CN219948556U - Oil tank inerting system - Google Patents
Oil tank inerting system Download PDFInfo
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- CN219948556U CN219948556U CN202321400388.5U CN202321400388U CN219948556U CN 219948556 U CN219948556 U CN 219948556U CN 202321400388 U CN202321400388 U CN 202321400388U CN 219948556 U CN219948556 U CN 219948556U
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- 230000036541 health Effects 0.000 claims abstract description 54
- 238000012544 monitoring process Methods 0.000 claims abstract description 43
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 41
- 239000001301 oxygen Substances 0.000 claims abstract description 41
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 41
- 238000012545 processing Methods 0.000 claims abstract description 29
- 239000002828 fuel tank Substances 0.000 claims abstract description 27
- 230000001105 regulatory effect Effects 0.000 claims abstract description 14
- 238000002955 isolation Methods 0.000 claims description 38
- 239000007789 gas Substances 0.000 claims description 26
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 24
- 238000012423 maintenance Methods 0.000 claims description 23
- 229910052757 nitrogen Inorganic materials 0.000 claims description 12
- 238000011144 upstream manufacturing Methods 0.000 claims description 7
- 230000003862 health status Effects 0.000 claims description 3
- 230000015556 catabolic process Effects 0.000 abstract description 19
- 238000006731 degradation reaction Methods 0.000 abstract description 19
- 239000000306 component Substances 0.000 description 65
- 238000012360 testing method Methods 0.000 description 8
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 6
- 239000008358 core component Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000008929 regeneration Effects 0.000 description 2
- 238000011069 regeneration method Methods 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 201000008217 Aggressive systemic mastocytosis Diseases 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 210000001944 turbinate Anatomy 0.000 description 1
- 238000004260 weight control Methods 0.000 description 1
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Abstract
An oil tank inerting system comprising: temperature regulating device, air separator, temperature sensor, pressure sensor, oxygen sensor and inerting system controller. The inerting system controller is electrically and/or signally connected with each component of the tank inerting system. The inerting system controller comprises a data acquisition part, a health monitoring processing part, a truth table storage part and a notification instruction part. The health monitoring processing part receives the data from the data acquisition part, performs table lookup on the truth table stored in the truth table storage part based on the data to determine the health condition of the components of the fuel tank inerting system, and sends the health condition to the notification indicating part. The structure of the fuel tank inerting system can monitor the health state of the fuel tank inerting system and can predict degradation or degradation trend of each relevant part of the fuel tank inerting system.
Description
Technical Field
The utility model belongs to the field of civil aircraft design, relates to improvement of an oil tank inerting system of a civil aircraft, and particularly relates to fault Prediction and Health Management (PHM) of the inerting system.
Background
There is a requirement in the national aviation regulations for fuel tank flammability in civil aircraft fuselages (CCAR 25.981 clause and CCAR 26.37 clause). To meet this clause, inerting systems are commonly used on civilian aircraft to reduce the flammability of the fuel tanks.
Conventional aircraft fuel tank inerting systems currently introduce high temperature gases from an engine and/or gas supply system, or alternatively, non-high temperature gases from a booster system. After conditioning the gas by means such as a heat exchanger, the air is separated into nitrogen-rich gas and oxygen-rich gas by an Air Separator (ASM). And distributing the nitrogen-rich gas to the target oil tank, and reducing the oxygen concentration in the oil tank, thereby reducing the combustibility of the oil tank. The oxygen-enriched gas is then discharged from the aircraft.
As the run time of the inerting system builds up, the performance of the various components of the inerting system may decrease, for example its core component ASM. In addition to the degradation of its own performance, the degradation of the associated system components may also cause the ASM to operate under severe conditions to accelerate its performance degradation. Therefore, the health monitoring technology of the inerting system is developed in the field of civil aircrafts, and through the health monitoring technology, the service lives of ASM and related components of the inerting system can be effectively prolonged, the reliability of the civil aircrafts, particularly the inerting system of the civil aircrafts, is improved, the maintenance and operation efficiency of the aircrafts are further improved, the maintenance cost is reduced, and the aims of reducing the cost and enhancing the efficiency are fulfilled.
