CN115030824B - Self-adaptive oil supply system and method under full flight profile of helicopter - Google Patents
Self-adaptive oil supply system and method under full flight profile of helicopter Download PDFInfo
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- CN115030824B CN115030824B CN202210958098.6A CN202210958098A CN115030824B CN 115030824 B CN115030824 B CN 115030824B CN 202210958098 A CN202210958098 A CN 202210958098A CN 115030824 B CN115030824 B CN 115030824B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/70—Type of control algorithm
- F05D2270/706—Type of control algorithm proportional-integral-differential
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a self-adaptive oil supply system and a self-adaptive oil supply method under a full flight profile of a helicopter, wherein the system comprises an onboard power supply, a control device, an oil supply pump, a fuel tank, a pressure sensor and an engine; the power supply end of the control device is connected with an onboard power supply through a cable, and the control end of the control device is connected with an oil supply pump arranged in the fuel tank through a cable; the oil supply pump is connected with the engine through an oil supply pipeline, and pressure sensors are arranged on the oil supply pipeline on the outlet side of the oil supply pump and the oil supply pipeline on the inlet side of the engine and are connected with the signal input end of a control signal through a cable. The invention collects the engine inlet pressure in real time on the full flight section of the helicopter, compares the engine inlet pressure with the set engine inlet pressure value, calculates, adjusts the rotating speed of the fuel feed pump in real time through the control device, adjusts the fuel feed pressure, ensures that the engine inlet pressure of the helicopter is maintained at the set value in the full-flight section of the full flow range, positive overload, no overload and negative overload, meets the requirement of the inlet of the engine and ensures the flight safety.
Description
Technical Field
The invention belongs to the technical field of oil supply of a helicopter secondary system, and particularly relates to a self-adaptive oil supply system and method under a full flight profile of a helicopter.
Background
The mounting height between the helicopter oil supply system and the engine is high, when the maneuvering flight is carried out on the full flight section, the fuel oil in the oil supply pipe between the fuel oil system and the engine generates downward/upward overload force under the positive/negative overload condition to cause the reduction/increase of the oil supply pressure, if the oil supply pressure is not adjusted in real time under the flight condition, the engine has the fault of air parking after the oil supply pressure exceeds the inlet pressure range of the engine,
by adopting the technology of adjusting the oil supply pressure by adopting self-adaptive closed-loop control, the inlet pressure of the engine is ensured not to exceed the limit, and the flight safety is ensured.
Disclosure of Invention
Aiming at the defects in the prior art, the self-adaptive oil supply system and the self-adaptive oil supply method under the full flight profile of the helicopter provided by the invention solve the problem that the self-adaptive adjustment of the oil supply system is difficult to realize under overload conditions and normal flight switching processes due to the height difference between the engine and the fuel tank of the helicopter, so that the helicopter stops in the air.
In order to achieve the purpose of the invention, the invention adopts the technical scheme that: a self-adaptive oil supply system under a full flight section of a helicopter is characterized by comprising an onboard power supply, a control device, an oil supply pump, a fuel tank, a pressure sensor and an engine;
the power supply end of the control device is connected with the onboard power supply through a cable, and the control end of the control device is connected with an oil supply pump arranged in the fuel tank through a cable;
the oil supply pump is connected with the engine through an oil supply pipeline, and a first pressure sensor and a second pressure sensor are respectively arranged on the oil supply pipeline on the outlet side of the oil supply pump and the oil supply pipeline on the inlet side of the engine;
and the first pressure sensor and the second pressure sensor are connected with the signal input end of the control device through cables.
Further, the control device comprises a preprocessor, a fuzzy controller and a PID controller;
the preprocessor is used for calculating an error and an error change rate of an oil supply pressure value between the preprocessor and the pressure value at the inlet side of the engine, which is acquired by the second pressure sensor, according to a set pressure value, and inputting the error and the error change rate into the fuzzy controller;
the fuzzy controller is used for calculating a PID parameter according to the input oil supply pressure value error and the error change rate and inputting the PID parameter into the PID controller;
the PID controller is used for generating a duty ratio control signal according to an input PID parameter, adjusting the rotating speed of a motor in the oil supply pump according to the duty ratio control signal, and further controlling the pressurization capacity of the oil supply pump;
and the rotating speed of the motor in the oil supply pump, and pressure signals acquired by the first pressure sensor and the second pressure sensor are transmitted to the preprocessor together.
