CN114136416B - Flight weight monitoring method and system for aircraft, storage medium and electronic equipment - Google Patents
Flight weight monitoring method and system for aircraft, storage medium and electronic equipment Download PDFInfo
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Abstract
The invention discloses a flight weight monitoring method and system of an aircraft, a storage medium and electronic equipment, and relates to the technical field of aircraft control, wherein the method comprises the following steps: collecting flight parameters and state parameters of an aircraft; calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft; evaluating and processing the state parameters to obtain the deviation degree of the estimated flight weight; and performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft. The invention can improve the monitoring accuracy of the flight weight of the aircraft and realize that the flight weight is suitable for full-flight envelope.
Description
Technical Field
The invention relates to the technical field of airplane control, in particular to a flight weight monitoring method and system of an aircraft, a storage medium and electronic equipment.
Background
The flight weight of the aircraft needs to be monitored in real time in the flight process, and the flight weight can be used for control law functions such as control law parameter adjustment and characteristic speed calculation.
At present, when the flight weight of an aircraft is determined, the flight weight is usually determined by directly calculating according to obtained flight parameters, so that different working conditions in flight are not comprehensively considered, the flight weight monitoring precision is low in a specific state, and the flight weight is not suitable for a full-flight envelope.
Disclosure of Invention
The embodiment of the invention provides a scheme, which can effectively improve the monitoring accuracy of the flight weight of an aircraft and realize that the flight weight is suitable for full-flight envelope.
The embodiment of the invention provides the following technical scheme:
according to one embodiment of the invention, a method of flight weight monitoring for an aircraft comprises: collecting flight parameters and state parameters of an aircraft; calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft; performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight; and performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
According to one embodiment of the invention, a flight weight monitoring system for an aircraft comprises: the acquisition module is used for acquiring flight parameters and state parameters of the aircraft; the weight preliminary estimation module is used for calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft; the estimation locking module is used for carrying out estimation processing based on the state parameters so as to obtain the deviation degree of the estimated flight weight; and the logical operation module is used for carrying out logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
According to another embodiment of the present invention, a storage medium has stored thereon a computer program which, when executed by a processor of a computer, causes the computer to perform the method according to an embodiment of the present invention.
According to another embodiment of the present invention, an electronic device may include: a memory storing a computer program; and the processor reads the computer program stored in the memory to execute the method of the embodiment of the invention.
In the embodiment of the invention, flight parameters and state parameters of an aircraft are collected; calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft; evaluating and processing the state parameters to obtain the deviation degree of the estimated flight weight; and performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
In this way, a preliminary flight weight, that is, an estimated flight weight, can be obtained by performing calculation processing according to weight calculation logic based on the flight parameters. Furthermore, the deviation degree of the estimated flight weight can be obtained according to the state of the aircraft by carrying out evaluation processing based on the state parameters, the deviation degree can reflect the accuracy of the estimated flight weight, and the deviation degree is determined based on the state parameters and can reflect the influences of different working conditions in flight. Furthermore, the target flight weight obtained by performing logical operation processing according to the deviation degree can improve the accuracy of the flight weight and is suitable for the full-flight envelope.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 illustrates a flow diagram of a method of flight weight monitoring of an aircraft according to one embodiment of the invention.
FIG. 2 illustrates a block diagram of a flight weight monitoring system of an aircraft according to one embodiment of the invention.
FIG. 3 illustrates a block diagram of a flight weight monitoring system of an aircraft according to another embodiment of the invention.
FIG. 4 shows a block diagram of an electronic device according to an embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 invention.
FIG. 1 schematically illustrates a flow diagram of a method of flight weight monitoring of an aircraft according to one embodiment of the invention. The main body of the aircraft flight weight monitoring method can be any equipment, such as a flight control computer.
As shown in fig. 1, the flight weight monitoring method of the aircraft may include steps S110 to S140.
Step S110, collecting flight parameters and state parameters of an aircraft;
step S120, calculating based on the flight parameters to obtain the estimated flight weight of the aircraft;
step S130, performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight;
and step S140, performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
An aircraft is flight equipment, in one example an aircraft is an airplane. The flight parameters are flight-related parameters of the aircraft, and the state parameters are parameters capable of reflecting the state of the aircraft.
The calculation processing is performed according to the weight calculation logic based on the flight parameters, and the preliminary flight weight, namely the estimated flight weight, can be obtained.
Furthermore, evaluation processing is carried out based on the state parameters, the deviation degree of the estimated flight weight can be obtained according to the state of the aircraft, the deviation degree can effectively reflect the accuracy of the estimated flight weight, and the deviation degree is determined based on the state parameters and can reflect the influences of different working conditions in flight.
Furthermore, the target flight weight obtained by performing logical operation processing according to the deviation degree can improve the accuracy of the flight weight and is suitable for full-flight envelope.
