CN108255150B - Judgment method for automatically adjusting overload limit of airplane - Google Patents
Judgment method for automatically adjusting overload limit of airplane Download PDFInfo
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- CN108255150B CN108255150B CN201711293924.5A CN201711293924A CN108255150B CN 108255150 B CN108255150 B CN 108255150B CN 201711293924 A CN201711293924 A CN 201711293924A CN 108255150 B CN108255150 B CN 108255150B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0221—Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24048—Remote test, monitoring, diagnostic
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- Automation & Control Theory (AREA)
- Traffic Control Systems (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention belongs to the aviation aircraft control technology, and relates to a judgment method for automatically adjusting aircraft overload limit. The invention adjusts the overload limit of an airplane according to the fuel quantity information of an external fuel tank, comprising the following steps: 1) automatically judging the plug-in configuration and designing a monitoring logic; 2) and (3) monitoring the fuel quantity of the external auxiliary fuel tank and generating a logic design of a fuel exhaustion signal. The invention utilizes the comprehensive interaction capability of multi-system data of a new generation of fighter to realize the integration of wing hanging point information and the quantity of external oil tank oil, and improves the utilization rate of the maneuvering capability of the airplane on the premise of ensuring the safety not to be reduced.
Description
Technical Field
The invention belongs to the aviation aircraft control technology, and relates to a judgment method for automatically adjusting aircraft overload limit.
Background
The traditional three-generation aircraft lacks data cross-linking among three systems of flight control, electromechanics and tasks, the configuration used by the flight control law of the traditional three-generation aircraft requires a pilot to select manually, and the flight safety is influenced due to selection errors caused by human negligence. Meanwhile, when the external fuel tank is in a configuration flight, the control law cannot automatically select proper load limitation according to the fuel quantity of the external fuel tank, and a pilot needs to perform manual judgment, so that the remaining maneuvering capacity of the airplane cannot be fully exerted when the fuel quantity of the airplane is exhausted.
Disclosure of Invention
The purpose of the invention is: the judgment method for automatically adjusting the overload limit of the airplane is characterized in that on the basis of hanging point information acquired by a hangar management system and oil quantity information acquired by an electromechanical system, the matching of a suspended structure is monitored, the oil quantity is monitored and calculated in real time, and the calculation of oil utilization signals and effectiveness of a control law is realized.
The technical scheme of the invention is as follows: a judgment method for automatically adjusting aircraft overload limit, which adjusts the aircraft overload limit according to the external fuel tank fuel quantity information, comprises the following steps:
1) external hanging configuration automatic judgment and monitoring logic design
The flight control system can automatically judge the configuration of the aircraft in the air or in the air by acquiring the aircraft plug-in information acquired by the electromechanical system;
in the automatic judgment process, firstly, redundant oil tank hanging point data collected by an electromechanical system remote collecting unit is selected for hanging point suspension confirmation, and if the redundant oil tank hanging point data is separated, the automatic configuration is judged to be invalid; then, comparing the hanging point hanging confirmation result of the under-wing hanging with the data reported by the task system hanging object management system, if the two are contradictory, judging that the automatic configuration is invalid, otherwise, judging the control law type of the flight control system as a hanging point information indication state;
in addition to obtaining the automatic configuration state through the electromechanical management system and the suspension management system, a pilot can also manually select the current control law to be flown according to the actual situation, and the flight control system judges that the automatic configuration is invalid at the moment;
2) external auxiliary fuel tank fuel quantity monitoring and fuel-out signal generation logic design
The method comprises the steps of monitoring the oil quantity of an externally-hung auxiliary oil tank and generating a logic of an oil exhaustion signal, judging the oil consumption of the externally-hung oil tank, and using the generated oil exhaustion signal for controlling overload limiting conditions of a law, wherein the logic is as follows:
2.1) when the external hanging configuration automatic judgment and monitoring logic judges that the automatic configuration fails, setting an oil-out signal as a safety value-oil-out;
2.2) sequentially judging the hanging points with hanging in the oil tank hanging points;
2.3) performing an AND operation on the judgment results of all the oil tank hanging point signals, wherein the result is an oil exhaustion signal used by a control law;
for the effectiveness of the oil-out signal, the source of the effectiveness is the effectiveness of the oil quantity collected by the external auxiliary oil tank of the electromechanical system, whether the measured oil quantity is accurate is represented, and the filtering combination judgment is carried out according to the following mode:
a) if the corresponding hanging point oil quantity signal is invalid for a plurality of continuous beats, setting the hanging point oil-out signal invalid 0;
b) when the hanging point oil mass signal is effective for a plurality of continuous beats, the hanging point oil-out signal is recovered to be effective 1;
c) the validity phases of all the oil tank hanging point signals are compared, and the result is the validity of the oil-out signal used by the control law;
after the validity of the oil-out signal and the oil-out signal is integrated, an overload limitation releasing sign of the control law is generated, the sign can be set to be 1 only when the oil-out signal is 1, the validity of the oil-out signal is 1, and the automatic configuration judgment is valid, so that the overload limitation is released without considering the load under the wing of the airplane by the control law, and the maximum maneuvering performance of the airplane is realized while the pilot operates without worry.
