Method, device, computer equipment and storage medium for determining risk probability value

Abstract

The present application relates to a method, device, computer equipment and storage medium for determining a risk probability value. The method comprises: determining at least one target component affected by each type of debris from the entire structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft; determining the collision risk angle interval of each type of debris colliding with each target component according to a predefined debris scattering angle range and the size parameters of the rotor corresponding to each type of debris; obtaining the risk probability value of each type of debris causing a risk to the aircraft according to the collision risk angle of each type of debris colliding with each target component. The use of this method can improve the efficiency of evaluating the risk probability value of the risk caused by aircraft debris to the aircraft.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft risk assessment, and in particular to a method, device, computer equipment and storage medium for determining a risk probability value. Background Art

[0002] When an aircraft tire explodes or an engine rotor is hit, aircraft debris of different sizes will be generated. The aircraft debris will be ejected from any angle and may damage the aircraft's wings, horizontal tail, landing gear and other key parts. Therefore, it is of great significance to analyze and evaluate the damage caused by aircraft debris in the aircraft design stage.

[0003] In traditional technology, the risk probability of aircraft debris colliding with aircraft parts during each release process is calculated based on an exhaustive method, thereby obtaining the risk probability of aircraft debris causing risks to the aircraft.

[0004] However, conventional technologies have the problem of low efficiency in assessing the risk probability of aircraft accidents caused by aircraft debris. Summary of the invention

[0005] Based on this, it is necessary to provide a method, device, computer equipment and storage medium for determining a risk probability value that can improve the efficiency of assessing the risk probability of aircraft debris causing risks to aircraft in order to address the above technical problems.

[0006] In a first aspect, the present application provides a method for determining a risk probability value. The method comprises:

[0007] Determining at least one target component affected by each type of debris from the entire structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft;

[0008] Determining a collision risk angle interval of each type of debris colliding with each target component according to a predefined debris scattering angle range and a size parameter of a rotor corresponding to each type of debris;

[0009] According to the collision risk angle interval of each type of debris colliding with each target component, a risk probability value of the risk of the aircraft being caused by each type of debris is obtained.

[0010] In one embodiment, obtaining the risk probability value of the aircraft being caused by each type of debris according to the collision risk angle interval of each type of debris colliding with the target component includes:

[0011] Determining the probability value of each type of debris hitting the target component at the same time according to the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval;

[0012] Determine the probability value of the risk caused by the rotor of each type of debris to the aircraft according to the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft;

[0013] According to the probability value of each type of debris causing the aircraft to occur and the number of the rotors, the risk probability value of each type of debris causing the aircraft to occur is obtained.

[0014] In one embodiment, obtaining the risk probability value of the risk of each type of debris causing the aircraft to occur according to the probability value of each type of debris causing the aircraft to occur and the number of the rotors includes:

[0015] The ratio of the sum of the probability values ​​of each type of debris causing the aircraft to occur to the number of the rotors is determined as the risk probability value of the risk of each type of debris causing the aircraft to occur.

[0016] In one embodiment, the collision risk angle includes a sweep risk angle interval and a scatter risk angle interval, and determining the collision risk angle interval of each type of debris colliding with each target component according to a predefined debris scatter angle range and a size parameter of a rotor corresponding to each type of debris includes:

[0017] According to the debris scattering angle range and the number of preset scattering angle sections, a scattering angle calculation step length is obtained;

[0018] Determine the sweep angle corresponding to each of the scatter angle sections according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris;

[0019] The maximum value of each of the sweeping angles is used as the upper limit of the sweeping risk angle interval, and the minimum value of each of the sweeping angles is used as the lower limit of the sweeping risk angle, to obtain the sweeping risk angle interval;

[0020] The scatter risk angle interval is acquired according to the sweep risk angle interval and the number of preset sweep angle sections.

[0021] In one embodiment, determining the sweep angle corresponding to each of the scatter angle sections according to the scatter angle calculation step and the size parameter of the rotor corresponding to each type of debris comprises:

[0022] Determine the swept rotation surface corresponding to each of the scatter angle sections according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris;

[0023] Determining a first intersection angle corresponding to an intersection area between each of the swept rotational surfaces and each of the target components;

[0024] The sweep angle corresponding to each of the swept rotation surfaces is determined from each of the first intersection angles using a preset extreme value function.

[0025] In one embodiment, the step of obtaining the flyaway risk angle interval according to the sweep risk angle interval and the number of preset sweep angle sections includes:

[0026] Obtaining a sweep angle calculation step length according to the sweep risk angle interval and the number of preset sweep angle sections;

[0027] Determine the scattering plane corresponding to each of the sweep angle sections according to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris;

[0028] Determining a scattering angle corresponding to each scattering plane according to each scattering plane and each target component;

[0029] The scatter risk angle interval is obtained by taking the maximum value of each scatter angle as the upper limit value of the scatter risk angle interval and taking the minimum value of each scatter angle as the lower limit value of the scatter risk angle interval.

[0030] In one embodiment, determining the scattering angle corresponding to each scattering plane according to each scattering plane and each target component includes:

[0031] determining a second intersection angle corresponding to an intersection area between each of the scattering planes and each of the target components;

[0032] The scattering angle corresponding to each scattering plane is determined from each of the second intersection angles using a preset extreme value function.

[0033] In one embodiment, the method further comprises:

[0034] According to the comparison result of each of the risk probability values ​​and the risk assessment criteria corresponding to each of the types of debris, it is determined whether to adjust the entire structure of the aircraft.

[0035] In one embodiment, the determining, based on the impact range corresponding to each type of debris of the aircraft, at least one target component affected by each type of debris from the entire structure of the aircraft includes:

[0036] According to a preset Boolean operation, components intersecting with each of the influence ranges in the overall structure of the aircraft are determined as the target components.

[0037] In a second aspect, the present application also provides a device for determining a risk probability value. The device comprises:

[0038] A first determination module is used to determine at least one target component affected by each type of debris from the entire structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft;

[0039] A second determination module is used to determine the collision risk angle of each type of debris colliding with each target component according to a predefined debris scattering angle range and the thickness and radius of the rotor corresponding to each type of debris;

[0040] The acquisition module is used to acquire the risk probability value of the aircraft caused by each type of debris according to the collision risk angle interval of each type of debris colliding with each target component.

[0041] In a third aspect, the present application further provides a computer device, wherein the computer device comprises a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the steps of the method described in the first aspect are implemented.

[0042] In a fourth aspect, the present application further provides a computer-readable storage medium, wherein a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the steps of the method described in the first aspect are implemented.

[0043] In a fifth aspect, the present application further provides a computer program product, wherein the computer program product comprises a computer program, and when the computer program is executed by a processor, the steps of the method described in the first aspect are implemented.

[0044] The above-mentioned method, device, computer equipment and storage medium for determining the risk probability value can accurately determine at least one target component affected by each type of debris from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft. Since the amount of calculation required to determine the target component based on the impact range corresponding to the debris and the overall structure of the aircraft is small and the calculation process is relatively simple, the target component can be determined quickly, and thus, according to the predefined debris scattering angle range and the size parameters of the rotor corresponding to each type of debris, the collision risk angle interval of each type of debris colliding with each target component can be quickly determined, and then, according to the collision risk angle interval of each type of debris colliding with each target component, the target component can be determined accurately. The risk probability value of each type of debris causing the risk of an aircraft occurring can be obtained. Since the calculation process of determining the collision risk angle interval of each type of debris colliding with each target component according to the debris scattering angle range and the size parameters of the corresponding rotor involves less calculation amount, the probability value of the collision between each type of debris and each target component can be quickly and accurately determined according to the collision risk angle interval, so that the risk probability value of the risk of the aircraft occurring due to the debris can be quickly and accurately determined according to each probability value, thereby avoiding the problem of calculating the probability of the collision between the debris and the target component multiple times in order to accurately determine the risk probability value in the process of determining the risk probability value, thereby improving the efficiency of determining the risk probability value. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 A diagram of an application environment of a method for determining a risk probability value in an embodiment;