A self-adaptive oil supply method under a full flight profile of a helicopter comprises the following steps: s1, determining a pressure state of an inlet side of an engine on a helicopter;
and S2, regulating the rotating speed of a motor in the oil supply pump through a control device according to the pressure state of the inlet side of the engine and the pressure data acquired by the first pressure sensor and the second pressure sensor so as to keep the pressure of the inlet side of the engine constant and realize self-adaptive oil supply.
Further, the step S1 is specifically to acquire a pressure signal on the inlet side of the engine through a second pressure sensor, and compare the pressure signal with a set pressure value, so as to determine a pressure state on the inlet side of the engine;
the pressure state comprises a normal state, a state higher than a set pressure value and a state lower than a set pressure value.
Further, in the step S2, in a normal state, the control device adjusts the rotation speed of the motor in the fuel feed pump to be constant, and stabilizes the pressurization capacity of the fuel feed pump, so as to keep the pressure on the inlet side of the engine constant, thereby implementing adaptive fuel feeding;
under the condition of being lower than the pressure set value, the rotating speed of a motor in the oil supply pump is adjusted to be increased through the control device, and the supercharging capacity of the oil supply pump is improved, so that the pressure on the inlet side of the engine is kept constant, and self-adaptive oil supply is realized;
and under the condition that the pressure value is higher than the set pressure value, the rotating speed of a motor in the oil supply pump is regulated to be reduced through the control device, and the supercharging capacity of the oil supply pump is reduced, so that the pressure on the inlet side of the engine is kept constant, and self-adaptive oil supply is realized.
Further, the oil supply pump outlet side pressure
Comprises the following steps:
the engine inlet side pressure
Comprises the following steps:
in the formula (I), the compound is shown in the specification,
the pressure of the oil supply pump is increased,
as the density of the fuel oil,ais the absolute acceleration of the aircraft and,his the height of the liquid level in the fuel tank,
in order to supply the mounting height of the oil pump to the engine,a 0 is the overload acceleration;
the engine inlet side pressure is normal
Controlling the pressurization capacity of the pump to be unchanged;
the engine inlet side pressure is lower than the pressure set value
Control the pressure boosting capacity of the fuel feed pump to be improved
；
The pressure at the inlet side of the engine is higher than the set pressure valueAt the state of the engine inlet side pressure
Control the decrease of the pressurizing capacity of the feed pump
。
Further, the method for adjusting the rotating speed of the motor in the oil supply pump through the control device specifically comprises the following steps:
a1, calculating an oil supply pressure value error and an error change rate between a set pressure value in a control device and the pressure at the inlet side of the engine acquired by a second pressure sensor;
a2, taking the calculated error and the error change rate of the oil supply pressure value as the input of a fuzzy controller, obtaining a PID parameter and inputting the PID parameter into the PID controller;
and A3, outputting a PWM duty ratio control signal in the PID controller according to the input PID control parameter, and adjusting the rotating speed of a motor in the oil supply pump according to the PWM duty ratio control signal.
Further, the step A2 specifically includes:
a2-1, constructing a fuzzy control table in a fuzzy controller;
the data in the fuzzy control table includes an error in the supply pressure valueeError rate of changeec，△K p 、△K i And ΔK d All are output PID parameter adjustment quantities; wherein, the error of the oil supply pressure valueeError rate of changeecAre divided into 3 intervals ΔK p 、△K i And ΔK d Are divided into 2 intervals;
a2-2, based on the currently input oil supply pressure value error e and error change rate ec, currently calculating delta by using a gravity center method according to a fuzzy control tableK p 、△K i And ΔK d And further obtain PID parametersK p ，K i AndK d ；
wherein, the first and the second end of the pipe are connected with each other,K p ，K i andK d respectively a proportionality coefficient, an integral action coefficient and a differential action coefficient,
，
，
，
、
、
is the initial value of the PID parameter.
Further, in the step A3, a PWM duty control signal is outputu k The expression of (a) is:
in the formula (I), the compound is shown in the specification,
is the current time of the systemkThe value of the pressure error is,
is the previous time of the systemk-1 of the pressure error of the pressure sensor,
is a time of dayjOf the pressure error value.
