CN115828473B - Airborne store wall thickness calculation method and system with multiple physical parameters as targets - Google Patents
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Abstract
The invention relates to the technical field of structural component testing in intelligent manufacturing, and discloses an airborne store wall thickness calculation method and system with multiple physical parameters as targets, so as to simplify a data processing process and ensure that the multiple physical parameters meet requirements simultaneously. The method comprises the following steps: establishing a three-dimensional coordinate system by taking the important focus direction of the moment of inertia as a Y axis; respectively disposing a first fan-shaped annular wall thickness structure and a second fan-shaped annular wall thickness structure with symmetry axes parallel to the X axis in the positive and negative directions of the X axis; respectively disposing third and fourth annular wall thickness structures with symmetry axes parallel to the Z axis in the positive and negative directions of the Z axis; in the positive direction of the Y axis, a first, a second and a third annular wall thickness structures which are symmetrical in the Y axis and are respectively arranged at the front, the middle and the back are respectively arranged; the four fan-shaped annular wall thickness structures and the three annular wall thickness structures have symmetry, and when the size parameters of each component are adjusted, the mass center can be changed on a symmetry axis and can form a quantitative relation with the size parameters; thereby simplifying the data processing process of solving.
Description
Technical Field
The invention relates to the technical field of structural component testing in intelligent manufacturing, in particular to an airborne store wall thickness calculation method and system with multiple physical parameters as targets.
Background
When delivering, accepting or training a pilot, the aircraft often needs to mount various airborne stores to simulate the aerodynamic shape, weight distribution and loading conditions of the aircraft when actually mounting various airborne equipment (such as civil fire-extinguishing bombs, rescue capsules and the like). Thus, the aerodynamic shape, mass, centroid and moment of inertia of the on-board stores for the metrology are generally consistent with subsequent real on-board equipment and also ensure longer fly life. In the process, the airborne stores for the counterweight omit the electrical structure in the real airborne equipment, simplify the internal space, restore the flying environment of the real airborne equipment through the wall thickness design, ensure the flying life and reduce the potential safety hazard and the economic cost brought by the real airborne equipment.
In the structural design stage of the airborne external mass for the counterweight, the mass center position and the rotational inertia of the airborne external mass are usually required to be adjusted, so that the mass, the mass center and the real airborne equipment are kept consistent, and the rotational inertia is similar to that of the corresponding airborne equipment. Currently, the adjustment of the mass, mass center and moment of inertia of the airborne stores (the airborne stores described in the present invention, unless specified otherwise, refer to weight stores for simulating real airborne equipment, and are not described in detail later) is usually achieved by adjusting wall thickness dimension parameters. The traditional wall thickness dimension parameter is obtained by repeated iterative debugging according to the requirements of mass, mass center and rotational inertia. However, iterative debugging processes are easy to take into account, which makes it difficult for the final result to meet the requirements of multiple physical parameters simultaneously.
Disclosure of Invention
The invention aims to disclose an airborne store wall thickness calculation method and system with multiple physical parameters as targets, so as to simplify the data processing process and ensure that the multiple physical parameters meet the requirements at the same time.
In order to achieve the above purpose, the invention discloses a method for calculating the wall thickness of an airborne store with multiple physical parameters as targets, which comprises the following steps:
and establishing a three-dimensional coordinate system by taking the important focus direction of the moment of inertia as a Y axis, wherein the three-dimensional coordinate system takes the end point of the head of the airborne store as an origin, the axial direction is the Y axis, and the radial directions are an X axis and a Z axis respectively.
And respectively arranging a first fan-shaped annular wall thickness structure and a second fan-shaped annular wall thickness structure, wherein the symmetry axis of the first fan-shaped annular wall thickness structure is parallel to the X axis, each section perpendicular to the Y axis in the first fan-shaped annular wall thickness structure is the fan ring with the first dimension specification, and each section perpendicular to the Y axis in the second fan-shaped annular wall thickness structure is the fan ring with the second dimension specification.
And respectively arranging a third fan-shaped annular wall thickness structure and a fourth fan-shaped annular wall thickness structure, wherein the symmetry axis of the third fan-shaped annular wall thickness structure is parallel to the Z axis, each section perpendicular to the Y axis in the third fan-shaped annular wall thickness structure is a fan ring with a third dimension specification, and each section perpendicular to the Y axis in the fourth fan-shaped annular wall thickness structure is a fan ring with a fourth dimension specification.
