CN111324928B - Method and system for calculating explosion risk of non-inclusive rotor of aircraft engine - Google Patents
Method and system for calculating explosion risk of non-inclusive rotor of aircraft engine Download PDFInfo
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Abstract
The application discloses a method and a system for calculating explosion risks of a non-inclusive rotor of an aeroengine, wherein the method comprises the following steps: representing the geometric shape of a part to be measured of the aircraft by a discrete dot matrix, and determining the coordinate of each discrete point of the discrete dot matrix; acquiring attribute information of a specific fragment, wherein the attribute information comprises a fragment type and geometric information of a rotor of an engine corresponding to the fragment; calculating a flying risk angle of the component to be detected according to the attribute information of the fragments; projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor, and determining the coordinate of each projected point; determining the direction vectors of two critical swept track lines corresponding to each projection point, and calculating the translational risk angle of the component to be measured according to the direction vector of each critical swept track line and the first reference vector; and calculating the probability of the part to be detected being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle. The method and the device can improve the efficiency and the precision of calculating the risk angle.
Description
Technical Field
The invention relates to a special risk assessment technology of an airplane, in particular to a method and a system for calculating explosion risk of a non-inclusive rotor of an aircraft engine.
Background
The non-inclusive rotor blasting of the aero-engine means that when a rotor and a part of the aero-turbine engine are impacted by a foreign object or subjected to fatigue fracture, rotor blades or wheel disc fragments are thrown out under the action of huge centrifugal force, and if the fragments cannot be contained (blocked) by an engine casing at the moment, high-speed and high-energy fragments which fly out of the engine or a nacelle are very likely to damage a key system or a structural part of the aircraft, so that various risks such as aircraft cabin decompression, system part failure or equipment failure are caused, and the aircraft is likely to have catastrophic accidents seriously.
While large engine manufacturers have been improving the containment of the case by using new materials and new structures to reduce the likelihood of broken blade or disk fragments flying out of the engine or nacelle, the problem of uncontained rotor failure is inevitable. The analysis of the uncontained safety of the engine rotor of the airplane aims at discovering the weak link of the system design by identifying and evaluating the potential danger of the airplane design aiming at the uncontained fragments, particularly the catastrophic danger which is enough to cause the death of the airplane and the human beings, and determining the optimal method for controlling and lightening the danger by adjusting and optimizing the design scheme, thereby reducing the damage of the rotor blasting to the airplane to the minimum in the design stage.
In analyzing the risk events which may cause catastrophic accidents to the aircraft, the measurement of the risk angles, including the fly-away risk angle and the translational risk angle, is required for the components corresponding to the basic risk events. Because system or structural components of the aircraft often have complex shape curved surfaces, the positions of critical points can be accurately determined after the geometric shapes of the components are projected in the risk angle measurement process, so that the workload of manual measurement is further increased. In the process of risk angle measurement, the measurement accuracy of each component is difficult to guarantee by huge workload, and the accuracy of the result is affected by the level difference of measurement personnel. Therefore, there is a need for a programmatically implemented analysis method, especially risk quantification process, for this problem.
Disclosure of Invention
The invention mainly aims to provide a method and a system for calculating the explosion risk of a non-inclusive rotor of an aeroengine, which are used for solving the problems of low efficiency and low precision of manually measuring a risk angle in the prior art.
In order to solve the above problem, according to an aspect of the present invention, a method for calculating a risk of explosion of a non-inclusive rotor of an aircraft engine is provided, including: representing the geometric shape of a part to be measured of the aircraft by a discrete dot matrix, and determining the coordinate of each discrete point of the discrete dot matrix; acquiring attribute information of a specific fragment, wherein the attribute information comprises a fragment type and geometrical information of a rotor of an engine corresponding to the fragment; calculating a flying risk angle of the part to be tested according to the attribute information of the fragments; projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor, and determining the coordinate of each projected point; determining the direction vectors of two critical swept track lines corresponding to each projection point, and calculating the translational risk angle of the component to be measured according to the direction vector of each critical swept track line and a first reference vector; and calculating the probability of the part to be tested being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
Wherein the calculating the flying risk angle of the part to be measured according to the attribute information of the fragments comprises: determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments; determining a plurality of direction vectors according to the plurality of discrete points and the rotation central point of the rotor; calculating an angle of the plurality of direction vectors to a second reference vector, wherein the second reference vector is associated with an axial direction of an engine; determining the maximum scattering range of the fragments according to the types of the fragments; and determining the flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments.
