A prediction method and system for ensuring safe takeoff of aircraft

Abstract

The present invention discloses a prediction method and system for ensuring safe takeoff of an aircraft, and relates to the field of aircraft. The aircraft takeoff performance prediction method comprises the following steps: collecting basic aircraft parameters and determining environmental condition parameters when the aircraft takes off; calculating the thrust utilization efficiency when the aircraft takes off according to the maximum thrust of the aircraft engine; calculating the minimum speed and lift-to-drag ratio required when the aircraft takes off according to the basic aircraft parameters and environmental condition parameters; calculating the takeoff acceleration according to the basic aircraft parameters, and obtaining the acceleration performance index by normalizing the acceleration; calculating the takeoff distance required for the aircraft according to the takeoff acceleration; comprehensively evaluating and predicting the conditions when the aircraft takes off according to the above aspects, judging whether the aircraft can take off safely under the current conditions, and if not, giving corresponding adjustment measures. The present invention comprehensively predicts the performance of the aircraft when taking off from multiple aspects, thereby improving the safety of the aircraft when taking off.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a prediction method and system for ensuring safe take-off of an aircraft. Background Art

[0002] Takeoff is one of the most dangerous stages in the flight process, and takeoff performance is an important part of flight safety. Inaccurate takeoff performance prediction may lead to takeoff failure and cause serious safety accidents. During the takeoff phase, the aircraft needs to reach a sufficient speed and altitude within the limited runway length and maintain the necessary climb rate to avoid obstacles and ensure a safe takeoff. At the same time, it is also necessary to consider the impact of the takeoff environment on takeoff. Different environmental conditions will change the aerodynamic performance, engine performance and flight control system response of the aircraft, thereby affecting the safety and efficiency of takeoff. In view of this, the present invention proposes a prediction method to ensure the safe takeoff of the aircraft, which predicts the performance of the aircraft during takeoff from multiple aspects. Summary of the invention

[0003] The present invention provides a prediction method for ensuring safe take-off of an aircraft, comprising:

[0004] S10, collecting basic parameters of the aircraft and determining environmental condition parameters when the aircraft takes off;

[0005] S20, calculating the thrust utilization efficiency of the aircraft when taking off according to the maximum thrust of the aircraft engine;

[0006] S30, calculating the minimum speed and lift-to-drag ratio required for the aircraft to take off based on the basic parameters of the aircraft and the environmental condition parameters;

[0007] S40, calculating the take-off acceleration according to the basic parameters of the aircraft, and obtaining the acceleration performance index by normalizing the acceleration;

[0008] S50, calculating the take-off distance required for the aircraft according to the take-off acceleration;

[0009] S60, calculating the take-off and climb performance index of the aircraft according to the maximum ceiling of the aircraft;

[0010] S70, comprehensively evaluate and predict the conditions for the aircraft to take off based on the thrust utilization efficiency, the minimum speed required for takeoff, the lift-to-drag ratio, the acceleration performance index, the required takeoff distance, and the climb performance index, and determine whether the aircraft can take off safely under the current conditions. If not, provide corresponding adjustment measures.

[0011] A prediction method for ensuring safe takeoff of an aircraft as described above, wherein the thrust utilization efficiency of the aircraft during takeoff is the ratio of the thrust required for takeoff to the maximum thrust of the engine, and is used to evaluate the takeoff performance of the aircraft.

[0012] A prediction method for ensuring safe takeoff of an aircraft as described above, wherein the speed of the aircraft during takeoff should be greater than the minimum speed required for takeoff, and the minimum speed required for takeoff is calculated based on the lift of the aircraft during takeoff. The lift is the upward force generated by the wings to overcome the gravity of the aircraft so that it can leave the ground and enter the air.

[0013] As described above, a prediction method for ensuring the safe takeoff of an aircraft, in order to accurately calculate the lift and drag of the aircraft when taking off, needs to calculate the air density when the aircraft takes off based on the actual air pressure, humidity, and temperature, which can more truly reflect the actual conditions of the environment in which the aircraft is located when taking off.

[0014] A prediction method for ensuring safe takeoff of an aircraft as described above, wherein the takeoff performance of the aircraft is predicted by calculating the acceleration of the aircraft during takeoff, the acceleration reflects the acceleration capability of the aircraft during takeoff, and a takeoff acceleration performance index is introduced to standardize the acceleration.