In the positive direction of the Y axis, a first annular wall thickness structure, a second annular wall thickness structure and a third annular wall thickness structure which are symmetrical in the Y axis and are respectively arranged at the front, middle and back of the Y axis are respectively arranged; each section perpendicular to the Y axis in the first annular wall thickness structure is a ring with a first dimension, each section perpendicular to the Y axis in the second annular wall thickness structure is a ring with a second dimension, and each section perpendicular to the Y axis in the third annular wall thickness structure is a ring with a third dimension.
And constructing a balance equation of mass and mass center based on moment balance and mass balance according to known basic parameters of the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure, and obtaining solving results corresponding to parameters to be solved of the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure respectively.
And constructing a balance equation of mass and mass center based on moment balance and mass balance according to known basic parameters of the third fan annular wall thickness structure and the fourth fan annular wall thickness structure, and obtaining solving results respectively corresponding to parameters to be solved of the third fan annular wall thickness structure and the fourth fan annular wall thickness structure.
And calculating Y-axis rotational inertia of the first fan-shaped annular wall thickness structure, the second fan-shaped annular wall thickness structure, the third fan-shaped annular wall thickness structure and the fourth fan-shaped annular wall thickness structure according to solving results respectively corresponding to parameters to be solved of the four fan-shaped annular wall thickness structures.
And establishing balance equations of mass, centroid and moment of inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and moment of inertia balance, and solving results respectively corresponding to parameters to be solved of the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure according to Y-axis moment of inertia and other known basic parameters of the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure.
In the present invention, preferably, the known basic parameters include: profile related data of the pylon, properties of the counterweight material, target values consisting of overall mass, X-axis centroid position, Y-axis centroid position and Z-axis centroid position and Y-axis moment of inertia; the four fan-shaped annular wall thickness structures and the three annular wall thickness structures respectively correspond to material density and deployed coordinate information; the parameters to be solved include: the first to fourth fan-shaped wall thickness structures and the first to third annular wall thickness structures respectively correspond to the inner ring radiuses.
Preferably, the method specifically comprises the following steps:
and constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining the inner circle radius corresponding to the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure according to the target mass center position of the X axis, the known outer circle radius of the fan-shaped annular wall thickness structure corresponding to the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure respectively and other known basic parameters.
And constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining the inner circle radius corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure according to the target mass center position of the Z axis, the known outer circle radius of the fan annular wall thickness structure corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure respectively and other known basic parameters.
Calculating Y-axis moment of inertia of the first, second, third and fourth fan-ring wall thickness structures of the determined dimensions.
And establishing balance equations of mass, centroid and moment of inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and moment of inertia balance, and solving inner circle radiuses corresponding to the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure respectively according to Y-axis moment of inertia of the first circular wall thickness structure, the second circular wall thickness structure and the fourth circular wall thickness structure, respectively known outer circle radiuses of the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure and other known basic parameters.
The invention also discloses an airborne store wall thickness calculation system aiming at multiple physical parameters, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor realizes the method when executing the computer program.
The invention has the following beneficial effects:
based on the invention, the four fan-shaped annular wall thickness structures and the three annular wall thickness structures have symmetry, when the size parameters of each component are adjusted, the mass center can change on the symmetry axis, and the size parameters form a quantitative relation; thereby simplifying the solved data processing process; at the same time, the centroid will vary on the symmetry axis and will be quantitatively related to the dimensional parameters; the wall thickness meeting a plurality of physical parameters can be solved by constructing equations of mass, mass center, rotational inertia and size parameters of each component. In the solving process, firstly determining parameters solved by the four fan-shaped annular wall thickness structures, then calculating the rotational inertia generated by the four fan-shaped annular wall thickness structures on the Y axis, and enabling the solving result of the three annular wall thickness structures to simultaneously meet the target requirements common to the quality, the quality and the rotational inertia in a logically reasonable sequence without carrying out secondary iteration on the determined parameters solved by the four fan-shaped annular wall thickness structures; the design of the wall thickness of each component can be completed once.
According to the method and the system disclosed by the invention, the hanging environment of the real airborne equipment is restored through the wall thickness design, the hanging service life is ensured, and the potential safety hazard and the economic cost brought by the real airborne equipment are reduced.
