Aircraft four-dimensional motion rapid analysis method based on longitudinal static aerodynamic force simplification

Abstract

The invention relates to the technical field of aircraft four-dimensional motion simulation analysis, in particular to an aircraft four-dimensional motion rapid analysis method based on longitudinal static aerodynamic force simplification, which comprises the following steps: obtaining an aerodynamic data lookup table and an engine data lookup table based on aerodynamic data and engine data of an aircraft; establishing an aircraft four-dimensional motion analysis model for calculating flight state parameters according to the external influence parameters of the aircraft; acquiring a control signal of four-dimensional motion analysis of the aircraft to obtain the external influence parameters in the flight process; analyzing external influence parameters based on the aircraft four-dimensional motion analysis model to obtain flight state parameters; and processing the flight state parameters in the flight process to obtain a flight animation of the aircraft, and taking the flight animation and the flight state parameters in the flight process as analysis results. The method can improve the calculation efficiency of aircraft analysis.

Description

Technical Field

[0001] The present invention relates to the technical field of four-dimensional motion simulation analysis of aircraft, and in particular to a method for rapid analysis of four-dimensional motion of aircraft based on longitudinal static aerodynamic simplification. Background Art

[0002] In modern aerospace, flight simulation and analysis technology has become an indispensable tool in the design, testing, and validation of aircraft. By simulating the various performance and behaviors of aircraft on a computer, engineers can identify potential problems and optimize designs before actual flight testing, thereby reducing costs, shortening development cycles, and improving safety.

[0003] Four-dimensional motion simulation analysis of aircraft refers to the analysis of four dimensions of motion, including the increase and decrease of aircraft speed, the rise and fall of center of mass height, and pitch, as well as the time dimension. Currently, research on four-dimensional motion simulation analysis of aircraft mainly focuses on the following aspects: Establishment of dynamic model: The dynamic model of the aircraft is established through the method of numerical integration to simulate its motion behavior and response characteristics; Aerodynamic characteristics analysis: The aerodynamic database of the aircraft is introduced into the simulation model, and the aerodynamic characteristics and motion response of the aircraft are analyzed through simulation to evaluate its performance under different flight conditions; Engine characteristics and fuel consumption modeling: The engine model is established to analyze its performance and fuel consumption characteristics.

[0004] However, traditional simulation analysis methods have limitations in comprehensively considering aerodynamic, engine, and fuel consumption characteristics, making it difficult to meet the demands of rapid iteration in the early stages of design. For example, traditional simulation analysis models require extensive aerodynamic data, including static and dynamic derivatives, and require multiple integral calculations to simulate the aircraft's attitude. This computationally intensive and time-consuming simulation hinders the rapid iteration required in aircraft design and testing. Therefore, an integrated simulation analysis framework is urgently needed that can rapidly evaluate aircraft performance in the early stages of design and provide reliable data support for subsequent design and testing. Summary of the Invention

[0005] In view of the above problems, the present invention provides a method for rapid analysis of four-dimensional motion of an aircraft based on simplified longitudinal static aerodynamics, which solves the technical problem of low simulation calculation efficiency in the prior art.

[0006] The present invention provides a method for rapid analysis of four-dimensional motion of an aircraft based on longitudinal static aerodynamic simplification, comprising the following steps: Step S1, obtaining aerodynamic data and engine data of an aircraft during flight through aerodynamic numerical simulation or through sensors in a wind tunnel test, processing the aerodynamic data and engine data to obtain an aerodynamic data lookup table and an engine data lookup table; Step S2: establishing a four-dimensional motion analysis model for the aircraft, wherein the four-dimensional motion analysis model for the aircraft is capable of calculating flight state parameters based on external influencing parameters of the aircraft and a control signal of the four-dimensional motion analysis; Step S3, obtaining a control signal for four-dimensional motion analysis of the aircraft, and obtaining the external influencing parameters during flight based on the control signal and the aerodynamic data lookup table and the engine data lookup table; Step S4: analyzing the external influencing parameters during the flight based on the aircraft four-dimensional motion analysis model to obtain the flight state parameters during the flight; Step S5: Process the flight state parameters during the flight process to obtain a flight animation of the aircraft, and use the flight animation and the flight state parameters during the flight process as analysis results.

