Flight performance calculation method and device
Through flight action mechanics equations and iterative calculation methods, combined with the initial state of the aircraft and flight environment parameters, the problems of inefficiency and large errors of traditional flight performance calculation methods are solved, and fast and accurate flight performance calculation and state evaluation are achieved to ensure the safe takeoff and landing of the aircraft.
Patent Information
- Application Number
- CN202411628033.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-14
- Publication Date
- 2025-04-25
AI Technical Summary
Traditional aircraft flight performance data calculation methods are inefficient in calculations, have large errors, and cannot intuitively observe the aircraft's flight results.
The flight performance parameters of the aircraft are calculated through the flight action mechanics equation, including parameters such as aircraft weight, altitude, Mach number, overload and fuel consumption. Combined with the aircraft's initial state parameters and flight environment parameters, iterative calculations are performed to obtain the flight performance state of each discrete point, and the flight performance state of the complete aircraft segment is accumulated through the three-degree of freedom equation.
It realizes the rapid and accurate calculation of aircraft flight performance parameters and status, which facilitates the expansion of operations under different loads, configurations and loading conditions, provides a new fuel consumption calculation model, and can quickly calculate aircraft flight status and parameters, ensuring the safe speed and distance of ship-based take-off and landing.
Smart Images
Figure CN119884566A_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of aviation vehicle performance calculation, and in particular, relates to a flight performance calculation method and device. Background Art
[0002] Traditionally, aircraft flight performance data is calculated by using interpolation method to look up tables of various aircraft performance parameters based on prior data. However, this calculation method has low efficiency, large errors, and cannot intuitively observe the aircraft's flight results. Summary of the invention
[0003] The purpose of the present application is to provide a flight performance calculation method and device to solve or alleviate at least one problem in the background technology.
[0004] The technical solution of the present application is: a flight performance calculation method, comprising:
[0005] The flight performance parameters of the aircraft are calculated by using the flight dynamics equations based on the aerodynamic and engine data of the aircraft in cruise, climb and descent states under different load and configuration conditions.
[0006] Determine the aircraft's initial state parameters and flight environment parameters;
[0007] Obtain aircraft flight segment information, select the corresponding aircraft configuration and flight performance parameters under load conditions according to the flight segment type, and discretize the flight state;
[0008] Calculating the flight performance state in a single-step flight state according to the current flight performance parameters, the aircraft initial state parameters and the flight environment parameters, and performing iterative calculations to obtain the flight performance state of each discrete point, wherein the flight performance state in the single-step flight state includes the flight performance parameters during a constant speed climb or descent and the aircraft performance state during a constant speed level flight;
[0009] The flight performance status of the complete aircraft segment is obtained by accumulating the flight performance status of discrete points through the three-degree-of-freedom equation.
[0010] Furthermore, the flight performance parameters of the aircraft include aircraft weight, altitude, Mach number, overload, and fuel consumption rate;
[0011] The initial state parameters include empty weight, aviation fuel weight, and aircraft load weight;
[0012] The flight environment parameters include ambient temperature, ambient wind speed, and ambient wind direction.
[0013] Furthermore, the flight performance parameters calculation method for constant speed climb or descent is:
[0014]
[0015] Where N y is the longitudinal overload, γ is the roll angle, θ is the pitch angle, SFC is the first test data of the aircraft fuel consumption per hour, Interp is the interpolation function, ceil is the upward rounding function, H is the flight altitude, Ma is the Mach number, Amode is the aircraft load state, floor is the downward rounding function, v is the aircraft flight speed, T is the time constant, e is the natural constant, and t is the flight time.
[0016] Furthermore, the calculation method of the aircraft performance state during constant speed level flight is:
[0017]
[0018] Where N x is the normal overload, a is the coefficient, g is the gravitational acceleration at the current position, and k is the rate of change of unit height velocity at the current height.
[0019] Furthermore, the method of obtaining the flight performance state of the complete aircraft segment by accumulating the flight performance state of discrete points through the three-degree-of-freedom equation is:
[0020]
[0021] Where Ψ is the roll angle.