In this way, based on steps S110 to S140, when monitoring the flight weight of the aircraft, the influence of different working conditions in flight can be effectively coped with, so that the accuracy of the target flight weight is improved, and the method is suitable for full-flight envelope.
Specific embodiments of the steps performed when making the determination of the aircraft control mode are described below.
In step S110, flight parameters and state parameters of the aircraft are collected.
I.e. flight related parameters of the aircraft, and the state parameters, i.e. parameters that may reflect the state of the aircraft. Flight parameters such as dynamic pressure, aircraft wing reference area, normal overload, gravitational acceleration, and lift coefficient of the wing-body assembly. The state parameters comprise normal overload, a speed reducing plate command signal, an effective attack angle protection signal, an abnormal attitude signal, a horizontal tail lifting rudder position signal and the like. Flight parameters and state parameters can be acquired from aircraft sensors or flight control systems.
In step S120, calculation processing is performed based on the flight parameters to obtain an estimated flight weight of the aircraft.
In one embodiment, step S120, performing calculation processing based on the flight parameters to obtain the estimated flight weight of the aircraft includes:
acquiring deflection degree of a control plane of an aircraft; performing signal correction processing on the flight parameters based on the deflection skewness of the control surface to obtain corrected flight parameters; and calculating and processing based on the corrected flight parameters to obtain the estimated flight weight of the aircraft.
The control surface deflection degree can reflect the state of the aircraft, and the flight parameters are subjected to signal correction processing based on the elastic correction control surface deflection degree, so that corrected flight parameters for improving the calculation accuracy of the estimated flight weight can be obtained, and the accuracy of the estimated flight weight is improved.
When the flight parameters are subjected to signal correction processing based on the control surface deflection degree, all or part of the flight parameters may be corrected to obtain corrected flight parameters, for example, a corrected lift coefficient obtained by performing signal correction processing on a lift coefficient of a wing-body combination only based on the control surface deflection degree in one example. The method of the correction processing may be a correction method of performing parameter adjustment based on a correction table, a correction method of performing calculation adjustment based on a correction formula, or the like.
In one embodiment, the flight parameters include dynamic pressure of the aircraft, aircraft wing reference area, normal overload, gravitational acceleration, and lift coefficient of the wing-body combination; calculating and processing based on the corrected flight parameters to obtain the estimated flight weight of the aircraft, wherein the method comprises the following steps:
and calculating based on a formula W ═ QSCL)/(Ng) to obtain the estimated flight weight of the aircraft, wherein W is the estimated flight weight, Q is dynamic pressure, S is the reference area of the aircraft wing, N is normal overload, g is gravity acceleration, and CL is the corrected lift coefficient obtained by performing signal correction processing on the lift coefficient of the wing-body combination based on the deflection of the control surface.
In this embodiment, the corrected lift coefficient obtained by performing signal correction processing on the lift coefficient of the wing-body assembly based on the control plane deflection skewness is calculated based on the formula W ═ QSCL)/(Ng), and in this way, the accuracy of the estimated flight weight of the aircraft can be further improved.
And step S130, performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight.
In one embodiment, the degree of deviation includes deviation and non-deviation; step S130, performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight, including:
determining whether the state parameters meet preset deviation conditions or not to obtain a determination result; if the determined result is that the preset deviation condition is met, determining the deviation degree of the estimated flight weight as deviation; and if the determined result is that the preset deviation condition is not met, determining that the deviation degree of the estimated flight weight is not deviated.
The preset deviation condition is a condition for judging whether the parameter deviates from the requirement or not and reflecting whether the estimated flight weight deviates or not, and the preset deviation condition can be set according to the actual condition. In this way, the deviation degree of the estimated flight weight can be determined efficiently and accurately based on the deviation condition of the state parameter.
In one embodiment, the determination result includes any one of a first determination result, a second determination result, a third determination result, a fourth determination result, and a fifth determination result; determining whether the state parameter meets a preset deviation condition to obtain a determination result, wherein the determination result comprises the following steps:
determining whether the normal overload is smaller than a first threshold or larger than a second threshold to obtain a first determination result, wherein the first threshold is smaller than the second threshold; determining whether the instruction signal of the speed reducing plate is larger than a third threshold value or not to obtain a second determination result; determining whether the attack angle protection effective signal is enabled or not to obtain a third determination result; determining whether the abnormal attitude signal shows that the aircraft is in an abnormal attitude or not to obtain a fourth determination result; and determining whether the horizontal tail rudder position signal is invalid or not to obtain a fifth determination result.
And determining the deviation degree of the estimated flight weight as deviation when the determined result comprises any one of a first determined result, a second determined result, a third determined result, a fourth determined result and a fifth determined result, namely any one of the first determined result, the second determined result, the third determined result, the fourth determined result and the fifth determined result is that the state parameter meets the preset deviation condition.