Meanwhile, as a special example of the invention, one or two of the three annular wall thickness structures can be regarded as zero treatment, or single or multiple annular wall thickness structures are further decomposed into a corresponding number of substructures, so that the invention has good expansibility.
Further, in the practice of the present invention, the required wall thickness parameters may be solved based on different basic parameters known in different scenarios, such as: the inner diameter of each component can be solved by knowing the outer diameter, material parameters and position information of each structure; the material with the density meeting the requirement can also be screened by knowing the inner diameter and the outer diameter; such variations will readily occur to those skilled in the art, thereby also providing the present invention with great flexibility.
The invention will be described in further detail with reference to the accompanying drawings.
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 specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a front three-axis view of various components for adjusting wall thickness in accordance with an embodiment of the present invention.
Fig. 2 is a schematic diagram of centroid calculation of fan-shaped wall thickness according to an embodiment of the present invention.
Fig. 3 is a front view and a left view of a circular wall thickness according to an embodiment of the present invention.
Fig. 4 is a schematic diagram of calculation for adding a balancing weight on the basis of the existing product according to the embodiment of the invention.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawings, but the invention can be implemented in a number of different ways, which are defined and covered by the claims.
Example 1
The purpose of this embodiment is to provide a fast, reliable and accurate calculation method for the wall thickness of the on-board pylon targeting the moment of inertia in the mass, centroid (X/Y/Z axis) and the direction of important interest (e.g. Y axis).
As shown in FIG. 1, the present embodiment is used for calculating wall thicknessMainly comprises X 1 ，X 2 ，Y 1 ，Y 2 ，Y 3 ，Z 1 And Z 2 . The method specifically comprises the following steps:
and establishing a three-dimensional coordinate system by taking the important focus direction of the moment of inertia as a Y axis, wherein the three-dimensional coordinate system takes the end point of the head of the tubular airborne store as an origin, the axial direction is the Y axis, and the radial directions are an X axis and a Z axis respectively. The tubular airborne stores, that is, the airborne stores whose internal space can be configured as a tubular shape at least in part, are mostly not limited by specific external physical characteristics during specific application.
Then, in the positive and negative directions of the X axis, respectively disposing a first fan-shaped annular wall thickness structure X with the symmetry axis parallel to the X axis 1 And a second fan annular wall thickness structure X 2 The sections perpendicular to the Y axis in the first fan-shaped wall thickness structure are the fan rings with the first dimension, and the sections perpendicular to the Y axis in the second fan-shaped wall thickness structure are the fan rings with the second dimension.
In the positive and negative directions of the Z axis, third fan-shaped annular wall thickness structures Z with symmetry axes parallel to the Z axis are respectively arranged 1 And a fourth fan annular wall thickness structure Z 2 And each section of the third fan-shaped annular wall thickness structure perpendicular to the Y axis is the fan ring with the third dimension specification, and each section of the fourth fan-shaped annular wall thickness structure perpendicular to the Y axis is the fan ring with the fourth dimension specification.
In the positive direction of the Y axis, first circular wall thickness structures Y which are symmetrical with the Y axis and are respectively arranged at the front, the middle and the back are respectively arranged 1 Second circular wall thickness structure Y 2 And a third annular wall thickness structure Y 3 The method comprises the steps of carrying out a first treatment on the surface of the All sections perpendicular to the Y axis in the first annular wall thickness structure are circular rings of a first size specification, all sections perpendicular to the Y axis in the second annular wall thickness structure are circular rings of a second size specification, and all sections perpendicular to the Y axis in the third annular wall thickness structure are circular rings of a third size specification. Typically, in the front, middle, and rear profiles, at least one of the three annular wall thickness structures has a Y-axis centroid with a coordinate less than the Y-axis target centroid and at least one of the three annular wall thickness structures has a Y-axis centroid with a coordinate greater than the Y-axis target centroid.
Whereby X is 1 And X 2 Is an axisymmetric structure with the symmetry axis parallel to the X-axis direction, and the centroids are respectively positioned on the symmetry axes. Similarly, Z 1 And Z 2 Is also an axisymmetric structure with the symmetry axis parallel to the Z-axis direction, and the centroids are respectively positioned on the symmetry axes. Therefore, when the size parameter of the wall thickness of the fan ring is adjusted, the centroid position only falls on the symmetrical point, and the size parameter are in quantitative relation.
