signals for hydraulic pipeline segments are obtained from multiple hydraulic components, wherein at least two of the hydraulic components are located in different aircraft sections;

[0112] Obtain (106) electrical signals and associated impedances associated with multiple electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections;

[0113] Automatically verify the operating conditions of one or more components of the aircraft based on airflow-related signals, hydraulic-related signals, electrical signals, and associated impedances; and

[0114] The operating conditions (110) are displayed on the screen.

[0115] Item 19. The method according to Item 18, wherein the operating conditions are further verified based on the conditions of the assembly data.

[0116] Item 20. The method according to Item 19 further includes conditionally filtering false alarm information based on assembly data.

[0117] Item 21. The method according to item 18 further includes:

[0118] Inquire about the circuit breakers coupled to the aircraft; and

[0119] Control the circuit breaker based on the query results.

[0120] Item 22. The method according to Item 18, wherein the operating conditions are presented via one or more of a cockpit display or a remote display in the aircraft.

[0121] The term “coupled” may be used herein to refer to any type of direct or indirect relationship between the components under discussion, and may be applied to electrical, mechanical, fluid, optical, electromagnetic, electromechanical, or other connections. Furthermore, the terms “first,” “second,” etc., may be used herein merely for ease of discussion and do not carry a specific temporal or chronological meaning unless otherwise specified.

[0122] As used in this application and claims, a series of items joined by the term "one or more" may mean any combination of the listed terms. For example, the phrase "one or more of A, B, or C" may mean A; B; C; A and B; A and C; B and C; or A, B, and C.

[0123] Those skilled in the art will understand from the foregoing description that a wide range of techniques can be implemented in various forms. Therefore, while embodiments have been described in conjunction with specific examples, the true scope of the embodiments should not be limited thereto, as other modifications will become apparent to those skilled in the art upon examination of the drawings, specification, and appended claims.

Claims

1. A verification system for an aircraft, comprising: Multiple airflow accessories, wherein at least two of the airflow accessories are located in different aircraft sections adjacent to each other, and wherein each airflow accessory is connected to an airflow duct section and includes one or more duct sensors to generate airflow-related signals with respect to the airflow duct section; Multiple hydraulic components, wherein at least two of the hydraulic components are located in the different aircraft sections, and wherein each hydraulic component is connected to a hydraulic line segment and includes one or more line sensors to generate hydraulic-related signals about the hydraulic line segment; A plurality of electrical connectors, wherein at least two of the electrical connectors are located in the different aircraft sections and are connected to the wiring in the different aircraft sections; The line-replaceable unit senses electrical signals and associated impedances corresponding to the plurality of electrical connectors; and The verification function subsystem automatically verifies the operating conditions of one or more components of the aircraft based on the airflow-related signals, the hydraulic-related signals, and the electrical signals and associated impedances, and presents the operating conditions via a display.

2. The verification system according to claim 1, wherein, The verification function subsystem further verifies the operating conditions based on the conditions of the assembly data.

3. The verification system according to claim 2, wherein, The verification function subsystem filters out false alarms based on the conditions of the assembly data.

4. The verification system according to claim 1, wherein, The verification function subsystem verifies the operating conditions during the assembly of the aircraft.

5. The verification system according to claim 1, wherein, The verification function subsystem verifies the operating conditions after the aircraft is assembled.

6. The verification system according to claim 1, wherein, The verification function subsystem queries the circuit breakers coupled to the aircraft and controls the circuit breakers based on the query results.

7. The verification system according to claim 1, wherein, The one or more duct sensors include a pressure sensor, an air quality sensor, and a temperature sensor.

8. The verification system according to claim 1, wherein, The one or more pipeline sensors include pressure sensors, fluid level sensors, contamination control sensors, and temperature sensors.

9. The verification system according to claim 1, wherein, The operating conditions will be displayed via cockpit displays in the aircraft.

10. The verification system according to claim 9, wherein, The verification function subsystem is configured upon startup to further detect non-operating conditions of the identified components and generate information indicating the non-operating conditions of the identified components in a specific section to the output of the cockpit display.

11. The verification system according to claim 1, wherein, The different aircraft sections include at least two adjacent sections of a production aircraft being assembled, and wherein, upon startup, the verification function subsystem is configured to further detect non-operating conditions of components and generate information indicating the non-operating conditions of the components in a particular section to the output of a display before assembling additional aircraft sections.

12. A method for operating a verification system during aircraft assembly, the method comprising: Airflow-related signals about airflow duct sections are obtained from multiple airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections that are adjacent to each other; Hydraulic-related signals about hydraulic pipeline segments are obtained from multiple hydraulic components, wherein at least two of the hydraulic components are located in different aircraft sections; Obtain electrical signals and associated impedances associated with multiple electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; The operating conditions of one or more components of the aircraft are automatically verified based on the airflow-related signals, the hydraulic-related signals, and the electrical signals and associated impedances; and The operating conditions are displayed on the screen.

13. The method according to claim 12, wherein, The operating conditions are further verified based on the assembly data, and the method also includes a step of filtering out false alarms based on the conditions of the assembly data.

14. The method of claim 12, further comprising: Queries the circuit breakers coupled to the aircraft; as well as The circuit breaker is controlled based on the result of the query.

15. The method of claim 12, further comprising continuing the operation of the verification system after the aircraft is assembled, wherein, The method further includes: Airflow-related signals about airflow duct sections are obtained from multiple airflow fittings, wherein at least two of the airflow fittings are located in different aircraft sections that are adjacent to each other; Hydraulic-related signals about hydraulic pipeline segments are obtained from multiple hydraulic components, wherein at least two of the hydraulic components are located in different aircraft sections; Obtain electrical signals and associated impedances associated with multiple electrical connectors, wherein at least two of the electrical connectors are located in different aircraft sections; The operating conditions of one or more components of the aircraft are automatically verified based on the airflow-related signals, the hydraulic-related signals, and the electrical signals and associated impedances; and The operating conditions are sent to the cockpit display in the aircraft.

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