[0046] Figure 2 Schematic diagram of a process for determining a risk probability value in one embodiment;

[0047] Figure 3 A schematic diagram of a large fragment of a 1 / 3 roulette wheel in one embodiment;

[0048] Figure 4 is a schematic diagram of fragments in one embodiment;

[0049] Figure 5 A schematic diagram of a small fragment in one embodiment;

[0050] Figure 6 is a schematic diagram of fan fragments in one embodiment;

[0051] Figure 7 is a flow chart of a method for determining a risk probability value in another embodiment;

[0052] Figure 8 is a flow chart of a method for determining a risk probability value in another embodiment;

[0053] Fig. 9 is a schematic diagram of the debris scattering angle in one embodiment;

[0054] Fig.10 is a schematic diagram of a sweep angle in one embodiment;

[0055] Fig.11 A schematic diagram of sweeping a risk angle interval in one embodiment;

[0056] Fig.12 is a schematic diagram of a scatter risk angle interval in one embodiment;

[0057] Fig.13 is a flow chart of a method for determining a risk probability value in another embodiment;

[0058] Fig.14 is a flow chart of a method for determining a risk probability value in another embodiment;

[0059] Fig.15 is a flow chart of a method for determining a risk probability value in another embodiment;

[0060] Fig.16 is a structural block diagram of a device for determining a risk probability value in one embodiment;

[0061] Fig.17 FIG. 4 is a structural block diagram of a device for determining a risk probability value in another embodiment. DETAILED DESCRIPTION

[0062] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0063] The method for determining the risk probability value provided in the embodiment of the present application can be applied to Figure 1 In the application environment shown. Figure 1 A computer device is provided, which may be a server, and its internal structure diagram may be as follows: Figure 1As shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. The processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store data on the risk probability value of the risk of aircraft caused by various types of debris. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for determining a risk probability value is implemented.

[0064] Those skilled in the art will understand that Figure 1 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0065] In one embodiment, Figure 2 As shown, a method for determining the risk probability value is provided, and the method is applied to Figure 1 The computer device in the example is used to illustrate, including the following steps:

[0066] S201 , determining at least one target component affected by each type of debris from the entire structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft.

[0067] Among them, various types of aircraft debris refer to non-contained rotor fragments in the aircraft engine. Different types of debris may correspond to different impact ranges of aircraft debris. For example, the types of aircraft debris may be large 1 / 3 wheel fragments, medium fragments, small fragments, fan fragments and other types of fragments.

[0068] For example, Figure 3 The figure shows a schematic diagram of a 1 / 3 wheel disk fragment, where R is the wheel disk radius, b is the rotor blade length corresponding to the fragment, the maximum size is the maximum size of the fan-shaped object formed by 1 / 3 wheel disk plus 1 / 3 blade length, the mass is 1 / 3 of the mass of the bladed wheel disk, and the center of gravity is located at the center of the maximum size. Figure 4The figure shows a schematic diagram of a medium fragment, where R is the radius of the disk, b is the blade length of the rotor corresponding to the fragment, the maximum size of the medium fragment is 1 / 3 (R+b), the maximum size is 1 / 3 of the radius of the disk with blades, the mass is 1 / 30 of the mass of the disk with blades, and the center of gravity is located at the edge of the disk. Figure 5 The diagram shows a small fragment. R is the radius of the wheel, b is the blade length of the rotor corresponding to the fragment, and the maximum size of the small fragment is 1 / 2b. , the maximum size is the size corresponding to 1 / 2 of the rotor blade length, the mass is 1 / 2 of the rotor blade mass, and the center of gravity is located at the geometric center of the small fragment. Figure 6 The figure shows a schematic diagram of fan debris, where X is the length of the fan blade, the maximum size is 1 / 3 of the fan blade airfoil height from the wing tip, the mass is 1 / 3 of the fan blade mass, and the center of gravity is located at the geometric center of the fan debris. It can be understood that the debris in the aircraft will be emitted from different angles and may collide with the components in the aircraft. Severe collisions will cause catastrophic failure of the aircraft. The impact range corresponding to the aircraft debris refers to the radiation range corresponding to the components in the overall structure of the aircraft that are emitted at a scattered angle by various types of aircraft debris and collide with the aircraft. The structure of the aircraft may include wings, horizontal tails, landing gears, engines, pipes, airborne equipment and other components. In this embodiment, the components that collide with various types of debris can be determined as target components, where the number of components affected by each type of debris may be one or more, and correspondingly, the target component may be one or more.

[0069] For example, the size parameters of large fragments of a single 1 / 3 wheel disk may be as shown in Table 1, the size parameters of medium fragments may be as shown in Table 2, the size parameters of small fragments may be as shown in Table 3, and the size parameters of fan fragments may be as shown in Table 4.

[0070] Table 1 Size parameters of a single 1 / 3 wheel large fragment

[0071]

[0072] Table 2 Size parameters of the fragments

[0073]

[0074] Table 3 Size parameters of small fragments

[0075]

[0076] Table 4 Size parameters of fan fragments

[0077]

[0078] In this embodiment, the influence range corresponding to each type of debris of the aircraft can be determined, and the target component can be determined according to the probability of collision between the influence range corresponding to each type of debris and the components in the overall structure of the aircraft. Optionally, if the probability of collision between the influence range of each type of debris and a certain component is greater than 0, the component can be determined as the target component.

[0079] S202, determining a collision risk angle interval of each type of debris colliding with each target component according to a predefined debris scattering angle range and size parameters of a rotor corresponding to each type of debris.

[0080] It is understandable that for each type of fragment, the launch angle of each type of fragment can be determined according to the size, mass, center of gravity, translational energy and other parameters of the fragment, and the angle measured forward or backward at the intersection of the single rotor rotation plane corresponding to the fragment and the engine axis line, indicating the possible dispersion range of the fragment is determined as the dispersion angle of the fragment, and the dispersion angle range of each type of fragment is determined according to all the launch angles corresponding to each type of fragment, wherein the dispersion angle range of 1 / 3 wheel large fragments can be ±3°, the dispersion angle range of medium fragments can be ±5°, the dispersion angle range of small fragments can be ±15°, and the dispersion angle range of fan fragments can be ±15°. The engine includes multiple stages of different rotors, and the types of rotors can include compressors, turbines, fans, etc. The parameters of each stage of the rotor can include relative position, rotation direction, geometric dimensions, rotor mass, rotor speed, wherein the geometric dimensions of the rotor can include wheel radius, blade / fan length, blade / fan thickness, and the size parameters of the rotor corresponding to each type of fragment can include rotor thickness and rotor radius. In this embodiment, the collision angles at which various types of fragments are emitted from different scattering angles and collide with various target components can be determined as collision risk angles, and the collision risk angle interval is determined according to the maximum and minimum values ​​of all collision risk angles. Exemplarily, the size parameters corresponding to the rotors of each stage in the engine can be shown in Table 5.

[0081] Table 5 Dimensional parameters of rotors at each level

[0082]

[0083] In this embodiment, based on the debris scattering angle range corresponding to each type of debris, the collision area where the debris emitted at each scattering angle collides with the corresponding target components can be calculated, and the angle corresponding to each collision area can be determined as the collision risk angle corresponding to each scattering angle. Then, the collision risk angle interval can be determined based on the maximum and minimum values ​​of each collision risk angle, the maximum value of all collision risk angles can be determined as the upper limit value of the collision risk angle interval, and the minimum value of all collision risk angles can be determined as the lower limit value of the collision risk angle interval, so as to obtain the collision risk angle interval.

[0084] S203, obtaining a risk probability value of each type of debris causing a risk to the aircraft according to the collision risk angle interval of each type of debris colliding with each target component.

[0085] It should be noted that in order to ensure the safety of the aircraft during flight, there may be redundant structures in the overall structure of the aircraft. Therefore, after the aircraft debris collides with the redundant components, no failure that affects the safe operation of the aircraft will occur. After the aircraft debris collides with a single core component, a failure that affects the safe operation of the aircraft may occur. Therefore, it is necessary to calculate the risk probability value of the aircraft caused by each type of debris based on the collision risk angle interval after each type of debris collides with the target component. Among them, the risk probability value refers to the probability of a failure that affects the safe operation of the aircraft after each type of debris collides with each target component in the aircraft.