The invention has the beneficial effects that:
(1) The invention collects the engine inlet pressure in real time on the full flight section of the helicopter, compares the engine inlet pressure with the set engine inlet pressure value, calculates, adjusts the rotating speed of the fuel feed pump in real time through the control device, adjusts the fuel feed pressure, ensures that the engine inlet pressure of the helicopter is maintained at the set value in the full flight section of the full flow range, positive overload, no overload and negative overload, meets the requirement of the inlet of the engine and ensures the flight safety.
(2) Compared with the traditional PID control, the control method provided by the embodiment of the invention has the advantages that the fuzzy PID algorithm formed by the fuzzy controller and the PID controller is more flexible and stable, and particularly for the controlled object with large time-varying property and nonlinearity.
Drawings
FIG. 1 is a schematic structural diagram of a self-adaptive oil supply system under a flight profile of a helicopter provided by the invention.
Fig. 2 is a structural diagram of a control device provided by the present invention.
FIG. 3 is a flow chart of a method for adaptively supplying fuel under a flight profile of a helicopter provided by the invention.
FIG. 4 is a schematic diagram of a helicopter fuel system according to the present invention.
Wherein: 1. an onboard power supply; 2. a control device; 3. an oil supply pump; 4. a fuel tank; 5. a first pressure sensor; 6. a second pressure sensor; 7. an engine; 8. an oil supply line.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
Example 1:
the embodiment of the invention provides a self-adaptive oil supply system under a full flight section of a helicopter, which comprises an onboard power supply 1, a control device 2, an oil supply pump 3, a fuel tank 4, a pressure sensor and an engine 7, wherein the onboard power supply 1 is connected with the control device 2;
the power supply end of the control device 2 is connected with the onboard power supply 1 through a cable, and the control end of the control device 2 is connected with an oil supply pump 3 arranged in a fuel tank 4 through a cable;
the fuel feed pump 3 is connected with the engine 7 through a fuel feed pipeline 8, and a first pressure sensor 5 and a second pressure sensor 6 are respectively arranged on the fuel feed pipeline 8 at the outlet side of the fuel feed pump 3 and the inlet side of the engine 7;
the first pressure sensor 5 and the second pressure sensor 6 are both connected with the signal input end of the control device through cables.
The control device 2 in the embodiment of the present invention is shown in fig. 2, and includes a preprocessor, a fuzzy controller, and a PID controller;
the preprocessor is used for calculating the error of the oil supply pressure value and the error change rate between the preset pressure value and the pressure at the inlet side of the engine 7 acquired by the second pressure sensor 6 and inputting the error into the fuzzy controller;
the fuzzy controller is used for calculating a PID parameter according to the input oil supply pressure value error and the error change rate and inputting the PID parameter into the PID controller;
the PID controller is used for generating a duty ratio control signal according to an input PID parameter, adjusting the rotating speed of a motor in the oil supply pump 3 according to the duty ratio control signal, and further controlling the pressurization capacity of the oil supply pump 3;
wherein, the rotating speed of the motor in the oil supply pump 3, and the pressure signals collected by the first pressure sensor 5 and the second pressure sensor 6 are transmitted to the preprocessor together.
In the embodiment of the invention, the control device collects the signal of the pressure sensor as a feedback unit, and the line length of the on-board sensor and the on-board electromagnetic interference have large interference on the output signal of the pressure sensor, so that a digital filter is designed according to the maximum overload frequency of an airplane and the response characteristics of the sensor to extract the pressure value of the sensor, a preset fuzzy PID control algorithm model is used for correcting the system parameters in real time according to the pressure deviation and the deviation change rate of an oil supply pipeline at the inlet side of a generator, and the output signal provides power for a signal amplifier (a motor drive control component) to control the rotation of a motor to provide power for a pump, thereby improving the quick response capability of the system and improving the stability and the anti-interference capability of the system.