[0015] As described above, a prediction method for ensuring safe takeoff of an aircraft is provided, wherein the takeoff performance of the aircraft is predicted by comparing the runway length required for takeoff of the aircraft with the actual runway length, and evaluating whether the actual runway length meets the takeoff requirements.

[0016] A prediction method for ensuring safe takeoff of an aircraft as described above, wherein the takeoff performance of the aircraft is predicted by calculating the takeoff climb performance index of the aircraft. A high climb performance index means that the aircraft can reach a higher altitude in a short time, thereby crossing obstacles more safely.

[0017] The present invention also provides a prediction system for ensuring safe takeoff of an aircraft, comprising: a parameter collection module, a thrust calculation module, a speed calculation module, a lift-to-drag ratio module, an acceleration calculation module, a takeoff distance module, a climb calculation module, and a comprehensive evaluation module.

[0018] Parameter collection module: used to collect basic aircraft parameters and environmental condition parameters when the aircraft takes off.

[0019] Thrust calculation module: used to calculate the thrust utilization efficiency of the aircraft during takeoff based on the maximum thrust of the aircraft engine.

[0020] Speed ​​calculation module: used to calculate the minimum speed required for the aircraft to take off based on the basic parameters of the aircraft.

[0021] Lift-to-drag ratio module: used to calculate the lift-to-drag ratio of an aircraft during takeoff based on the basic parameters of the aircraft and environmental conditions.

[0022] Acceleration calculation module: used to calculate takeoff acceleration based on basic aircraft parameters and standardize acceleration to obtain acceleration performance index.

[0023] Takeoff distance module: used to calculate the takeoff distance required by the aircraft based on the takeoff acceleration.

[0024] Climb calculation module: used to calculate the aircraft takeoff climb performance index based on the aircraft's maximum ceiling.

[0025] Comprehensive evaluation and prediction module: It is used to comprehensively evaluate and predict the conditions for aircraft takeoff based on thrust utilization efficiency, minimum speed required for takeoff, lift-to-drag ratio, acceleration performance index, required takeoff distance, and climb performance index, and to determine whether the aircraft can take off safely under the current conditions. If not, corresponding adjustment measures are given.

[0026] The beneficial effects achieved by the present invention are as follows: The present invention comprehensively predicts the performance of an aircraft during takeoff from multiple aspects, thereby improving the safety of the aircraft during takeoff. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0028] Figure 1 This is a flow chart of a prediction method for ensuring safe takeoff of an aircraft provided in Example 1 of the present application.

[0029] Figure 2 This is a schematic diagram of a prediction system for ensuring safe takeoff of an aircraft provided in Example 2 of the present application. DETAILED DESCRIPTION

[0030] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0031] Embodiment 1

[0032] like Figure 1 As shown, the first embodiment of the present application provides a prediction method for ensuring safe takeoff of an aircraft, including:

[0033] S10: Collect basic parameters of the aircraft and determine environmental condition parameters when the aircraft takes off.

[0034] The basic parameters of the aircraft include the wing area S wing , aircraft gross weight W, empty weight Wempty , Maximum take-off weight W max 、Maximum engine thrust M max , take-off speed V speed 、The maximum ceiling of the aircraft H max , these data can usually be found in the technical manual provided by the manufacturer.

[0035] When an aircraft takes off, the environmental conditions have a significant impact on its takeoff performance. The environmental conditions when the aircraft takes off include temperature T temp , relative humidity H humidity , air pressure P pressure .

[0036] S20. Calculate the thrust utilization efficiency of the aircraft when taking off based on the maximum thrust of the aircraft engine.