[0007] Preferably, in step S1, the aerodynamic data includes elevator deflection angle, angle of attack, lift coefficient, drag coefficient and pitch moment coefficient; the engine data includes engine shaft speed, throttle lever amount, aircraft speed and altitude, fuel pump speed and fuel consumption rate.

[0008] Preferably, in step S1, the processing of the pneumatic data and the engine data to obtain the pneumatic data lookup table and the engine data lookup table specifically includes: For any given elevator angle, multiple aircraft angle of attack and pitching moment coefficient pairs corresponding to the given elevator angle are obtained from the aerodynamic data. Two linear interpolation processes are performed based on the multiple aircraft angle of attack and pitching moment coefficient pairs to obtain a functional relationship between the pitching moment coefficient and the aircraft angle of attack:

[0009] in, The function that calculates the corresponding angle of attack from the pitching moment coefficient for a given elevator deflection angle, represents the pitching moment coefficient, is the angle of attack; solve the following equation numerically: Get the aircraft's trim angle of attack ; Based on the given elevator deflection angle and the trim angle of attack, searching the aerodynamic data to obtain a lift coefficient and a drag coefficient corresponding to the given elevator deflection angle and the trim angle of attack, ultimately obtaining the trim angle of attack, lift coefficient, and drag coefficient at different elevator deflection angles; and forming an aerodynamic data lookup table based on the trim angles of attack, lift coefficient, and drag coefficient at different elevator deflection angles; Based on the engine data, an engine data lookup table is formed by combining the relationship between the engine shaft rotation speed and the throttle lever amount, the relationship between the engine shaft rotation speed and the oil pump rotation speed, the relationship between the engine shaft rotation speed and the current speed and altitude of the aircraft and the engine thrust, and the relationship between the oil pump rotation speed and fuel consumption rate; The engine data lookup table includes a first engine data lookup table that records the engine shaft speed and the throttle lever amount, a second engine data lookup table that records the engine shaft speed and the oil pump speed, a third engine data lookup table that records the engine shaft speed and the current speed and altitude of the aircraft and the engine thrust, and a fourth engine data lookup table that records the oil pump speed and fuel consumption rate.

[0010] Preferably, the step S2 specifically includes: Step S2-1, determining a first relationship between the external influencing parameter and the aircraft force in the wind axis system; Step S2-2, determining a second relationship between the aircraft force under the wind axis system and the flight state parameter; Step S2-3: establishing the aircraft four-dimensional motion analysis model based on the first relationship and the second relationship.

[0011] Preferably, the step S2-1 specifically includes: Determining the external influencing parameters, wherein the external influencing parameters include lift, drag, thrust, gravity, trim angle of attack, track climb angle, and roll angle; the aircraft forces under the wind axis system include force components under the wind axis system x-axis and z-axis; The expression for determining the first relationship is:

[0012]

[0013] in, , They are the force components under the x-axis and z-axis of the wind axis, Indicates thrust, represents the trim angle of attack, Indicates resistance, represents gravity, represents the track climb angle, represents lift, Indicates the roll angle.

[0014] Preferably, the step S2-2 specifically includes: Determine the flight state parameters, where the flight state parameters include track climb angle, speed, forward distance, and altitude; the speed includes horizontal speed and vertical speed; and determine the expression for the second relationship as follows:

[0015]

[0016]

[0017]

[0018] in, represents the rate of change of the track climb angle, Indicates time, represents the vertical acceleration, represents the horizontal speed, Indicates the mass of the aircraft, represents the vertical speed, Represents the mass of the aircraft over time The change function of Indicates the distance traveled. Indicates height; The step S2-3 specifically includes: establishing a four-dimensional motion analysis model of the aircraft in combination with the first relationship and the second relationship, wherein the four-dimensional motion analysis model of the aircraft can calculate flight state parameters according to external influencing parameters of the aircraft.

[0019] Preferably, the step S3 specifically includes: Step S3-1, obtaining an input control signal, wherein the control signal includes a virtual joystick pitch signal and a virtual throttle signal; Step S3-2, obtaining the trim angle of attack, lift, drag, thrust and gravity according to the control signal and the aerodynamic data lookup table and the engine data lookup table; setting the track climb angle and roll angle.

