CN111252258A - Fault interlocking method for inclined plate adjusting system - Google Patents
Fault interlocking method for inclined plate adjusting system Download PDFInfo
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- CN111252258A CN111252258A CN202010022634.2A CN202010022634A CN111252258A CN 111252258 A CN111252258 A CN 111252258A CN 202010022634 A CN202010022634 A CN 202010022634A CN 111252258 A CN111252258 A CN 111252258A
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- swash plate
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- adjusting system
- adjustment system
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 230000008859 change Effects 0.000 claims description 10
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 230000002411 adverse Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 6
- 238000001514 detection method Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000035772 mutation Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Testing Of Engines (AREA)
- Feedback Control In General (AREA)
Abstract
The application belongs to the field of airplane air inlet swash plate adjusting systems, and particularly relates to a fault interlocking method for a swash plate adjusting system. The method comprises the following steps: determining a failure mode of the swash plate adjustment system; and identifying the fault mode through a digital absolute pressure ratio computer of the inclined plate adjusting system, and sending a fault interlocking signal to the servo valve to lock the inclined plate so as to avoid parking in the air. The fault interlocking method for the swash plate adjusting system can avoid the engine in-air parking caused by the fault of the swash plate adjusting system, can identify and isolate the dangerous fault state causing the engine in-air parking, avoids causing serious adverse effect, and meets the use requirements of the outfield airplane.
Description
Technical Field
The application belongs to the field of airplane air inlet swash plate adjusting systems, and particularly relates to a fault interlocking method for a swash plate adjusting system.
Background
The air inlet sloping plate adjusting system of the airplane is an important functional system related to flight safety and airplane performance, and has the main functions of automatically and continuously adjusting the rotating angle of the air inlet sloping plate and changing the air inlet flow so as to ensure that the common work of an air inlet and an engine is in the best matching state, thereby obtaining the maximum effective thrust of the engine, stably working and preventing the surge of the air inlet. When the airplane is used in an external field, accidents of air parking caused by faults of the inclined plate adjusting system can occur, and serious adverse effects can be caused in the aspect of safety.
The inclined plate regulating system of the airplane is divided into an analog automatic control system and a digital automatic control system. Due to the restriction of the component parts of the analog control system and the comprehensive technical level in the design stage, the analog control system does not have complex fault detection and fault isolation functions and can only realize alarm and interlocking functions in some simple modes. Although a digital control system is provided with computer products, certain specific fault modes are not predicted enough in the design stage, and certain fault alarm modes are set, but in the actual use process of the airplane, the system still has difficulty in identifying and isolating dangerous fault states causing engine in-flight stop.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a fault interlocking method of a swash plate adjusting system, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a swash plate adjustment system fault interlock method comprising:
determining a failure mode of the swash plate adjustment system;
and identifying the fault mode through a digital absolute pressure ratio computer of the inclined plate adjusting system, and sending a fault interlocking signal to the servo valve to lock the inclined plate so as to avoid parking in the air.
Optionally, the determining the failure mode of the swash plate adjustment system includes:
and setting a first threshold value, and when the angle change rate of the inclined plate is greater than the first threshold value, determining that the fault mode of the inclined plate adjusting system is a first fault mode.
Optionally, the first threshold is 4 °/s.
Optionally, the determining the failure mode of the swash plate adjustment system includes:
and setting a second threshold value, and determining that the fault mode of the swash plate adjusting system is a second fault mode when the swash plate deviation initial position is greater than the second threshold value when the start condition of the swash plate adjusting system is not met.
Optionally, the second threshold is 2 °.
Optionally, the determining the failure mode of the swash plate adjustment system includes:
and setting a third threshold value, and determining that the fault mode of the swash plate regulating system is a third fault mode when the difference value between the actual position of the swash plate and the theoretical position of the swash plate output by the digital absolute pressure ratio computer is greater than the third threshold value.
Optionally, the third threshold is 3 °.
The invention has at least the following beneficial technical effects:
the fault interlocking method for the swash plate adjusting system can avoid the engine in-air parking caused by the fault of the swash plate adjusting system, can identify and isolate the dangerous fault state causing the engine in-air parking, avoids causing serious adverse effect, and meets the use requirements of the outfield airplane.
Drawings
FIG. 1 is a flow chart of a swash plate adjustment system fault interlock method according to one embodiment of the present application;
FIG. 2 is a recorded plot of an engine in-flight shutdown flight parameter of an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides a fault interlocking method for an inclined plate adjusting system, which comprises the following steps:
determining a failure mode of the swash plate adjustment system;
the failure mode is identified by a digital absolute pressure ratio computer of the sloping plate adjusting system, and a failure interlocking signal is sent to the servo valve to lock the sloping plate and avoid parking in the air.
The core technology of the fault interlocking method for the swash plate adjusting system is to determine the fault mode of the swash plate adjusting system and select a digital absolute pressure ratio computer of the digital swash plate adjusting system as a fault identification component. In this embodiment, three failure mode determination methods are provided.