[0037] The thrust utilization efficiency of an aircraft during takeoff is the ratio of the thrust required for takeoff to the maximum thrust of the engine, and is used to evaluate the takeoff performance of the aircraft. Specifically, the formula is M required It represents the thrust required for takeoff, which is the sum of the resistance and gravity that the aircraft needs to overcome when taking off. required =D total +Wsinγ+κ,D total M represents the total upward resistance that the aircraft needs to overcome when taking off, W represents the total weight of the aircraft, γ represents the take-off climb angle of the aircraft, and κ represents the wind force. When taking off with the wind, the aircraft needs a larger thrust ratio to overcome the problem of insufficient lift. max It is the maximum thrust of the engine under dry conditions. ΔT° / ° indicates the percentage of engine thrust reduction caused by water entering the engine's air intake system in rainy and snowy weather. It indicates the percentage of thrust reduction due to the increase of engine service life, and φ indicates the percentage of engine thrust reduction due to temperature. This ratio reflects the relative size of the engine thrust demand when the aircraft takes off. The smaller the ratio, the smaller the thrust required for takeoff and the higher the efficiency of engine thrust utilization; the larger the ratio, the larger the thrust required for takeoff and the lower the efficiency of engine thrust utilization. This ratio indirectly reflects the takeoff performance of the aircraft. For the same type of aircraft, the smaller the ratio of the thrust required for takeoff to the maximum thrust of the engine, the better the takeoff performance and the easier it is for the aircraft to take off.

[0038] S30. Calculate the minimum speed and lift-to-drag ratio required for the aircraft to take off based on the basic parameters of the aircraft and the environmental condition parameters.

[0039] S31. Calculate the minimum take-off speed of the aircraft according to the basic parameters of the aircraft.

[0040] The speed of the aircraft during takeoff should be greater than the minimum speed required for takeoff. The minimum speed required for takeoff is calculated based on the lift of the aircraft during takeoff. Lift is the upward force generated by the wings, which is used to overcome the gravity of the aircraft and enable it to leave the ground and enter the air. Specifically, the lift calculation formula is The lift should be at least greater than or equal to the total weight W of the aircraft, so Solve the inequality to get the minimum takeoff speed required for the aircraft to take off, Where ρ represents the air density when the aircraft takes off, S wing represents the wing area, C L It represents the takeoff lift coefficient, which is the ratio of lift per unit area to dynamic pressure. The lift coefficient depends on the shape of the wing, the angle of attack and the flight state. The specific value can be obtained from the aircraft's technical manual.

[0041] S32. Calculate the air density of the aircraft when it takes off according to the environmental condition parameters.

[0042] In order to accurately calculate the lift and drag of an aircraft when it takes off, it is necessary to calculate the air density of the aircraft when it takes off based on the actual air pressure, humidity, and temperature, which can more truly reflect the actual conditions of the environment in which the aircraft is located when it takes off. Specifically, the formula is Where ρ represents the air density, P v represents the partial pressure of water vapor at takeoff, P v =H humidity ×P sat (T), H humidity Relative humidity, P sat (T) represents the saturated vapor pressure, R v The gas constant for water vapor, P d Indicates the dry air partial pressure P at takeoff d =P pressure -P v , P pressure Indicates the current takeoff environment air pressure, R d is the dry air gas constant, T temp Indicates the current takeoff environment temperature.

[0043] S33. Calculate the lift-to-drag ratio of the aircraft at takeoff based on the basic parameters of the aircraft and the air density of the aircraft at takeoff.

[0044] Lift-to-drag ratio is used to evaluate the aerodynamic efficiency of an aircraft. The higher the lift-to-drag ratio, the higher the fuel efficiency of the aircraft. Specifically, the calculation formula is: Where F is the lift-to-drag ratio, represents the lift of the aircraft, ρ represents the air density when the aircraft takes off, V speed Indicates takeoff speed, S wingrepresents the wing area, C L represents the takeoff lift coefficient, P λ Indicates the effect of pressure caused by altitude on the lift of the aircraft. It indicates the resistance encountered by the aircraft during takeoff. It represents the drag coefficient of an aircraft in a zero-lift state, which can usually be obtained through wind tunnel tests or empirical data. It represents the induced drag coefficient, where induced drag is the drag caused by lift, π represents pi, AR is the aspect ratio of the wing, e is the induced drag efficiency factor, and θ is the influence of the fuselage area of ​​different types of aircraft on the drag of the aircraft.

[0045] S40. Calculate the takeoff acceleration based on the basic parameters of the aircraft, and standardize the acceleration to obtain an acceleration performance index.