[0020] Preferably, the step S3-2 specifically includes: The virtual joystick pitch signal in the control signal is converted into the elevator deflection angle, and the expression is:

[0021] in, Indicates the virtual joystick pitch signal, is the preset maximum elevator deflection angle, Indicates the elevator deflection angle; Input the elevator deflection angle corresponding to the virtual joystick pitch signal into the aerodynamic data lookup table to obtain the corresponding trim angle of attack , lift coefficient and drag coefficient , the lift and drag of the aircraft are calculated using the following expressions:

[0022]

[0023] in, Indicates the dynamic pressure in flight state, Indicates the aircraft reference area; determining a throttle lever amount based on the virtual throttle signal, inputting the throttle lever amount into the first engine data lookup table to obtain a corresponding engine shaft speed; inputting the engine shaft speed and the current speed and altitude of the aircraft into the third engine data lookup table to obtain a corresponding engine thrust; The engine shaft speed is input into the second engine data lookup table to obtain the oil pump speed; the oil pump speed is input into the fourth engine data lookup table to obtain the fuel consumption rate; the total weight of the front aircraft is obtained based on the fuel consumption rate, and the expression is:

[0024]

[0025]

[0026] in, is the initial fuel mass, Indicates the current fuel quality, Indicates fuel consumption rate, Indicates the mass of the aircraft after removing the fuel. Indicates the mass of the current aircraft. Indicates the current gravity of the aircraft. represents the acceleration due to gravity; Determine the initial track climb angle as , use the signal generator to generate the roll angle of the aircraft at different times.

[0027] Preferably, the step S4 specifically includes: A time-step simulation calculation method is adopted to calculate the flight state parameters according to the external influencing parameters at each time step, and the flight state parameters of the current time step are fed back to the next time step, and finally the flight state parameters of each time step are obtained.

[0028] Preferably, the step S5 specifically includes: The flight animation is generated based on the flight state parameters of each time step; and the aircraft speed change curve, the track climb angle change curve, the angle of attack change curve, and the forward distance and altitude change curve are generated based on the flight state parameters of each time step.

[0029] Compared with the prior art, the present invention has at least the following beneficial effects: (1) The four-dimensional aircraft motion analysis method provided by the present invention comprehensively considers the aircraft's engine characteristics, fuel characteristics, and weight characteristics, and can comprehensively evaluate flight performance and conduct simulation verification before a test flight. It has good versatility and can be applied to different types of aircraft by simply changing the aerodynamic data and engine data, significantly improving the flexibility and efficiency of the design process. In particular, in the early stages of aircraft design, the flight performance characteristics of different mission profiles can be calculated by simply inputting the aerodynamic coefficients and rudder deflection angles, avoiding the resource consumption of large-scale aerodynamic calculations.

[0030] (2) The present invention solves the trim angle of the aircraft at different rudder deflection angles through two linear interpolations, and determines the aircraft's attitude and aerodynamic forces by table lookup. This avoids the speed reduction problem caused by high-order multi-degree-of-freedom simulation and significantly improves the efficiency of simulation experiments. At the same time, the method of the present invention considers the impact of mass changes on aircraft motion and is designed as a portable Simulink package module, which is convenient for flexible application in other simulation models.

[0031] (3) The present invention comprehensively considers the effect of lateral maneuvers, namely the roll angle, on the forces acting on four-dimensional flight simulations. This effect is further reflected in changes in fuel consumption, making the simulation results more accurate. This comprehensive consideration significantly improves the accuracy and reliability of the simulation model, provides more scientific and accurate technical support for aircraft design and performance evaluation, and effectively reduces the risks and costs of actual test flights. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings are only for purposes of illustrating particular embodiments and are not to be considered limiting of the invention.

[0033] Figure 1 The present invention provides a flowchart of a method for rapid analysis of four-dimensional motion of an aircraft based on simplified longitudinal static aerodynamics.

[0034] Figure 2 A detailed flow chart of the method for rapid analysis of four-dimensional motion of an aircraft based on longitudinal static aerodynamic simplification provided by the present invention. DETAILED DESCRIPTION

[0035] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. In addition, the present invention can also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited by the specific embodiments disclosed below.