Wherein, the direction vectors of the two critical sweep trajectory lines corresponding to each projection point are: and the direction vector of the flight trajectory line of the fragments flies along the tangential direction of the rotation trajectory line of the gravity center of the fragments and the edges of the fragments are in contact with the projection point.
Wherein, the calculating the translational risk angle of the component to be measured according to the direction vector of each critical sweep trajectory line and the first reference vector comprises: and calculating angle values of direction vectors of the two critical sweep trajectory lines corresponding to the projection point along clockwise rotation of the first reference vector, and calculating a translational risk angle of the component to be measured according to the angle values.
Wherein, still include: and respectively calculating and summarizing the probability that the part to be detected is damaged by fragments of rotors of all stages of the engine.
According to another aspect of the present invention, there is also provided an aircraft engine non-inclusive rotor burst risk calculation system, including: the discretization processing module is used for representing the geometric appearance of the part to be measured of the aircraft by a discretization lattice and determining the coordinate of each discrete point of the discretization lattice; the system comprises a fragment attribute information acquisition module, a fragment attribute information acquisition module and a fragment identification module, wherein the fragment attribute information acquisition module is used for acquiring attribute information of a specific fragment, and the attribute information comprises a fragment type and geometric information of a rotor of an engine corresponding to the fragment; the flying risk angle calculation module is used for calculating the flying risk angle of the component to be detected according to the attribute information of the fragments; the projection point coordinate calculation module is used for projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor and determining the coordinate of each projection point; the translation risk angle calculation module is used for determining the direction vectors of the two critical swept track lines corresponding to each projection point, and calculating the translation risk angle of the component to be measured according to the direction vector of each critical swept track line and the first reference vector; and the first probability calculation module is used for calculating the probability of the part to be tested being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
Wherein the fly-away risk angle calculation module is further to: determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments; determining a plurality of direction vectors according to the plurality of discrete points and the rotation central point of the rotor; calculating an angle of the plurality of direction vectors to a second reference vector, wherein the second reference vector is associated with an axial direction of an engine; determining the maximum scattering range of the fragments according to the types of the fragments; and determining the flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments.
Wherein, the direction vectors of the two critical sweeping trajectory lines corresponding to each projection point are: and the direction vector of the flight trajectory line of the fragments flies along the tangential direction of the rotation trajectory line of the gravity center of the fragments and the edges of the fragments are in contact with the projection point.
Wherein the translational risk angle calculation module is further to: and calculating angle values of direction vectors of the two critical sweep trajectory lines corresponding to the projection point along clockwise rotation of the first reference vector, and calculating a translational risk angle of the component to be measured according to the angle values.
Wherein the system further comprises: and the second probability calculation module is used for respectively calculating and summarizing the probability that the part to be detected is damaged by fragments of rotors at all levels of the engine.
According to the technical scheme, the geometrical appearance and the spatial position information of the part are represented by using the discrete dot matrix and the coordinates of the discrete points, and the numerical value of the risk angle of the part is calculated for the discrete points on the basis. In addition, layout optimization design can be performed according to the calculation result, and the layout position and the placing posture of the high-risk component are adjusted in a targeted manner according to the calculation result of the translation risk angle and the scattering risk angle of the high-risk component, so that the risk probability of the high-risk component is effectively reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a flow chart of a method for calculating the risk of explosion of an aircraft engine non-containment rotor according to an embodiment of the invention;
FIG. 2 is a schematic illustration of calculating a divergence angle, according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a projection of a part geometry according to an embodiment of the invention;
FIGS. 4A and 4B are schematic diagrams of calculating a translational risk angle according to an embodiment of the invention;
FIG. 5 is a block diagram of a system for calculating risk of explosion of an aircraft engine non-containment rotor in accordance with an embodiment of the present invention;
fig. 6 is a block diagram of a terminal device according to an embodiment of the present application;
fig. 7 is a block diagram of a processor according to an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the specific embodiments of the present invention and the accompanying drawings. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The technical solutions provided by the embodiments of the present invention are described in detail below with reference to the accompanying drawings.