[0046] Acceleration reflects the acceleration capability of the aircraft during takeoff. To calculate takeoff acceleration, the formula is: Among them, M max represents the maximum thrust of the engine, (μ a +μ b )W represents the friction between the aircraft and the ground during takeoff, μ a is the friction coefficient between the aircraft tire and the dry ground, μ b represents the friction coefficient caused by the aircraft's brake system not being fully released or partially braking, W represents the total weight of the aircraft, μ c Indicates the reduced ground friction of a wet runway. represents the friction between the aircraft and the air during takeoff, ρ represents the air density, V speed Indicates takeoff speed, S wing represents the wing area, It represents the drag coefficient of the aircraft in the zero lift state, which can usually be obtained through wind tunnel tests or empirical data. L It represents the take-off lift coefficient. The specific value can be obtained from the aircraft's technical manual. represents the induced drag coefficient, induced drag is the drag caused by lift, π represents pi, AR is the aspect ratio of the wing, and e is the induced drag efficiency factor. Wsinα represents the aircraft gravity component, α represents the flight path angle, and m represents the aircraft mass.

[0047] In order to standardize the acceleration, the takeoff acceleration performance index A is introduced pi , the calculation formula is Where a is the takeoff acceleration, g is the acceleration due to gravity, and W max is the maximum take-off weight of the aircraft, W empty is the empty weight of the aircraft.

[0048] S50: Calculate the takeoff distance required for the aircraft according to the takeoff acceleration.

[0049] Takeoff distance is the runway length required for an aircraft to accelerate from rest to takeoff speed. Specifically, the calculation formula is: Among them, d distance Indicates the take-off distance of the aircraft, V speed represents the take-off speed, a represents the take-off acceleration, and k represents the safety margin of the aircraft for take-off.

[0050] S60. Calculate the takeoff and climb performance index of the aircraft according to the maximum ceiling of the aircraft.

[0051] During takeoff, the aircraft needs to climb quickly to avoid obstacles around the airport, such as buildings and trees. A high climb performance index means that the aircraft can reach a higher altitude in a short period of time, thereby crossing obstacles more safely. In emergency situations, such as engine failure, the aircraft needs to have sufficient climb performance to maintain the flight altitude or quickly descend to a safe altitude. A high climb performance index can improve the survivability of the aircraft in these situations.

[0052] Specifically, the climb performance index formula is: H max Indicates the maximum ceiling of the aircraft, R 0 C represents the climbing speed, Δh represents the climbing height, Δs represents the horizontal distance, represents the climb gradient, ψ represents an empirical coefficient used to adjust the influence of the climb gradient on the performance index, which is determined according to the type and purpose of the aircraft. It indicates the effect of different weights of the aircraft at takeoff on the climb performance index. represents the change of fuel remaining with flight time, t c represents the climbing time, z system Indicates the effect of the flight control system's response on climb performance.

[0053] S70, comprehensively evaluate and predict the conditions for the aircraft to take off based on the thrust utilization efficiency, the minimum speed required for takeoff, the lift-to-drag ratio, the acceleration performance index, the required takeoff distance, and the climb performance index, and determine whether the aircraft can take off safely under the current conditions. If not, provide corresponding adjustment measures.

[0054] Comprehensively evaluate and predict parameters such as thrust utilization efficiency, minimum takeoff speed, lift-to-drag ratio, acceleration performance index, runway length requirement, and climb performance index to determine whether the aircraft can take off safely under current conditions. The prediction formula is: β represents the weight of the thrust utilization efficiency of the aircraft takeoff, is the thrust utilization efficiency of the aircraft during takeoff, It should be greater than 1, indicating that the aircraft has enough thrust to overcome gravity and take off. δ represents the weight of the aircraft's takeoff speed, V actual is the actual take-off speed of the aircraft, V min is the minimum speed required for the aircraft to take off, The value of should be greater than 1 to ensure that the aircraft has sufficient takeoff speed. ε represents the weight of the lift-to-drag ratio, F is the lift-to-drag ratio of the aircraft when taking off, to ensure the fuel efficiency of the aircraft. σ represents the weight of the acceleration performance index, A pi is the acceleration performance index of the aircraft during takeoff, reflecting the acceleration capability of the aircraft during takeoff. ω represents the weight of the runway length, d actual is the actual runway length, d distance The length of the runway required for the aircraft to take off. The value should be greater than or equal to 1.3 to ensure that the runway is long enough. Indicates the weight of the climb performance index, I climb is the aircraft's climb performance index, which reflects the aircraft's climb capability. The aircraft's climb performance index should be above the safety threshold to ensure that the aircraft can avoid obstacles and take off safely. If f does not meet the takeoff requirements, corresponding adjustment measures are given until f meets the safe takeoff requirements.