[0036] The present invention provides a method for rapid analysis of the four-dimensional motion of an aircraft based on simplified longitudinal static aerodynamics. By integrating the aerodynamic characteristics, engine characteristics and fuel consumption characteristics of the aircraft, the entire flight process of the aircraft can be efficiently simulated. Through the analysis method of the present invention, only the longitudinal aerodynamic static aerodynamic coefficients (lift, drag, pitch moment coefficient and rudder deflection angle) are needed to quickly predict the flight state, fuel demand and flight envelope range of the aircraft before the flight test, thereby reducing the complexity and data volume of the aerodynamic calculation work, and can optimize the flight mission plan, reduce the test risk, and improve the design efficiency and decision-making quality. The method provided by the present invention is not only of great significance in the early stage of design, but also provides strong support for subsequent aircraft improvements and performance optimization.

[0037] In order to illustrate the effectiveness of the method proposed by the present invention, the above technical solution of the present invention is described in detail below through a specific embodiment. Figure 1 、 Figure 2 As shown, a method for rapid analysis of four-dimensional motion of an aircraft based on longitudinal static aerodynamic simplification is disclosed. The specific implementation steps are as follows: Step S1: Acquiring aerodynamic data and engine data of an aircraft during flight through aerodynamic numerical simulation or through sensors in a wind tunnel test, processing the aerodynamic data and engine data to obtain an aerodynamic data lookup table and an engine data lookup table; the aerodynamic data includes elevator deflection angle, angle of attack, lift coefficient, drag coefficient, and pitching moment coefficient; and the engine data includes engine shaft speed, throttle lever amount, aircraft speed and altitude, fuel pump speed, and fuel consumption rate; In this step, the aerodynamic data and engine data of the aircraft during flight are first obtained.

[0038] In some embodiments, the aerodynamic data can be obtained through wind tunnel testing or computational fluid dynamics simulation. Specifically, in a wind tunnel test, an aircraft model is placed in a wind tunnel with sensors installed on the aircraft model. By varying the angle of attack and elevator deflection, the sensors measure the lift coefficient, drag coefficient, and pitching moment coefficient acting on the model. The lift coefficient, drag coefficient, and pitching moment coefficient corresponding to different elevator deflection and angle of attack are recorded to generate the aerodynamic data. Alternatively, computational fluid dynamics simulation methods can be used to numerically simulate the aircraft, calculating the lift coefficient, drag coefficient, and pitching moment coefficient at different angles of attack and elevator deflection to generate the aerodynamic data.

[0039] In some embodiments, data including the relationship between the engine shaft speed and the throttle lever amount, the relationship between the engine shaft speed and the current speed and altitude of the aircraft and the engine thrust, the relationship between the engine shaft speed and the oil pump speed, and the relationship between the oil pump speed and the fuel consumption rate can be obtained through engine bench testing, engine simulation or based on historical flight test data.

[0040] After obtaining the pneumatic data and the engine data, the present invention processes them to obtain a pneumatic data lookup table and an engine data lookup table.

[0041] The present invention obtains the trim angle of attack, lift coefficient, and drag coefficient at different elevator deflection angles for the aerodynamic data, and forms an aerodynamic data lookup table. The aerodynamic data lookup table uses the elevator deflection angle as an input key and the trim angle of attack, lift coefficient, and drag coefficient as output values.

[0042] The specific process of obtaining the trim angle of attack, lift coefficient and drag coefficient under different elevator deflection angles includes: Assume that the pitch moment coefficient of the aircraft is , then the pitching moment coefficient, angle of attack, and elevator deflection angle have the following relationship:

[0043] in, is the angle of attack, For a given elevator angle, The pitch moment coefficient is a function of the aircraft's angle of attack and the given elevator deflection angle. Based on this relationship, the trim angle of attack is obtained as follows.