The invention has the beneficial effects that: according to the invention, through the software and data interactive design, the flight control system needs to acquire the related plug-in data of the task system and the electromechanical system at the same time and monitor the propriety of the data, when the data is invalid, the oil-out state is set according to the fault safety, when the data is valid, the oil-out signal is settled in a 15ms period according to the algorithm, and meanwhile, the maximization of the pilot authority under any condition is ensured through monitoring the configuration. The invention also provides an effective judgment criterion according to the comprehensive external hanging configuration of the suspension management system and the suspension signal of the electromechanical oil tank, so that the reliability of the oil quantity information calculation and the safety of the use of the control law are guaranteed.
Drawings
FIG. 1 is a schematic view of an electromechanical management system and a suspension management system according to the present invention;
FIG. 2 is a logic diagram for judging the oil exhaustion of the external oil tank in the present invention.
Detailed Description
The following further describes the embodiments of the present invention with reference to the drawings.
The advanced control law design of the fourth generation advanced fighter represented by a certain type of machine enables a pilot to realize carefree operation in each flight envelope and to exchange a plurality of limiting conditions including overload and attack angle with a flight control computer. The judgment of the limiting conditions is not only related to the flight state, but also closely related to the external hanging state of the airplane, and due to the fact that the airplane adopts an advanced multi-system interactive management design, the flight control system can acquire the external hanging and weight information of the airplane through the airplane management system, and after the information is logically judged, the reliable oil-out state of the external hanging oil tank can be obtained for the control law to conduct airplane control parameter adjustment and flight envelope adjustment.
The invention discloses a judgment method for automatically adjusting aircraft overload limit, which adjusts the aircraft overload limit according to the external fuel tank fuel quantity information and comprises the following steps:
1) external hanging configuration automatic judgment and monitoring logic design
The flight control system can automatically judge the configuration of the aircraft in the air or in the air by acquiring the aircraft plug-in information acquired by the electromechanical system;
in the automatic judgment process, firstly, redundant oil tank hanging point data collected by an electromechanical system remote collecting unit is selected for hanging point suspension confirmation, and if the redundant oil tank hanging point data is separated, the automatic configuration is judged to be invalid; then, comparing the hanging point hanging confirmation result of the under-wing hanging with the data reported by the task system hanging object management system, if the two are contradictory, judging that the automatic configuration is invalid, otherwise, judging the control law type of the flight control system as a hanging point information indication state;
as shown in fig. 1, in addition to obtaining the automatic configuration state through the electromechanical management system and the suspension management system, the pilot may also manually select the current flight control law according to the actual situation, and at this time, the flight control system also determines that the automatic configuration is invalid;
2) external auxiliary fuel tank fuel quantity monitoring and fuel-out signal generation logic design
When the aircraft is in the external auxiliary fuel tank, the structural stress and the overload are proportional due to the external hanging, so that the control law can be limited for overload according to the characteristic of careless operation of the fourth generation of aircraft, and the limitation needs to be timely removed when the fuel oil of the external auxiliary fuel tank of the aircraft is exhausted, so that the maximum maneuverability of the aircraft can be exerted.
Therefore, the external auxiliary oil tank fuel quantity monitoring and oil-out signal generating logic designed by the invention can judge the consumption of the external oil tank fuel quantity, and the generated oil-out signal can be used for controlling the overload limiting condition of the law, and the related detailed logic is as follows:
2.1) when the external hanging configuration automatic judgment and monitoring logic judges that the automatic configuration fails, setting an oil-out signal as a safety value-oil-out;
2.2) sequentially judging whether hanging points exist among the hanging points No. 1, 2, 11 and 12 in the figure 1, wherein the judgment logic is as shown in figure 2.
2.3) performing an ANDing operation on the judgment results of the 4 hanging point signals, wherein the result is an oil-out signal used by a control law;
for the effectiveness of the oil-out signal, the source of the effectiveness is the effectiveness of the oil quantity collected by the external auxiliary oil tank of the electromechanical system, whether the measured oil quantity is accurate is represented, and the filtering combination judgment is carried out according to the following mode:
a) if the corresponding hanging point oil quantity signal is invalid by 12 continuous beats, setting the hanging point oil-out signal invalid 0;
b) when the hanging point oil mass signal is continuously effective for 12 beats, the hanging point oil-out signal is recovered to be effective 1;
c) comparing the validity phases of the 4 hanging point signals, wherein the result is the validity of the oil-out signal used by the control law;
after the validity of the oil-out signal and the oil-out signal is integrated, an overload limitation releasing sign of the control law can be generated, the sign can be set to be 1 only when the oil-out signal is 1, the validity of the oil-out signal is 1, and the automatic configuration judgment is valid, so that the overload limitation can be released without considering the load under the wing of the airplane by representing the control law at the moment, and the maximum maneuvering performance of the airplane can be realized while the pilot operates without worry.
The invention realizes the integration of wing hanging point information and external oil tank oil mass by utilizing the comprehensive interaction capacity of multi-system data of a new generation of fighter. The oil quantity of the all-aircraft mounted auxiliary oil tank is calculated according to the oil quantity information sent by the system, and the generated oil-out signal is used for controlling the release of the law overload limitation.