[0055] Embodiment 2

[0056] like Figure 2 As shown, the second embodiment of the present application provides a prediction system for ensuring safe takeoff of an aircraft, including:

[0057] Parameter collection module: used to collect basic aircraft parameters and environmental condition parameters when the aircraft takes off.

[0058] The basic parameters of the aircraft include the wing area S wing , aircraft gross weight W, empty weight W empty , Maximum take-off weight W max 、Maximum engine thrust M max , take-off speed V speed 、The maximum ceiling of the aircraft H max , these data can usually be found in the technical manual provided by the manufacturer.

[0059] When an aircraft takes off, the environmental conditions have a significant impact on its takeoff performance. The environmental conditions when the aircraft takes off include temperature T temp , relative humidity H humidity , air pressure P pressure .

[0060] Thrust calculation module: used to calculate the thrust utilization efficiency of the aircraft during takeoff based on the maximum thrust of the aircraft engine.

[0061] The thrust utilization efficiency of an aircraft during takeoff is the ratio of the thrust required for takeoff to the maximum thrust of the engine, and is used to evaluate the takeoff performance of the aircraft. Specifically, the formula is M required It represents the thrust required for takeoff, which is the sum of the resistance and gravity that the aircraft needs to overcome when taking off. required =D total +Wsinγ+κ,D total M represents the total upward resistance that the aircraft needs to overcome when taking off, W represents the total weight of the aircraft, γ represents the take-off climb angle of the aircraft, and κ represents the wind force. When taking off with the wind, the aircraft needs a larger thrust ratio to overcome the problem of insufficient lift. max It is the maximum thrust of the engine under dry conditions. ΔT° / ° indicates the percentage of engine thrust reduction caused by water entering the engine's air intake system in rainy and snowy weather. It indicates the percentage of thrust reduction due to the increase of engine service life, and φ indicates the percentage of engine thrust reduction due to temperature. This ratio reflects the relative size of the engine thrust demand when the aircraft takes off. The smaller the ratio, the smaller the thrust required for takeoff and the higher the efficiency of engine thrust utilization; the larger the ratio, the larger the thrust required for takeoff and the lower the efficiency of engine thrust utilization. This ratio indirectly reflects the takeoff performance of the aircraft. For the same type of aircraft, the smaller the ratio of the thrust required for takeoff to the maximum thrust of the engine, the better the takeoff performance and the easier it is for the aircraft to take off.

[0062] Speed ​​calculation module: used to calculate the minimum speed required for the aircraft to take off based on the basic parameters of the aircraft.

[0063] The speed of the aircraft during takeoff should be greater than the minimum speed required for takeoff. The minimum speed required for takeoff is calculated based on the lift of the aircraft during takeoff. Lift is the upward force generated by the wings, which is used to overcome the gravity of the aircraft and enable it to leave the ground and enter the air. Specifically, the lift calculation formula is The lift should be at least greater than or equal to the total weight W of the aircraft, so Solve the inequality to get the minimum takeoff speed required for the aircraft to take off, Where ρ represents the air density when the aircraft takes off, S wing represents the wing area, C L It represents the takeoff lift coefficient, which is the ratio of lift per unit area to dynamic pressure. The lift coefficient depends on the shape of the wing, the angle of attack and the flight state. The specific value can be obtained from the aircraft's technical manual.

[0064] Lift-to-drag ratio module: includes air density calculation submodule and lift-to-drag ratio calculation submodule.

[0065] Air density calculation submodule: used to calculate the air density of the aircraft when taking off based on environmental condition parameters.

[0066] In order to accurately calculate the lift and drag of an aircraft when it takes off, it is necessary to calculate the air density of the aircraft when it takes off based on the actual air pressure, humidity, and temperature, which can more truly reflect the actual conditions of the environment in which the aircraft is located when it takes off. Specifically, the formula is Where ρ represents the air density, P v represents the partial pressure of water vapor at takeoff, P v =H humidity ×P sat (T), H humidity Relative humidity, P sat (T) represents the saturated vapor pressure, R v The gas constant for water vapor, P d Indicates the dry air partial pressure P at takeoff d =P pressure -P v , P pressure Indicates the current takeoff environment air pressure, R d is the dry air gas constant, T temp Indicates the current takeoff environment temperature.