When the self-adaptive oil supply system provided by the embodiment of the invention works, the inlet side pressure of an engine 7 of a helicopter is set to be a constant value, when the inlet pressure of the engine 7 is changed under the conditions of oil consumption change, flight attitude and overload of the engine 7, the control device 2 compares the received inlet side pressure of the engine 7 with a set value, and when the inlet pressure of the engine 7 is smaller than the set value, the control device 2 regulates the rotating speed of a motor in an oil supply pump 3 in real time through a PID (proportion integration differentiation) controller, increases the oil supply pressure and ensures that the inlet pressure of the engine 7 is increased to the set value; when the pressure of the inlet side of the engine 7 is larger than a set value, the control device 2 adjusts the rotating speed of the oil supply pump 3 in real time through a PID (proportion integration differentiation) controller, reduces the oil supply pressure and ensures that the pressure of the inlet side of the engine 7 is reduced to the set value; in the process, the rotating speed of the motor in the fuel feed pump 3 is regulated through the closed-loop control of the PID controller, the self-adaptive pressure regulation technology is realized, and further the self-adaptive fuel feed under the full flight section of the helicopter is realized.
Example 2:
the embodiment of the invention provides a helicopter full-flight profile lower adaptive oil supply method based on the helicopter full-flight profile lower adaptive oil supply system in the embodiment 1, as shown in fig. 3, the method comprises the following steps:
s1, determining a pressure state of an inlet side of an engine 7 on the helicopter;
and S2, regulating the rotating speed of a motor in the oil supply pump 3 through the control device 2 according to the pressure data collected by the first pressure sensor 5 and the second pressure sensor 6 according to the pressure state of the inlet side of the engine 7 so as to keep the pressure of the inlet side of the engine 7 constant and realize self-adaptive oil supply.
Step S1 of the embodiment of the present invention specifically includes acquiring a pressure signal at the inlet side of the engine 7 by the second pressure sensor 6, and comparing the pressure signal with a set pressure value, thereby determining a pressure state at the inlet side of the engine 7;
the pressure state comprises a normal state, a state higher than a set pressure value and a state lower than a set pressure value.
The reasons causing the change of the pressure at the inlet side of the engine 7 in the embodiment include the change of the oil consumption of the engine 7, the flight attitude, the overload condition and the like; under the condition of positive overload, the pressure of the inlet side of the engine 7 is smaller than a set value, the rotating speed of the motor needs to be increased, and the supercharging capacity is improved; under the condition of negative overload, the pressure of the inlet side of the engine 7 is larger than a set value, the rotating speed of the motor needs to be reduced, and the supercharging capacity needs to be reduced.
In step S2 of this embodiment, in a normal state, the control device 2 adjusts the rotation speed of the motor in the fuel feed pump 3 to keep constant, and stabilizes the pressure boost capability of the fuel feed pump 3 to keep the pressure at the inlet side of the engine 7 constant, thereby implementing adaptive fuel feeding;
under the state of being lower than the pressure set value, the control device 2 adjusts the rotation speed increase of the motor in the oil supply pump 3, and improves the pressurization capacity of the oil supply pump 3 so as to keep the pressure of the inlet side of the engine 7 constant and realize self-adaptive oil supply;
and under the condition of being higher than the set pressure value, the control device 2 regulates the reduction of the rotating speed of the motor in the fuel supply pump 3, and reduces the pressurizing capacity of the fuel supply pump 3 so as to keep the pressure of the inlet side of the engine 7 constant and realize self-adaptive fuel supply.
In the embodiment of the present invention, as shown in fig. 4, the helicopter overload acceleration is equal to the sum of the system absolute acceleration and the gravity acceleration, that is:
when the aircraft is overloaded with accelerations of
Then, the aircraft absolute acceleration is:
based on this, the outlet-side pressure of the fuel feed pump 3
Comprises the following steps:
inlet side pressure of engine 7
Comprises the following steps:
in the formula (I), the compound is shown in the specification,
the pressure of the oil supply pump is increased,
as the density of the fuel oil,ais the absolute acceleration of the aircraft and,his the height of the liquid level in the fuel tank,Hin order to supply the mounting height of the oil pump to the engine,a 0 is the overload acceleration;
the inlet side pressure of the engine 7 is normal, and the inlet side pressure of the engine 7 is normal
Controlling the pressurization capacity of the pump to be unchanged;
the inlet side pressure of the engine 7 is lower than the set pressure value
Control the pressure boosting capacity of the feed pump 3 to be improved
；
The pressure at the inlet side of the engine 7 is higher than the pressure set value
Control the decrease of the pressurizing capacity of the feed pump 3
。
In the embodiment of the present invention, according to the pump similarity law, the relationship between the rotation speed and the pressure of the feed pump 3 is:
in the formula (I), the compound is shown in the specification,P 1 the oil supply pressure, kPa, at which the oil supply pump 3 is not overloaded;P 2 the fuel supply pressure, kPa, at the time of overload of the fuel supply pump 3;n 1 the rotating speed of the oil supply pump 3 is no overload, r/min;n 2 the rotating speed r/min is the rotating speed of the oil supply pump 3 during overload.