[0022] In addition, the present application also provides an aircraft performance calculation device, which adopts any of the above aircraft performance calculation methods, including:
[0023] A preprocessing module is used to calculate the flight performance parameters of the aircraft through flight dynamics equations based on the aerodynamic data and engine data of the aircraft in cruise, climb and descent states under different load and configuration conditions of the aircraft;
[0024] A parameter acquisition module is used to determine the initial state parameters of the aircraft and the flight environment parameters;
[0025] The flight segment acquisition module is used to obtain the aircraft segment information, select the corresponding aircraft configuration and flight performance parameters under load conditions according to the segment type, and discretize the flight state
[0026] A discrete calculation module is used to calculate the flight performance state in a single-step flight state according to the current flight performance parameters, the aircraft initial state parameters and the flight environment parameters, and perform iterative calculations to obtain the flight performance state of each discrete point, wherein the flight performance state in the single-step flight state includes the flight performance parameters during constant speed climbing or descending and the aircraft performance state during constant speed level flight;
[0027] The cumulative calculation module is used to accumulate the flight performance status of discrete points through the three-degree-of-freedom equation to obtain the flight performance status of the complete aircraft flight segment.
[0028] The present application can quickly and accurately calculate the aircraft flight performance parameters and aircraft status of the target flight segment, and can conveniently expand the calculation method under different aircraft loads, configurations and mounting conditions, thereby obtaining a new fuel consumption calculation model for the aircraft. The aircraft flight status and flight parameters can be quickly calculated according to different environmental conditions, and the safe speed and distance calculation for aircraft carrier-based takeoff and landing can be realized. BRIEF DESCRIPTION OF THE DRAWINGS
[0029] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.
[0030] Figure 1 This is a schematic diagram of the flight parameter calculation method of this application.
[0031] Figure 2 This is a composition diagram of the flight parameter calculation device of the present application. DETAILED DESCRIPTION
[0032] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.
[0033] This application proposes a flight parameter calculation method, which uses flight kinematics equations for calculation and software programming to achieve rapid and accurate calculation of flight performance parameters based on flight segments and aircraft take-off and landing status, allowing users to easily realize flight performance calculation evaluation.
[0034] like Figure 1 As shown, the flight performance calculation method provided by the present application includes the following steps:
[0035] Step S10, calculating flight performance parameters by flight dynamics equations based on aerodynamic and engine data of the aircraft in cruising, climbing and descending states under different load and configuration conditions of the aircraft, the flight performance parameters including parameters such as aircraft weight, altitude, Mach number, overload, fuel consumption rate, etc.;
[0036] Step S20, determining the initial state parameters of the aircraft and the flight environment parameters, wherein the state parameters include the empty weight, aviation fuel weight, aircraft load weight, etc., and the flight environment parameters include the ambient temperature, ambient wind speed, ambient wind direction, etc.;
[0037] Step S30, obtaining the flight segment information of the aircraft, selecting the corresponding aircraft configuration and flight performance parameters under load conditions according to the flight segment type, and discretizing the flight state. The flight segment information includes the flight segment type, the flight segment starting point (longitude, latitude, altitude, starting speed type and starting speed), the flight segment ending point (longitude, latitude, altitude, ending speed type and ending speed), etc.;
[0038] Step S40: Calculate the flight performance state in the single-step flight state according to the current flight performance parameters, the flight initial state parameters and the flight environment parameters, including the flight performance parameters during constant speed climb / descent and the aircraft performance state during constant speed level flight. Perform iterative calculation according to the flight parameter state calculation results in the single-step flight state to obtain the aircraft flight performance state of each discrete point:
[0039] Among them, the calculation method of the aircraft performance status during constant speed level flight is:
[0040]
[0041] Where N y is the longitudinal overload, γ is the roll angle, θ is the pitch angle, SFC is the first test data of the aircraft fuel consumption per hour, Interp is the interpolation function, ceil is the upward rounding function, H is the flight altitude, Ma is the Mach number, Amode is the aircraft load state, floor is the downward rounding function, v is the aircraft flight speed, T is the time constant, e is the natural constant, and t is the flight time;
[0042] The calculation method for the aircraft performance status during constant speed climb / descent is:
[0043]
[0044] Where N x is the normal overload, a is the coefficient, g is the gravitational acceleration at the current position, and k is the rate of change of unit height velocity at the current height.
[0045] Step S50: Accumulate the flight performance state through the three-degree-of-freedom aircraft equation until the complete flight segment is calculated to obtain the flight performance state of the complete aircraft segment, the method is:
[0046]
[0047] Where Ψ is the roll angle.
[0048] The present application can quickly and accurately calculate the aircraft flight performance parameters and aircraft status of the target flight segment, and can conveniently expand the calculation method under different aircraft loads, configurations and mounting conditions, thereby obtaining a new fuel consumption calculation model for the aircraft. The aircraft flight status and flight parameters can be quickly calculated according to different environmental conditions, and the safe speed and distance calculation for aircraft carrier-based takeoff and landing can be realized.