Claims (1)
1. A method for automatically adjusting aircraft overload limits, comprising: the method for adjusting the overload limit of the airplane according to the fuel quantity information of the external fuel tank comprises the following steps:
1) external hanging configuration automatic judgment and monitoring logic design
The flight control system can automatically judge the configuration of the aircraft in the air or in the air by acquiring the aircraft plug-in information acquired by the electromechanical system;
in the automatic judgment process, firstly, redundant oil tank hanging point data collected by an electromechanical system remote collecting unit is selected for hanging point suspension confirmation, and if the redundant oil tank hanging point data is separated, the automatic configuration is judged to be invalid; then, comparing the hanging point hanging confirmation result of the under-wing hanging with the data reported by the task system hanging object management system, if the two are contradictory, judging that the automatic configuration is invalid, otherwise, judging the control law type of the flight control system as a hanging point information indication state;
in addition to obtaining the automatic configuration state through the electromechanical management system and the suspension management system, a pilot can also manually select the current control law to be flown according to the actual situation, and the flight control system judges that the automatic configuration is invalid at the moment;
2) external auxiliary fuel tank fuel quantity monitoring and fuel-out signal generation logic design
The method comprises the steps of monitoring the oil quantity of an externally-hung auxiliary oil tank and generating a logic of an oil exhaustion signal, judging the oil consumption of the externally-hung oil tank, and using the generated oil exhaustion signal for controlling overload limiting conditions of a law, wherein the logic is as follows:
2.1) when the external hanging configuration automatic judgment and monitoring logic judges that the automatic configuration fails, setting an oil-out signal as a safety value-oil-out;
2.2) sequentially judging the hanging points with hanging in the oil tank hanging points;
2.3) performing an AND operation on the judgment results of all the oil tank hanging point signals, wherein the result is an oil exhaustion signal used by a control law;
for the effectiveness of the oil-out signal, the source of the effectiveness is the effectiveness of the oil quantity collected by the external auxiliary oil tank of the electromechanical system, whether the measured oil quantity is accurate is represented, and the filtering combination judgment is carried out according to the following mode:
a) if the corresponding hanging point oil quantity signal is invalid by 12 continuous beats, setting the hanging point oil-out signal invalid 0;
b) when the hanging point oil mass signal is continuously effective for 12 beats, the hanging point oil-out signal is recovered to be effective 1;
c) the validity phases of all the oil tank hanging point signals are compared, and the result is the validity of the oil-out signal used by the control law;
after the validity of the oil-out signal and the oil-out signal is integrated, an overload limitation releasing sign of the control law is generated, the sign can be set to be 1 only when the oil-out signal is 1, the validity of the oil-out signal is 1, and the automatic configuration judgment is valid, so that the overload limitation is released without considering the load under the wing of the airplane by the control law, and the maximum maneuvering performance of the airplane is realized while the pilot operates without worry.
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| CN201711293924.5A CN108255150B (en) | 2017-12-08 | 2017-12-08 | Judgment method for automatically adjusting overload limit of airplane |
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| CN201711293924.5A CN108255150B (en) | 2017-12-08 | 2017-12-08 | Judgment method for automatically adjusting overload limit of airplane |
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| CN108255150A CN108255150A (en) | 2018-07-06 |
| CN108255150B true CN108255150B (en) | 2020-12-29 |
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| CN111006749B (en) * | 2019-12-25 | 2021-07-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for calculating and alarming longitudinal limit overload limit value of airplane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329450A (en) * | 2015-11-01 | 2016-02-17 | 四川泛华航空仪表电器有限公司 | Airborne fuel system remote interface unit |
| CN105468851A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining aircraft dynamic weight characteristic |
| CN205748559U (en) * | 2016-06-27 | 2016-11-30 | 苏州天亿达科技有限公司 | Auxiliary tank of aircraft detection equipment |
| CN206125449U (en) * | 2016-09-23 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Trainer aircraft redundancy human -computer interaction system |
| RU2619793C1 (en) * | 2016-04-14 | 2017-05-18 | Акционерное общество "Российская самолетостроительная корпорация "МиГ" (АО "РСК "МиГ") | System of automatic control of the aircraft at the climb and stabilization of the total height of the flight |
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- 2017-12-08 CN CN201711293924.5A patent/CN108255150B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329450A (en) * | 2015-11-01 | 2016-02-17 | 四川泛华航空仪表电器有限公司 | Airborne fuel system remote interface unit |
| CN105468851A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining aircraft dynamic weight characteristic |
| RU2619793C1 (en) * | 2016-04-14 | 2017-05-18 | Акционерное общество "Российская самолетостроительная корпорация "МиГ" (АО "РСК "МиГ") | System of automatic control of the aircraft at the climb and stabilization of the total height of the flight |
| CN205748559U (en) * | 2016-06-27 | 2016-11-30 | 苏州天亿达科技有限公司 | Auxiliary tank of aircraft detection equipment |
| CN206125449U (en) * | 2016-09-23 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Trainer aircraft redundancy human -computer interaction system |
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