In the embodiment of the invention, the rotating speed of the oil supply pump 3 is regulated by acquiring the oil supply pressure at the inlet side of the engine 7 through the second pressure sensor 6, the control device 2 takes the error value and the error change rate of the oil supply pressure of the given pressure value and the acquired oil supply pressure as input to the fuzzy controller, and regulates the rotating speed of a motor in the oil supply pump 3 according to the PID parameters output by the PID controller, so as to achieve the purpose of regulating the pressure.
Based on this, the method for adjusting the rotation speed of the motor in the fuel feed pump 3 through the control device 2 in the embodiment of the invention specifically comprises the following steps:
a1, calculating an oil supply pressure value error and an error change rate between a set pressure value in a control device 2 and the pressure at the inlet side of an engine 7 acquired by a second pressure sensor 6;
a2, taking the calculated error and the error change rate of the oil supply pressure value as the input of a fuzzy controller, obtaining a PID parameter and inputting the PID parameter into the PID controller;
and A3, outputting a PWM duty ratio control signal in the PID controller according to the input PID control parameter, and regulating the rotating speed of a motor in the oil supply pump 3 according to the PWM duty ratio control signal.
Step A2 in this embodiment specifically includes:
a2-1, constructing a fuzzy control table in a fuzzy controller;
blurringData in the control table includes fueling pressure value erroreError rate of changeec，△K p 、△K i And ΔK d All are output PID parameter adjustment quantities; wherein, the error of the oil supply pressure valueeError rate of changeecAre divided into 3 intervals ΔK p 、△K i And deltaK d Are divided into 2 intervals.
A2-2, oil supply pressure value error based on current inputeAnd rate of error changeecAt present, according to fuzzy control table, the method of gravity center is used to calculate deltaK p 、△K i And ΔK d Further obtain PID parametersK p ，K i AndK d ；
wherein the content of the first and second substances,K p ，K i andK d proportional coefficient, integral coefficient, and differential coefficient,
，
，
，
、
、
is the initial value of the PID parameter.
In step A2-1 of this embodiment, according to realityeHas a variation range of (0, 300), and is divided into 3 sections, each of which isPS, PM,PB(ii) a Error of the measurementRate of changeecThe variation range (-300,300) is divided into 3 intervals:N，Z，P； △K p 、△K i 、△K d the division into 2 intervals:N，Pobtaining a fuzzy control table as shown in table 1;
table 1: fuzzy control table
In step A3 of this embodiment, a PWM duty control signal is outputu k The expression of (c) is:
in the formula (I), the compound is shown in the specification,
is the current time of the systemkThe value of the pressure error is such that,
is the previous time of the systemk-1 of the pressure error of the pressure sensor,
is a time of dayjOf the pressure error value.
PID parameters in the present embodimentK p ，K i AndK d the explanation of (A) is as follows:
coefficient of proportionalityK p : the response speed of the system is increased, and the adjustment precision of the system is improved.K p The larger the system, the faster the response speed of the system, but the overshoot is easy and the system is unstable.K p If the value is too small, the adjustment precision is reduced, the response speed is slow, the adjustment time is prolonged, and the static and dynamic characteristics of the system are deteriorated.
Integral coefficient of actionK i : and eliminating the steady-state error of the system.K i The larger the system, the faster the static error cancellation of the system, butK i Too large, integral saturation may occur during the response process, thereby causing a large overshoot of the response process. If it isK i Too small, makes the system static error difficult to eliminate.
Coefficient of differential actionK d : the dynamic characteristic of the system is improved, and the effect of the system is mainly to restrain the change of the deviation to any direction in the response process and forecast the deviation change in advance. But do notK d If the response time is too large, the response process can be advanced, so that the adjustment time is prolonged, and the anti-interference performance of the system can be reduced.
