CN114235427A - Method and system for displaying engine state parameters in aircraft cockpit - Google Patents
Method and system for displaying engine state parameters in aircraft cockpit Download PDFInfo
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- CN114235427A CN114235427A CN202111611332.XA CN202111611332A CN114235427A CN 114235427 A CN114235427 A CN 114235427A CN 202111611332 A CN202111611332 A CN 202111611332A CN 114235427 A CN114235427 A CN 114235427A
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Abstract
The application provides a method and a system for displaying engine state parameters in an aircraft cockpit, wherein the method is partially designed in the aircraft cockpit, the engine state parameters are divided into a state indication type parameter, a prompt type parameter, a four-level alarm type parameter, a three-level alarm type parameter, a two-level alarm type parameter and a one-level alarm type parameter, and the state indication type parameter comprises an engine starting parameter and an stressing parameter; the prompt parameters comprise parameters which can cause the loss of the control margin of the engine, do not influence the flight safety of the airplane and do not cause the flight degradation; the class four warning parameters include parameters that degrade engine performance or function, but do not significantly affect engine usage; the three-level alarm parameters comprise parameters which can degrade the performance or the function of the engine and obviously influence the use of the engine; secondary alarm class parameters include parameters that can significantly degrade engine performance or function; the primary alarm class parameters include parameters that may cause a loss of engine performance or function.
Description
Technical Field
The application belongs to the technical field of engine state parameter display in an aircraft cockpit, and particularly relates to an engine state parameter display method and system in the aircraft cockpit.
Background
The aircraft engine has a plurality of state parameters which need to be monitored during working, including engine process parameters, fuel system parameters, lubricating oil system parameters, air system parameters, anti-icing system parameters, vibration parameters, air inlet parameters, characteristic section pressure change frequency parameters and the like.
Under the condition that the number of the state parameters of the aircraft engine is large, currently, the aircraft health management system can only display part of the state parameters in the aircraft cockpit in a centralized manner, part of warning functions are simply integrated, the warning levels are not distinguished, a driver needs to judge the warning levels according to the displayed state parameters, the situation that the specific state of the engine cannot be accurately judged due to the lack of the state parameters exists, the driver cannot rapidly take corresponding operations, and a large burden exists.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method and system for displaying engine state parameters within an aircraft cockpit to overcome or alleviate at least one of the technical deficiencies of the known prior art.
The technical scheme of the application is as follows:
in one aspect, a method for displaying engine state parameters in an aircraft cockpit is provided, including:
in an aircraft cockpit, dividing the engine state parameters into a state indication class parameter, a prompt class parameter, a four-level alarm class parameter, a three-level alarm class parameter, a two-level alarm class parameter and a one-level alarm class parameter, and displaying the parameters in different areas;
wherein the content of the first and second substances,
the state indicating parameters comprise engine starting parameters and stress parameters;
the prompt parameters comprise parameters which can cause the loss of the control margin of the engine, do not influence the flight safety of the airplane and do not cause the flight degradation;
the class four warning parameters include parameters that degrade engine performance or function, but do not significantly affect engine usage;
the three-level alarm parameters comprise parameters which can degrade the performance or the function of the engine and obviously influence the use of the engine;
secondary alarm class parameters include parameters that can significantly degrade engine performance or function;
the primary alarm class parameters include parameters that may cause a loss of engine performance or function.
According to at least one embodiment of the application, in the method for displaying the engine state parameters in the aircraft cockpit, the prompt parameters specifically include single-channel measurement fault parameters of the high and low rotating speeds of the engine, single-channel measurement fault parameters of the fan inlet guide vane angle, and single-channel fault parameters of the fan inlet guide vane angle actuating mechanism.
According to at least one embodiment of the application, in the method for displaying the engine state parameters in the aircraft cockpit, the four-level warning parameters specifically include an engine fuel temperature parameter, a surge differential pressure sensor measurement fault parameter, and a fire detector measurement fault parameter.
According to at least one embodiment of the application, in the method for displaying the engine state parameters in the aircraft cockpit, the three-level warning parameters specifically include a power-on fault parameter, a high-low pressure rotating speed measurement fault parameter, and a fan inlet total temperature double-channel measurement fault parameter.
According to at least one embodiment of the present application, in the method for displaying the engine state parameters in the aircraft cockpit, the secondary warning parameters specifically include an engine over-vibration parameter, a surge parameter, and a lubricant temperature parameter.
According to at least one embodiment of the application, in the method for displaying the engine state parameters in the aircraft cockpit, the primary alarm parameters specifically include an engine in-air parking parameter and a firing parameter.
