Aircraft early warning method, system, device and computer-readable storage medium based on flight quality

Abstract

The present invention belongs to the field of flight control technology, and specifically relates to an aircraft warning method, system, device and computer-readable storage medium based on flight quality, aiming to solve the problem of the lack of real-time risk prediction capability of aircraft. The method of the present invention includes: establishing a longitudinal dynamic model of the aircraft; determining the longitudinal short-period frequency of the aircraft based on the model; determining the longitudinal short-period damping ratio of the aircraft based on the flight quality; constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio; generating the desired control parameters of the aircraft based on the constrained longitudinal short-period frequency; and issuing a warning based on the desired control parameters. The present invention can convert the longitudinal dynamic characteristics of the aircraft into quantifiable desired control indicators, and realize abnormal warning of flight quality through real-time comparison; improve the comfort and accuracy of the pilot's operation, reduce the probability of unsafe events in the aircraft, provide a scientific monitoring method for the safe operation of the aircraft, and improve the safety of the aircraft.

Description

Technical Field

[0001] The present invention belongs to the field of flight control technology, and in particular relates to an aircraft early warning method, system, device and computer-readable storage medium based on flight quality. Background Art

[0002] Flying qualities, also known as aircraft handling qualities, are the various characteristics of an aircraft that affect flight safety and the ease with which the pilot controls it. Aircraft design must adhere to and meet certain quality standards.

[0003] Forward research on flight qualities involves proactively optimizing aircraft performance, stability, and controllability through theoretical modeling, simulation verification, and experimental analysis, drawing on perspectives such as aircraft design, control theory, and human-machine interaction. Reverse research on flight qualities is a crucial pillar of aviation safety and performance optimization. By employing a "workaround" approach, it overcomes the idealistic limitations of forward design and promotes quality management throughout the aircraft lifecycle.

[0004] Traditional flight quality reverse engineering studies often employ a passive accident analysis model, limited to analyzing black box data after an accident. Accidents are only discovered and corrected after the fact, lacking real-time risk prediction capabilities. This results in potential safety hazards not being detected in time during flight, leading to accidents. Summary of the Invention

[0005] In order to solve the above-mentioned problem in the prior art, namely, the problem that aircraft lack real-time risk prediction capability, the present invention provides an aircraft early warning method based on flight quality, comprising:

[0006] Establish the longitudinal dynamics model of the aircraft;

[0007] determining the longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model;

[0008] determining a longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft;

[0009] constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio;

[0010] Generate the desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency;

[0011] An early warning is issued based on the desired manipulation parameters.

[0012] In an optional embodiment, determining the longitudinal short-period damping ratio of the aircraft according to the flight qualities of the aircraft includes:

[0013] In a pre-stored correspondence table, according to the flight grade corresponding to the aircraft flying quality, searching for a damping ratio corresponding to the flight grade and determining that the damping ratio is a longitudinal short-period damping ratio;

[0014] The correspondence table is a data table for storing flight levels and damping ratios corresponding to the flight levels.

[0015] In an optional embodiment, constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio includes:

[0016] determining a short-period damping ratio of the aircraft according to the longitudinal short-period frequency;

[0017] The short-period damping ratio is determined to be within a fluctuation range of the longitudinal short-period damping ratio.

[0018] In an optional embodiment, generating the desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency includes:

[0019] The longitudinal short-period frequency is input into a preset expected calculation model to obtain the expected control parameters of the aircraft.

[0020] The expected calculation model is:

[0021] ;

[0022] in, is the longitudinal short-period frequency of the aircraft, is normal overload; is the angle of attack, which is the angle between the aircraft velocity vector and the chord line of the wing.

[0023] In an optional embodiment, the issuing of an early warning based on the expected manipulation parameter includes:

[0024] The stability range of the aircraft is determined according to the desired manipulation parameter, and an early warning is issued when it is determined that the desired manipulation parameter is greater than a preset value.

[0025] In an optional embodiment, the longitudinal dynamics model is:

[0026] ;

[0027] in, is the longitudinal short-period frequency of the aircraft; is the longitudinal static stability derivative; is the derivative of the pitching moment with respect to the pitching angular velocity; is the derivative of the normal force with respect to the angle of attack.