[0044] For any given elevator angle, multiple aircraft angle of attack and pitching moment coefficient pairs corresponding to the given elevator angle are obtained from the aerodynamic data. Two linear interpolation processes are performed based on the multiple aircraft angle of attack and pitching moment coefficient pairs to obtain a functional relationship between the pitching moment coefficient and the aircraft angle of attack:

[0045] in, for The inverse function of The function that calculates the corresponding angle of attack from the pitch moment coefficient when the elevator deflection angle is given. When , the aircraft reaches balance at this elevator deflection angle, and the following equation can be solved numerically:

[0046] Get the aircraft's trim angle of attack Then, based on the given elevator deflection angle and the trim angle of attack, the aerodynamic data is searched to obtain the lift coefficient and the drag coefficient corresponding to the given elevator deflection angle and the trim angle of attack.

[0047] Repeat the above process to finally obtain the trim angle of attack, lift coefficient and drag coefficient under different elevator deflection angles.

[0048] For the engine data, an engine data lookup table is formed by combining the relationship between the engine shaft speed and the throttle lever amount, the relationship between the engine shaft speed and the oil pump speed, the relationship between the engine shaft speed and the current speed and altitude of the aircraft and the engine thrust, and the relationship between the oil pump speed and the fuel consumption rate; the engine data lookup table includes four groups of lookup tables, namely, a lookup table between the engine shaft speed and the throttle lever amount, a lookup table between the engine shaft speed and the oil pump speed, a lookup table between the engine shaft speed and the current speed and altitude of the aircraft and the engine thrust, and a lookup table between the oil pump speed and the fuel consumption rate.

[0049] Step S2: establishing a four-dimensional motion analysis model for the aircraft, wherein the four-dimensional motion analysis model for the aircraft is capable of calculating flight state parameters based on external influencing parameters of the aircraft and a control signal of the four-dimensional motion analysis; The external influencing parameters include lift, drag, thrust, gravity, trim angle of attack, track climb angle and roll angle, and the flight status parameters include track climb angle, speed, forward distance and altitude.

[0050] The four-dimensional aircraft motion analysis model provided by this invention not only considers the forces acting on the aircraft during motion but also incorporates aircraft weight and roll angle as reference factors. After determining lift, drag, thrust, gravity, angle of attack, track climb angle, and roll angle, the aircraft forces acting on the wind axis are calculated. The wind axis is a coordinate system fixed relative to the airflow direction and is commonly used to describe the aerodynamic characteristics of an aircraft. The expression is as follows:

[0051]

[0052] in, , They are the force components under the x-axis and z-axis of the wind axis, Indicates thrust, represents the trim angle of attack, Indicates resistance, represents gravity, represents the track climb angle, represents lift, Indicates the roll angle.

[0053] The track climb angle is the complementary angle between the velocity direction of the aircraft and the plumb line of the geodetic plane coordinate system.

[0054] In the above manner, the present invention introduces the roll angle when decomposing the force acting on the aircraft into the wind axis. The roll angle can change the direction of lift and thrust, requiring decomposition to more accurately calculate the force components in the wind axis. Therefore, the present invention incorporates the roll angle to achieve more accurate simulation results for four-dimensional motion. The force components in the wind axis are further used to calculate the aircraft's acceleration and velocity changes, thereby simulating the aircraft's trajectory.

[0055] For the calculation of flight state parameters, the present invention improves the fixed mass setting to allow real-time mass input, and then uses the integral method to calculate the flight path climb angle, speed, forward distance and altitude of the aircraft in the earth axis system. The expression is:

[0056]

[0057]

[0058]

[0059] in, represents the rate of change of the track climb angle, Indicates time, represents the vertical acceleration, represents the horizontal velocity, Indicates the mass of the aircraft, represents the vertical speed, Represents the mass of the aircraft over time The change function of Indicates the distance traveled. Indicates altitude.

[0060] In some embodiments, the process of calculating the flight path climb angle, speed, distance traveled, and altitude of the aircraft in the Earth's axis system can be specifically performed by modifying the Simulink 4th Order Point Mass module, improving the fixed mass setting to allow real-time mass input, and encapsulating the module. The Simulink 4th Order Point Mass module belongs to the analysis workspace of the numerical simulation software.

[0061] By calculating the aforementioned flight state parameters, integrating acceleration to obtain velocity, and then integrating velocity to obtain displacement, this method, combined with real-time mass changes, can more accurately simulate the trajectory of an aircraft. The aircraft's four-dimensional motion analysis model enables time-step-by-time simulation by feeding back the flight path climb angle and velocity to the previous time step.