The method aims at the condition parameters including normal overload, a speed reduction plate instruction signal, an angle of attack protection effective signal, an abnormal attitude signal and a horizontal tail rudder position signal, each condition parameter corresponds to a preset deviation condition, each condition parameter corresponds to a determination result, and further the deviation degree of the estimated flight weight can be efficiently and accurately determined.
And step S140, performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
In one embodiment, the logic operation processing according to the deviation degree to obtain the target flight weight of the aircraft comprises:
if the deviation degree is deviation, descending the target flight weight based on the target descending speed to obtain the non-deviated flight weight to be confirmed, wherein the target flight weight is historical estimated flight weight obtained by calculation processing based on flight parameters at the target moment, and the target moment is the calculation moment before the moment when the estimated flight weight deviates; if the deviation degree is not deviated, the estimated flight weight is taken as the flight weight to be confirmed; a target flight weight for the aircraft is generated based on the flight weight to be confirmed.
In this embodiment, the calculation logic is set for the deviation and the non-deviation according to the deviation degree, so that the accuracy of the target flight weight can be further improved.
That is, if the deviation degree of the estimated flight weight calculated at the current calculation time is deviation, the operation logic is as follows: and (3) descending the target flight weight based on the target descending rate to obtain the non-deviated flight weight to be confirmed, namely continuously reducing the initial weight based on the target descending rate by taking the target flight weight as the initial weight until the real-time state parameters of the aircraft do not accord with the preset deviation condition to obtain the non-deviated flight weight to be confirmed. The target flight weight is a historical estimated flight weight obtained by calculation processing based on flight parameters at a target time, and the target time is a calculation time before a deviation time (which may be equal to a calculation time of the estimated flight weight) of the estimated flight weight. The applicant finds that in this way, when the estimated flight weight calculated at the current calculation time deviates, the non-deviated flight weight to be confirmed can be efficiently and accurately acquired based on the historical estimated flight weight deviating from the previous time. The target flight weight of the aircraft can be accurately generated based on the flight weight to be confirmed.
If the deviation degree of the estimated flight weight calculated at the current calculation moment is not deviated, the operation logic is as follows: taking the estimated flight weight calculated currently as the flight weight to be confirmed; a target flight weight for the aircraft is generated based on the flight weight to be confirmed.
In one embodiment, the descending processing of the target flight weight based on the target descending rate to obtain the flight weight to be confirmed without deviation comprises:
calculating the product of the default oil consumption rate and the deviation duration to obtain a target drop value, wherein the deviation duration is the time period from the specific time to the activation time of the drop processing; and continuously subtracting the target descending value by using the target flight weight until the state parameter of the aircraft does not accord with the preset deviation condition, and obtaining the flight weight to be confirmed without deviation.
The activation timing of the lowering process is a timing at which the lowering process of the target flight weight based on the target lowering rate is started, and may be a timing at which the estimated flight weight is determined to be deviated. The specific time instant may be the time instant at which the aircraft is started or a specified starting time instant. This embodiment continues according to the formula: the flight weight to be confirmed without deviation is calculated as the target flight weight- (default fuel consumption rate × deviation period). In this way, based on the calculation mode of the default fuel consumption rate, the accuracy of the flight weight to be confirmed, which is not deviated, can be further improved, and the accuracy of the target flight weight is further improved.
In one embodiment, generating a target flight weight for an aircraft based on a flight weight to be confirmed includes: if the aircraft is within a preset time after taking off, filtering the flight weight to be confirmed based on the first-order filter to obtain the target flight weight of the aircraft; and if the aircraft is in the preset takeoff time, filtering the flight weight to be confirmed based on the second first-order filter to obtain the target flight weight of the aircraft.
The first-order filter, for example, the filter with the time constant of T0, and the second first-order filter, for example, the filter with the time constant of T1, perform filtering processing on the flight weight to be confirmed through the filter corresponding to the flight time period in which the aircraft is located, obtain the target flight weight of the aircraft, and further improve the accuracy of the target flight weight.
Further, in one embodiment, the time constant T0 of the first order filter may be smaller than the time constant T1 of the second order filter, which may further improve the accuracy of the target flight weight.
In one embodiment, the method of flight weight monitoring of an aircraft further comprises: checking the target flight weight to obtain the effectiveness of the target flight weight; and determining the effective flight weight of the aircraft according to the effectiveness.
The target flight weight is checked, the effective flight weight of the aircraft is determined according to effectiveness, the monitoring accuracy of the flight weight is further improved, control law functions such as control law parameter adjustment and characteristic speed calculation are used according to the effective flight weight, the flight control performance is further improved, and the method is further effectively suitable for a full flight envelope.