The main current health monitoring device mainly performs fault detection and prompt alarm. For example, by detecting the pressure and oxygen concentration upstream and downstream of the ASM, it is determined whether the ASM is normal or not based on the detected values. If it is determined that the ASM is abnormal, an alarm signal is sent (e.g., information is sent to a ground maintainer), and maintenance and repair work such as testing, component replacement, etc. is performed on the ASM based on the alarm signal.
However, such a solution presents the following drawbacks in implementation: the health monitoring of conventional inerting systems is limited to two functions, namely fault detection and prompt warning (including power-on self-test, start-up test, continuous test, etc.), and no prediction of performance degradation or degradation trend of system core components (ASMs) and other related components is provided.
In US patent application 20170296965A1, a method for health monitoring of an aircraft inerting system is disclosed, which provides at least one respective sensor for each component of the inerting system, from which a health monitoring network is formed, from which the number of operating hours of the component remaining before a fault is estimated on the basis of an empirical formula. However, such a solution requires a large number of sensors to be arranged so that sufficient data can be obtained for formula fitting and subsequent measurement. Such a solution would add additional weight to the system, which is difficult to use in practice on aircraft where weight control is a high requirement.
Accordingly, there is a need in the art of aircraft inerting system design for further improvements in failure prediction and health management of aircraft inerting systems
Disclosure of Invention
The present utility model has been made to solve the above-mentioned problems occurring in the prior art. The utility model aims to provide a fuel tank inerting system comprising a fault prediction and health management device, which can monitor the health state of the fuel tank inerting system of an aircraft and predict degradation or degradation trend of each relevant component of the fuel tank inerting system.
The utility model provides an oil tank inerting system, which comprises: a temperature regulating device that regulates a temperature of air entering the tank inerting system; an air separator for separating the air temperature-regulated by the temperature regulator into nitrogen-rich gas and oxygen-rich gas; a temperature sensor that monitors the temperature of air in the tank inerting system; a pressure sensor monitoring air pressure in the tank inerting system; and an oxygen sensor that monitors the oxygen content in the nitrogen-rich gas. The fuel tank inerting system further comprises an inerting system controller which is electrically and/or signally connected with at least one of the temperature regulating device, the temperature sensor, the pressure sensor and the oxygen sensor. The inerting system controller includes: the data acquisition part is connected with at least one of the temperature regulating device, the temperature sensor, the pressure sensor and the oxygen sensor so as to receive real-time operation parameters of the fuel tank inerting system; the health monitoring processing part is connected with the data acquisition part to receive the real-time operation parameters sent by the data acquisition part; the truth table storage part is used for storing a truth table of real-time operation parameters, and the health monitoring processing part is connected with the truth table storage part; and a notification instruction unit connected to the health monitoring processing unit, whereby the health monitoring processing unit can notify the health status of the component through the notification instruction unit.
The truth table may be formed by laboratory calibration, and the health monitoring processing unit may look up the truth table in the truth table storing unit.
By the structure of the fuel tank inerting system, the degradation of each component of the fuel tank inerting system can be predicted by looking up a table based on a curing truth table calibrated in a laboratory and comparing the table with detected real-time operation parameters to determine the difference, and sensors are not required to be arranged for all the components to monitor. The degradation or failure condition of each component of the fuel tank inerting system can be prejudged in advance, so that spare parts and tool equipment can be prepared in advance, the maintenance time is shortened, and the operation efficiency is improved.
In addition, for the fuel tank inerting system, the degradation or fault condition of the components in the system can be judged through one-time flight. The turbinates reduce the risk of the fuel tank inerting system exposed to performance degradation and even faults, and improve the flight safety of the aircraft.
Moreover, by self-maintenance and replacement of the degraded component in advance, the degraded component can be prevented from affecting the operation of the ASM, so that the ASM is in a stable operating state for a long period of time, thereby being beneficial to improving the operation life of the ASM as a core component.
Further, the tank inerting system further comprises an inlet isolation valve disposed at an inlet of the tank inerting system; the temperature regulating device comprises a temperature control valve and a temperature isolation valve positioned downstream of the temperature control valve. Furthermore, two temperature sensors, namely a first temperature sensor, which is provided downstream of the temperature control valve and upstream of the temperature isolation valve, and a second temperature sensor, which is provided downstream of the second temperature sensor, are included.