[0028] Another aspect of the present invention provides an aircraft warning system based on flight quality, comprising:

[0029] Model module, used to establish the longitudinal dynamics model of the aircraft;

[0030] a processing module, configured to determine a longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model;

[0031] a damping ratio module, configured to determine a longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft;

[0032] a constraint module, configured to constrain the longitudinal short-period frequency based on the longitudinal short-period damping ratio;

[0033] A parameter module, used for generating desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency;

[0034] An early warning module is used to issue an early warning based on the expected manipulation parameters.

[0035] A third aspect of the present invention provides an electronic device, comprising:

[0036] at least one processor;

[0037] and a memory communicatively coupled to at least one of said processors;

[0038] The memory stores instructions that can be executed by the processor, and the instructions are used to be executed by the processor to implement the above-mentioned aircraft warning method based on flight quality.

[0039] In a fourth aspect of the present invention, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are used to be executed by the computer to implement the above-mentioned aircraft warning method based on flight quality.

[0040] Beneficial effects of the present invention:

[0041] (1) The present invention can convert the longitudinal dynamic characteristics of an aircraft into quantifiable control expectation indicators, and then realize abnormal flight quality warning through real-time comparison.

[0042] (2) The present invention can improve the comfort and accuracy of pilot operations, reduce the probability of aircraft unsafe incidents, provide a scientific monitoring method for the safe operation of aircraft, and improve the safety of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Other features, objects and advantages of the present application will become more apparent upon reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0044] Figure 1 This is a flow chart of an aircraft early warning method based on flight quality provided by this application.

[0045] Figure 2 It is a structural diagram of a computer system of a server for implementing the method, system, and device embodiments of the present application. DETAILED DESCRIPTION

[0046] The present application will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are intended only to illustrate the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the relevant invention are shown in the accompanying drawings.

[0047] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0048] The present invention provides an aircraft early warning method based on flight quality. In order to more clearly explain the aircraft early warning method based on flight quality of the present invention, the following is combined with Figure 1 Each step in the embodiment of the present invention is described in detail.

[0049] The aircraft warning method based on flight quality according to the first embodiment of the present invention includes steps S101 to S106, each of which is described in detail as follows:

[0050] S101: Establish a longitudinal dynamics model of the aircraft.

[0051] In this step, a mathematical model describing the aircraft's longitudinal (pitch) motion characteristics, known as the longitudinal dynamics model, is constructed. This model captures the essential characteristics of the aircraft's longitudinal motion, namely its short-period modes, forming a computable and analyzable mathematical framework. This allows for a precise description of the aircraft's longitudinal motion patterns, providing data support for subsequent frequency analysis and the generation of warning parameters.

[0052] In this embodiment, the longitudinal dynamic model is:

[0053] ;

[0054] in, The aircraft's longitudinal short-period frequency, measured in rad / s, describes the speed of the aircraft's longitudinal short-period oscillations and is an important parameter for measuring the aircraft's longitudinal short-period dynamic characteristics. The higher this frequency, the more frequent the aircraft's longitudinal short-period oscillations. This is the derivative of longitudinal static stability, also known as the dimensionless derivative of the pitching moment with respect to the angle of attack. It reflects the change in the pitching moment of the aircraft as the angle of attack changes. When the derivative of longitudinal static stability is less than zero, the aircraft has longitudinal static stability. A larger absolute value indicates greater static stability. The derivative of the pitching moment with respect to the pitching angular velocity, also called the dimensionless derivative of the pitching moment with respect to the pitching angular velocity, reflects the change in pitching moment when the pitching angular velocity changes, primarily reflecting the effect of aerodynamic damping on the pitching moment. is the derivative of the normal force with respect to the angle of attack. It reflects the change in the normal force as the angle of attack changes. In longitudinal dynamics analysis, it and parameters related to the pitching moment jointly affect the longitudinal motion characteristics of the aircraft.

[0055] S102: Determine the longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model.

[0056] In this step, the oscillation frequency of the aircraft's short-period mode is extracted from the longitudinal dynamics model. This frequency is a core parameter that characterizes the aircraft's longitudinal dynamic stability and control response characteristics. The short-period frequency reflects the aircraft's rapid response characteristics in the pitch direction, such as the oscillation frequency of the aircraft's pitch angle when the pilot operates the elevator. A higher frequency generally means a faster response, but may also be accompanied by greater control difficulty. The frequency parameter is used to assess whether the aircraft's flight qualities meet design standards (such as the control quality specifications for military or civilian aircraft, such as MIL-F-8785E) and determine whether it is in a safe and controllable state. Converting the dynamic model into characteristic parameters (short-period frequency) provides a direct basis for quantifying flight qualities and is a key intermediate quantity connecting the physical model with the early warning logic.