In one embodiment, the verifying the target flight weight to obtain the validity of the target flight weight includes: acquiring a ground speed signal and/or a wheel-borne signal of an aircraft; and evaluating according to the ground speed signal and/or the wheel load signal to obtain the effectiveness of the target flight weight.
The applicant finds that the ground speed signal and the wheel load signal can reflect the motion state of the airplane, and effective evaluation processing is carried out on the basis of the ground speed signal and/or the wheel load signal to obtain the effectiveness of the target flight weight.
In one embodiment, the evaluation processing according to the ground speed signal and/or the wheel load signal to obtain the effectiveness of the target flight weight comprises: if the ground speed signal meets the signal validity condition and the ground speed signal is smaller than the preset threshold value and/or the wheel-mounted signal meets the signal validity condition, the validity of the target flight weight is invalid; and if the ground speed signal does not meet the signal validity condition and/or the ground speed signal is greater than a preset threshold value and/or the wheel-borne signal does not meet the signal validity condition, the validity of the target flight weight is valid.
The wheel load signal meets the signal validity condition, namely the wheel load signal is valid, namely the wheel load sensor provides the wheel load signal with validity, and the wheel load size is larger than 0, and conversely, the wheel load signal provided by the wheel load sensor does not have validity or the wheel load size is equal to 0, then the wheel load signal is invalid. The ground speed signal accords with the signal validity condition, namely the ground speed signal is valid, and the ground speed signal is valid, namely the validity of the signal provided by the ground speed signal sensor. Based on the evaluation manner of this embodiment, the effectiveness of the target flight weight can be effectively judged.
In one embodiment, determining an effective flight weight of an aircraft based on effectiveness includes: if the effectiveness is effective, taking the target flight weight as the effective flight weight of the aircraft; and if the validity is invalid, determining the system evaluation flight weight provided by the flight management system as the valid flight weight of the aircraft, wherein the system evaluation flight weight is obtained by subtracting the real-time oil consumption from the aircraft weight.
In this embodiment, the effective flight weight of the aircraft is determined according to the correspondingly designed logic respectively according to whether the effectiveness of the target flight weight is effective or ineffective, and the accuracy of the effective flight weight is further improved.
In one embodiment, after considering the target flight weight as the effective flight weight of the aircraft if the effectiveness is effective, the method further comprises: comparing the difference between the target flight weight as the effective flight weight and the system assessment flight weight provided by the flight management system; and generating a weight estimation deviation warning message according to the difference.
And comparing the difference between the target flight weight serving as the effective flight weight and the system evaluation flight weight provided by the flight management system, so that the weight estimation result and the weight provided by the flight management system (namely the flight management system of the aircraft) are compared with each other, the accuracy of the estimation result is ensured, and the integrity of the weight signal of the aircraft is improved.
Further, a weight estimation deviation warning message is generated according to the difference, for example, when the difference exceeds 15%, the generated deviation warning message can provide a weight estimation deviation warning display for the pilot, and the flight weight monitoring reliability is further improved.
In order to better implement the flight weight monitoring method of the aircraft provided by the embodiment of the invention, the embodiment of the invention also provides a flight weight monitoring system of the aircraft based on the flight weight monitoring method of the aircraft. The terms are the same as those in the flight weight monitoring method of the aircraft, and specific implementation details can be referred to the description in the method embodiment. FIG. 2 illustrates a block diagram of a flight weight monitoring system of an aircraft according to one embodiment of the invention. FIG. 3 illustrates a block diagram of a flight weight monitoring system of an aircraft according to one embodiment of the invention.
As shown in fig. 2 and 3, the flight weight monitoring system 200 of the aircraft may include an acquisition module 210, a weight preliminary estimation module 220, an estimation locking module 230, and a logic operation module 240.
The acquisition module 210 may be configured to acquire flight parameters and state parameters of the aircraft; the weight preliminary estimation module 220 may be configured to perform calculation processing based on the flight parameters to obtain an estimated flight weight of the aircraft; the estimated locking module 230 may be configured to perform an evaluation process based on the state parameter to obtain a deviation degree of the estimated flight weight; the logic operation module 240 may be configured to perform logic operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
In one embodiment, the degree of deviation includes deviation and non-deviation; the estimate lock module 230, comprising: the deviation evaluation unit is used for determining whether the state parameters meet preset deviation conditions or not to obtain a determination result; a first deviation determining unit, configured to determine, if the determination result is that the preset deviation condition is met, that the deviation degree of the estimated flight weight is a deviation; and the second deviation determining unit is used for determining that the deviation degree of the estimated flight weight is not deviated if the determination result is that the preset deviation condition is not met.