Before describing the present application in detail, a brief description of some technical terms referred to herein will be provided.
Risk identification: according to the functional risk analysis of the whole airplane, the risk event which is possibly caused by the explosion of the non-inclusive rotor of the engine and causes the catastrophic accident of the airplane is determined by combining the hanging position of the engine and the scattering range of fragments.
Risk quantification: and carrying out risk angle measurement on risk events which possibly cause catastrophic accidents of the airplane, calculating the probability of occurrence of the basic risk events, and further calculating the average risk probability of the catastrophic accidents caused by the explosion of the non-inclusive rotor of the whole airplane.
Fig. 1 is a flow chart of a method for calculating the risk of explosion of an uncontained rotor of an aircraft engine according to an embodiment of the present invention, as shown in fig. 1, the method comprising the steps of:
step S102, representing the geometric shape of the part to be measured of the aircraft by a discrete lattice, and determining the coordinates of each discrete point of the discrete lattice.
Determining a part to be tested of the aircraft, and carrying out discretization processing on an outer envelope surface or an envelope line of the part to be tested. In the digital model of the whole machine, a discrete lattice with a certain density is used for representing the geometric appearance of the part to be measured, and the density of the discrete lattice depends on the geometric complexity of the envelope surface or envelope line of the part. And the coordinate value of each discrete point is a coordinate under a global Cartesian coordinate system of the whole machine model.
And step S104, acquiring attribute information of a specific fragment, wherein the attribute information comprises a fragment type and geometric information of a rotor of the engine corresponding to the fragment.
Typically, aircraft engines include multiple stages of rotors, and the rotors in each stage may burst to produce fragments that can damage the engine. When the damage of the rotor blasting to the engine is specifically analyzed, the rotor of each stage and different types of fragments generated by the rotor of each stage need to be analyzed one by one.
Firstly, the position of the rotation center of each rotor stage of the engine, namely the rotation center point coordinate, needs to be determined according to the layout position of the engine in the whole engine model. And determining the fragment type, the gravity center position and the sweep radius of the fragments according to the geometric information of the rotors at each stage, wherein the fragment type (refer to the basic assumption of AC20-128A, and AC20-128A is the advisory notice issued by the Federal Aviation Administration (FAA) in 1997) comprises the following steps: large chips (1/3 wheel chips), medium chips, small chips.
And S106, calculating the flying risk angle of the part to be measured according to the attribute information of the fragments.
In the present application, the fly-away risk angle refers to the angle at which debris flying from the rotor stage may shift forward or backward out of the rotor rotation plane and hit the target component to be measured. Specifically, the step of calculating the flight risk angle of the component to be tested includes: determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments, determining a plurality of direction vectors according to the plurality of discrete points and the rotation center point of the rotor, and calculating angles from the plurality of direction vectors to a second reference vector, wherein the second reference vector is related to the axial direction of the engine; determining the maximum scattering range of the fragments according to the types of the fragments; and determining the flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments.
Taking the example of calculating the risk angle of scattering of 1/3 disk fragments of a hexahedral element for a certain level of rotors (with a maximum scattering range of fragments of ± 3), referring to fig. 2, the hexahedral element is characterized by a discrete lattice, and the geometrical shape and spatial position of the element can be characterized by eight vertices of the hexahedron and its coordinates. Wherein the vector
The axial direction of the engine can be determined according to the rotation center coordinates of any two stages of rotors, and is also a selected space reference direction when the fly-away angle is calculated. The direction vector of the connecting line between each vertex of the hexahedron and the center of rotation of the rotor stage to be analyzed is recorded as
Firstly, each vector is obtained by calculation according to the formula (1)
To a reference vector
Angle alpha of i ：
Then, the flying risk angle ψ of the part is calculated according to the formula (2):
ψ＝min{α i ,93}-max{α i ,87} (2)
step S108, projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor, and determining the coordinates of each projected point.
And projecting all discrete points of the discrete dot matrix corresponding to the component to be measured into a rotating plane of the rotor, and calculating the projection point coordinates of each discrete point in all the discrete points. In order to determine the translational risk angle of the component under test, it is necessary to project the geometric shape or envelope of the component under test onto the rotor rotation plane. After the part to be measured is characterized by the discrete dot matrix in step S102, each discrete point can be easily projected onto the rotor rotation plane, and the coordinates of the projected points can be obtained by formula (3).