Wherein the pressure sensor is located downstream of the second temperature sensor and upstream of the air separator; an oxygen sensor is disposed downstream of the air separator.
In the present utility model, the above-described real-time operation parameters include at least one of the following parameters: a sensor signal, a component status signal, a component input signal, and a component output signal. Wherein the sensor signal includes at least one of a temperature signal detected by a temperature sensor, an air pressure signal detected by a pressure sensor, and an oxygen concentration signal in the nitrogen-rich gas detected by an oxygen sensor. The component status signal includes at least one of a signal regarding a switching state and/or an opening degree of the temperature control valve, a switching state of the inlet isolation valve, and a switching state of the temperature isolation valve. The component input signals include at least one of a voltage/current signal input to the inlet isolation valve, a voltage/current signal input to the temperature control valve, a voltage/current signal input to the temperature isolation valve, a voltage/current signal input to the pressure sensor, and a voltage/current signal input to the oxygen sensor. The component output signals include at least one of an output voltage/current signal from the inlet isolation valve, an output voltage/current signal from the temperature isolation valve, a voltage/current signal from the pressure sensor, and a voltage/current signal from the oxygen sensor.
Correspondingly, the truth table stored in the truth table storage section includes at least one of the following: sensor data truth table, component status signal truth table, component input signal truth table, and component output signal truth table.
Preferably, the inerting system controller further comprises a self-maintenance part, wherein the self-maintenance part is connected with the health monitoring processing part to receive the notification of the health condition of the oil tank inerting system from the health monitoring processing part, and is also connected with the notification indicating part to send a self-maintenance instruction to the notification indicating part.
When the health monitoring processing part determines that degradation or failure exists in one or more components in the fuel tank inerting system based on the acquired operation parameters in combination with the table look-up operation of the truth table in the truth table storage part, the self-maintenance part can send a notification to the self-maintenance part, and the self-maintenance part can send a self-maintenance instruction to the notification instruction part according to the notification so as to perform self-maintenance of the fuel tank inerting system, such as regeneration operation of ASM and the like.
Preferably, the inerting system controller further comprises a system operation logic portion, wherein the system operation logic portion stores the system operation logic of the aircraft and is connected with the health monitoring processing portion.
The health monitoring process may combine the look-up table operation with the system operating logic to more accurately determine whether performance degradation or failure conditions exist for various components of the tank inerting system.
Drawings
Preferred embodiments of the present utility model are illustrated in the accompanying drawings, from which detailed embodiments of the utility model can be more clearly understood, wherein:
fig. 1 shows a schematic diagram of the tank inerting system of the present utility model.
FIG. 2 shows a schematic block diagram of the inerting system controller of FIG. 1.
(symbol description)
1 tank inerting system
10 inerting system controller
11 data acquisition unit
12 health monitoring and processing part
13 truth table storage unit
14 notification instruction unit
15 self-maintenance part
16 system operation logic
41 sensor signal
42 component status signal
43 part input signal
44 component output signal
21 first temperature sensor
22 second temperature sensor
23 pressure sensor
24 oxygen sensor
30 air separator
31 temperature control valve
32 inlet isolation valve
33 ozone converter
34 temperature isolation valve
35 outlet check valve
Detailed Description
The following detailed description of the embodiments of the utility model refers to the accompanying drawings. It should be understood that the drawings are only illustrative of the preferred embodiments of the present utility model and are not intended to limit the scope of the present utility model. Various obvious modifications, variations, equivalent substitutions of the present utility model may be made by those skilled in the art on the basis of the embodiments shown in the drawings, and the technical features of the different embodiments described below may be arbitrarily combined with each other without contradiction, which fall within the scope of the present utility model.
In the following description of the structure of the tank inerting system 1, "upstream" and "downstream" are used with reference to the flow direction of the gas in the tank inerting system 1 indicated by arrow a in fig. 1.
Fig. 1 shows a schematic structure of a tank inerting system 1 of the present utility model. As shown, the tank inerting system 1 comprises an air separator 30, the air separator 30 separating the intake air into a nitrogen-rich gas and an oxygen-rich gas, wherein the nitrogen-rich gas is fed into the target component to be inerted, such as the tank of an aircraft, and the oxygen-rich gas is discharged.