According to at least one embodiment of the application, in the method for displaying the engine state parameter in the aircraft cockpit, the engine state parameter is displayed in different colors, the engine state parameter is displayed in a first color in a normal range, the engine state parameter is displayed in a second color close to the limit boundary, and the engine state parameter is displayed in a third color beyond the limit boundary.
In another aspect, an aircraft cockpit engine status parameter display system is provided, comprising:
the display is arranged in the aircraft cockpit, is accessed into the aircraft health management system, and is provided with a state indication type parameter display area, a prompt type parameter display area, a four-level alarm type parameter display area, a three-level alarm type parameter display area, a two-level alarm type parameter display area and a one-level alarm type parameter display area.
According to at least one embodiment of the application, in the above-mentioned system for displaying the engine state parameters in the aircraft cockpit, the indication type parameter display area is touched to display the engine starting parameters and the boosting parameters;
the prompt type parameter display area is touched to display single-channel measurement fault parameters of the high and low rotating speeds of the engine, single-channel measurement fault parameters of the fan inlet guide vane angle and single-channel fault parameters of the fan inlet guide vane angle actuating mechanism;
the four-level alarm parameter display area is touched to display the fuel temperature parameter of the engine, the surge differential pressure sensor measures the fault parameter, and the fire alarm detector measures the fault parameter;
the three-level alarm parameter display area is touched to display an engine stress application connection fault parameter, a high-low pressure rotating speed measurement fault parameter and a fan inlet total temperature double-channel measurement fault parameter;
the secondary alarm parameter display area is touched to display engine over-vibration parameters, surge parameters and lubricating oil temperature parameters;
and the primary alarm type parameter display area is touched to display the air parking parameters and the ignition parameters of the engine.
According to at least one embodiment of the application, in the above-mentioned system for displaying the engine state parameter in the aircraft cockpit, the display is displayed in a color different from the color of the engine state parameter, in a first color in a normal range, in a second color near the limit boundary, and in a third color beyond the limit boundary.
The application has at least the following beneficial technical effects:
on the one hand, the method for displaying the engine state parameters in the aircraft cockpit divides the engine state parameters into a state indication type parameter, a prompt type parameter, a four-level alarm type parameter, a three-level alarm type parameter, a two-level alarm type parameter and a one-level alarm type parameter according to the influence on the performance and the function of an engine in the aircraft cockpit, and displays the state indication type parameter, the prompt type parameter, the four-level alarm type parameter, the three-level alarm type parameter, the two-level alarm type parameter and the one-level alarm type parameter in a regional mode.
On the other hand, the system for displaying the engine state parameters in the aircraft cockpit is provided, and is used for realizing the method for displaying the engine state parameters in the aircraft cockpit.
Drawings
FIG. 1 is a schematic diagram of a system for displaying engine state parameters in an aircraft cockpit, according to an embodiment of the present disclosure.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; furthermore, the drawings are for illustrative purposes and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The word "comprising" or "comprises", and the like, when used in the description of this application, is intended to indicate that the subject matter presented in front of the word "comprises" or "comprising" includes "that includes" and/or "including" that includes "and/or" includes "that includes" and/or "including" that includes "and/or" including "and/or" including "and/or" including "and.
The present application is described in further detail below with reference to fig. 1.
In one aspect, a method for displaying engine state parameters in an aircraft cockpit is provided, including:
in an aircraft cockpit, dividing the engine state parameters into a state indication class parameter, a prompt class parameter, a four-level alarm class parameter, a three-level alarm class parameter, a two-level alarm class parameter and a one-level alarm class parameter, and displaying the parameters in different areas;
wherein the content of the first and second substances,
the state indicating parameters comprise parameters such as engine starting, stress application and the like;
the prompt parameters comprise parameters which can cause the loss of the control margin of the engine, do not influence the flight safety of the airplane and do not cause the flight degradation;
the class four warning parameters include parameters that degrade engine performance or function, but do not significantly affect engine usage;
the three-level alarm parameters comprise parameters which can degrade the performance or the function of the engine and obviously influence the use of the engine;
secondary alarm class parameters include parameters that can significantly degrade engine performance or function;
the primary alarm class parameters include parameters that may cause a loss of engine performance or function.
For the method for displaying the engine state parameters in the aircraft cockpit disclosed in the above embodiment, it can be understood by those skilled in the art that the method divides the engine state parameters into the state indication type parameter, the prompt type parameter, the fourth-level warning type parameter, the third-level warning type parameter, the second-level warning type parameter and the first-level warning type parameter according to the influence on the performance and function of the engine in the aircraft cockpit, and displays the engine state parameters in different areas.