Referring to fig. 3, M, N in equation (3) are two points on the rotor axis respectively, which are used to characterize the direction vector of the rotor axis, P is the rotation axis of the rotor, C i Is the coordinate, C ', of the discrete point of the part under test after discretization' i Are the coordinates after discrete point projection.
Step S110, determining the direction vector of two critical sweep trajectory lines corresponding to each projection point, and calculating the translational risk angle of the component to be tested according to the direction vector of each critical sweep trajectory line and the first reference vector.
The translation risk angle is used for describing a projecting direction of the fragments in a rotor rotation plane, a reference direction can be arranged in the rotor rotation plane, and an angle from a fragment flying-out direction to the reference direction in the rotor rotation plane is defined as the translation risk angle. In the present application, it is assumed that the failed fragments are thrown out along the tangential direction of the gravity center rotation trajectory line before the failure, and then fly along a straight line without the fragments turning over during the flight.
When calculating the translational risk angle of the component to be measured, the projection points C of the fragment sweeping path and each discrete point can be calculated first i The direction vector at the tangent. According to the embodiment of the application, when the rotor rotates clockwise, each discrete point can determine two critical sweep trajectory lines, the direction vector of the critical sweep trajectory line is a fragment with a certain size flying along the tangential direction of the rotation trajectory line of the gravity center of the fragment, and theoretically, the edge of the critical sweep trajectory line just can contact the direction vector of the flight trajectory line of the fragment when the projected point is reached, such as the tangential line T in fig. 4B i1 N i1 And T i2 N i2 . Separately determining each projection point C i ' corresponding two critical sweep railsDirection vector of trace
And
the translational risk angle of the risk component can be calculated using equation (5), α in equation (4) i And beta i Respectively from a reference direction
Rotate clockwise to vector
And
the angle value of (c).
To determine alpha i And beta i First, a projection point C is determined according to the sweep radius R of the debris i ' corresponding two critical sweep positions, point N i1 And point N i2 The coordinates of (a). As shown in FIG. 4A, point P is the center of rotation of the rotor, R 0 The radius of the gravity center rotation trajectory line before the fragment is thrown out is assumed that the rotor rotates clockwise and passes through an arbitrary projection point C i ' tangent to the clockwise rotation trajectory at a point T i . Point N according to an embodiment of the present application i1 And point N i2 Is connected with the tangent line T i C i Is perpendicular to and at point N i1 And point N i2 To C i ' is equal to the sweep radius R of the chip. Passing point N i1 And point N i2 Two straight lines T tangent to the trajectory of the center of gravity of the clockwise rotating debris can be obtained i1 N i1 And T i2 N i2 。
In the embodiment of the present application, the tangent point T in FIG. 4A i May be expressed as (y) Ti ,z Ti )＝(R 0 cosη,R 0 sin η), where η ═ φ i1 +φ i2 . The angle phi can be calculated by using the formulas (5) and (6), respectively i1 And phi i2 Value of (1), then tangent T i C i The direction vector of' can be expressed as equation (7).
Calculating point N using the vertical relationship and the value of sweep radius R i1 And point N i2 Coordinate (y) of n1 ,z n1 ) And (y) n2 ,z n2 ) As shown in equations (8) and (9). At the point of acquisition N i1 And point N i2 After the coordinates of (c), the previously solved tangent T can be used i C i ' the method of direction vector obtains the tangent T i1 N i1 And T i2 N i2 The direction vector of (2) and finally alpha can be obtained i And beta i The angle value of (c) is as shown in equation (10).
Substituting the formulas (5) - (10) into the formula (4) to obtain the final productMeasuring the translational risk angle corresponding to the component
And step S112, calculating the probability that the part to be tested is damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
The flying risk angle and the translational risk angle of the part to be tested relative to a certain fragment are obtained according to the steps S106 and S110, the flying risk angle and the translational risk angle of the part to be tested which can be hit by various fragments generated by each rotor stage are calculated according to the steps, and the probability that the part to be tested is damaged by the rotor blasting fragments, namely the risk probability of a single risk event, is calculated through the formula (11).
For multiple basic risk events, that is, basic events in which two or more components are damaged simultaneously to cause a risk accident, the intersection of the translational risk angle and the dispersive risk angle corresponding to each relevant component can be calculated, and then the probability value of the multiple basic risk events is calculated according to the formula (12).