In the normal flight process of the airplane, the inclined plate adjusting system pi is adjusted according to the working characteristics of an engine and an air inlet channelkValue according to engine state, flying M number and heightThe temperature and the total atmospheric temperature are continuously changed, no sudden jump occurs, the change rate of the temperature and the total atmospheric temperature does not exceed a certain value, and according to the control principle of the inclined plate adjusting system, the opening angle of the inclined plate does not suddenly change in the flight process, and the change rate of the angle does not exceed a certain value. And under certain flight conditions and engine states, the angle change rate of the inclined plate is used as a basis for judging whether the inclined plate adjusting system fails.
In this embodiment, determining the failure mode of the swash plate adjustment system includes: and setting a first threshold value, and determining that the failure mode of the swash plate adjusting system is a first failure mode when the swash plate angle change rate is greater than the first threshold value. Aiming at the fault mode, an alarm function is set in the digital absolute pressure ratio computer, the flight parameter record data of the airplane, the working state of an engine, the ground maintenance condition of the airplane and the working principle of an inclined plate adjusting system are comprehensively considered, if the abnormal angle change rate of the inclined plate is detected, the digital absolute pressure ratio computer outputs an alarm signal, the inclined plate is locked at the fault position, and the aerial parking is avoided.
In one embodiment of the present application, the flight reference data for the aircraft with the right engine on-air stop is shown in table 1 and the flight reference curve is shown in fig. 2.
TABLE 1
| t | n1L | n1R | P2L | P2R | θL | θR |
| 13'53" | 101.1 | 101.5 | 414.4 | 403.2 | 7.43 | 7.5 |
| 13'54" | 408.8 | 392 | 7.35 | 7.35 | ||
| 13'55" | 100.9 | 100.9 | 397.6 | 274.4 | 7.28 | 7.35 |
| 13'56" | 386.4 | 100.8 | 7.2 | 12.09(M number 1.82) | ||
| 13'57" | 100.9 | 99.5 | 375.2 | 89.6 | 7.13 | 14.73 |
| 13'58" | 369.6 | 89.6 | 7.05 | 15.41 | ||
| 13'59" | 100.9 | 80 | 358.4 | 89.6 | 6.9 | 15.63 |
| 14’ | 352.8 | 84 | 6.83 | 15.71 | ||
| 14'01" | 101.2 | 72.4 | 347.2 | 78.4 | 6.68 | 15.78 |
In the above table, t is the time, and n1R is the low-pressure rotor speed of the right engine; n1L is the left engine low pressure rotor speed; p2RFor the right hairThe outlet pressure of the engine compressor; p2LIs the left engine compressor outlet pressure; thetaRIs the angle of the right sloping plate; thetaLIs the angle of the left sloping plate.
As can be seen from table 1 and fig. 2, before the occurrence of an air stop of the right engine, the opening angle θ of the right swash plateRA mutation occurs.
And comprehensively considering the flight parameter recorded data of the airplane, the working state of an engine, the ground maintenance condition of the airplane and the working principle of a swash plate adjusting system, and determining the alarm time and the alarm quantity value of the angle change rate of the swash plate of the airplane. In one embodiment of the present application, the first failure mode is identified by a digital absolute pressure ratio computer of the swash plate adjustment system:
(1) when the control voltage value U of the inclined plateπkAnd a feedback voltage magnitude UfWhen the corresponding plate position angle change rates are all larger than 4 degrees/s, carrying out rate regulation alarm, namely setting the first threshold value to be 4 degrees/s;
(2) when the starting signal of the inclined plate is effective and the stress application signal is switched on from off, the speed regulation alarm check is delayed by 3s and then started;
(3) when the M1.5 discrete magnitude signal is switched on from off, the speed regulation alarm check is delayed by 3s and then started;
(4) when the aircraft decelerates such that the M1.5 discrete magnitude signal goes from on to off and the boost signal is still active, the throttle rate alarm check delay 4s begins again.
According to the working principle of the swash plate adjusting system, under the condition that the starting condition of the swash plate system is not met (M is less than or equal to 1.4), the swash plate is locked at an initial position, but the swash plate is mistakenly opened or locked due to the failure of an atmospheric machine, the failure of a relay of the swash plate adjusting system or the failure of a servo valve of the swash plate, so that the air inlet/outlet mismatching is caused, and the surge or the stop of an engine is caused.
In this embodiment, determining the failure mode of the swash plate adjustment system includes: and setting a second threshold value, and determining that the fault mode of the swash plate adjusting system is a second fault mode when the starting condition of the swash plate adjusting system is not met and the deviation initial position of the swash plate is greater than the second threshold value. Aiming at the fault mode, an alarm function is set in the digital absolute pressure ratio computer, various states of the airplane and the engine are comprehensively considered, and when the system does not meet the starting and adjusting conditions, if abnormal output of the inclined plate is detected, the digital absolute pressure ratio computer outputs an alarm signal to lock the inclined plate at the fault position, so that the aerial parking is avoided.