In some optional embodiments, in the method for displaying the engine state parameters in the aircraft cockpit, the prompt parameters specifically include parameters such as a single-channel measurement fault of a high-speed and low-speed engine, a single-channel measurement fault of an angle of a fan inlet guide vane, a single-channel fault of an angle actuator of the fan inlet guide vane, and the like.
In some optional embodiments, in the method for displaying engine state parameters in an aircraft cockpit, the four-stage warning parameters specifically include parameters such as high engine fuel temperature, measurement fault of a surge differential pressure sensor, measurement fault of a fire detector, and the like.
In some optional embodiments, in the method for displaying the engine state parameters in the aircraft cockpit, the three-level warning parameters specifically include a power-on failure, a high-low pressure rotation speed measurement failure, a fan inlet total temperature double-channel measurement failure, and other parameters.
In some optional embodiments, in the above method for displaying the engine state parameters in the aircraft cockpit, the secondary warning parameters specifically include parameters such as engine over-vibration, surge, and oil temperature.
In some optional embodiments, in the above method for displaying the engine state parameters in the aircraft cockpit, the primary alarm class parameters specifically include an engine in-air stop parameter and a fire parameter.
In some optional embodiments, in the above method for displaying the engine state parameter in the aircraft cockpit, the engine state parameter is displayed in different colors, and is displayed in a first color in a normal range, in a second color near the limit boundary, and in a third color beyond the limit boundary, where the first color may be green, the second color may be blue, and the third color may be red, so as to improve the recognition of the abnormality of the engine state parameter by the driver.
In another aspect, an aircraft cockpit engine status parameter display system is provided, comprising:
the display is arranged in the aircraft cockpit, is accessed into the aircraft health management system, and is provided with a state indication type parameter display area, a prompt type parameter display area, a four-level alarm type parameter display area, a three-level alarm type parameter display area, a two-level alarm type parameter display area and a one-level alarm type parameter display area.
In some optional embodiments, in the above-mentioned system for displaying engine state parameters in an aircraft cockpit, the indication type parameter display area is touched to display parameters such as engine starting and thrust augmentation;
the prompt parameter display area is touched to display parameters of single-channel measurement fault of high and low rotating speeds of the engine, single-channel measurement fault of the angle of a guide vane at a fan inlet, single-channel of an angle actuating mechanism of the guide vane at the fan inlet and the like, the four-level alarm parameter display area is touched to display parameters of high fuel temperature of the engine, measurement fault of a surge pressure difference sensor, measurement fault of a fire alarm detector and the like, the three-level alarm parameter display area is touched to display parameters of stress application connection fault of the engine, measurement fault of high and low rotating speeds, measurement fault of total temperature of the fan inlet and the like, the second-level alarm parameter display area is touched to display parameters of over-vibration, surge, high temperature of lubricating oil and the like of the engine, the first-level alarm parameter display area is touched to display parameters of air stopping, ignition and the like of the engine, thereby realizing layered display of state parameters of the engine and being beneficial to increase the display quantity of state parameters of the aircraft engine, the method is convenient for the pilot to accurately judge the specific situation of the state of the aircraft engine.
With the aircraft cockpit engine state parameter display system disclosed in the above embodiments,
in some optional embodiments, in the above-mentioned system for displaying the engine state parameter in the aircraft cockpit, the display may display the engine state parameter in a different color, and display the engine state parameter in a first color in a normal range, in a second color near the limit boundary, and in a third color beyond the limit boundary, where the first color may be green, the second color may be blue, and the third color may be red.
For the system for displaying the engine state parameter in the aircraft cockpit disclosed in the above embodiment, the description is simple, specific relevant points may refer to the description of relevant parts of the method for displaying the engine state parameter in the aircraft cockpit, and the technical effects may also refer to the technical effects of relevant parts of the method for displaying the engine state parameter in the aircraft cockpit, which are not described herein again.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (10)
1. A method of displaying engine state parameters within an aircraft cockpit, comprising:
in an aircraft cockpit, dividing the engine state parameters into a state indication class parameter, a prompt class parameter, a four-level alarm class parameter, a three-level alarm class parameter, a two-level alarm class parameter and a one-level alarm class parameter, and displaying the parameters in different areas;
wherein the content of the first and second substances,
the state indicating parameters comprise engine starting parameters and stress parameters;
the prompt parameters comprise parameters which can cause the loss of the control margin of the engine, do not influence the flight safety of the airplane and do not cause the flight degradation;
the class four warning parameters include parameters that degrade engine performance or function, but do not significantly affect engine usage;
the three-level alarm parameters comprise parameters which can degrade the performance or the function of the engine and obviously influence the use of the engine;
secondary alarm class parameters include parameters that can significantly degrade engine performance or function;
the primary alarm class parameters include parameters that may cause a loss of engine performance or function.
2. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the prompting parameters specifically comprise single-channel measurement fault parameters of the high and low rotating speeds of the engine, single-channel measurement fault parameters of the fan inlet guide vane angle and single-channel fault parameters of the fan inlet guide vane angle actuating mechanism.
3. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the four-level alarm parameters specifically comprise engine fuel temperature parameters, fault parameters measured by a surge pressure difference sensor and fault parameters measured by a fire alarm detector.
4. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the three-level alarm parameters specifically comprise a power-on switching-on fault parameter, a high-low pressure rotating speed measurement fault parameter and a fan inlet total temperature double-channel measurement fault parameter.
5. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the secondary alarm parameters specifically comprise engine over-vibration parameters, surge parameters and lubricating oil temperature parameters.
6. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the first-level alarm parameters specifically comprise engine air parking parameters and ignition parameters.
7. The method of displaying engine status parameters within an aircraft cockpit according to claim 1,
the engine state parameter is displayed in a first color within the normal range, in a second color near the limit boundary, and in a third color beyond the limit boundary.
8. An engine state parameter display system in an aircraft cockpit, comprising:
the display is arranged in the aircraft cockpit, is accessed into the aircraft health management system, and is provided with a state indication type parameter display area, a prompt type parameter display area, a four-level alarm type parameter display area, a three-level alarm type parameter display area, a two-level alarm type parameter display area and a one-level alarm type parameter display area.
9. An aircraft cockpit engine status parameter display system according to claim 8,
the indication type parameter display area is touched to display the starting parameters and the stress application parameters of the engine;
the prompt type parameter display area is touched to display single-channel measurement fault parameters of the high and low rotating speeds of the engine, single-channel measurement fault parameters of the fan inlet guide vane angle and single-channel fault parameters of the fan inlet guide vane angle actuating mechanism;
the four-level alarm parameter display area is touched to display the fuel temperature parameter of the engine, the surge differential pressure sensor measures the fault parameter, and the fire alarm detector measures the fault parameter;
the three-level alarm parameter display area is touched to display an engine stress application connection fault parameter, a high-low pressure rotating speed measurement fault parameter and a fan inlet total temperature double-channel measurement fault parameter;
the secondary alarm parameter display area is touched to display engine over-vibration parameters, surge parameters and lubricating oil temperature parameters;
and the primary alarm type parameter display area is touched to display the air parking parameters and the ignition parameters of the engine.
10. An aircraft cockpit engine status parameter display system according to claim 8,
the display is displayed in a differentiated color for the engine state parameter, in a first color within the normal range, in a second color near the limit boundary, and in a third color beyond the limit boundary.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111611332.XA CN114235427A (en) | 2021-12-27 | 2021-12-27 | Method and system for displaying engine state parameters in aircraft cockpit |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111611332.XA CN114235427A (en) | 2021-12-27 | 2021-12-27 | Method and system for displaying engine state parameters in aircraft cockpit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107764338A (en) * | 2017-11-30 | 2018-03-06 | 中国科学院工程热物理研究所 | Unmanned plane sensor parameters acquisition system |
| CN108369103A (en) * | 2015-06-12 | 2018-08-03 | 国立民用航空学院 | Based on movable resource management system |
| CN113283315A (en) * | 2021-05-12 | 2021-08-20 | 中国航空工业集团公司上海航空测控技术研究所 | Multi-flight-state helicopter fault dynamic monitoring and alarming method |
| CN113672670A (en) * | 2021-07-23 | 2021-11-19 | 中国航空工业集团公司上海航空测控技术研究所 | Aircraft CAS alarm message-based aircraft structured manual display method |
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- 2021-12-27 CN CN202111611332.XA patent/CN114235427A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108369103A (en) * | 2015-06-12 | 2018-08-03 | 国立民用航空学院 | Based on movable resource management system |
| CN107764338A (en) * | 2017-11-30 | 2018-03-06 | 中国科学院工程热物理研究所 | Unmanned plane sensor parameters acquisition system |
| CN113283315A (en) * | 2021-05-12 | 2021-08-20 | 中国航空工业集团公司上海航空测控技术研究所 | Multi-flight-state helicopter fault dynamic monitoring and alarming method |
| CN113672670A (en) * | 2021-07-23 | 2021-11-19 | 中国航空工业集团公司上海航空测控技术研究所 | Aircraft CAS alarm message-based aircraft structured manual display method |
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