In the description of the present invention, it is to be understood that the terms "center", "thickness", "upper", "lower", "horizontal", "top", "bottom", "inner", "outer", "radial", and the like, indicate orientations and positional relationships based on the orientations and positional relationships shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or an implicit indication of the number of technical features. Thus, features defined as "first", "second", "third" may explicitly or implicitly include one or more of the features.
Claims (4)
1. A self-adaptive oil supply method under a full-flight section of a helicopter is characterized in that a system for realizing the self-adaptive oil supply under the full-flight section of the helicopter comprises an onboard power supply (1), a control device (2), an oil supply pump (3), a fuel tank (4), a pressure sensor and an engine (7);
the power supply end of the control device (2) is connected with the onboard power supply (1) through a cable, and the control end of the control device (2) is connected with an oil supply pump (3) arranged in a fuel tank (4) through a cable;
the oil supply pump (3) is connected with the engine (7) through an oil supply pipeline (8), and a first pressure sensor (5) and a second pressure sensor (6) are respectively arranged on the oil supply pipeline (8) on the outlet side of the oil supply pump (3) and the inlet side of the engine (7);
the first pressure sensor (5) and the second pressure sensor (6) are connected with the signal input end of the control device through cables;
the control device (2) comprises a preprocessor, a fuzzy controller and a PID controller;
the preprocessor is used for calculating an error and an error change rate of an oil supply pressure value between the preprocessor and the inlet side pressure of the engine (7) acquired by the second pressure sensor (6) according to a set pressure value, and inputting the error and the error change rate into the fuzzy controller;
the fuzzy controller is used for calculating a PID parameter according to the input oil supply pressure value error and the error change rate and inputting the PID parameter into the PID controller;
the PID controller is used for generating a duty ratio control signal according to an input PID parameter, adjusting the rotating speed of a motor in the oil supply pump (3) according to the duty ratio control signal, and further controlling the pressurization capacity of the oil supply pump (3);
the device comprises an oil supply pump (3), a first pressure sensor (5), a second pressure sensor (6), a preprocessor and a controller, wherein the rotating speed of a motor in the oil supply pump (3), and pressure signals acquired by the first pressure sensor (5) and the second pressure sensor (6) are transmitted to the preprocessor;
the method is characterized by comprising the following steps:
s1, determining a pressure state of an inlet side of an engine (7) on a helicopter;
s2, according to the pressure state of the inlet side of the engine (7), the rotating speed of a motor in the oil supply pump (3) is adjusted through the control device (2) according to pressure data collected by the first pressure sensor (5) and the second pressure sensor (6) so as to keep the pressure of the inlet side of the engine (7) constant and realize self-adaptive oil supply;
the step S1 is specifically that a pressure signal at the inlet side of the engine (7) is collected through a second pressure sensor (6) and is compared with a set pressure value, and then the pressure state at the inlet side of the engine (7) is determined;
the pressure state comprises a normal state, a state higher than a set pressure value and a state lower than a set pressure value;
in the step S2, in a normal state, the rotating speed of a motor in the oil supply pump (3) is adjusted to be kept unchanged through the control device (2), the supercharging capacity of the oil supply pump (3) is stabilized, so that the pressure on the inlet side of the engine (7) is kept constant, and self-adaptive oil supply is realized;
under the condition of being lower than the pressure set value, the control device (2) is used for adjusting the rotating speed of the motor in the oil supply pump (3) to increase, the pressure boost capability of the oil supply pump (3) is improved, so that the pressure on the inlet side of the engine (7) is kept constant, and self-adaptive oil supply is realized;
when the pressure value is higher than the set pressure value, the rotating speed of a motor in the oil supply pump (3) is adjusted to be reduced through the control device (2), and the supercharging capacity of the oil supply pump (3) is reduced, so that the pressure on the inlet side of the engine (7) is kept constant, and self-adaptive oil supply is realized;
outlet side pressure of the oil supply pump (3)
Comprises the following steps:
inlet side pressure of the engine (7)
Comprises the following steps:
in the formula (I), the compound is shown in the specification,
the pressure of the oil supply pump (3) is increased,
as the density of the fuel oil,ais the absolute acceleration of the aircraft and,his the height of the liquid level in the fuel tank (4),Hfor supplying the mounting height of the pump (3) to the engine (7),a 0 is the overload acceleration;
the pressure on the inlet side of the engine (7) is normal
Controlling the pressurization capacity of the pump to be unchanged;
the pressure on the inlet side of the engine (7) is lower than the pressure set value
Control the pressure boosting capacity of the fuel feed pump (3) to be increased
；
The pressure on the inlet side of the engine (7) is higher than the pressure set value
Controlling the decrease of the pressurizing capacity of the fuel feed pump (3)
；
The relation between the rotating speed and the pressure of the oil supply pump (3) is as follows:
in the formula (I), the compound is shown in the specification,P 1 the oil supply pump (3) has no overload oil supply pressure,kPa；P 2 the pressure is the oil supply pressure, kPa, when the oil supply pump (3) is overloaded;n 1 the rotating speed of the oil supply pump (3) is no overload, r/min;n 2 the rotating speed r/min is the rotating speed of the oil supply pump (3) during overload.