[0086] In this embodiment, the probability values ​​of collision between the debris and each target component can be calculated respectively according to the collision risk angle interval of each type of debris colliding with each target component, thereby the correspondence between each target component and the safety of aircraft operation, and the risk probability value of the risk of aircraft caused by the debris can be calculated with each probability value.

[0087] In the above-mentioned method for determining the risk probability value, at least one target component affected by each type of debris can be accurately determined from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft. Since the amount of calculation for determining the target component according to the impact range corresponding to the debris and the overall structure of the aircraft is small, the calculation process is relatively simple, and the target component can be quickly determined, so that according to the predefined debris scattering angle range and the size parameters of the rotor corresponding to each type of debris, the collision risk angle interval of each type of debris colliding with each target component can be quickly determined, and then according to the collision risk angle interval of each type of debris colliding with each target component, the risk probability value of the risk of the aircraft caused by each type of debris can be obtained. Since the amount of calculation involved in the calculation process of determining the collision risk angle interval of each type of debris colliding with each target component according to the debris scattering angle range and the size parameters of the corresponding rotor is small, the probability value of the collision between each type of debris and each target component can be quickly and accurately determined according to the collision risk angle interval, so that the risk probability value of the risk of the aircraft caused by the debris can be quickly and accurately determined according to each probability value, and then the problem of calculating the probability of the collision between the debris and the target component multiple times in order to accurately determine the risk probability value in the process of determining the risk probability value can be avoided, thereby improving the efficiency of determining the risk probability value.

[0088] In the above scenario where the risk probability value of each type of debris causing the aircraft to encounter a risk is obtained based on the collision risk angle interval of each type of debris colliding with each target component, the risk probability value of each type of debris causing the aircraft to encounter a risk can be determined by determining the probability value of each type of debris hitting the target component at the same time, thereby determining the risk probability value of each type of debris causing the aircraft to encounter a risk based on the probability value of each type of debris hitting the target component at the same time. Figure 7 As shown, the above S203 includes:

[0089] S301 , determining probability values ​​of each type of debris hitting the target component at the same time according to the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval.

[0090] It is understandable that failures that affect the safe operation of an aircraft are usually caused by the simultaneous collision of multiple related components. Therefore, the risk probability value of causing the aircraft risk can be determined based on the probability value of each type of debris hitting the target component at the same time.

[0091] In this embodiment, the target components corresponding to each fault that causes the aircraft can be determined in advance, so as to calculate the product between the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval, and use the product as the probability value of all target components causing each fault being hit at the same time. The corresponding target component combination is , the probability density function corresponding to each collision risk angle interval is , it can be calculated according to the following formula The probability that the target parts in are hit simultaneously : ,in, is the upper limit of the collision risk angle interval, is the lower limit of the collision risk angle interval. For example, the minimum target component combination corresponding to different aircraft failures is shown in Table 6.

[0092] Table 6 Minimum target component combinations corresponding to different aircraft failures

[0093]

[0094] S302, determining the probability value of each type of debris corresponding to the rotor causing the aircraft risk based on the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft.

[0095] Among them, flight risk factors It is used to define the probability of an uncontained rotor explosion failure of the aircraft engine at different flight stages. Different types of aircraft may correspond to different flight stages. In this embodiment, the aircraft stage can be divided into 7 stages: take-off to V1 speed stage, V1 speed to first power reduction stage, climb stage, cruise stage, descent stage, approach stage and landing / go-around stage. The value range of the flight stage risk factor can be 0.0~1.0, and the 7 stage risk factors The total is 1.0. Impact Factor Indicates that the aircraft flight safety failure occurred in The impact on aircraft safety during each flight phase, among which the impact factor The value range may be 0.0 to 1.0. For example, the flight risk factors preset in each flight phase may be as shown in Table 7.

[0096] Table 7 Preset flight risk factors for each flight phase

[0097]

[0098] In this embodiment, the product of the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft can be used as the probability value of the risk of the aircraft caused by the corresponding rotor of each type of debris. For example, the probability value of the risk of the aircraft caused by the corresponding rotor of each type of debris can be calculated according to the following formula: : ,in, It represents the number of failures that affect flight safety, and s represents each flight phase.

[0099] S303, obtaining a risk probability value of the risk of each type of debris causing the aircraft to occur according to the probability value of each type of debris causing the aircraft to occur and the number of rotors.

[0100] The aircraft engine may include different types of rotors, for example, fan-type rotors, compressor-type rotors, and turbine-type rotors, wherein the stages of each type of rotor are different and the corresponding quantities are also different. For example, an engine may include a 1-stage fan, a 5-stage high-pressure compressor, a 1-stage high-pressure turbine, and a 4-stage low-pressure turbine. In this embodiment, corresponding weights may be assigned to the probability values ​​of the risk of each type of debris causing an aircraft accident according to the degree of harm caused by each type of debris causing the aircraft accident, so that the weighted sum of the probability values ​​of each type of debris causing an aircraft accident is determined as the risk probability value of each type of debris causing an aircraft accident.

[0101] In this embodiment, based on the collision risk angle intervals of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval, the probability value of each type of debris hitting the target component at the same time can be accurately determined, so that based on the probability value, the flight risk factor preset for each flight stage of the aircraft, and the influencing factor of the risk occurring in each flight stage of the aircraft, the probability value of the risk of the aircraft caused by the corresponding rotor of each type of debris can be quickly and accurately determined, and then based on the probability value of the aircraft caused by each type of debris and the number of rotors, the risk probability value of the aircraft caused by each type of debris can be obtained. The above process of obtaining the risk probability value is simple in calculation, which reduces the amount of calculation of the risk probability value and improves the efficiency of obtaining the risk probability value.

[0102] In the scenario where the risk probability value of each type of debris causing the aircraft to occur is obtained based on the probability value of each type of debris causing the aircraft to occur and the number of rotors, the risk probability value of each type of debris causing the aircraft to occur can be determined based on the ratio between the probability value of each type of debris causing the aircraft to occur and the number of rotors. In one embodiment, the above S303 includes: determining the ratio of the sum of the probability values ​​of each type of debris causing the aircraft to occur and the number of rotors as the risk probability value of each type of debris causing the aircraft to occur.

[0103] In this embodiment, the ratio between the cumulative sum of the probability values ​​of each type of debris causing the aircraft to encounter risks and the number of rotors can be determined as the risk probability value. For example, the risk probability value can be obtained by the following formula: , where M is the number of rotors.

[0104] As an optional implementation, assuming that the aircraft includes E engines, the risk probability value is Can be .

[0105] In this embodiment, the risk probability value of the risk of aircraft occurrence caused by each type of debris is determined by the ratio of the sum of the probability values ​​of the aircraft occurrence caused by each type of debris to the number of rotors. In the process of determining the risk probability value of the risk of aircraft occurrence caused by each type of debris, the correlation between the number of rotors and the risk of aircraft occurrence can be considered, so that the risk probability value of the risk of aircraft occurrence caused by each type of debris can be accurately determined according to the probability value of the aircraft occurrence caused by each type of debris corresponding to each rotor.

[0106] In the above scenario where the collision risk angle intervals of each type of debris colliding with each target component are determined based on the predefined debris scattering angle range and the size parameters of the rotor corresponding to each type of debris, the collision risk angle may include a sweeping risk angle interval and a scattering risk angle interval. The sweeping angle corresponding to each scattering angle section may be determined based on the debris scattering angle range and the number of scattering angle sections, thereby determining the sweeping risk angle interval, and further determining the scattering risk angle interval based on the sweeping risk angle interval and the number of sweeping angle sections. In one embodiment, Figure 8 As shown, the above S202 includes:

[0107] S401, obtaining a scattering angle calculation step length according to a debris scattering angle range and a preset number of scattering angle sections.