In one embodiment, the determination result includes any one of a first determination result, a second determination result, a third determination result, a fourth determination result, and a fifth determination result; the deviation evaluation unit is configured to: determining whether the normal overload is smaller than a first threshold or larger than a second threshold to obtain a first determination result, wherein the first threshold is smaller than the second threshold; determining whether the instruction signal of the speed reducing plate is larger than a third threshold value or not to obtain a second determination result; determining whether the attack angle protection effective signal is enabled or not to obtain a third determination result; determining whether the abnormal attitude signal shows that the aircraft is in an abnormal attitude or not to obtain a fourth determination result; and determining whether the position signal of the horizontal tail elevator rudder is invalid or not to obtain a fifth determination result.
In one embodiment, the logic operation module 240 includes: a first operation unit, configured to, if the deviation degree is a deviation, perform descent processing on a target flight weight based on a target descent rate to obtain an undistorted flight weight to be confirmed, where the target flight weight is a historical estimated flight weight obtained by calculation processing based on flight parameters at a target time, and the target time is a calculation time before a time at which the estimated flight weight deviates; the second operation unit is used for taking the estimated flight weight as the flight weight to be confirmed if the deviation degree is not deviated; a weight generating unit for generating a target flight weight of the aircraft based on the flight weight to be confirmed.
In one embodiment, the first arithmetic unit is configured to: calculating the product of the default oil consumption rate and the deviation duration of the descending treatment to obtain a target descending value, wherein the deviation duration is the time period from the specific time to the activation time of the descending treatment; and continuously subtracting the target descending value by using the target flight weight until the state parameter of the aircraft does not accord with the preset deviation condition, and obtaining the flight weight to be confirmed without deviation.
In one embodiment, the weight generating unit is configured to: if the aircraft is within a preset time after taking off, carrying out filtering processing on the flight weight to be confirmed based on a first-order filter to obtain the target flight weight of the aircraft; and if the aircraft is in the preset takeoff time, filtering the flight weight to be confirmed based on a second first-order filter to obtain the target flight weight of the aircraft.
In one embodiment, referring to fig. 3, the system further comprises a validity checking module 250 comprising: the verification unit is used for verifying the target flight weight to obtain the validity of the target flight weight; an effectiveness determination unit for determining an effective flight weight of the aircraft based on the effectiveness.
In one embodiment, the verification unit includes: the signal acquisition subunit is used for acquiring a ground speed signal and/or a wheel load signal of the aircraft; and the signal checking subunit is used for evaluating and processing according to the ground speed signal and/or the wheel-borne signal to obtain the effectiveness of the target flight weight.
In one embodiment, the signal checking subunit is configured to: if the ground speed signal meets a signal validity condition and the ground speed signal is smaller than a preset threshold value, and/or the wheel-mounted signal meets a signal validity condition, the validity of the target flight weight is invalid; and if the ground speed signal does not meet the signal validity condition and/or the ground speed signal is greater than the preset threshold value and/or the wheel load signal does not meet the signal validity condition, the validity of the target flight weight is valid.
In one embodiment, the validity determination unit is configured to: if the effectiveness is effective, taking the target flight weight as the effective flight weight of the aircraft; and if the effectiveness is invalid, determining the system estimated flight weight provided by the flight management system as the effective flight weight of the aircraft, wherein the system estimated flight weight is obtained by subtracting the real-time oil consumption from the aircraft weight.
In one embodiment, the system further comprises an estimate comparison module 260 for: comparing the target flight weight as the effective flight weight to a difference in system assessment flight weight provided by a flight management system; generating a weight estimate deviation warning message based on the difference.
In one embodiment, the weight preliminary estimation module 220 includes: the correcting unit is used for acquiring the deflection degree of a control plane of the aircraft; performing signal correction processing on the flight parameters based on the deflection skewness of the control surface to obtain corrected flight parameters; and the calculation processing unit is used for calculating and processing the corrected flight parameters to obtain the estimated flight weight of the aircraft.
In one embodiment, the flight parameters include dynamic pressure of the aircraft, aircraft wing reference area, normal overload, gravitational acceleration, and lift coefficient of a wing-body combination; the calculation processing unit is configured to: and calculating based on a formula W (QSCL)/(Ng) to obtain the estimated flight weight of the aircraft, wherein W is the estimated flight weight, Q is the dynamic pressure, S is the aircraft wing reference area, N is the normal overload, g is the gravitational acceleration, and CL is a corrected lift coefficient obtained by performing signal correction processing on the lift coefficient of the wing-body combination based on the control plane deflection.
It should be noted that although in the above detailed description several modules or units of the device for action execution are mentioned, such a division is not mandatory. Indeed, the features and functionality of two or more modules or units described above may be embodied in one module or unit, according to embodiments of the invention. Conversely, the features and functions of one module or unit described above may be further divided into embodiments by a plurality of modules or units.