The tank inerting system 1 also comprises other components, for example an inlet isolation valve 32 is provided at the inlet of the system, through which inlet isolation valve 32 the inlet air of the tank inerting system 1 can be opened and closed. An ozone converter 33 is also provided in the tank inerting system 1, the ozone converter 33 being capable of converting ozone in the inhaled air into oxygen to prevent damage to components in the tank inerting system 1 by ozone.
A temperature control valve 31 and a temperature isolation valve 34 as temperature adjusting means are provided in this order downstream of the ozone converter 33, and further comprise a part such as an outlet check valve 35 provided at or near the outlet of the tank inerting system 1, the roles of which are known and will not be described in detail herein.
A number of sensors are also provided in the tank inerting system 1 to monitor the operational status and health of the components of the tank inerting system 1. Specifically, at least one temperature sensor is provided downstream of the temperature control valve 31 to detect the temperature of the air temperature-regulated by the temperature control valve 31. In the exemplary configuration shown in the figures, two temperature sensors are included, a first temperature sensor 21 located upstream of the temperature isolation valve 34 and a second temperature sensor 22 located downstream of the temperature isolation valve 34, respectively. A pressure sensor 23 for detecting the pressure of the air temperature-regulated by the temperature control valve 31 is provided downstream of the second temperature sensor 22. By detecting the air temperature and pressure, the performance of the temperature control valve 31 may be monitored for determining a failure of the temperature control valve 31 or predicting a performance degradation of the temperature control valve 31.
An oxygen sensor 24 is provided downstream of the air separator 30, the oxygen sensor 24 detecting the oxygen content in the nitrogen-enriched air flowing out of the air separator 30. By monitoring the amount of oxygen in the air, the operating performance of the air separator 30 may be monitored to determine a malfunction of the air separator 30 or to predict a degradation in the performance of the air separator 30.
The tank inerting system 1 further includes an inerting system controller 10, the inerting system controller 10 being in electrical and/or signal connection with components of the tank inerting system 1 (e.g., temperature control valve 31, inlet isolation valve 32, temperature isolation valve 34, first temperature sensor 21, second temperature sensor 22, pressure sensor 23, oxygen sensor 24, etc.), which are capable of receiving sensor signals, input and output voltage/current signals for the components, etc. For example, as shown in the figures, the tank inerting system 1 may receive output voltages/currents from the temperature control valve 31, inlet isolation valve 32, temperature isolation valve 34, pressure sensor 23, oxygen sensor 24, etc., and send input voltages/currents to these components, as illustrated by the solid arrows between these components and the inerting system controller 10. The inerting system controller 10 also receives sensor signals of a first temperature sensor 21, a second temperature sensor 22, a pressure sensor 23 and an oxygen sensor 24. In addition, the inerting system controller 10 is also capable of receiving position signals of the temperature control valve 31, the inlet isolation valve 32 and the temperature isolation valve 34, as shown by the dashed arrows between these valves and the inerting system controller 10.
Herein, the term "electrical and/or signal connection" includes both wired and wireless connections, which are within the scope of the present utility model.
The inerting system controller 10 is capable of processing these signals and is used to diagnose the status of the various components of the tank inerting system 1 and to perform operations such as self-maintenance when a degradation in performance of a component is detected, as will be described in more detail below.
Fig. 2 shows an exemplary block diagram of the inerting system controller 10 from which the interconnections and communication relationships of the various components of the inerting system controller 10 can be seen. The inerting system controller 10 includes a data acquisition section 11, a health monitoring processing section 12, a truth table storage section 13, and a notification instruction section 14.
The data acquisition portion 11 receives operational data from components of the tank inerting system 1, including at least one of a sensor signal 41, a component status signal 42, a component input signal 43, and a component output signal 44.
The sensor signal 41 is, for example, a temperature signal detected by the first temperature sensor 21 and/or the second temperature sensor 22, an air pressure signal detected by the pressure sensor 23, and an oxygen concentration signal in the nitrogen-rich gas detected by the oxygen sensor 24.
The component status signal 42 is an operation status signal regarding each component of the tank inerting system 1, specifically including position signals of the opening and/or closing state of the temperature control valve 31, the opening and closing states of the inlet isolation valve 32 and the temperature isolation valve 34, and the like.