[0108] The preset scatter angle section refers to the collision surface corresponding to when the fragments are launched and collide with the target component. It can be understood that when the target component corresponds to a plane, the number of scatter angle sections is 1. When the target component is irregular in shape, it can be divided into multiple planes, and the number of scatter angle sections is the number of planes corresponding to the target component. Therefore, when calculating the collision risk angle corresponding to the fragments, the risk angle corresponding to each scatter angle section can be calculated according to the number of scatter angle sections, thereby obtaining the collision risk angle. For example, the fragment scatter angle is as follows: Fig. 9 As shown, different types of debris correspond to different scattering angle ranges.

[0109] In this embodiment, the ratio of the angle difference corresponding to the debris scattering angle range to the number of scattering angle sections can be determined as the scattering angle calculation step. , the debris scattering angle range is [- ,+ ], then the step length of the divergence angle calculation is Can be .

[0110] S402, determining the sweep angle corresponding to each scatter angle section according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0111] Among them, the dimensional parameters of the rotor may include the thickness and radius of the rotor. The sweep angle corresponding to the scatter angle section refers to the angle corresponding to the intersection area between the radiation surface formed by the fragments emitted at various scatter angles and each scatter angle section. The sweep angle corresponding to each scatter angle section is used to characterize the range in which the fragments collide with each scatter angle section.

[0112] In this embodiment, the radiation range corresponding to the fragments emitted at the scattering angle corresponding to each scattering angle calculation step can be calculated based on the size parameters of the rotor corresponding to each type of fragments, and then the intersection angle corresponding to the intersection area between each radiation range and each target component, that is, the sweep angle corresponding to each scattering angle section, can be calculated.

[0113] For example, the sweep angle is Fig.10 shown.

[0114] S403, taking the maximum value of each sweeping angle as the upper limit of the sweeping risk angle interval, and taking the minimum value of each sweeping angle as the lower limit of the sweeping risk angle, to obtain the sweeping risk angle interval.

[0115] The sweep risk angle interval refers to the angle range corresponding to the intersection area between the radiation range and the target components after the debris is emitted at each scattering angle in the scattering angle range. The sweep risk angle interval can characterize the range of the debris colliding with each target component. For example, the sweep risk angle interval is as follows: Fig.11 As shown, the rotation plane refers to the rotation plane of the rotor where the fragments are located.

[0116] In this embodiment, the maximum value and the minimum value of each sweep angle can be determined by using an extreme value function, so that the maximum value of each sweep angle is used as the upper limit of the sweep risk angle interval, and the minimum value of each sweep angle is used as the lower limit of the sweep risk angle. The sweep risk angle interval is obtained according to the upper limit and the lower limit. Exemplarily, the sweep risk angle interval of a single 1 / 3 wheel disk large fragment of the first-stage rotor can be shown in Table 8.

[0117] S404: Acquire a scattering risk angle interval according to the sweep risk angle interval and the number of preset sweep angle sections.

[0118] The scatter risk angle interval refers to the angle interval of the possible scattering range of the debris emitted at the scatter angle. In this embodiment, the calculation step length corresponding to the scatter risk angle can be determined according to the number of each sweep angle section in the sweep risk angle interval, so that the scatter angle corresponding to each sweep angle section is calculated in turn according to the calculation step length corresponding to the scatter risk angle, and the scatter risk angle is determined according to each scatter angle. Exemplarily, the scatter risk angle interval is as follows: Fig.12 As shown. Exemplarily, the large debris sweep risk angle interval of a single 1 / 3 wheel disk of the first stage rotor can be as shown in Table 9.

[0119] As an optional implementation, according to the sweep risk angle interval, the scatter risk angle interval, the probability density function corresponding to each sweep risk angle interval, and the probability density function corresponding to each scatter risk angle interval of each type of debris colliding with the target component, the probability value of each type of debris hitting the target component at the same time can be expressed as:

[0120]

[0121] In the formula, is the random variable of the debris scattering angle The probability density function of the debris scattering angle interval is The upper one follows a uniform distribution, . The probability density function of . is the random variable of the debris sweep angle The probability density function of the fragment sweep angle is In the interval The upper one follows a uniform distribution, , The probability density function of .

[0122] Table 8 Large debris sweep risk angle interval for a single 1 / 3 disk of the first stage rotor

[0123]

[0124] Table 9 Risk angle interval of large debris flying from a single 1 / 3 disk of the first-stage rotor

[0125]

[0126] In this embodiment, the scatter angle calculation step is obtained according to the debris scatter angle range and the number of preset scatter angle sections, and the sweep angle corresponding to each swept rotation surface is determined according to the scatter angle calculation step and the size parameters of the rotor corresponding to each type of debris, so that the maximum value of each sweep angle can be used as the upper limit value of the sweep risk angle interval, and the minimum value of each sweep angle can be used as the lower limit value of the sweep risk angle to obtain the sweep risk angle interval. In the above process of obtaining the sweep risk angle interval, the sweep risk angle interval can be obtained only according to the scatter angle range and the size parameters of the corresponding rotor. The calculation process is simple, and the amount of calculation involved in the calculation process is small. The sweep risk angle interval can be quickly obtained, and then the scatter risk angle interval can be obtained according to the sweep risk angle interval and the number of preset sweep angle sections. Since the scatter risk angle interval can be obtained only by the sweep risk angle interval and the number of sweep angle sections, the amount of calculation in the calculation process of obtaining the scatter risk angle interval is reduced, and the efficiency of obtaining the sweep risk angle interval and the scatter risk angle interval is improved.

[0127] In the above scenario where the sweep angle corresponding to each scatter angle section is determined based on the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris, each swept rotation surface can be determined based on the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris, thereby determining the corresponding sweep angle based on each swept rotation surface. In one embodiment, Fig.13 As shown, the above S402 includes:

[0128] S501, determining a swept rotation surface corresponding to each scatter angle section according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0129] Among them, the swept rotation surface refers to the range that can be radiated after the fragments are emitted at a certain spread angle during the rotation of the engine rotor. In this embodiment, the rotation generatrix of each swept rotation surface can be determined according to the spread angle calculation step size and the size parameters of the rotor corresponding to each type of fragments, thereby obtaining each swept rotation surface.

[0130] In this embodiment, the dispersion angle corresponding to each calculation step can be determined in sequence, the rotation center of the engine rotor is used as a reference point, the boundary point of the radiation range of the fragments is determined according to the thickness of the rotor, the boundary point is used as a reference point, the radius of the rotor is used as the length to determine the starting point, and the end point is determined according to the dispersion angle corresponding to each calculation step, so that the line between the starting point and the end point is determined as the rotation generatrix of each swept rotation surface, and then the surface swept by the rotation generatrix around the rotor is determined as the swept rotation surface. Exemplarily, if the cycle parameter m=1 in the process of calculating the swept rotation surface, the dispersion angle corresponding to each dispersion angle section can be determined according to the dispersion angle calculation step. for .

[0131] S502: Determine a first intersection angle corresponding to an intersection area between each swept rotational surface and each target component.

[0132] It is understandable that each swept rotation curved surface may completely intersect with each target component or may partially intersect with each target component. Therefore, the sweep angle corresponding to each swept rotation curved surface can be determined by determining the angle of intersection between each swept rotation curved surface and each target component. The first intersection angle is the angle corresponding to the intersection area between each swept rotation curved surface and each target component.

[0133] In this embodiment, Boolean operations can be used to calculate whether each swept rotation surface intersects with each target component. If so, the intersection area between each swept rotation surface and each target component is determined as the target area, thereby calculating the range of angles corresponding to the target area, and determining the angle as the first intersection angle. Exemplarily, multiple first intersection angles corresponding to the intersection area between the swept rotation surface corresponding to each divergence angle step and each target component can be iteratively calculated by adding 1 to the loop parameter.

[0134] S503: Determine the sweep angle corresponding to each swept rotation surface from each first intersection angle using a preset extreme value function.