[0057] Specifically, the longitudinal static stability derivative of the aircraft, the derivative of the pitching moment with respect to the pitch angular velocity, and the derivative of the normal force with respect to the angle of attack are obtained, and the obtained longitudinal static stability derivative of the aircraft, the derivative of the pitching moment with respect to the pitch angular velocity, and the derivative of the normal force with respect to the angle of attack are input into the longitudinal dynamic model in step S101 to obtain the longitudinal short-period frequency of the aircraft.

[0058] S103: Determine the longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft.

[0059] S104: constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio.

[0060] S105: Generate desired control parameters for the aircraft according to the constrained longitudinal short-cycle frequency.

[0061] In steps S103, S104, and S105, the short-period frequency is used to derive the desired parameters that the pilot should meet when maneuvering the aircraft. These parameters include the relationship between control surface deflection and pitch acceleration, the matching value between joystick force and response frequency, and so on. A mapping relationship between "frequency characteristics" and "maneuverability expectations" is established, transforming abstract dynamic parameters into concrete indicators that can directly guide pilot operation or autopilot system control. For example, if the short-period frequency deviates from the designed value, the desired maneuverability parameters can prompt the pilot to adjust their control force or strategy. Furthermore, a range of maneuverability parameters under "normal flight quality" is defined. When the actual maneuverability parameters deviate from the desired parameters beyond a threshold, this can serve as a basis for early warning.

[0062] When determining the longitudinal short-period damping ratio of the aircraft based on the flight qualities of the aircraft, a damping ratio corresponding to the flight level corresponding to the flight qualities of the aircraft is searched in a pre-stored correspondence table, and the damping ratio is determined to be the longitudinal short-period damping ratio.

[0063] The corresponding relationship table is used to store the flight level and the damping ratio corresponding to the flight level. The data table in this embodiment is as follows:

[0064]

[0065] It should be noted that an aircraft's flight qualities can be divided into three levels according to the Cooper-Harper scale: Level 1: The handling qualities are clearly suitable for completing flight missions; Level 2: The handling qualities meet the requirements for safe operation, but the pilot's workload is increased or the mission completion effect is poor, or both; Level 3: The handling qualities meet the requirements for safe operation, but the pilot's workload is too heavy or the mission completion effect is poor, or both.

[0066] When the longitudinal short period frequency is constrained based on the longitudinal short period damping ratio, the short period damping ratio of the aircraft is determined according to the longitudinal short period frequency. ; Determine that the short-period damping ratio is within the fluctuation range of the longitudinal short-period damping ratio.

[0067] Specifically, the short-period damping ratio of the aircraft is calculated by the following formula: .

[0068] .

[0069] Through the above formula, based on the longitudinal short period frequency Ability to determine short-period damping ratio .

[0070] As shown in the table above, after determining that the aircraft's flight quality is level 1, the damping ratio is determined. The range of (0.35-1.3, or 0.3-2.0) is the fluctuation range of the longitudinal short-period damping ratio. It is necessary to determine the short-period damping ratio The ratio is within the fluctuation range of the longitudinal short-period damping ratio.

[0071] When generating the desired control parameters of the aircraft according to the longitudinal short-cycle frequency, the longitudinal short-cycle frequency is input into a preset desired calculation model to obtain the desired control parameters of the aircraft.

[0072] Specifically, the control anticipation parameter (CAP) is the ratio of the initial pitch attitude change to the steady-state flight normal overload change. The CAP reflects the relationship between the short-period natural oscillation frequency and overload sensitivity, and also reflects the speed of the pilot's control response. The preset anticipation calculation model is as follows:

[0073] ;

[0074] in, Normal overload is the ratio of the normal force acting on the aircraft to its own gravity. It reflects the force acting on the aircraft in the vertical direction and its maneuverability. The angle of attack is the angle between the aircraft's velocity vector and the wing's chord. The angle of attack significantly affects the aircraft's aerodynamic characteristics, such as lift and drag, and is a crucial parameter for an aircraft's flight state.

[0075] S106: Produce a warning based on the expected manipulation parameters.