The component input signal 43 is, for example, a voltage/current signal input to the inlet isolation valve 32, a voltage/current signal input to the temperature control valve 31, a voltage/current signal input to the temperature isolation valve 34, a voltage/current signal input to the pressure sensor 23, a voltage/current signal input to the oxygen sensor 24, or the like.
The component output signal 44 is, for example, an output voltage/current signal from the inlet isolation valve 32, an output voltage/current signal from the temperature isolation valve 34, a voltage/current signal from the pressure sensor 23, a voltage/current signal from the oxygen sensor 24, etc.
The data acquisition part 11 is communicated with the health monitoring processing part 12, and transmits the acquired data related to the operation of the fuel tank inerting system 1 to the health monitoring processing part 12. The health monitoring processing section 12 is also in communication with a truth table storage section 13. The truth table memory 13 stores truth tables (i.e., sensor data truth tables) of data monitored by the sensors of the tank inerting system 1, which indicate normal ranges of values (or calibration ranges) of operating parameters for gas temperature, gas pressure, oxygen content, etc. during different phases of flight. The truth table storage unit 13 also stores a component status signal truth table, a component input signal truth table, a component output signal truth table, etc., which reflect the numerical ranges of parameters such as component status (for example, valve opening), input voltage/current, output voltage/current, etc. of the fuel tank inerting system 1 in different flight phases under the normal operation state.
The operating parameter truth table, component status signal truth table, component input signal truth table, and component output signal truth table described above may be prepared by laboratory personnel through data calibration tests. By way of example, one example of a temperature range calibration truth table is provided below, with other truth tables being similarly available through experimentation.
TABLE 1 truth table for calibrating temperature ranges at different flight phases
After the health monitoring processing section 12 obtains the data of the relevant parameters from the data acquisition section 11, the health monitoring processing section 12 can communicate with the truth table storage section 13 for the obtained data to perform a table lookup operation. The look-up operation is performed, for example, by interpolation. The difference between the detected real-time data and the calibrated range in the corresponding truth table in the health monitoring processing section 12 is determined by the table look-up operation of the health monitoring processing section 12. The health monitoring process 12 may determine if the difference exceeds a predetermined range of values and further determine if the associated components (e.g., temperature control valve 31, temperature isolation valve 34, sensors, etc.) have degraded performance or even have failed.
The health monitoring processing section 12 communicates with the notification instruction section 14, and performs notification concerning the health condition of the component, such as on-board notification, notification to the ground, and the like, through the notification instruction section 14.
Preferably, the inerting system controller 10 further includes a self-maintenance section 15, and the self-maintenance section 15 is capable of communicating with the health monitoring processing section 12, receiving notification about the health condition of the component, and transmitting an instruction to perform self-maintenance to the notification instructing section 14 based on the notification.
The relevant components may be self-maintained in a manner known in the art. For example, the self-maintenance approach for ASM is as follows: the ASM is operated under conditions of high temperature gas flow or high velocity gas flow, thereby effecting regeneration of ASM performance.
Further, if the tank inerting system 1 cannot be restored to the normal performance state even after the self-maintenance, it may be notified by the notification indicator 14, for example, remotely notifying the ground, that the component repair and replacement is ready to be performed by the ground serviceman.
Further preferably, the tank inerting system 1 further comprises a system operation logic section 16 in which the system operation logic of the aircraft is stored. The system operation logic 16 is coupled to communicate with the health monitoring processor 12 such that the health monitoring processor 12 further analyzes and determines whether the data differences are outside of a predetermined range in conjunction with the system operation logic based on having performed a look-up table operation. The system operation logic uses parameters such as component status signal 42, component input signal 43, component output signal 44, etc. to determine whether performance degradation exists for the associated component. In this way, the health monitoring processing unit 12 can more accurately determine the health status of each component of the tank inerting system 1.
The fuel tank inerting system 1 of the present utility model can be used for power-on self-test, start-up test and normal run-time duration test. In addition, during the flight phase of the aircraft, an additional 3 or more comprehensive physical examinations may be performed. Typical predetermined body checkpoints include three phases of climb, cruise and descent, each taking a point in time to initiate health monitoring. In this way, the health of the components of the tank inerting system 1 can be more fully evaluated.