[0135] Among them, the extreme value function refers to a function for determining the maximum and minimum values. In this embodiment, all angle values ​​corresponding to each first intersection angle can be input into the preset extreme value function to determine the maximum and minimum values ​​among all angle values ​​corresponding to each first intersection angle, so that each maximum value is determined as the upper limit value of the sweeping angle corresponding to each swept rotation surface, and each minimum value is determined as the lower limit value of the sweeping angle corresponding to each swept rotation surface, so as to obtain the sweeping angle corresponding to each swept rotation surface.

[0136] In this embodiment, by calculating the step size according to the scattering angle and the size parameters of the rotor corresponding to each type of fragment, the swept rotation surface corresponding to each scattering angle section can be determined, so that the first intersection angle corresponding to the intersection area of ​​each swept rotation surface and each target component can be determined. Since each first intersection angle can be accurately determined according to the intersection area, the swept angle corresponding to each swept rotation surface can be accurately determined from each first intersection angle using a preset extreme value function.

[0137] In the above scenario where the scattering risk angle interval is obtained based on the sweeping risk angle interval and the number of preset sweeping angle sections, the sweeping angle calculation step length can be obtained based on the sweeping risk angle interval and the number of preset sweeping angle sections, thereby determining the scattering plane corresponding to each sweeping angle section, and then determining the scattering risk angle interval based on the scattering angle corresponding to each scattering plane. In one embodiment, Fig.14 As shown, the above S404 includes:

[0138] S601, obtaining a sweep angle calculation step length according to a sweep risk angle interval and the number of preset sweep angle sections.

[0139] Among them, the preset sweep angle section refers to the surface corresponding to the sweep risk angle when the fragments are emitted, and the number of sweep angle sections can be determined according to the shape of the surface corresponding to the sweep risk angle. Therefore, when calculating the scatter risk angle corresponding to the fragments, the risk angle corresponding to each sweep angle section can be calculated respectively according to the number of sweep angle sections, so as to obtain the scatter risk angle.

[0140] In this embodiment, the ratio of the angle difference between the upper limit value and the lower limit value of the sweep risk angle interval to the number of sweep angle sections can be determined as the sweep angle calculation step length. , the sweep risk angle interval is [ ], then the sweep angle calculation step length Can be .

[0141] S602, determining the scattering plane corresponding to each sweep angle section according to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0142] Among them, the size parameters of the rotor may include the thickness and radius of the rotor, and the scattering plane corresponding to the sweep angle section refers to the plane formed by the scattering angles of the fragments emitted corresponding to different sweep angle sections. In this embodiment, the sweep angle corresponding to each calculation step can be determined in sequence, with the rotation center of the engine rotor as the reference point, and the boundary point of the radiation range of the fragments determined according to the thickness of the rotor. The boundary point is used as the reference point and the radius of the rotor is used as the length to determine the starting point, and the end point is determined with the scattering angle corresponding to each calculation step, so that the line between the starting point and the end point is determined as the rotation generatrix of each swept rotation surface, and then the surface swept by the rotation generatrix around the rotor for one rotation is determined as the scattering plane. Exemplarily, if the cyclic parameter n=1 in the process of calculating the scattering plane, the scattering angle corresponding to each scattering angle section can be determined according to the scattering angle calculation step. for .

[0143] S603: Determine the scattering angle corresponding to each scattering plane according to each scattering plane and each target component.

[0144] The scattering angle corresponding to each scattering plane refers to the angle of the intersection area between each sweep angle section and each target component. In this embodiment, the intersection area between each scattering plane and each target component can be calculated respectively, so as to determine the scattering angle corresponding to each scattering plane according to the intersection area.

[0145] S604: Taking the maximum value of each scattering angle as the upper limit of the scattering risk angle interval, and taking the minimum value of each scattering angle as the lower limit of the scattering risk angle interval, to obtain the scattering risk angle interval.

[0146] The scatter risk angle interval refers to the angle range of the intersection of the range of debris emitted at the scatter angle and the range of the target component. The scatter risk angle interval can characterize the range of debris emitted at the scatter angle and the target component.

[0147] In this embodiment, the maximum value and the minimum value of each scattering angle can be determined by using an extreme value function, so that the maximum value of each scattering angle is used as the upper limit value of the scattering risk angle interval, and the minimum value of each scattering angle is used as the lower limit value of the scattering risk angle, and the scattering risk angle interval is obtained according to the upper limit value and the lower limit value.

[0148] In this embodiment, the sweep angle calculation step can be obtained according to the sweeping risk angle interval and the number of preset sweeping angle sections, and the scattering plane corresponding to each sweeping angle section can be determined according to the sweeping angle calculation step and the size parameters of the rotor corresponding to each type of debris, so that the scattering angle corresponding to each scattering plane can be determined according to each scattering plane and each target component, and the maximum value of each scattering angle is used as the upper limit value of the scattering risk angle interval, and the minimum value of each scattering angle is used as the lower limit value of the scattering risk angle interval to obtain the scattering risk angle interval. In the above process of obtaining the scattering risk angle interval, the sweeping risk angle interval can be obtained only according to the sweeping risk angle interval and the number of sweeping angle sections, the calculation process is simple, and the amount of calculation involved in the calculation process is small, so the scattering risk angle interval can be obtained quickly.

[0149] In the above scenario where the scattering angles corresponding to the scattering planes are determined based on the scattering planes and the target components, the scattering angles can be determined based on the second intersection angles of the intersection areas between the scattering planes and the target components. Fig.15 As shown, the above S603 includes:

[0150] S701, determining a second intersection angle corresponding to an intersection area between each scattering plane and each target component.

[0151] It is understandable that each scattering plane may completely intersect with each target component or may partially intersect with each target component. Therefore, the scattering angle corresponding to each scattering plane may be determined by determining the angle of intersection between each scattering plane and each target component. The second intersection angle is the angle corresponding to the intersection area between each scattering plane and each target component.

[0152] In this embodiment, Boolean operations can be used to calculate whether each scattering plane intersects with each target component. If they intersect, the intersection area between each scattering plane and each target component is determined as the target area, thereby calculating the range of the angle corresponding to the target area, and determining the angle as the second intersection angle. Exemplarily, multiple second intersection angles corresponding to the intersection area between the scattering plane corresponding to each sweep angle step and each target component can be iteratively calculated by adding 1 to the loop parameter.

[0153] S702: Determine the scattering angle corresponding to each scattering plane from each second intersection angle using a preset extreme value function.

[0154] Among them, the extreme value function refers to a function that determines the maximum and minimum values. In this embodiment, all angle values ​​corresponding to each second intersection angle can be input into the preset extreme value function to determine the maximum and minimum values ​​of all angle values ​​corresponding to each second intersection angle, so that each maximum value is determined as the upper limit value of the scattering angle corresponding to each scattering plane, and each minimum value is determined as the lower limit value of the scattering angle corresponding to each scattering plane, so as to obtain the scattering angle corresponding to each scattering plane.

[0155] In this embodiment, by determining the second intersection angle corresponding to the intersection area of ​​each scattering plane and each target component, the scattering angle corresponding to each scattering plane can be quickly determined from each second intersection angle using a preset extreme value function. Since the calculation process of determining the scattering angle corresponding to each scattering plane based on each second intersection angle is relatively simple, the scattering angle corresponding to each scattering plane can be quickly obtained.

[0156] In one embodiment, the method further includes: determining whether to adjust the overall structure of the aircraft according to a comparison result of each risk probability value and a risk assessment criterion corresponding to each type of debris.

[0157] The risk assessment criteria corresponding to each type of debris refers to the threshold of the probability that each type of debris causes a risk to the aircraft. In this embodiment, the risk probability value corresponding to each type of debris can be compared with the probability threshold in the risk assessment criteria corresponding to each type of debris. If the comparison result is that each risk probability value is greater than or equal to the corresponding probability threshold, it means that the design scheme of the target component that the debris type may collide with needs to be adjusted. Furthermore, the computer device can determine how to adjust the aircraft structure according to the impact range of each type of debris on the target component of the aircraft structure, thereby generating an adjustment scheme for the entire structure of the aircraft.