[0076] In this step, the actual aircraft control parameters are compared with the desired parameters generated in step S105. If the deviation exceeds a preset threshold, a warning is triggered, indicating potential flight quality degradation or control risk. For example, if the short cycle frequency decreases due to aerodynamic changes (such as icing or component failure), the deviation between the desired and actual control parameters will increase, and the warning system can promptly alert the pilot to take action.

[0077] This step provides intuitive safety warnings by comparing expected control parameters, identifying signs of flight quality degradation in advance, avoiding the risk of loss of control due to abnormal control characteristics, and improving flight safety. It also provides decision support for aircraft fault diagnosis and emergency response.

[0078] In this embodiment, issuing an early warning based on the expected manipulation parameter includes:

[0079] The stability range of the aircraft is determined according to the desired manipulation parameter, and an early warning is issued when it is determined that the desired manipulation parameter is greater than a preset value.

[0080] It should be noted that the stability range refers to the reasonable range of desired control parameters that an aircraft should meet under normal flight qualities. This range is determined based on the aircraft's dynamic characteristics and ensures the aircraft's controllability and safety within this range. In this embodiment, flight tests or simulations are conducted to verify the actual response of the aircraft under different desired control parameters. Parameter values ​​that cause oscillation, loss of control, or difficulty in control are eliminated, ultimately determining a safe and stable range.

[0081] In this step, the preset value is the upper threshold of the stability range. If the desired control parameter (such as the pitch rate corresponding to the joystick displacement) is too large, a small maneuver by the pilot may cause the aircraft to pitch violently, increasing control difficulty and even triggering pilot-induced oscillations (PIO). Exceeding the limit of the desired control parameter may indicate abnormal aerodynamic characteristics (such as aft center of gravity shift, control surface binding) or system failure, resulting in an abnormal increase in short-term frequency and decreased stability.

[0082] Specifically, the system collects actual aircraft control parameters (such as current joystick force and pitch response gain) and compares them with the desired control parameters generated in step S105 and preset thresholds. If the desired control parameter (such as a gain value) exceeds the preset upper limit, the system determines that the aircraft is "overly sensitive" or "dynamically abnormal," triggering a warning signal (such as an audible and visual alarm, or a cockpit prompt).

[0083] As can be seen from the foregoing description, the flight quality-based aircraft warning method provided in the embodiments of the present application establishes an aircraft longitudinal dynamics model; determines the aircraft's longitudinal short-cycle frequency based on the longitudinal dynamics model; generates the aircraft's desired control parameters based on the longitudinal short-cycle frequency; and issues warnings based on the desired control parameters. This method can convert the aircraft's longitudinal dynamics characteristics into quantifiable desired control indicators, and then provide warnings for abnormal flight quality through real-time comparison. This method improves pilot comfort and accuracy, reduces the probability of unsafe aircraft events (such as loss of control, stall, and abnormal vibration), and provides a scientific monitoring method for safe aircraft operation, thereby enhancing aircraft safety.

[0084] Although the various steps in the above embodiment are described in the above-mentioned order, those skilled in the art will understand that in order to achieve the effect of this embodiment, different steps do not have to be executed in such an order. They can be executed simultaneously (in parallel) or in a reverse order. These simple changes are within the scope of protection of the present invention.

[0085] The aircraft warning system based on flight quality according to the second embodiment of the present invention includes:

[0086] Model module, used to establish the longitudinal dynamics model of the aircraft;

[0087] a processing module, configured to determine a longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model;

[0088] a damping ratio module, configured to determine a longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft;

[0089] a constraint module, configured to constrain the longitudinal short-period frequency based on the longitudinal short-period damping ratio;

[0090] A parameter module, used for generating desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency;

[0091] An early warning module is used to issue an early warning based on the expected manipulation parameters.

[0092] Among them, the damping ratio module includes:

[0093] a damping unit configured to search a pre-stored correspondence table for a damping ratio corresponding to a flight level corresponding to the aircraft flying qualities, and determine that the damping ratio is a longitudinal short-period damping ratio;

[0094] The correspondence table is a data table for storing flight levels and damping ratios corresponding to the flight levels.

[0095] The constraint module includes:

[0096] A constraint unit is used to determine the short-period damping ratio of the aircraft according to the longitudinal short-period frequency; and to determine that the short-period damping ratio is within a fluctuation range of the longitudinal short-period damping ratio.