[0062] Step S3: Acquire a control signal for the four-dimensional motion analysis of the aircraft, and obtain the external influencing parameters based on the control signal and the aerodynamic data lookup table and the engine data lookup table; like Figure 2 As shown, the present invention first obtains the input control signal when performing the four-dimensional motion analysis of the aircraft. The control signal includes a virtual joystick pitch signal and a virtual throttle signal, and the value ranges are respectively and .

[0063] In some embodiments, the control signals can be obtained through a user interface or virtual input device, such as a user inputting signals by operating a virtual joystick and throttle interface. These signals are processed by the acquisition module and converted into digital signals that can be used in the aircraft control system.

[0064] The virtual joystick pitch signal in the control signal After input, it is converted into elevator deflection angle, and the expression is:

[0065] in, Indicates the virtual joystick pitch signal, is the preset maximum elevator deflection angle, Indicates the elevator deflection angle.

[0066] Input the elevator deflection angle corresponding to the virtual joystick pitch signal into the aerodynamic data lookup table in step S1 to obtain the corresponding trim angle of attack , lift coefficient and drag coefficient The lift and drag of the aircraft are calculated using the following expressions:

[0067]

[0068] in, Indicates the dynamic pressure in flight state, Indicates the reference area of ​​the aircraft. In the case of fixed-wing aircraft, it generally refers to the main wing area.

[0069] The present invention obtains the thrust of the aircraft based on the virtual throttle signal, wherein the virtual throttle signal corresponds one-to-one with the rotational speed of the engine shaft. A throttle lever amount is determined based on the virtual throttle signal and then input into the engine data lookup table in step S1. Based on a lookup table of engine shaft rotational speed and throttle lever amount, and a lookup table of engine shaft rotational speed, current aircraft speed and altitude, and engine thrust, the corresponding engine shaft rotational speed is obtained from the throttle lever amount. Furthermore, the corresponding engine thrust is obtained from the lookup table based on the engine shaft rotational speed, current aircraft speed and altitude.

[0070] On the other hand, based on the engine shaft speed and oil pump speed lookup table and the oil pump speed and fuel consumption rate lookup table, the oil pump speed is obtained according to the engine shaft speed lookup table, and the fuel consumption rate is further obtained by looking up the table. For the real-time fuel consumption rate, the aircraft fuel consumption is simulated by integration to obtain the current fuel weight. The expression is:

[0071]

[0072]

[0073] in, is the initial fuel mass, Indicates the current fuel quality, Indicates fuel consumption rate, Indicates the mass of the aircraft after removing the fuel. Indicates the mass of the current aircraft. Indicates the current gravity of the aircraft. Represents the acceleration due to gravity.

[0074] The present invention can set the initial track climb angle as required The present invention uses a signal generator or a time-dependent function to set the roll angle of the aircraft at different times. The roll angle affects the model in terms of lift and thrust. Introducing the roll angle makes the simulation results of four-dimensional motion more accurate.

[0075] In the above manner, the present invention obtains external influencing parameters such as lift, drag, thrust, gravity, trim angle of attack, track climb angle and roll angle according to the input control signal, which are used for subsequent four-dimensional motion analysis.

[0076] Step S4: Analyze external influencing parameters during the flight process based on the aircraft four-dimensional motion analysis model to obtain flight state parameters during the flight process.

[0077] In this step, the present invention analyzes external parameters affecting flight using the aircraft's four-dimensional motion analysis model using a time-step simulation method. First, within each time step, the aircraft's acceleration is determined by calculating the force components in the wind axis. Velocity is then integrated to obtain velocity, and displacement is then integrated to obtain velocity. This process takes into account real-time mass changes, using the aforementioned fuel consumption calculation formula to determine the current aircraft gross weight, allowing for more accurate calculations of the flight path climb angle, horizontal velocity, and vertical velocity.

[0078] The aircraft's 4D motion analysis model implements time-step simulation calculations through a feedback mechanism. This mechanism uses the flight path climb angle and velocity calculated in the current time step as initial conditions for the next time step. Specifically, at the end of each time step, the calculated flight path climb angle, horizontal velocity, and vertical velocity state parameters are used as inputs for the next time step, ensuring the continuity and accuracy of the simulation process.