[0158] In this embodiment, by comparing the risk probability value with the risk assessment criteria corresponding to each type of debris, it is possible to quickly obtain a result on whether the risk probability value meets the risk assessment criteria, thereby being able to quickly determine an adjustment plan for the overall structure of the generated aircraft when the risk probability value does not meet the risk assessment criteria.

[0159] In the above scenario of determining at least one target component affected by each type of debris from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft, a Boolean operation can be used to determine the component determined to intersect with each impact range and the overall structure of the aircraft as the target component. In one embodiment, the above S201 includes: according to a preset Boolean operation, determining the component determined to intersect with each impact range and the overall structure of the aircraft as the target component.

[0160] Among them, Boolean operation is a logical number calculation method, including union, intersection, and subtraction. In image processing, Boolean operation can be used to calculate the logical relationship between two images. For example, Boolean operation can be used to calculate whether the influence range of the debris and the range of the components in the overall structure of the aircraft intersect. In this embodiment, Boolean operation can be used to calculate the logical operation results between each influence range corresponding to each type of debris and the spatial size of each component in the overall structure of the aircraft, so as to determine the component with the intersection result as the target component.

[0161] Exemplarily, the target parts list affected by large debris of a single 1 / 3 wheel disk of the first stage rotor may be as shown in Table 10.

[0162] Exemplarily, the risk probability values ​​of the first-stage rotors of the left and right engines causing aircraft risks under the condition of a single 1 / 3 wheel disk large fragment may be as shown in Table 11.

[0163] Table 10 List of target parts affected by large debris of a single 1 / 3 disk of the first stage rotor

[0164]

[0165] Table 11 Risk probability values ​​of the first stage rotors of the left and right engines causing aircraft risks

[0166]

[0167] In this embodiment, by using the preset Boolean operation, the banana relationship between each influence range and each component in the overall structure of the aircraft can be quickly determined, so that the components intersecting each influence range with the overall structure of the aircraft can be quickly determined as target components, thereby improving the efficiency of determining the target components.

[0168] To facilitate understanding by those skilled in the art, the following is a detailed introduction to the method for determining the risk probability value provided by the present application. The method may include:

[0169] S1, according to a preset Boolean operation, determining the components that intersect with the entire structure of the aircraft in each influence range as target components.

[0170] S2, obtaining a scattering angle calculation step length according to the debris scattering angle range and the number of preset scattering angle sections.

[0171] S3, determining the swept rotation surface corresponding to each scatter angle section according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0172] S4, determining a first intersection angle corresponding to an intersection area between each swept rotational surface and each target component.

[0173] S5, determining the sweep angle corresponding to each swept rotation surface from each first intersection angle using a preset extreme value function.

[0174] S6, taking the maximum value of each sweep angle as the upper limit of the sweep risk angle interval, and taking the minimum value of each sweep angle as the lower limit of the sweep risk angle, to obtain the sweep risk angle interval.

[0175] S7, obtaining a sweep angle calculation step length according to the sweep risk angle and the number of preset sweep angle sections.

[0176] S8, determining the scattering plane corresponding to each sweep angle section according to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0177] S9, determining a second intersection angle corresponding to an intersection area between each scattering plane and each target component.

[0178] S10, determining the scattering angle corresponding to each scattering plane from each second intersection angle using a preset extreme value function.

[0179] S11, determining the probability value of each type of debris hitting the target component at the same time according to the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval.

[0180] S12, determining the probability value of each type of debris corresponding to the rotor causing the aircraft to have a risk based on the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft.

[0181] S13, determining the ratio of the sum of the probability values ​​of each type of debris causing an aircraft accident to the number of rotors as the risk probability value of each type of debris causing an aircraft accident.

[0182] S14, when each risk probability value is greater than or equal to the risk assessment criteria corresponding to each type of debris, determining to adjust the entire structure of the aircraft.

[0183] It should be noted that for the descriptions in the above S1-S14, reference may be made to the relevant descriptions in the above embodiments, and the effects are similar, so this embodiment will not be repeated here.

[0184] It should be understood that, although the steps in the flowcharts involved in the above embodiments are displayed in sequence according to the indication of the arrows, these steps are not necessarily executed in sequence according to the order indicated by the arrows. Unless there is a clear explanation in this article, the execution of these steps is not strictly limited in order, and these steps can be executed in other orders. Moreover, at least a part of the steps in the flowcharts involved in the above embodiments may include multiple steps or multiple stages, and these steps or stages are not necessarily executed at the same time, but can be executed at different times, and the execution order of these steps or stages is not necessarily carried out in sequence, but can be executed in turn or alternately with other steps or at least a part of the steps or stages in other steps.

[0185] Based on the same inventive concept, the embodiment of the present application also provides a device for determining a risk probability value for implementing the above-mentioned method for determining a risk probability value. The implementation scheme for solving the problem provided by the device is similar to the implementation scheme recorded in the above-mentioned method, so the specific limitations in the embodiments of the device for determining one or more risk probability values ​​provided below can refer to the limitations of the method for determining a risk probability value above, and will not be repeated here.

[0186] In one embodiment, Fig.16 As shown, a device for determining a risk probability value is provided, comprising: a first determining module 11, a second determining module 12 and an obtaining module 13, wherein:

[0187] The first determination module 11 is used to determine at least one target component affected by each type of debris from the entire structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft.

[0188] The second determination module 12 is used to determine the collision risk angle of each type of debris colliding with each target component according to a predefined debris scattering angle range and the thickness and radius of the rotor corresponding to each type of debris.

[0189] The acquisition module 13 is used to acquire the risk probability value of each type of debris causing the aircraft to encounter risks according to the collision risk angle of each type of debris colliding with each target component.

[0190] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0191] In one embodiment, Fig.17 As shown, the acquisition module 13 includes: a first determination unit 131, a second determination unit 132 and a first acquisition unit 133, wherein:

[0192] The first determining unit 131 is used to determine the probability value of each type of debris hitting the target component at the same time according to the collision risk angle of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval.

[0193] The second determining unit 132 is used to determine the probability value of each type of debris corresponding to the rotor causing the aircraft risk according to the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft.

[0194] The first acquisition unit 133 is used to acquire the risk probability value of the risk of each type of debris causing the aircraft to occur according to the probability value of each type of debris causing the aircraft to occur and the number of rotors.

[0195] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0196] In one embodiment, please continue to refer to Fig.17 The acquisition unit 133 is specifically used to determine the risk probability value of the aircraft caused by each type of debris as the risk probability value of the aircraft caused by each type of debris.

[0197] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0198] In one embodiment, the collision risk angle includes a sweep risk angle interval and a flyaway risk angle interval. Please continue to refer to Fig.17 The second determination module 12 includes: a second acquisition unit 121, a third determination unit 122, a third acquisition unit 123 and a fourth acquisition unit 124, wherein:

[0199] The second acquisition unit 121 is used to obtain a scattering angle calculation step length according to the debris scattering angle range and the number of preset scattering angle sections.

[0200] The third determining unit 122 is used to determine the sweep angle corresponding to each scatter angle section according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris.

[0201] The third acquisition unit 123 is used to use the maximum value of each sweeping angle as the upper limit value of the sweeping risk angle interval, and use the minimum value of each sweeping angle as the lower limit value of the sweeping risk angle to obtain the sweeping risk angle interval.

[0202] The fourth acquiring unit 124 is configured to acquire the scattering risk angle interval according to the sweeping risk angle interval and the number of preset sweeping angle sections.

[0203] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0204] In one embodiment, please continue to refer to Fig.17 The third determination unit 122 is specifically used to: determine the swept rotation surface corresponding to each scatter angle section according to the scatter angle calculation step and the size parameters of the rotor corresponding to each type of fragment; determine the first intersection angle corresponding to the intersection area of ​​each swept rotation surface and each target component; and determine the sweep angle corresponding to each swept rotation surface from each first intersection angle using a preset extreme value function.