Claims (7)
1. A tank inerting system, the tank inerting system comprising: a temperature regulating device that regulates the temperature of air entering the tank inerting system; the air separator is used for separating the air with the temperature regulated by the temperature regulating device into nitrogen-rich gas and oxygen-rich gas; a temperature sensor that monitors the temperature of air in the tank inerting system; a pressure sensor monitoring air pressure in the tank inerting system; and an oxygen sensor that monitors the oxygen content in the nitrogen-rich gas; the fuel tank inerting system is characterized by further comprising an inerting system controller, wherein the inerting system controller is electrically and/or signally connected with at least one of the temperature regulating device, the temperature sensor, the pressure sensor and the oxygen sensor, and the inerting system controller comprises:
the data acquisition part is connected with at least one of the temperature regulating device, the temperature sensor, the pressure sensor and the oxygen sensor so as to receive real-time operation parameters of the fuel tank inerting system;
the health monitoring processing part is connected with the data acquisition part to receive the real-time operation parameters sent by the data acquisition part;
the truth table storage part is used for storing the truth table of the real-time operation parameters, and the health monitoring processing part is connected with the truth table storage part; and
and a notification instruction unit connected to the health monitoring unit, whereby the health monitoring unit can notify the health status of the component via the notification instruction unit.
2. The fuel tank inerting system of claim 1, wherein,
the fuel tank inerting system further comprises an inlet isolation valve arranged at an inlet of the fuel tank inerting system;
the temperature regulating device comprises a temperature control valve and a temperature isolation valve positioned at the downstream of the temperature control valve; and
the temperature sensor comprises two temperature sensors, namely a first temperature sensor and a second temperature sensor, wherein the first temperature sensor is arranged at the downstream of the temperature control valve and the upstream of the temperature isolation valve, and the second temperature sensor is arranged at the downstream of the second temperature sensor.
3. The tank inerting system of claim 2, wherein the pressure sensor is located downstream of the second temperature sensor and upstream of the air separator; the oxygen sensor is disposed downstream of the air separator.
4. The tank inerting system of claim 2, wherein the real-time operating parameters include at least one of:
a sensor signal including at least one of a temperature signal detected by the temperature sensor, an air pressure signal detected by the pressure sensor, and an oxygen concentration signal in the nitrogen-rich gas detected by the oxygen sensor;
a component status signal including at least one of a signal regarding a switching state and/or an opening degree of the temperature control valve, a switching state of the inlet isolation valve, and a signal of a switching state of the temperature isolation valve;
a component input signal including at least one of a voltage/current signal input to the inlet isolation valve, a voltage/current signal input to the temperature control valve, a voltage/current signal input to the temperature isolation valve, a voltage/current signal input to the pressure sensor, and a voltage/current signal input to the oxygen sensor; and
a component output signal comprising at least one of an output voltage/current signal from the inlet isolation valve, an output voltage/current signal from the temperature isolation valve, a voltage/current signal from the pressure sensor, and a voltage/current signal from the oxygen sensor.
5. The tank inerting system of claim 4, wherein the truth table comprises at least one of: sensor data truth table, component status signal truth table, component input signal truth table, and component output signal truth table.
6. The tank inerting system of any of claims 1 to 5, wherein the inerting system controller further comprises a self-maintenance section connected to the health monitoring processing section to receive notification from the health monitoring processing section regarding the health condition of the tank inerting system, the self-maintenance section further connected to the notification indicating section to issue an instruction to the notification indicating section to perform self-maintenance.
7. The tank inerting system of any of claims 1 to 5, wherein the inerting system controller further comprises a system operation logic portion having stored therein system operation logic of the aircraft and coupled to the health monitoring processing portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321400388.5U CN219948556U (en) | 2023-06-02 | 2023-06-02 | Oil tank inerting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321400388.5U CN219948556U (en) | 2023-06-02 | 2023-06-02 | Oil tank inerting system |
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| Publication Number | Publication Date |
|---|---|
| CN219948556U true CN219948556U (en) | 2023-11-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321400388.5U Active CN219948556U (en) | 2023-06-02 | 2023-06-02 | Oil tank inerting system |
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| Country | Link |
|---|---|
| CN (1) | CN219948556U (en) |
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- 2023-06-02 CN CN202321400388.5U patent/CN219948556U/en active Active
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