[0067] Lift-to-drag ratio calculation submodule: used to calculate the lift-to-drag ratio of the aircraft at takeoff based on the basic parameters of the aircraft and the air density of the aircraft at takeoff.

[0068] Lift-to-drag ratio is used to evaluate the aerodynamic efficiency of an aircraft. The higher the lift-to-drag ratio, the higher the fuel efficiency of the aircraft. Specifically, the calculation formula is: Where F is the lift-to-drag ratio, represents the lift of the aircraft, ρ represents the air density when the aircraft takes off, V speed Indicates takeoff speed, S wing represents the wing area, C L represents the takeoff lift coefficient, P λ Indicates the effect of pressure caused by altitude on the lift of the aircraft. It indicates the resistance encountered by the aircraft during takeoff. It represents the drag coefficient of an aircraft in a zero-lift state, which can usually be obtained through wind tunnel tests or empirical data. It represents the induced drag coefficient, where induced drag is the drag caused by lift, π represents pi, AR is the aspect ratio of the wing, e is the induced drag efficiency factor, and θ is the influence of the fuselage area of ​​different types of aircraft on the drag of the aircraft.

[0069] Acceleration calculation module: includes acceleration submodule and standardization submodule.

[0070] Acceleration submodule: used to calculate takeoff acceleration based on the basic parameters of the aircraft.

[0071] Acceleration reflects the acceleration capability of the aircraft during takeoff. To calculate takeoff acceleration, the formula is: Among them, M max represents the maximum thrust of the engine, (μ a +μ b )W represents the friction between the aircraft and the ground during takeoff, μ a is the friction coefficient between the aircraft tire and the dry ground, μ b represents the friction coefficient caused by the aircraft's brake system not being fully released or partially braking, W represents the total weight of the aircraft, μ c Indicates the reduced ground friction of a wet runway. represents the friction between the aircraft and the air during takeoff, ρ represents the air density, V speed Indicates takeoff speed, S wing represents the wing area, It represents the drag coefficient of the aircraft in the zero lift state, which can usually be obtained through wind tunnel tests or empirical data. L It represents the take-off lift coefficient. The specific value can be obtained from the aircraft's technical manual. represents the induced drag coefficient, induced drag is the drag caused by lift, π represents pi, AR is the aspect ratio of the wing, and e is the induced drag efficiency factor. Wsinα represents the aircraft gravity component, α represents the flight path angle, and m represents the aircraft mass.

[0072] Standardization submodule: used to standardize acceleration and obtain acceleration performance index.

[0073] In order to standardize the acceleration, the takeoff acceleration performance index A is introduced pi , the calculation formula is Where a is the takeoff acceleration, g is the acceleration due to gravity, and W max is the maximum take-off weight of the aircraft, W empty is the empty weight of the aircraft.

[0074] Takeoff distance module: used to calculate the takeoff distance required by the aircraft based on the takeoff acceleration.

[0075] Takeoff distance is the runway length required for an aircraft to accelerate from rest to takeoff speed. Specifically, the calculation formula is: Among them, d distance Indicates the take-off distance of the aircraft, V speed represents the take-off speed, a represents the take-off acceleration, and k represents the safety margin of the aircraft for take-off.

[0076] Climb calculation module: used to calculate the aircraft takeoff climb performance index based on the aircraft's maximum ceiling.

[0077] During takeoff, the aircraft needs to climb quickly to avoid obstacles around the airport, such as buildings and trees. A high climb performance index means that the aircraft can reach a higher altitude in a short period of time, thereby crossing obstacles more safely. In emergency situations, such as engine failure, the aircraft needs to have sufficient climb performance to maintain the flight altitude or quickly descend to a safe altitude. A high climb performance index can improve the survivability of the aircraft in these situations.

[0078] Specifically, the climb performance index formula is: H max Indicates the maximum ceiling of the aircraft, R 0 C represents the climbing speed, Δh represents the climbing height, Δs represents the horizontal distance, represents the climb gradient, ψ represents an empirical coefficient used to adjust the influence of the climb gradient on the performance index, which is determined according to the type and purpose of the aircraft. It indicates the effect of different weights of the aircraft at takeoff on the climb performance index. represents the change of fuel remaining with flight time, t c represents the climbing time, z system Indicates the effect of the flight control system's response on climb performance.