[0205] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0206] In one embodiment, please continue to refer to Fig.17 The fourth acquisition unit 124 is specifically used to: obtain a sweep angle calculation step according to a sweep angle interval and a number of preset sweep angle sections; determine a scattering plane corresponding to each sweep angle section according to the sweep angle calculation step and a size parameter of a rotor corresponding to each type of debris; determine a scattering angle corresponding to each scattering plane according to each scattering plane and each target component; and obtain a scattering risk angle interval by taking the maximum value of each scattering angle as the upper limit of the scattering risk angle interval and taking the minimum value of each scattering angle as the lower limit of the scattering risk angle interval.

[0207] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0208] In one embodiment, please continue to refer to Fig.17 The fourth acquisition unit 124 is specifically used to: determine the second intersection angle corresponding to the intersection area of ​​each scattering plane and each target component; and determine the scattering angle corresponding to each scattering plane from each second intersection angle using a preset extreme value function.

[0209] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0210] In one embodiment, please continue to refer to Fig.17 The above device further includes: a third determination 14, wherein:

[0211] The third determination module 14 is used to determine whether to adjust the entire structure of the aircraft according to the comparison result of each risk probability value and the risk assessment criteria corresponding to each type of debris.

[0212] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0213] In one embodiment, please continue to refer to Fig.17 The first determining module 11 includes: a fourth determining unit 111, wherein:

[0214] The fourth determining unit 111 is used to determine the components that intersect each influence range with the entire structure of the aircraft as target components according to a preset Boolean operation.

[0215] The device for determining the risk probability value provided in this embodiment can execute the above method embodiment, and its implementation principle and technical effect are similar, which will not be repeated here.

[0216] Each module in the above-mentioned device for determining the risk probability value can be implemented in whole or in part by software, hardware, or a combination thereof. Each of the above-mentioned modules can be embedded in or independent of a processor in a computer device in the form of hardware, or can be stored in a memory in a computer device in the form of software, so that the processor can call and execute operations corresponding to each of the above modules.

[0217] In one embodiment, a computer device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and when the processor executes the computer program, the following steps are implemented:

[0218] Determine at least one target component affected by each type of debris from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft;

[0219] According to the predefined debris scattering angle range and the size parameters of the rotors corresponding to the debris of each type, the collision risk angle interval of each type of debris colliding with each target component is determined;

[0220] According to the collision risk angle of each type of debris colliding with each target component, the risk probability value of the aircraft being caused by each type of debris is obtained.

[0221] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0222] Determine the probability value of each type of debris hitting the target component at the same time according to the collision risk angle of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval;

[0223] Determine the probability value of each type of debris corresponding to the rotor causing the aircraft risk based on the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft;

[0224] According to the probability value of each type of debris causing an aircraft accident and the number of rotors, the risk probability value of each type of debris causing an aircraft accident is obtained.

[0225] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0226] The ratio of the sum of the probability values ​​of each type of debris causing an aircraft accident to the number of rotors is determined as the risk probability value of the risk of each type of debris causing an aircraft accident.

[0227] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0228] According to the debris scattering angle range and the number of preset scattering angle sections, the scattering angle calculation step length is obtained;

[0229] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the sweep angle corresponding to each scatter angle section is determined;

[0230] The maximum value of each sweep angle is taken as the upper limit of the sweep risk angle interval, and the minimum value of each sweep angle is taken as the lower limit of the sweep risk angle, to obtain the sweep risk angle interval;

[0231] The flying risk angle interval is obtained according to the sweep risk angle interval and the number of preset sweep angle sections.

[0232] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0233] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the swept rotation surface corresponding to each scatter angle section is determined;

[0234] Determining a first intersection angle corresponding to an intersection area between each swept rotation surface and each target component;

[0235] The sweep angle corresponding to each swept rotation surface is determined from each first intersection angle using a preset extreme value function.

[0236] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0237] According to the sweep risk angle interval and the number of preset sweep angle sections, the sweep angle calculation step length is obtained;

[0238] According to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris, the scattering plane corresponding to each sweep angle section is determined;

[0239] Determine the scattering angle corresponding to each scattering plane according to each scattering plane and each target component;

[0240] The scattering risk angle interval is obtained by taking the maximum value of each scattering angle as the upper limit value of the scattering risk angle interval and taking the minimum value of each scattering angle as the lower limit value of the scattering risk angle interval.

[0241] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0242] Determining a second intersection angle corresponding to an intersection area between each scattering plane and each target component;

[0243] The scattering angle corresponding to each scattering plane is determined from each second intersection angle using a preset extreme value function.

[0244] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0245] Based on the comparison results of each risk probability value and the risk assessment criteria corresponding to each type of debris, it is determined whether the overall structure of the aircraft should be adjusted.

[0246] In one embodiment, when the processor executes the computer program, the processor further implements the following steps:

[0247] According to the preset Boolean operation, the components intersecting with the overall structure of the aircraft in each influence range are determined as target components.

[0248] In one embodiment, a computer readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

[0249] Determine at least one target component affected by each type of debris from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft;

[0250] According to the predefined debris scattering angle range and the size parameters of the rotors corresponding to the debris of each type, the collision risk angle interval of each type of debris colliding with each target component is determined;

[0251] According to the collision risk angle of each type of debris colliding with each target component, the risk probability value of the aircraft being caused by each type of debris is obtained.

[0252] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0253] Determine the probability value of each type of debris hitting the target component at the same time according to the collision risk angle of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval;

[0254] Determine the probability value of each type of debris corresponding to the rotor causing the aircraft risk based on the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft;

[0255] According to the probability value of each type of debris causing an aircraft accident and the number of rotors, the risk probability value of each type of debris causing an aircraft accident is obtained.

[0256] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0257] The ratio of the sum of the probability values ​​of each type of debris causing an aircraft accident to the number of rotors is determined as the risk probability value of the risk of each type of debris causing an aircraft accident.

[0258] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0259] According to the debris scattering angle range and the number of preset scattering angle sections, the scattering angle calculation step length is obtained;

[0260] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the sweep angle corresponding to each scatter angle section is determined;

[0261] The maximum value of each sweep angle is taken as the upper limit of the sweep risk angle interval, and the minimum value of each sweep angle is taken as the lower limit of the sweep risk angle, to obtain the sweep risk angle interval;

[0262] The flying risk angle interval is obtained according to the sweep risk angle interval and the number of preset sweep angle sections.

[0263] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0264] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the swept rotation surface corresponding to each scatter angle section is determined;

[0265] Determining a first intersection angle corresponding to an intersection area between each swept rotation surface and each target component;

[0266] The sweep angle corresponding to each swept rotation surface is determined from each first intersection angle using a preset extreme value function.

[0267] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0268] According to the sweep risk angle interval and the number of preset sweep angle sections, the sweep angle calculation step length is obtained;

[0269] According to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris, the scattering plane corresponding to each sweep angle section is determined;

[0270] Determine the scattering angle corresponding to each scattering plane according to each scattering plane and each target component;

[0271] The scattering risk angle interval is obtained by taking the maximum value of each scattering angle as the upper limit value of the scattering risk angle interval and taking the minimum value of each scattering angle as the lower limit value of the scattering risk angle interval.

[0272] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0273] Determining a second intersection angle corresponding to an intersection area between each scattering plane and each target component;

[0274] The scattering angle corresponding to each scattering plane is determined from each second intersection angle using a preset extreme value function.

[0275] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0276] Based on the comparison results of each risk probability value and the risk assessment criteria corresponding to each type of debris, it is determined whether the overall structure of the aircraft should be adjusted.

[0277] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0278] According to the preset Boolean operation, the components intersecting with the overall structure of the aircraft in each influence range are determined as target components.

[0279] In one embodiment, a computer program product is provided, comprising a computer program, which, when executed by a processor, implements the following steps:

[0280] Determine at least one target component affected by each type of debris from the overall structure of the aircraft according to the impact range corresponding to each type of debris of the aircraft;

[0281] According to the predefined debris scattering angle range and the size parameters of the rotors corresponding to the debris of each type, the collision risk angle interval of each type of debris colliding with each target component is determined;

[0282] According to the collision risk angle of each type of debris colliding with each target component, the risk probability value of the aircraft being caused by each type of debris is obtained.