[0049] like Figure 2 As shown, on this basis, the present application also provides a flight performance calculation device, the device 100 includes:
[0050] The preprocessing module 110 is used to calculate the flight performance parameters of the aircraft through flight dynamics equations according to the aerodynamic data and engine data of the aircraft in the cruising, climbing and descending states under the aircraft's prior different load and configuration conditions;
[0051] The parameter acquisition module 120 is used to determine the initial state parameters of the aircraft and the flight environment parameters;
[0052] The flight segment acquisition module 130 is used to obtain the aircraft segment information, select the corresponding aircraft configuration and flight performance parameters under load conditions according to the segment type, and discretize the flight state.
[0053] The discrete calculation module 140 is used to calculate the flight performance state in the single-step flight state according to the current flight performance parameters, the initial state parameters of the aircraft and the flight environment parameters, and perform iterative calculation to obtain the flight performance state of each discrete point, wherein the flight performance state in the single-step flight state includes the flight performance parameters during constant speed climbing or descending and the aircraft performance state during constant speed level flight;
[0054] The cumulative calculation module 150 is used to accumulate the flight performance status of discrete points through the three-degree-of-freedom equation to obtain the flight performance status of the complete aircraft flight segment.
[0055] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.
Claims
1. A flight performance calculation method, characterized in that: include: The flight performance parameters of the aircraft are calculated by using the flight dynamics equations based on the aerodynamic and engine data of the aircraft in cruise, climb and descent states under different load and configuration conditions. Determine the aircraft's initial state parameters and flight environment parameters; Obtain aircraft flight segment information, select the corresponding aircraft configuration and flight performance parameters under load conditions according to the flight segment type, and discretize the flight state; Calculating the flight performance state in a single-step flight state according to the current flight performance parameters, the aircraft initial state parameters and the flight environment parameters, and performing iterative calculations to obtain the flight performance state of each discrete point, wherein the flight performance state in the single-step flight state includes the flight performance parameters during a constant speed climb or descent and the aircraft performance state during a constant speed level flight; The flight performance status of the complete aircraft segment is obtained by accumulating the flight performance status of discrete points through the three-degree-of-freedom equation.
2. The flight performance calculation method according to claim 1, characterized in that: The flight performance parameters of the aircraft include aircraft weight, altitude, Mach number, overload, and fuel consumption rate; The initial state parameters include empty weight, aviation fuel weight, and aircraft load weight; The flight environment parameters include ambient temperature, ambient wind speed, and ambient wind direction.
3. The flight performance calculation method according to claim 2, characterized in that: The calculation method of flight performance parameters during constant speed climb or descent is: Where N y is the longitudinal overload, γ is the roll angle, θ is the pitch angle, SFC is the first test data of the aircraft fuel consumption per hour, Interp is the interpolation function, ceil is the upward rounding function, H is the flight altitude, Ma is the Mach number, Amode is the aircraft load state, floor is the downward rounding function, v is the aircraft flight speed, T is the time constant, e is the natural constant, and t is the flight time.
4. The flight performance calculation method according to claim 3, characterized in that: The calculation method for the aircraft performance status during constant speed level flight is: Where N x is the normal overload, a is the coefficient, g is the gravitational acceleration at the current position, and k is the rate of change of unit height velocity at the current height.
5. The flight performance calculation method according to claim 4, characterized in that: The method of accumulating the flight performance status of discrete points through the three-degree-of-freedom equation to obtain the flight performance status of the complete aircraft segment is: Where Ψ is the roll angle.
6. An aircraft performance calculation device, using the aircraft performance calculation method according to any one of claims 1 to 5, characterized in that: include: A preprocessing module is used to calculate the flight performance parameters of the aircraft through flight dynamics equations based on the aerodynamic data and engine data of the aircraft in cruise, climb and descent states under different load and configuration conditions of the aircraft; A parameter acquisition module is used to determine the initial state parameters of the aircraft and the flight environment parameters; The flight segment acquisition module is used to obtain the aircraft flight segment information, select the corresponding aircraft configuration and flight performance parameters under load conditions according to the flight segment type, and discretize the flight state. The discrete calculation module is used to calculate the flight performance state under the single-step flight state according to the current flight performance parameters, the aircraft initial state parameters and the flight environment parameters, and perform iterative calculation to obtain the flight performance state of each discrete point, wherein the flight performance state under the single-step flight state includes the flight performance parameters during constant speed climbing or descending and the aircraft performance state during constant speed level flight; The cumulative calculation module is used to accumulate the flight performance status of discrete points through the three-degree-of-freedom equation to obtain the flight performance status of the complete aircraft flight segment.