[0079] Comprehensive evaluation and prediction module: It is used to comprehensively evaluate and predict the conditions for aircraft takeoff based on thrust utilization efficiency, minimum speed required for takeoff, lift-to-drag ratio, acceleration performance index, required takeoff distance, and climb performance index, and to determine whether the aircraft can take off safely under the current conditions. If not, corresponding adjustment measures are given.

[0080] Comprehensively evaluate and predict parameters such as thrust utilization efficiency, minimum takeoff speed, lift-to-drag ratio, acceleration performance index, runway length requirement, and climb performance index to determine whether the aircraft can take off safely under current conditions. The prediction formula is: β represents the weight of the thrust utilization efficiency of the aircraft takeoff, is the thrust utilization efficiency of the aircraft during takeoff, It should be greater than 1, indicating that the aircraft has enough thrust to overcome gravity and take off. δ represents the weight of the aircraft's takeoff speed, V actual is the actual take-off speed of the aircraft, V min is the minimum speed required for the aircraft to take off, The value of should be greater than 1 to ensure that the aircraft has sufficient takeoff speed. ε represents the weight of the lift-to-drag ratio, F is the lift-to-drag ratio of the aircraft when taking off, to ensure the fuel efficiency of the aircraft. σ represents the weight of the acceleration performance index, A pi is the acceleration performance index of the aircraft during takeoff, reflecting the acceleration capability of the aircraft during takeoff. ω represents the weight of the runway length, d actual is the actual runway length, d distance The length of the runway required for the aircraft to take off. The value should be greater than or equal to 1.3 to ensure that the runway is long enough. Indicates the weight of the climb performance index, I climb is the aircraft's climb performance index, which reflects the aircraft's climb capability. The aircraft's climb performance index should be above the safety threshold to ensure that the aircraft can avoid obstacles and take off safely. If f does not meet the takeoff requirements, corresponding adjustment measures are given until f meets the safe takeoff requirements.

[0081] Corresponding to the above embodiment, an embodiment of the present invention provides a computer storage medium, including: at least one memory and at least one processor;

[0082] The memory is used to store one or more program instructions;

[0083] The processor is used to run one or more program instructions to execute a prediction method for ensuring safe takeoff of an aircraft.

[0084] Corresponding to the above-mentioned embodiment, an embodiment of the present invention provides a computer-readable storage medium, wherein the computer storage medium contains one or more program instructions, and the one or more program instructions are used by a processor to execute a prediction method for ensuring safe take-off of an aircraft.

[0085] The embodiment disclosed in the present invention provides a computer-readable storage medium, in which computer program instructions are stored. When the computer program instructions are executed on a computer, the computer executes the above-mentioned prediction method for ensuring the safe take-off of an aircraft.

[0086] In the embodiment of the present invention, the processor may be an integrated circuit chip having the ability to process signals. The processor may be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components.

[0087] The methods, steps and logic block diagrams disclosed in the embodiments of the present invention can be implemented or executed. The general processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in the embodiments of the present invention can be directly embodied as a hardware decoding processor for execution, or can be executed by a combination of hardware and software modules in the decoding processor. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. The processor reads the information in the storage medium and completes the steps of the above method in combination with its hardware.

[0088] The storage medium may be a memory, which may be, for example, a volatile memory or a nonvolatile memory, or may include both volatile and nonvolatile memory.

[0089] Among them, the non-volatile memory can be a read-only memory (ROM), a programmable ROM (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), or a flash memory.

[0090] The volatile memory may be a random access memory (RAM) which is used as an external cache. By way of example and not limitation, many forms of RAM are available, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate synchronous DRAM (DDRSDRAM), enhanced synchronous DRAM (ESDRAM), synchronous link DRAM (SLDRAM), and direct RAM bus DRAM (DRRAM).

[0091] The storage media described in the embodiments of the present invention are intended to include, but are not limited to, these and any other suitable types of memory.