[0283] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0284] Determine the probability value of each type of debris hitting the target component at the same time according to the collision risk angle of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval;

[0285] Determine the probability value of each type of debris corresponding to the rotor causing the aircraft risk based on the probability value, the flight risk factor preset at each flight stage of the aircraft, and the influencing factor of the risk at each flight stage of the aircraft;

[0286] According to the probability value of each type of debris causing an aircraft accident and the number of rotors, the risk probability value of each type of debris causing an aircraft accident is obtained.

[0287] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0288] The ratio of the sum of the probability values ​​of each type of debris causing an aircraft accident to the number of rotors is determined as the risk probability value of the risk of each type of debris causing an aircraft accident.

[0289] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0290] According to the debris scattering angle range and the number of preset scattering angle sections, the scattering angle calculation step length is obtained;

[0291] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the sweep angle corresponding to each scatter angle section is determined;

[0292] The maximum value of each sweep angle is taken as the upper limit of the sweep risk angle interval, and the minimum value of each sweep angle is taken as the lower limit of the sweep risk angle, to obtain the sweep risk angle interval;

[0293] The flying risk angle interval is obtained according to the sweep risk angle interval and the number of preset sweep angle sections.

[0294] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0295] According to the calculation step length of the scatter angle and the size parameters of the rotor corresponding to each type of debris, the swept rotation surface corresponding to each scatter angle section is determined;

[0296] Determining a first intersection angle corresponding to an intersection area between each swept rotation surface and each target component;

[0297] The sweep angle corresponding to each swept rotation surface is determined from each first intersection angle using a preset extreme value function.

[0298] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0299] According to the sweep risk angle interval and the number of preset sweep angle sections, the sweep angle calculation step length is obtained;

[0300] According to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris, the scattering plane corresponding to each sweep angle section is determined;

[0301] Determine the scattering angle corresponding to each scattering plane according to each scattering plane and each target component;

[0302] The scattering risk angle interval is obtained by taking the maximum value of each scattering angle as the upper limit value of the scattering risk angle interval and taking the minimum value of each scattering angle as the lower limit value of the scattering risk angle interval.

[0303] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0304] Determining a second intersection angle corresponding to an intersection area between each scattering plane and each target component;

[0305] The scattering angle corresponding to each scattering plane is determined from each second intersection angle using a preset extreme value function.

[0306] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0307] Based on the comparison results of each risk probability value and the risk assessment criteria corresponding to each type of debris, it is determined whether the overall structure of the aircraft should be adjusted.

[0308] In one embodiment, when the computer program is executed by a processor, the following steps are also implemented:

[0309] According to the preset Boolean operation, the components intersecting with the overall structure of the aircraft in each influence range are determined as target components.

[0310] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. As an illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM). The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. Non-relational databases may include distributed databases based on blockchains, etc., but are not limited to this. The processor involved in each embodiment provided in this application may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but are not limited to this.

[0311] The technical features of the above embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0312] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A method for determining a risk probability value, characterized in that: The method comprises: According to a preset Boolean operation, the impact range corresponding to each type of debris of the aircraft and the components intersecting in the overall structure of the aircraft are determined as at least one target component affected by each type of debris; According to the predefined debris scattering angle range and the number of preset scattering angle sections, a scattering angle calculation step length is obtained; according to the scattering angle calculation step length and the size parameters of the rotor corresponding to each type of debris, the sweeping angle corresponding to each scattering angle section is determined; the maximum value of each sweeping angle is used as the upper limit value of the sweeping risk angle interval, and the minimum value of each sweeping angle is used as the lower limit value of the sweeping risk angle to obtain the sweeping risk angle interval; according to the sweeping risk angle interval and the number of preset sweeping angle sections, the scattering risk angle interval is obtained; According to the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval, the probability value of each type of debris hitting the target component at the same time is determined; according to the probability value, the flight risk factor preset for each flight stage of the aircraft and the influencing factor of the risk occurring in each flight stage of the aircraft, the probability value of the risk of the aircraft caused by the corresponding rotor of each type of debris is determined; according to the probability value of the aircraft caused by each type of debris and the number of rotors, the risk probability value of the risk of the aircraft caused by each type of debris is obtained; the collision risk angle interval includes the sweep risk angle interval and the scatter risk angle interval.

2. The method according to claim 1, characterized in that The step of obtaining the risk probability value of the risk of the aircraft being caused by each type of debris according to the probability value of the aircraft being caused by each type of debris and the number of the rotors includes: The ratio of the sum of the probability values ​​of each type of debris causing the aircraft to occur to the number of the rotors is determined as the risk probability value of the risk of each type of debris causing the aircraft to occur.

3. The method according to claim 1, characterized in that The step of calculating the scatter angle and the size parameter of the rotor corresponding to each type of debris to determine the sweep angle corresponding to each scatter angle section comprises: Determine the swept rotation surface corresponding to each of the scatter angle sections according to the scatter angle calculation step length and the size parameters of the rotor corresponding to each type of debris; Determining a first intersection angle corresponding to an intersection area between each of the swept rotational surfaces and each of the target components; The sweep angle corresponding to each of the swept rotation surfaces is determined from each of the first intersection angles using a preset extreme value function.

4. The method according to claim 3, characterized in that The acquiring the scattering risk angle interval according to the sweeping risk angle interval and the number of preset sweeping angle sections comprises: Obtaining a sweep angle calculation step length according to the sweep risk angle interval and the number of preset sweep angle sections; Determine the scattering plane corresponding to each of the sweep angle sections according to the sweep angle calculation step length and the size parameters of the rotor corresponding to each type of debris; Determining a scattering angle corresponding to each scattering plane according to each scattering plane and each target component; The scatter risk angle interval is obtained by taking the maximum value of each scatter angle as the upper limit value of the scatter risk angle interval and taking the minimum value of each scatter angle as the lower limit value of the scatter risk angle interval.

5. The method according to claim 4, characterized in that The step of determining the scattering angle corresponding to each scattering plane according to each scattering plane and each target component comprises: determining a second intersection angle corresponding to an intersection area between each of the scattering planes and each of the target components; The scattering angle corresponding to each scattering plane is determined from each of the second intersection angles using a preset extreme value function.

6. The method according to claim 5, characterized in that The method further comprises: According to the comparison result of each of the risk probability values ​​and the risk assessment criteria corresponding to each of the types of debris, it is determined whether to adjust the entire structure of the aircraft.

7. A device for determining a risk probability value, characterized in that: The device comprises: A first determination module is used to determine, according to a preset Boolean operation, the impact range corresponding to each type of debris of the aircraft and the components intersecting in the overall structure of the aircraft as at least one target component affected by each type of debris; The second determination module is used to obtain a scattering angle calculation step length according to a predefined debris scattering angle range and a preset number of scattering angle sections; determine a sweeping angle corresponding to each scattering angle section according to the scattering angle calculation step length and a size parameter of a rotor corresponding to each type of debris; use the maximum value of each sweeping angle as an upper limit value of a sweeping risk angle interval, and use the minimum value of each sweeping angle as a lower limit value of the sweeping risk angle to obtain a sweeping risk angle interval; obtain a scattering risk angle interval according to the sweeping risk angle interval and the preset number of sweeping angle sections; The acquisition module is used to determine the probability value of each type of debris hitting the target component at the same time according to the collision risk angle interval of each type of debris colliding with the target component and the probability density function corresponding to each collision risk angle interval; determine the probability value of the risk of the aircraft caused by the rotor corresponding to each type of debris according to the probability value, the flight risk factor preset at each flight stage of the aircraft and the influencing factor of the risk of each flight stage of the aircraft; obtain the risk probability value of the risk of the aircraft caused by each type of debris according to the probability value of the aircraft caused by each type of debris and the number of rotors; the collision risk angle interval includes the sweep risk angle interval and the scatter risk angle interval.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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