2. The adaptive fuel supply method under the full flight profile of a helicopter as claimed in claim 1, characterized in that the method for adjusting the rotational speed of the motor in the fuel supply pump (3) by means of the control device (2) is specifically:
a1, calculating an error and an error change rate of an oil supply pressure value between an internal set pressure value of a control device (2) and the pressure of the inlet side of an engine (7) acquired by a second pressure sensor (6);
a2, taking the calculated error and the error change rate of the oil supply pressure value as the input of a fuzzy controller, obtaining a PID parameter and inputting the PID parameter into the PID controller;
and A3, in the PID controller, outputting a PWM duty ratio control signal according to an input PID control parameter, and regulating the rotating speed of a motor in the oil supply pump (3) according to the PWM duty ratio control signal.
3. The method for self-adaptive oil supply under a full flight profile of a helicopter according to claim 2, wherein said step A2 is specifically:
a2-1, constructing a fuzzy control table in a fuzzy controller;
the data in the fuzzy control table includes the oil supply pressure value erroreError rate of changeec，△K p 、△K i And ΔK d All are output PID parameter regulating variables; wherein the error of the oil supply pressure valueeError rate of changeecAre divided into 3 intervals ΔK p 、△K i And deltaK d Are divided into 2 intervals;
a2-2, oil supply pressure value error based on current inputeAnd rate of change of errorecAt present, according to fuzzy control table, the method of gravity center is used to calculate deltaK p 、△K i And ΔK d And further obtain PID parametersK p ，K i AndK d ；
wherein, the first and the second end of the pipe are connected with each other,K p ，K i andK d proportional coefficient, integral action coefficient and differential action coefficient,
，
，
，
、
、
is the initial value of the PID parameter.
4. A helicopter full flight profile adaptive fueling method as claimed in claim 3 wherein in step A3, a PWM duty cycle control signal is outputu k The expression of (a) is:
in the formula (I), the compound is shown in the specification,
is the current time of the systemkThe value of the pressure error is,
is the previous time of the systemk-1, the pressure error of the pressure sensor,
is a time of dayjOf the pressure error value.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1182064A (en) * | 1968-03-13 | 1970-02-25 | United Aircraft Corp | Fuel Control Testing Device |
| US5660358A (en) * | 1994-03-02 | 1997-08-26 | Daimler-Benz Aerospace Ag | Fuel supply system |
| GB0210014D0 (en) * | 2001-07-18 | 2002-06-12 | Rolls Royce Plc | Fuel delivery system |
| CN101128661A (en) * | 2005-02-17 | 2008-02-20 | 伊斯帕诺-絮扎公司 | Device for supplying fuel to a gas turbine engine with regulated fuel flow rate |
| CN102678338A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Oil supply pressure regulating system for aircraft engine and regulating method thereof |
| CN104349977A (en) * | 2012-04-18 | 2015-02-11 | 伊顿有限公司 | Aircraft fuel supply systems |
| CN204213075U (en) * | 2014-09-28 | 2015-03-18 | 成都凯天电子股份有限公司 | Maintenance vehicle with workbench hydraulic control system |
| JP2015096714A (en) * | 2013-11-15 | 2015-05-21 | 三菱日立パワーシステムズ株式会社 | Control device, combustor, gas turbine, control method, and control program |
| CN110920915A (en) * | 2019-12-17 | 2020-03-27 | 南京航空航天大学 | Self-adaptive thermal management control device and method for aircraft fuel system |