Through the embodiment, the translational risk angle and the flying risk angle of each dangerous component corresponding to different rotor levels and different fragment types can be efficiently calculated, the calculation result has high precision, and the risk analysis efficiency of the whole machine is greatly improved while manual errors are eliminated.
Fig. 5 is a block diagram of a structure of a system for calculating risk of explosion of an uncontained rotor of an aircraft engine according to an embodiment of the present application, as shown in fig. 5, which includes:
the discretization processing module 51 is configured to characterize the geometric shape of the part to be measured of the aircraft by a discretization lattice, and determine coordinates of each discrete point of the discretization lattice;
a fragment attribute information obtaining module 52, configured to obtain attribute information of a specific fragment, where the attribute information includes a fragment type and geometric information of a rotor of the engine corresponding to the fragment;
a flying risk angle calculation module 53, configured to calculate a flying risk angle of the component to be tested according to the attribute information of the fragments;
a projection point coordinate calculation module 54, configured to project a plurality of discrete points of the discrete dot matrix onto a rotation plane of the rotor, and determine coordinates of each projection point;
the translation risk angle calculation module 55 is configured to determine direction vectors of two critical swept track lines corresponding to each projection point, and calculate a translation risk angle of the component to be measured according to the direction vector of each critical swept track line and the first reference vector;
a first probability calculation module 56, configured to calculate a probability that the component to be tested is damaged by a rotor blasting fragment according to the flying risk angle and the translational risk angle.
The internal functions and structure of the aircraft engine non-inclusive rotor blast risk calculation system are described above. In practice, the system may be implemented as a terminal device, as shown in fig. 6, the terminal device 60 includes: a memory 61 and a processor 62.
The memory 61 is configured to store a program.
In addition, the memory 61 may also be configured to store other various data to support operations on the terminal device. Examples of such data include instructions, messages, pictures, audio-video, etc. for any application or method operating on the terminal device.
In practical applications, the memory 61 may be implemented by any type of volatile or non-volatile storage device or combination thereof, such as: static Random Access Memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic memory, flash memory, magnetic or optical disks, or the like.
A processor 62 is coupled to the memory 61 and is configured to process programs stored by the memory 61. Referring to fig. 7, the processor 62 further includes:
the discretization processing module 71 is configured to characterize the geometric shape of the part to be measured of the aircraft by a discrete dot matrix, and determine coordinates of each discrete point of the discrete dot matrix;
a fragment attribute information obtaining module 72, configured to obtain attribute information of a specific fragment, where the attribute information includes a fragment type and geometric information of a rotor of the engine corresponding to the fragment;
a flying risk angle calculation module 73, configured to calculate a flying risk angle of the component to be tested according to the attribute information of the fragments;
a projection point coordinate calculation module 74, configured to project a plurality of discrete points of the discrete dot matrix onto a rotation plane of the rotor, and determine coordinates of each projection point;
the translation risk angle calculation module 75 is configured to determine direction vectors of two critical swept track lines corresponding to each projection point, and calculate a translation risk angle of the component to be measured according to the direction vector of each critical swept track line and the first reference vector;
and a first probability calculation module 76 for calculating the probability of the part to be tested being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
Further, the fly-away risk angle calculation module 73 is configured to: determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments; determining a plurality of direction vectors according to the plurality of discrete points and the rotation central point of the rotor; calculating an angle of the plurality of direction vectors to a second reference vector, wherein the second reference vector is associated with an axial direction of an engine; determining the maximum scattering range of the fragments according to the types of the fragments; and determining the flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments.
Wherein, the direction vectors of the two critical sweeping trajectory lines corresponding to each projection point are: and the direction vector of the flight trajectory line of the fragments flies along the tangential direction of the rotation trajectory line of the gravity center of the fragments and the edges of the fragments are in contact with the projection point. Further, the translational risk angle calculation module 75 is configured to: and calculating angle values of direction vectors of the two critical sweep trajectory lines corresponding to the projection point along clockwise rotation of the first reference vector, and calculating a translational risk angle of the component to be measured according to the angle values.
And in some embodiments, the processor 62 may further include: and a second probability calculation module (not shown) for respectively calculating and summarizing the probability that the part to be tested is damaged by fragments of rotors of all stages of the engine.