[0079] Step S5: Process the flight state parameters during the flight process to obtain a flight animation of the aircraft, and use the flight animation and the flight state parameters during the flight process as analysis results.

[0080] In this step, a dynamic animation display of the aircraft is generated by processing the flight status parameters during the flight.

[0081] In some embodiments, flight state parameters calculated time-by-time, such as track climb angle, speed, distance traveled, and altitude, are obtained and used to construct the trajectory of the aircraft in three-dimensional space. Computer graphics technology can then be used to convert this trajectory into a flight animation. In this animation, the aircraft's attitude, position, and motion path correspond to the actual calculated results, ensuring the authenticity and accuracy of the visual presentation. The animation not only displays the aircraft's external motion but also provides different viewing angles through virtual camera perspectives, enhancing the user's understanding of the flight process.

[0082] In some embodiments, based on the calculation results of each time step, an aircraft speed change curve, a track climb angle change curve, and a forward distance and altitude change curve can be drawn to intuitively display the change pattern of the aircraft's flight status parameters over time, providing a basis for aircraft performance evaluation and flight control strategy optimization.

[0083] Although the specific embodiments of the present invention have been described in a particular order, it should be understood that such actions or steps are required to be performed in the particular order shown or in a sequential order, or that all illustrated actions or steps are required to be performed to obtain the desired result. Under certain circumstances, multitasking and parallel processing may be advantageous. Similarly, although some specific implementation details have been included in the above discussion, these should not be construed as limiting the scope of the present disclosure. Some features described in the context of a separate embodiment can also be implemented in a single implementation in combination. On the contrary, the various features described in the context of a single implementation can also be implemented in multiple implementations individually or in any suitable sub-combination.

[0084] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

Claims

1. A method for rapid analysis of four-dimensional motion of an aircraft based on longitudinal static aerodynamic simplification, characterized in that: The following steps are involved: Step S1, obtaining aerodynamic data and engine data of an aircraft during flight through aerodynamic numerical simulation or through sensors in a wind tunnel test, processing the aerodynamic data and engine data to obtain an aerodynamic data lookup table and an engine data lookup table; Step S2: establishing a four-dimensional motion analysis model for the aircraft, wherein the four-dimensional motion analysis model for the aircraft is capable of calculating flight state parameters based on external influencing parameters of the aircraft and a control signal of the four-dimensional motion analysis; Step S3, obtaining a control signal for four-dimensional motion analysis of the aircraft, and obtaining the external influencing parameters during flight based on the control signal and the aerodynamic data lookup table and the engine data lookup table; Step S4: analyzing the external influencing parameters during the flight based on the aircraft four-dimensional motion analysis model to obtain the flight state parameters during the flight; Step S5: Process the flight state parameters during the flight process to obtain a flight animation of the aircraft, and use the flight animation and the flight state parameters during the flight process as analysis results.

2. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 1, characterized in that: In step S1, the aerodynamic data includes the elevator deflection angle, angle of attack, lift coefficient, drag coefficient and pitch moment coefficient; the engine data includes the engine shaft speed, throttle lever amount, aircraft speed and altitude, fuel pump speed and fuel consumption rate.

3. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 2, characterized in that: In step S1, the processing of the pneumatic data and the engine data to obtain the pneumatic data lookup table and the engine data lookup table specifically includes: For any given elevator angle, multiple aircraft angle of attack and pitching moment coefficient pairs corresponding to the given elevator angle are obtained from the aerodynamic data. Two linear interpolation processes are performed based on the multiple aircraft angle of attack and pitching moment coefficient pairs to obtain a functional relationship between the pitching moment coefficient and the aircraft angle of attack. Based on the functional relationship, the trim angle of attack of the aircraft is obtained. ; Based on the given elevator deflection angle and the trim angle of attack, searching the aerodynamic data to obtain a lift coefficient and a drag coefficient corresponding to the given elevator deflection angle and the trim angle of attack, ultimately obtaining the trim angle of attack, lift coefficient, and drag coefficient at different elevator deflection angles; and forming an aerodynamic data lookup table based on the trim angles of attack, lift coefficient, and drag coefficient at different elevator deflection angles; Based on the engine data, an engine data lookup table is formed by combining the relationship between the engine shaft rotation speed and the throttle lever amount, the relationship between the engine shaft rotation speed and the oil pump rotation speed, the relationship between the engine shaft rotation speed and the current speed and altitude of the aircraft and the engine thrust, and the relationship between the oil pump rotation speed and fuel consumption rate; The engine data lookup table includes a first engine data lookup table that records the engine shaft speed and the throttle lever amount, a second engine data lookup table that records the engine shaft speed and the oil pump speed, a third engine data lookup table that records the engine shaft speed and the current speed and altitude of the aircraft and the engine thrust, and a fourth engine data lookup table that records the oil pump speed and fuel consumption rate.

4. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 3, characterized in that: The step S2 specifically includes: Step S2-1, determining a first relationship between the external influencing parameter and the aircraft force in the wind axis system; Step S2-2, determining a second relationship between the aircraft force under the wind axis system and the flight state parameter; Step S2-3: establishing the aircraft four-dimensional motion analysis model based on the first relationship and the second relationship.

5. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 4, characterized in that: The step S2-1 specifically includes: Determine the external influencing parameters, which include lift, drag, thrust, gravity, trim angle of attack, track climb angle, and roll angle; and the aircraft forces under the wind axis system include force components under the x-axis and z-axis of the wind axis system.

6. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 5, characterized in that: The step S2-2 specifically includes: Determine the flight state parameters, where the flight state parameters include track climb angle, speed, forward distance, and altitude; the speed includes horizontal speed and vertical speed; and determine the expression for the second relationship as follows: in, represents the rate of change of the track climb angle, Indicates time, represents the vertical acceleration, represents the horizontal speed, Indicates the mass of the aircraft, represents the vertical speed, Represents the mass of the aircraft over time The change function of Indicates the distance traveled. Indicates height; The step S2-3 specifically includes: establishing a four-dimensional motion analysis model of the aircraft in combination with the first relationship and the second relationship, wherein the four-dimensional motion analysis model of the aircraft can calculate flight state parameters according to external influencing parameters of the aircraft.

7. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 6, characterized in that: The step S3 specifically includes: Step S3-1, obtaining an input control signal, wherein the control signal includes a virtual joystick pitch signal and a virtual throttle signal; Step S3-2, obtaining the trim angle of attack, lift, drag, thrust and gravity according to the control signal and the aerodynamic data lookup table and the engine data lookup table; setting the track climb angle and roll angle.

8. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 7, characterized in that: The step S3-2 specifically includes: Converting a virtual joystick pitch signal in the control signal into an elevator deflection angle; Input the elevator deflection angle corresponding to the virtual joystick pitch signal into the aerodynamic data lookup table to obtain the corresponding trim angle of attack , lift coefficient and drag coefficient , calculate the lift and drag of the aircraft; determining a throttle lever amount based on the virtual throttle signal, inputting the throttle lever amount into the first engine data lookup table to obtain a corresponding engine shaft speed; inputting the engine shaft speed and the current speed and altitude of the aircraft into the third engine data lookup table to obtain a corresponding engine thrust; Inputting the rotational speed of the engine shaft into the second engine data lookup table to obtain the rotational speed of the oil pump; inputting the rotational speed of the oil pump into the fourth engine data lookup table to obtain the fuel consumption rate; and obtaining the gross weight of the front aircraft based on the fuel consumption rate; Determine the initial track climb angle as , use the signal generator to generate the roll angle of the aircraft at different times.

9. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 8, characterized in that: The step S4 specifically includes: A time-step simulation calculation method is adopted to calculate the flight state parameters according to the external influencing parameters at each time step, and the flight state parameters of the current time step are fed back to the next time step, and finally the flight state parameters of each time step are obtained.

10. The method for rapid analysis of four-dimensional aircraft motion based on longitudinal static aerodynamic simplification according to claim 9, characterized in that: The step S5 specifically includes: The flight animation is generated based on the flight state parameters of each time step; and the aircraft speed change curve, the track climb angle change curve, the angle of attack change curve, and the forward distance and altitude change curve are generated based on the flight state parameters of each time step.

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