| CN112682177A (en) * | 2020-12-24 | 2021-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Overload self-adaptation oil feeding system |
| CN114750976A (en) * | 2022-06-15 | 2022-07-15 | 成都凯天电子股份有限公司 | Ground performance test system and method for self-adaptive oil supply system of helicopter |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3350880A (en) * | 1965-09-03 | 1967-11-07 | Bendix Corp | Gas turbine combustion engine fuel control |
| JP3854556B2 (en) * | 2002-09-11 | 2006-12-06 | 三菱重工業株式会社 | Gas turbine plant control mechanism |
| US8915088B2 (en) * | 2010-06-11 | 2014-12-23 | Hamilton Sundstrand Corporation | Fuel control method for starting a gas turbine engine |
| WO2015015129A1 (en) * | 2013-08-02 | 2015-02-05 | Snecma | Fuel circuit of an aircraft engine with a fuel recirculating valve controlled by a pressure differential of a low-pressure pump of the fuel system |
| US10317082B2 (en) * | 2014-08-12 | 2019-06-11 | Hamilton Sundstrand Corporation | Distributed fuel control system |
| US11001391B2 (en) * | 2015-03-25 | 2021-05-11 | Sikorsky Aircraft Corporation | Automatic adjusting fuel boost pump |
| FR3068114B1 (en) * | 2017-06-27 | 2019-08-16 | Safran Aircraft Engines | FLUID SUPPLY SYSTEM FOR TURBOMACHINE, COMPRISING A VARIABLE CYLINDER PUMP FOLLOWED BY A FLUID DOSER |
| US10934966B2 (en) * | 2019-02-19 | 2021-03-02 | Caterpillar Inc. | Combustion phasing control for high substitution lean burn of gaseous fuels in dual fuel engine |
| CN211717692U (en) * | 2020-04-28 | 2020-10-20 | 成都凯天电子股份有限公司 | Lubricating oil pressure sensor |
| CN112644721B (en) * | 2020-12-23 | 2022-06-03 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
-
2022
- 2022-08-11 CN CN202210958098.6A patent/CN115030824B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1182064A (en) * | 1968-03-13 | 1970-02-25 | United Aircraft Corp | Fuel Control Testing Device |
| US5660358A (en) * | 1994-03-02 | 1997-08-26 | Daimler-Benz Aerospace Ag | Fuel supply system |
| GB0210014D0 (en) * | 2001-07-18 | 2002-06-12 | Rolls Royce Plc | Fuel delivery system |
| CN101128661A (en) * | 2005-02-17 | 2008-02-20 | 伊斯帕诺-絮扎公司 | Device for supplying fuel to a gas turbine engine with regulated fuel flow rate |
| CN104349977A (en) * | 2012-04-18 | 2015-02-11 | 伊顿有限公司 | Aircraft fuel supply systems |
| CN102678338A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Oil supply pressure regulating system for aircraft engine and regulating method thereof |
| JP2015096714A (en) * | 2013-11-15 | 2015-05-21 | 三菱日立パワーシステムズ株式会社 | Control device, combustor, gas turbine, control method, and control program |
| CN204213075U (en) * | 2014-09-28 | 2015-03-18 | 成都凯天电子股份有限公司 | Maintenance vehicle with workbench hydraulic control system |
| CN110920915A (en) * | 2019-12-17 | 2020-03-27 | 南京航空航天大学 | Self-adaptive thermal management control device and method for aircraft fuel system |
| CN112682177A (en) * | 2020-12-24 | 2021-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Overload self-adaptation oil feeding system |
| CN114750976A (en) * | 2022-06-15 | 2022-07-15 | 成都凯天电子股份有限公司 | Ground performance test system and method for self-adaptive oil supply system of helicopter |
Non-Patent Citations (2)
| Title |
|---|
| Performance of an Integrated Thermal Management System for helicopter;Liping Pang等;《Energy》;20220115;全文 * |
| 基于代理模型的航空燃油泵空化性能分析;熊英华等;《航空学报》;20160411(第10期);全文 * |
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