With continued reference to fig. 6, the terminal device 60 further includes: communication components 63, power components 64, audio components 65, display 66, and the like. It should be noted that only some of the components are schematically shown in fig. 6, and the server device is not meant to include only the components shown in the figure.
The communication component 63 is configured to facilitate wired or wireless communication between the terminal device and other devices. The terminal device may access a wireless network based on a communication standard, such as WiFi, 2G or 3G, or a combination thereof. In an exemplary embodiment, the communication component 63 receives a broadcast signal or broadcast related information from an external broadcast management system via a broadcast channel. In an exemplary embodiment, the communication component 63 further includes a Near Field Communication (NFC) module to facilitate short-range communication. For example, the NFC module may be implemented based on Radio Frequency Identification (RFID) technology, infrared data association (IrDA) technology, Ultra Wideband (UWB) technology, Bluetooth (BT) technology, and other technologies.
And a power supply component 64 for providing power to the various components of the terminal device. The power components 64 may include a power management system, one or more power supplies, and other components associated with generating, managing, and distributing power for the terminal device.
The audio component 65 is configured to output and/or input an audio signal. For example, the audio component 65 includes a Microphone (MIC) configured to receive an external audio signal when the terminal device is in an operation mode, such as a call mode, a recording mode, and a voice recognition mode. The received audio signal may further be stored in the memory 61 or transmitted via the communication component 63. In some embodiments, audio assembly 65 also includes a speaker for outputting audio signals.
The display 66 includes a screen, which may include a Liquid Crystal Display (LCD) and a Touch Panel (TP). If the screen includes a touch panel, the screen may be implemented as a touch screen to receive an input signal from a user. The touch panel includes one or more touch sensors to sense touch, slide, and gestures on the touch panel. The touch sensor may not only sense the boundary of a touch or slide action, but also detect the duration and pressure associated with the touch or slide operation.
The operation steps of the method of the present invention correspond to the structural features of the system, and can be referred to each other, which is not described in detail.
According to the technical scheme of the application, the geometrical shape and the spatial position information of the part are represented by using the discrete dot matrix and the coordinates of each discrete point, and a numerical calculation scheme for each discrete point and the risk angle of the part is established on the basis of the geometrical shape and the spatial position information. The method and the device can efficiently calculate the translational risk angle and the flying risk angle of each dangerous component corresponding to different rotor levels and different fragment types, and greatly improve the risk analysis efficiency of the whole machine while eliminating manual errors. In addition, layout optimization design can be performed according to the calculation result, and the layout position and the placing posture of the high-risk component are adjusted in a targeted manner according to the calculation result of the translation risk angle and the scattering risk angle of the high-risk component, so that the risk probability of the high-risk component is effectively reduced.
Those of ordinary skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. For example, the above-described apparatus embodiments are merely illustrative, and for example, the division of the units is only one logical division, and other divisions may be realized in practice, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
The functions may be stored in a computer-readable storage medium if they are implemented in the form of software functional units and sold or used as separate products. Based on such understanding, the technical solution of the present invention or a part thereof, which essentially contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network side device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (4)
1. A method for calculating explosion risks of a non-inclusive rotor of an aeroengine is characterized by comprising the following steps:
representing the geometric shape of a part to be measured of the aircraft by a discrete dot matrix, and determining the coordinate of each discrete point of the discrete dot matrix;
acquiring attribute information of a specific fragment, wherein the attribute information comprises a fragment type and geometric information of a rotor of an engine corresponding to the fragment;
calculating a flying risk angle of the part to be tested according to the attribute information of the fragments, comprising:
determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments;
determining a plurality of direction vectors according to the plurality of discrete points and the rotation central point of the rotor;
calculating an angle of the plurality of direction vectors to a second reference vector, wherein the second reference vector is associated with an axial direction of an engine;
determining the maximum scattering range of the fragments according to the types of the fragments;
determining a flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments;
projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor, and determining the coordinate of each projected point;
determining the direction vectors of the two critical sweep trajectory lines corresponding to each projection point, wherein the direction vectors of the two critical sweep trajectory lines corresponding to each projection point are as follows: the direction vector of the flight trajectory line of the fragments flies out along the tangential direction of the rotation trajectory line of the gravity center of the fragments and the edges of the fragments are in contact with the projection point; calculating the translational risk angle of the component to be detected according to the direction vector of each critical sweep trajectory line and the first reference vector, wherein the method comprises the following steps: calculating angle values of direction vectors of the two critical sweeping track lines corresponding to the projection point along the clockwise rotation of the first reference vector respectively, and calculating a translational risk angle of the component to be measured according to the angle values;
and calculating the probability of the part to be tested being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
2. The method of claim 1, further comprising:
and respectively calculating and summarizing the probability that the part to be detected is damaged by fragments of rotors of all stages of the engine.