In addition, an embodiment of the present invention further provides an electronic device, where the electronic device may be a terminal or a server, as shown in fig. 4, which shows a schematic structural diagram of the electronic device according to the embodiment of the present invention, specifically:
the electronic device may include components such as a processor 301 of one or more processing cores, memory 302 of one or more computer-readable storage media, a power supply 303, and an input unit 304. Those skilled in the art will appreciate that the electronic device configuration shown in fig. 4 does not constitute a limitation of the electronic device and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components. Wherein:
the processor 301 is a control center of the electronic device, connects various parts of the entire computer device by using various interfaces and lines, and performs various functions of the computer device and processes data by running or executing software programs and/or modules stored in the memory 302 and calling data stored in the memory 302, thereby performing overall monitoring of the electronic device. Optionally, processor 301 may include one or more processing cores; preferably, the processor 301 may integrate an application processor, which mainly handles operating systems, user pages, application programs, etc., and a modem processor, which mainly handles wireless communications. It will be appreciated that the modem processor described above may not be integrated into the processor 301.
The memory 302 may be used to store software programs and modules, and the processor 301 executes various functional applications and data processing by operating the software programs and modules stored in the memory 302. The memory 302 may mainly include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application program required by at least one function (such as a sound playing function, an image playing function, etc.), and the like; the storage data area may store data created according to use of the computer device, and the like. Further, the memory 302 may include high speed random access memory, and may also include non-volatile memory, such as at least one magnetic disk storage device, flash memory device, or other volatile solid state storage device. Accordingly, the memory 302 may also include a memory controller to provide the processor 301 with access to the memory 302.
The electronic device further comprises a power supply 303 for supplying power to the various components, and preferably, the power supply 303 may be logically connected to the processor 301 through a power management system, so that functions of managing charging, discharging, and power consumption are realized through the power management system. The power supply 303 may also include any component of one or more dc or ac power sources, recharging systems, power failure detection circuitry, power converters or inverters, power status indicators, and the like.
The electronic device may further include an input unit 304, and the input unit 304 may be used to receive input numeric or character information and generate keyboard, mouse, joystick, optical or trackball signal inputs related to user settings and function control.
Although not shown, the electronic device may further include a display unit and the like, which are not described in detail herein. Specifically, in this embodiment, the processor 301 in the electronic device loads the executable file corresponding to the process of one or more computer programs into the memory 302 according to the following instructions, and the processor 301 runs the computer program stored in the memory 302, thereby implementing various functions of the embodiments of the present application. Such as processor 301, may perform the following steps:
collecting flight parameters and state parameters of an aircraft; calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft; performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight; and performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft.
It will be understood by those skilled in the art that all or part of the steps of the methods of the above embodiments may be performed by a computer program, which may be stored in a computer-readable storage medium and loaded and executed by a processor, or by related hardware controlled by the computer program.
To this end, the embodiment of the present invention further provides a storage medium, in which a computer program is stored, where the computer program can be loaded by a processor to execute the steps in any one of the methods provided by the embodiment of the present invention.
Wherein the storage medium may include: read Only Memory (ROM), Random Access Memory (RAM), magnetic or optical disks, and the like.
For details, see the foregoing embodiments, and are not described herein again, since the computer program stored in the storage medium may execute steps in any method provided in the embodiments of the present invention, so as to achieve the beneficial effects that can be achieved by the method provided in the embodiments of the present invention.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the embodiments disclosed herein. This invention is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains.
It will be understood that the invention is not limited to the embodiments that have been described above and shown in the drawings, but that various modifications and changes can be made without departing from the scope thereof.
Claims (13)
1. A method of monitoring a flight weight of an aircraft, comprising:
collecting flight parameters and state parameters of an aircraft;
calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft;
performing evaluation processing based on the state parameters to obtain the deviation degree of the estimated flight weight;
performing logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft;
the obtaining of the target flight weight of the aircraft by performing logical operation processing according to the deviation degree comprises the following steps:
if the deviation degree is deviation, descending the target flight weight based on the target descending speed to obtain the non-deviated flight weight to be confirmed, wherein the target flight weight is historical estimated flight weight obtained by calculation processing based on flight parameters at the target moment, and the target moment is a calculation moment before the moment when the estimated flight weight deviates;
if the deviation degree is not deviated, taking the estimated flight weight as the flight weight to be confirmed;
generating a target flight weight for the aircraft based on the flight weight to be confirmed;
the descending processing is carried out on the target flight weight based on the target descending speed, and the flight weight to be confirmed which is not deviated is obtained, and the descending processing comprises the following steps:
calculating the product of the default oil consumption rate and a deviation duration to obtain a target drop value, wherein the deviation duration is a time period from a specific time to the activation time of the drop processing;
continuously subtracting the target descending value by using the target flight weight until the state parameter of the aircraft does not accord with a preset deviation condition, and obtaining the flight weight to be confirmed without deviation;
the generating a target flight weight for the aircraft based on the flight weight to be confirmed comprises:
if the aircraft is within a preset time length after takeoff, filtering the flight weight to be confirmed based on a first order filter to obtain the target flight weight of the aircraft;
and if the aircraft is in the preset takeoff time, filtering the flight weight to be confirmed based on a second first-order filter to obtain the target flight weight of the aircraft.