[0097] The parameter module includes:

[0098] The expectation unit is used to input the constrained longitudinal short-period frequency into a preset expectation calculation model to obtain the control expectation parameter CAP of the aircraft.

[0099] Wherein, the expected calculation model is:

[0100] ;

[0101] in, is the longitudinal short-period frequency of the aircraft, is normal overload; is the angle of attack, which is the angle between the aircraft velocity vector and the chord line of the wing.

[0102] In an optional embodiment, the early warning module includes:

[0103] The early warning unit is used to determine the stability range of the aircraft according to the expected manipulation parameter, and to issue an early warning when it is determined that the expected manipulation parameter is greater than a preset value.

[0104] In an optional embodiment, the longitudinal dynamics model is:

[0105] ;

[0106] in, is the longitudinal short-period frequency of the aircraft; is the longitudinal static stability derivative; is the derivative of the pitching moment with respect to the pitching angular velocity; is the derivative of the normal force with respect to the angle of attack.

[0107] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working process and related instructions of the system described above can refer to the corresponding process in the aforementioned method embodiment and will not be repeated here.

[0108] It should be noted that the flight quality-based aircraft warning system provided in the above embodiment is only illustrated by the division of the above functional modules. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the modules or steps in the embodiments of the present invention can be further decomposed or combined. For example, the modules in the above embodiment can be combined into one module, or further divided into multiple sub-modules to complete all or part of the functions described above. The names of the modules and steps involved in the embodiments of the present invention are only for distinguishing the modules or steps and are not to be regarded as improper limitations on the present invention.

[0109] An electronic device according to a third embodiment of the present invention includes:

[0110] at least one processor;

[0111] and a memory communicatively coupled to at least one of said processors;

[0112] The memory stores instructions that can be executed by the processor, and the instructions are used to be executed by the processor to implement the above-mentioned aircraft warning method based on flight quality.

[0113] A fourth embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are configured to be executed by the computer to implement the aforementioned aircraft warning method based on flight quality.

[0114] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working processes and related instructions of the storage device and processing device described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0115] Those skilled in the art should be able to appreciate that the modules and method steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of the two, and the programs corresponding to the software modules and method steps can be placed in random access memory (RAM), internal memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disks, removable disks, CD-ROMs, or any other form of storage medium known in the art. In order to clearly illustrate the interchangeability of electronic hardware and software, the above description has generally described the components and steps of each example according to their functions. Whether these functions are performed in electronic hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0116] Reference below Figure 2 , which shows a structural diagram of a computer system of a server for implementing the method, system, and device embodiments of the present application. Figure 2 The server shown is merely an example and should not limit the functions and scope of use of the embodiments of the present application.

[0117] like Figure 2 As shown, the computer system includes a central processing unit (CPU) 201, which can perform various appropriate actions and processes according to the program stored in the read-only memory (ROM) 202 or the program loaded from the storage part 208 to the random access memory (RAM) 203. Various programs and data required for system operation are also stored in the RAM 203. The CPU 201, ROM 202 and RAM 203 are connected to each other via a bus 204. An input / output (I / O) interface 205 is also connected to the bus 204.

[0118] The following components are connected to the I / O interface 205: an input section 206 including a keyboard, a mouse, and the like; an output section 207 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 208 including a hard disk and the like; and a communication section 209 including a network interface card such as a LAN (Local Area Network) card or a modem. The communication section 209 performs communication processing via a network such as the Internet. A drive 210 is also connected to the I / O interface 205 as needed. A removable medium 211, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 210 as needed, so that a computer program read therefrom can be installed into the storage section 208 as needed.

[0119] In particular, according to an embodiment of the present disclosure, the process described above with reference to the flowchart can be implemented as a computer software program. For example, an embodiment of the present disclosure includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 209, and / or installed from the removable medium 211. When the computer program is executed by the central processing unit (CPU) 201, the above-mentioned functions defined in the method of the present application are executed. It should be noted that the computer-readable medium mentioned above in the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transfer a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code embodied on a computer-readable medium may be transmitted using any suitable medium, including, but not limited to, wireless, wire, optical cable, RF, etc., or any suitable combination thereof.

[0120] Computer program code for performing the operations of the present application may be written in one or more programming languages, or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a stand-alone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., through the Internet using an Internet service provider).