[0092] Those skilled in the art will appreciate that in one or more of the above examples, the functions described in the present invention can be implemented using a combination of hardware and software. When software is used, the corresponding functions can be stored in a computer-readable medium or transmitted as one or more instructions or codes on a computer-readable medium. Computer-readable media include computer storage media and communication media, wherein communication media include any media that facilitates the transmission of computer programs from one place to another. Storage media can be any available media that can be accessed by general or special-purpose computers.

[0093] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made on the basis of the technical solution of the present invention should be included in the scope of protection of the present invention.

Claims

1. A prediction method for ensuring safe takeoff of an aircraft, characterized in that: include: S10, collecting basic parameters of the aircraft and determining environmental condition parameters when the aircraft takes off; S20, calculating the thrust utilization efficiency of the aircraft when taking off according to the maximum thrust of the aircraft engine; S30, calculating the minimum speed and lift-to-drag ratio required for the aircraft to take off based on the basic parameters of the aircraft and the environmental condition parameters; S40, calculating the take-off acceleration according to the basic parameters of the aircraft, and obtaining the acceleration performance index by normalizing the acceleration; S50, calculating the take-off distance required for the aircraft according to the take-off acceleration; S60, calculating the take-off and climb performance index of the aircraft according to the maximum ceiling of the aircraft; S70, comprehensively evaluate and predict the conditions for the aircraft to take off based on the thrust utilization efficiency, the minimum speed required for takeoff, the lift-to-drag ratio, the acceleration performance index, the required takeoff distance, and the climb performance index, and determine whether the aircraft can take off safely under the current conditions. If not, provide corresponding adjustment measures.

2. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: The thrust utilization efficiency of an aircraft during takeoff is the ratio of the thrust required for takeoff to the maximum thrust of the engine, and is used to evaluate the takeoff performance of the aircraft.

3. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: The aircraft's takeoff speed should be greater than the minimum speed required for takeoff. The minimum speed required for takeoff is calculated based on the aircraft's lift at takeoff. Lift is the upward force generated by the wings to overcome the aircraft's gravity, allowing it to leave the ground and enter the air.

4. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: In order to accurately calculate the lift and drag of an aircraft when it takes off, it is necessary to calculate the air density when the aircraft takes off based on the actual air pressure, humidity, and temperature, which can more truly reflect the actual conditions of the environment in which the aircraft is located when it takes off.

5. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: To predict the takeoff performance of an aircraft, the acceleration of the aircraft during takeoff should be calculated. The acceleration reflects the acceleration capability of the aircraft during takeoff, and the takeoff acceleration performance index is introduced to standardize the acceleration.

6. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: To predict the takeoff performance of an aircraft, the runway length required for takeoff should be compared with the actual runway length to evaluate whether the actual runway length meets the takeoff requirements.

7. A prediction method for ensuring safe takeoff of an aircraft as claimed in claim 1, characterized in that: To predict the takeoff performance of an aircraft, the aircraft's takeoff climb performance index should be calculated. A high climb performance index means that the aircraft can reach a higher altitude in a shorter time and thus pass obstacles more safely.

8. A prediction system for ensuring safe takeoff of an aircraft, characterized in that: include: Parameter collection module: used to collect basic parameters of the aircraft and environmental conditions when the aircraft takes off; Thrust calculation module: used to calculate the thrust utilization efficiency of the aircraft during takeoff based on the maximum thrust of the aircraft engine; Speed ​​calculation module: used to calculate the minimum speed required for the aircraft to take off based on the basic parameters of the aircraft; Lift-to-drag ratio module: used to calculate the lift-to-drag ratio of the aircraft during takeoff based on the basic parameters of the aircraft and environmental conditions; Acceleration calculation module: used to calculate takeoff acceleration according to basic aircraft parameters, and standardize acceleration to obtain acceleration performance index; Takeoff distance module: used to calculate the takeoff distance required by the aircraft based on the takeoff acceleration; Climb calculation module: used to calculate the aircraft takeoff climb performance index according to the aircraft's maximum ceiling; Comprehensive evaluation and prediction module: It is used to comprehensively evaluate and predict the conditions for aircraft takeoff based on thrust utilization efficiency, minimum speed required for takeoff, lift-to-drag ratio, acceleration performance index, required takeoff distance, and climb performance index, and to determine whether the aircraft can take off safely under the current conditions. If not, corresponding adjustment measures are given.

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