2. The method of claim 1, wherein the degree of deviation comprises deviation and no deviation; the evaluating based on the state parameter to obtain the deviation degree of the estimated flight weight comprises the following steps:
determining whether the state parameters meet preset deviation conditions or not to obtain a determination result;
if the determined result is that the preset deviation condition is met, determining the deviation degree of the estimated flight weight as deviation;
and if the determined result is that the predicted flight weight does not meet the preset deviation condition, determining that the deviation degree of the predicted flight weight is not deviated.
3. The method according to claim 2, wherein the determination result includes any one of a first determination result, a second determination result, a third determination result, a fourth determination result, and a fifth determination result; the determining whether the state parameter meets a preset deviation condition to obtain a determination result includes:
determining whether the normal overload is smaller than a first threshold or larger than a second threshold to obtain a first determination result, wherein the first threshold is smaller than the second threshold;
determining whether the instruction signal of the speed reducing plate is larger than a third threshold value or not to obtain a second determination result;
determining whether the attack angle protection effective signal is enabled or not to obtain a third determination result;
determining whether the abnormal attitude signal shows that the aircraft is in an abnormal attitude or not to obtain a fourth determination result;
and determining whether the horizontal tail rudder position signal is invalid or not to obtain a fifth determination result.
4. The method of claim 1, further comprising:
checking the target flight weight to obtain the effectiveness of the target flight weight;
determining an effective flight weight of the aircraft based on the effectiveness.
5. The method of claim 4, wherein said verifying said target flight weight to obtain a validity of said target flight weight comprises:
acquiring a ground speed signal and/or a wheel load signal of the aircraft;
and evaluating according to the ground speed signal and/or the wheel load signal to obtain the effectiveness of the target flight weight.
6. The method according to claim 5, wherein the evaluating according to the ground speed signal and/or the wheel load signal to obtain the effectiveness of the target flight weight comprises:
if the ground speed signal meets a signal validity condition and the ground speed signal is smaller than a preset threshold value, and/or the wheel-mounted signal meets a signal validity condition, the validity of the target flight weight is invalid;
and if the ground speed signal does not meet the signal validity condition and/or the ground speed signal is greater than the preset threshold value and/or the wheel load signal does not meet the signal validity condition, the validity of the target flight weight is valid.
7. The method of claim 4, wherein said determining an effective flight weight of the aircraft based on the effectiveness comprises:
if the effectiveness is effective, taking the target flight weight as the effective flight weight of the aircraft;
and if the effectiveness is invalid, determining the system estimated flight weight provided by the flight management system as the effective flight weight of the aircraft, wherein the system estimated flight weight is obtained by subtracting the real-time oil consumption from the aircraft weight.
8. The method of claim 7, wherein after said taking said target flight weight as an effective flight weight of said aircraft if said effectiveness is effective, said method further comprises:
comparing the target flight weight as the effective flight weight to a difference in system assessment flight weight provided by a flight management system;
generating a weight estimate deviation warning message based on the difference.
9. The method of claim 1, wherein the performing a calculation process based on the flight parameter to obtain an estimated flight weight of the aircraft comprises:
acquiring deflection degree of a control plane of the aircraft;
performing signal correction processing on the flight parameters based on the deflection skewness of the control surface to obtain corrected flight parameters;
and calculating and processing based on the corrected flight parameters to obtain the estimated flight weight of the aircraft.
10. The method of claim 9, wherein the flight parameters include dynamic pressure of the aircraft, aircraft wing reference area, normal overload, gravitational acceleration, and lift coefficient of a wing-body combination;
the calculating and processing based on the corrected flight parameters to obtain the estimated flight weight of the aircraft comprises the following steps:
and calculating based on a formula W (QSCL)/(Ng) to obtain the estimated flight weight of the aircraft, wherein W is the estimated flight weight, Q is the dynamic pressure, S is the reference area of the aircraft wing, N is the normal overload, g is the gravity acceleration, and CL is a corrected lift coefficient obtained by performing signal correction processing on the lift coefficient of the wing-body combination based on the deflection of the control surface.