In one embodiment of the present application, the second failure mode is identified by the digital absolute pressure ratio computer of the swash plate adjustment system:
(1) when the start tone signal of the inclined plate is invalid and the actual plate position angle is greater than 2 degrees, generating zero position alarm;
(2) when the start signal of the inclined plate is switched from effective to ineffective, the zero position detection is carried out after delaying for 5 s.
According to the working principle of the swash plate adjusting system, in the normal flight process, the actual position of the swash plate is consistent with the theoretical position of the swash plate output by the digital absolute pressure ratio computer, and if the difference value between the actual position and the theoretical position exceeds a certain range, the fault state of the system is indicated.
In this embodiment, determining the failure mode of the swash plate adjustment system includes: and setting a third threshold value, and determining that the fault mode of the swash plate regulating system is a third fault mode when the difference value between the actual position of the swash plate and the theoretical position of the swash plate output by the digital absolute pressure ratio computer is greater than the third threshold value. Aiming at the fault mode, an alarm function is set in the digital absolute pressure ratio computer to control the voltage U of the inclined plateπkAnd a feedback voltage magnitude UfAnd comparing, and outputting an alarm signal by the digital absolute pressure ratio computer if the deviation between the theoretical value and the actual value of the inclined plate angle is detected to be overlarge according to the static error and the dynamic response speed of the control system and the reference flight parameter recorded data.
In one embodiment of the present application, the third failure mode is identified by the digital absolute pressure ratio computer of the swash plate adjustment system: when the boosting signal and the starting signal of the inclined plate are effective at the same time, the difference value between the actual plate position angle and the theoretical plate position angle is detected, and if the difference value is more than 3 degrees, an adjusting out-of-tolerance alarm signal is generated.
The fault interlocking method for the swash plate adjusting system can solve the problem that the outdoor aircraft stops in the air due to faults of the swash plate adjusting system in the using process. The method has complex fault detection and fault isolation functions, can realize alarm and interlocking functions in complex modes, and can identify and isolate dangerous fault states which can cause the engine to stop in the air in the actual use process of the airplane.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A swash plate adjustment system fault interlock method, comprising:
determining a failure mode of the swash plate adjustment system;
and identifying the fault mode through a digital absolute pressure ratio computer of the inclined plate adjusting system, and sending a fault interlocking signal to the servo valve to lock the inclined plate so as to avoid parking in the air.
2. The swash plate adjustment system fault interlocking method according to claim 1, wherein the determining the fault mode of the swash plate adjustment system includes:
and setting a first threshold value, and when the angle change rate of the inclined plate is greater than the first threshold value, determining that the fault mode of the inclined plate adjusting system is a first fault mode.
3. The swash plate adjustment system fault interlocking method according to claim 2, wherein the first threshold value is 4 °/s.
4. The swash plate adjustment system fault interlocking method according to claim 2, wherein the determining the fault mode of the swash plate adjustment system includes:
and setting a second threshold value, and determining that the fault mode of the swash plate adjusting system is a second fault mode when the swash plate deviation initial position is greater than the second threshold value when the start condition of the swash plate adjusting system is not met.
5. The swash plate adjustment system fault interlocking method according to claim 4, wherein the second threshold value is 2 °.
6. The swash plate adjustment system fault interlocking method according to claim 2, wherein the determining the fault mode of the swash plate adjustment system includes:
and setting a third threshold value, and determining that the fault mode of the swash plate regulating system is a third fault mode when the difference value between the actual position of the swash plate and the theoretical position of the swash plate output by the digital absolute pressure ratio computer is greater than the third threshold value.
7. The swash plate adjustment system fault interlocking method according to claim 6, wherein the third threshold value is 3 °.
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| CN202010022634.2A CN111252258B (en) | 2020-01-09 | 2020-01-09 | Fault interlocking method for inclined plate adjusting system |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730701A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Secondary flow system capable of changing secondary flow inlet area |
| CN106741975A (en) * | 2016-12-19 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of full electric drive inlet ramp regulation and control system |
| CN207195039U (en) * | 2017-06-26 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of parallel inlet central body |
| CN109159903A (en) * | 2018-08-23 | 2019-01-08 | 广州创链科技有限公司 | A kind of unmanned vehicle engine progress implication flow modulation device |
| KR102007880B1 (en) * | 2018-11-19 | 2019-08-06 | 박성규 | Variable air volume regulation device and control method of this |
-
2020
- 2020-01-09 CN CN202010022634.2A patent/CN111252258B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730701A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Secondary flow system capable of changing secondary flow inlet area |
| CN106741975A (en) * | 2016-12-19 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of full electric drive inlet ramp regulation and control system |
| CN207195039U (en) * | 2017-06-26 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of parallel inlet central body |
| CN109159903A (en) * | 2018-08-23 | 2019-01-08 | 广州创链科技有限公司 | A kind of unmanned vehicle engine progress implication flow modulation device |
| KR102007880B1 (en) * | 2018-11-19 | 2019-08-06 | 박성규 | Variable air volume regulation device and control method of this |
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