3. An aircraft engine non-containment rotor explosion risk calculation system, comprising:
the discretization processing module is used for representing the geometric appearance of the part to be measured of the aircraft by a discretization lattice and determining the coordinate of each discrete point of the discretization lattice;
the system comprises a fragment attribute information acquisition module, a fragment attribute information acquisition module and a fragment identification module, wherein the fragment attribute information acquisition module is used for acquiring attribute information of a specific fragment, and the attribute information comprises a fragment type and geometric information of a rotor of an engine corresponding to the fragment;
the flying risk angle calculation module is used for calculating the flying risk angle of the component to be detected according to the attribute information of the fragments; the fly-away risk angle calculation module is further to: determining coordinates of a rotation center point of a rotor of the engine corresponding to the fragments; determining a plurality of direction vectors according to the plurality of discrete points and the rotation central point of the rotor; calculating an angle of the plurality of direction vectors to a second reference vector, wherein the second reference vector is associated with an axial direction of an engine; determining the maximum scattering range of the fragments according to the types of the fragments; determining a flying risk angle of the part to be tested according to the angles from the plurality of direction vectors to a second reference vector and the maximum flying range of the fragments;
the projection point coordinate calculation module is used for projecting a plurality of discrete points of the discrete dot matrix to a rotating plane of the rotor and determining the coordinate of each projection point;
the translation risk angle calculation module is used for determining the direction vectors of the two critical swept track lines corresponding to each projection point, and calculating the translation risk angle of the component to be measured according to the direction vector of each critical swept track line and the first reference vector; the direction vectors of the two critical sweep trajectory lines corresponding to each projection point are as follows: the direction vector of the flight trajectory line of the fragments flies out along the tangential direction of the rotation trajectory line of the gravity center of the fragments when the edges of the fragments are in contact with the projection points; the translational risk angle calculation module is further configured to: calculating angle values of direction vectors of the two critical sweeping track lines corresponding to the projection point along the clockwise rotation of the first reference vector respectively, and calculating a translational risk angle of the component to be measured according to the angle values;
and the first probability calculation module is used for calculating the probability of the part to be tested being damaged by the rotor blasting fragments according to the flying risk angle and the translational risk angle.
4. The system of claim 3, further comprising:
and the second probability calculation module is used for respectively calculating and summarizing the probability that the part to be detected is damaged by fragments of rotors at all levels of the engine.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006249999A (en) * | 2005-03-09 | 2006-09-21 | Takashi Uchida | Translational vane machine |
| CN102609557A (en) * | 2011-11-11 | 2012-07-25 | 南京航空航天大学 | Safety analysis method for uncontained failure of aircraft engine rotors |
| CN102722598A (en) * | 2012-04-24 | 2012-10-10 | 南京航空航天大学 | Incompatible failure safety analysis system and method for air plane motor |
-
2018
- 2018-12-14 CN CN201811530072.1A patent/CN111324928B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006249999A (en) * | 2005-03-09 | 2006-09-21 | Takashi Uchida | Translational vane machine |
| CN102609557A (en) * | 2011-11-11 | 2012-07-25 | 南京航空航天大学 | Safety analysis method for uncontained failure of aircraft engine rotors |
| CN102722598A (en) * | 2012-04-24 | 2012-10-10 | 南京航空航天大学 | Incompatible failure safety analysis system and method for air plane motor |
Non-Patent Citations (2)
| Title |
|---|
| Fuzzy fault tree analysis of uncontained event of an areo-engine rotor;Yanfeng Li等;《IEEE Xplore》;20120723;第156-160页 * |
| 减小飞机发动机转子***危害的设计方法初探;王勤超;《科技信息》;20130731(第20期);第390-392页 * |
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