11. A flight weight monitoring system for an aircraft, comprising:
the acquisition module is used for acquiring flight parameters and state parameters of the aircraft;
the weight preliminary estimation module is used for calculating and processing based on the flight parameters to obtain the estimated flight weight of the aircraft;
the estimation locking module is used for carrying out estimation processing based on the state parameters so as to obtain the deviation degree of the estimated flight weight;
the logical operation module is used for carrying out logical operation processing according to the deviation degree to obtain the target flight weight of the aircraft;
the logic operation module comprises: a first operation unit, configured to, if the deviation degree is a deviation, perform descent processing on a target flight weight based on a target descent rate to obtain an undistorted flight weight to be confirmed, where the target flight weight is a historical estimated flight weight obtained by calculation processing based on flight parameters at a target time, and the target time is a calculation time before a time at which the estimated flight weight deviates; the second operation unit is used for taking the estimated flight weight as the flight weight to be confirmed if the deviation degree is not deviated; a weight generating unit for generating a target flight weight of the aircraft based on the flight weight to be confirmed;
the first arithmetic unit is configured to: calculating the product of the default oil consumption rate and the deviation duration of the descending treatment to obtain a target descending value, wherein the deviation duration is the time period from the specific time to the activation time of the descending treatment; continuously subtracting the target descending value by using the target flight weight until the state parameter of the aircraft does not accord with a preset deviation condition, and obtaining the flight weight to be confirmed without deviation;
the weight generation unit is configured to: if the aircraft is within a preset time length after takeoff, filtering the flight weight to be confirmed based on a first order filter to obtain the target flight weight of the aircraft; and if the aircraft is in the preset takeoff time, filtering the flight weight to be confirmed based on a second first-order filter to obtain the target flight weight of the aircraft.
12. A storage medium having stored thereon a computer program which, when executed by a processor of a computer, causes the computer to carry out the method of any one of claims 1 to 10.
13. An electronic device, comprising: a memory storing a computer program; a processor reading a computer program stored in the memory to perform the method of any one of claims 1 to 10.
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| CN117369528A (en) * | 2023-12-04 | 2024-01-09 | 黑龙江惠达科技股份有限公司 | Method and device for controlling planting operation of plant protection unmanned aerial vehicle and unmanned aerial vehicle |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69613175D1 (en) * | 1995-05-15 | 2001-07-12 | Boeing Co | Method and device for linear real-time estimation of an aircraft mass center |
| US20170284856A1 (en) * | 2016-03-31 | 2017-10-05 | Cessna Aircraft Company | Aircraft weight estimation |
| CN108931258A (en) * | 2017-05-23 | 2018-12-04 | 空中客车运营简化股份公司 | Method and apparatus for monitoring and estimating the relevant parameter of flight to aircraft |
| CN111079296A (en) * | 2019-12-20 | 2020-04-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft component and aircraft flight load assessment method |
| CN112683446A (en) * | 2020-12-29 | 2021-04-20 | 中国航空工业集团公司西安飞机设计研究所 | Real-time center-of-gravity position estimation method for airplane |
| CN112926133A (en) * | 2021-02-09 | 2021-06-08 | 中国人民解放军火箭军工程大学 | Aircraft wing weight calculation method and device |
| CN113496058A (en) * | 2021-09-07 | 2021-10-12 | 中国民航大学 | Optimization method for cargo airplane load balancing problem, server and storage medium |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10732023B2 (en) * | 2016-03-24 | 2020-08-04 | Sikorsky Aircraft Corporation | Measurement system for aircraft, aircraft having the same, and method of measuring weight for aircraft |
-
2021
- 2021-11-30 CN CN202111439507.3A patent/CN114136416B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69613175D1 (en) * | 1995-05-15 | 2001-07-12 | Boeing Co | Method and device for linear real-time estimation of an aircraft mass center |
| US20170284856A1 (en) * | 2016-03-31 | 2017-10-05 | Cessna Aircraft Company | Aircraft weight estimation |
| CN108931258A (en) * | 2017-05-23 | 2018-12-04 | 空中客车运营简化股份公司 | Method and apparatus for monitoring and estimating the relevant parameter of flight to aircraft |
| CN111079296A (en) * | 2019-12-20 | 2020-04-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft component and aircraft flight load assessment method |
| CN112683446A (en) * | 2020-12-29 | 2021-04-20 | 中国航空工业集团公司西安飞机设计研究所 | Real-time center-of-gravity position estimation method for airplane |
| CN112926133A (en) * | 2021-02-09 | 2021-06-08 | 中国人民解放军火箭军工程大学 | Aircraft wing weight calculation method and device |
| CN113496058A (en) * | 2021-09-07 | 2021-10-12 | 中国民航大学 | Optimization method for cargo airplane load balancing problem, server and storage medium |
Non-Patent Citations (4)
| Title |
|---|
| Flight Test Applications of an Improved Operational Load Monitoring Device;Chan Yik Park 等;《International Journal of Aeronautical and Space Sciences》;20201231;第1-14页 * |
| 地效飞行器重量估算方法;李军等;《航空学报》;20100625(第06期);第72-78页 * |
| 基于凸多面体的结构性故障模型对飞行包线影响研究;吴彦鹏等;《科学技术与工程》;20131108(第31期);第94-99页 * |
| 飞行载荷发展综述;闫中午等;《航空工程进展》;20201231(第6期);第873-886页 * |
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