[0121] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order than that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0122] The terms "first", "second", etc. are used to distinguish similar objects, rather than to describe or indicate a particular order or sequence.

[0123] The term "comprise" or any other similar term is intended to cover non-exclusive inclusion such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0124] Thus far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the scope of protection of the present invention is obviously not limited to these specific embodiments. Without departing from the principles of the present invention, those skilled in the art may make equivalent changes or substitutions to the relevant technical features, and the technical solutions after such changes or substitutions will fall within the scope of protection of the present invention.

Claims

1. An aircraft early warning method based on flight quality, characterized in that: include: A longitudinal dynamics model of the aircraft is established, which is: ； in, is the longitudinal short-period frequency of the aircraft; is the longitudinal static stability derivative; is the derivative of the pitching moment with respect to the pitching angular velocity; is the derivative of the normal force with respect to the angle of attack; determining the longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model; determining a longitudinal short-period damping ratio of the aircraft based on the flight quality of the aircraft; constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio; Generate the desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency; Producing an early warning based on the desired manipulation parameters; Determining the longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft includes: In a pre-stored correspondence table, according to the flight level corresponding to the aircraft flying qualities, searching for a damping ratio corresponding to the flight level and determining that the damping ratio is a longitudinal short-period damping ratio; wherein the correspondence table is a data table for storing flight levels and corresponding damping ratios; The constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio includes: Determining a short-period damping ratio of the aircraft according to the longitudinal short-period frequency; and determining that the short-period damping ratio is within a fluctuation range of the longitudinal short-period damping ratio; Generating the desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency includes: The constrained longitudinal short-period frequency is input into a preset expected calculation model to obtain the expected control parameters of the aircraft; the expected calculation model is: ； in, is the longitudinal short-period frequency of the aircraft, is normal overload; is the angle of attack, which is the angle between the aircraft velocity vector and the chord line of the wing.

2. The aircraft warning method based on flight quality according to claim 1, characterized in that: The issuing of an early warning based on the expected manipulation parameter includes: The stability range of the aircraft is determined according to the desired manipulation parameter, and an early warning is issued when it is determined that the desired manipulation parameter is greater than a preset value.

3. An aircraft warning system based on flight quality, characterized in that: include: The model module is used to establish the longitudinal dynamics model of the aircraft. The longitudinal dynamics model is: ； in, is the longitudinal short-period frequency of the aircraft; is the longitudinal static stability derivative; is the derivative of the pitching moment with respect to the pitching angular velocity; is the derivative of the normal force with respect to the angle of attack; a processing module, configured to determine a longitudinal short-period frequency of the aircraft according to the longitudinal dynamics model; a damping ratio module, configured to determine a longitudinal short-period damping ratio of the aircraft according to the flight quality of the aircraft; a constraint module, configured to constrain the longitudinal short-period frequency based on the longitudinal short-period damping ratio; A parameter module, used for generating desired control parameters of the aircraft according to the constrained longitudinal short-cycle frequency; An early warning module, configured to issue an early warning based on the expected manipulation parameters; The damping ratio module includes a damping unit, which is configured to search a pre-stored correspondence table for a damping ratio corresponding to a flight level corresponding to the flight quality of the aircraft, and determine that the damping ratio is a longitudinal short-period damping ratio; wherein the correspondence table is a data table for storing flight levels and corresponding damping ratios; The constraint module includes a constraint unit, the constraint unit being configured to determine a short-period damping ratio of the aircraft according to the longitudinal short-period frequency; and determining that the short-period damping ratio is within a fluctuation range of the longitudinal short-period damping ratio; The parameter module includes an expectation unit, which is used to input the constrained longitudinal short-period frequency into a preset expectation calculation model to obtain the aircraft's control expectation parameter CAP; wherein the expectation calculation model is: ； in, is the longitudinal short-period frequency of the aircraft, Normal overload; is the angle of attack, which is the angle between the aircraft velocity vector and the chord line of the wing.

4. An electronic device, characterized in that: include: at least one processor; and a memory communicatively coupled to at least one of said processors; The memory stores instructions that can be executed by the processor, and the instructions are used to be executed by the processor to implement the aircraft warning method based on flight quality as described in any one of claims 1-2.

5. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to be executed by the computer to implement the aircraft warning method based on flight quality according to any one of claims 1-2.

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