As shown in FIG. 2, in a second fan-shaped annular wall thickness structure X 2 For example, wherein the U-axis is the symmetry axis; based on the prime method, its mass and centroid (X-axis) can be expressed as:
wherein θ 2 X represents 2 The angle of the fan-shaped wall thickness corresponding to the structure,
x represents 2 Density corresponding to structure, < >>
X represents 2 The outer circle radius corresponding to the structure +.>
X represents 2 The radius of the inner circle corresponding to the structure L 2 X represents 2 The length corresponding to the structure.
As can be seen from formulas (1) and (2), X 2 The mass and centroid (X-axis) of the fan wall thickness are related to the outer/inner ring radius, fan angle and length. By analogy, the dimensional parameters of a fan-ring wall thickness structure (outer/inner ring radius, fan angle and length) symmetrical along an axis parallel to the X or Z direction are quantitatively related to its mass and centroid (X axis).
Y 1 ，Y 2 ，Y 3 Is a circular wall thickness structure symmetrical about the Y-axis as shown in fig. 3. Thus, when the outer/inner radius is changed, the centroid position of the annular wall thickness will only change on the symmetry axis, the magnitude of which is quantitatively related to the dimensional parameter. Based on the face element method, Y 1 The mass and moment of inertia (Y-axis) of (a) can be expressed as:
wherein, the liquid crystal display device comprises a liquid crystal display device,
is Y 1 Density of annular wall thickness corresponding to structure, R 3 Is Y 1 The outer circle radius corresponding to the structure, r 3 Is Y 1 The radius of the inner circle corresponding to the structure L 3 Is Y 1 The length corresponding to the structure.
As can be seen from formulas (3) and (4), Y 1 The mass and moment of inertia (Y-axis) of the fan wall thickness are both equal to the outer/inner ring radius (R 3 ，r 3 ) Length (L) 3 ) Related to the following. By analogy, the dimensional parameters (outer/inner ring radius and length) of the annular wall thickness structure with the Y-axis as the symmetry axis have quantitative relation with the mass and the rotational inertia (Y-axis).
According to the above formulas (1), (2), (3) and (4), the present invention builds X based on the moment balance, mass balance and moment of inertia (Y axis) balance of the X/Y/Z axis 1 ，X 2 ，Y 1 ，Y 2 ，Y 3 ，Z 1 And Z 2 Relationship between dimensional parameters and product design mass, centroid (X/Y/Z axis) and moment of inertia (Y axis).
Due to the wall thickness X of the fan ring 1 ，X 2 ，Z 1 And Z 2 The centroid (Y axis) of (C) is not zero, so the design mass and centroid based on X and Z axes are needed to be respectively carried out on X 1 ，X 2 ，Z 1 And Z 2 Designing the size; then, consider X comprehensively 1 ，X 2 ，Z 1 And Z 2 Mass and moment of inertia (Y axis) of (a) for Y 1 ，Y 2 And Y 3 The dimensions are designed. Wherein, the product design quality, mass center (X axis) and X 1 ，X 2 The equilibrium equation for the dimensional parameters can be expressed as:
wherein M is Total (S) X is the total design quality x For designing the mass center position on the X axis, M is the initial mass (in special cases, M can be 0, namely the method of the embodiment is not only suitable for the design of adding the balancing weight on the basis of the existing product, and can refer to FIG. 4, but also can be designed from zero), X is the initial mass center position on the X axis,
respectively X 1 And X 2 Mass of fan-shaped annular wall thickness structure->
Respectively X 1 And X 2 Centroid position of the fan-shaped annular wall thickness structure; r is R 1 、R 2 Respectively X 1 And X 2 Outer circle radius of fan-shaped wall thickness structure +.>
Represented as X 1 And X 2 The same density, theta, used for the fan-shaped annular wall thickness structure 1 、θ 2 Respectively X 1 And X 2 Angle of fan annular interface of fan annular wall thickness structure, M x Is the design quality of the X axis.
Product design quality and centroid (Z axis) and Z 1 ，Z 2 The equilibrium equation for the dimensional parameters can be expressed as:
wherein Z is z Expressed as the designed centroid position in the Z-axis direction, Z represents the initial centroid position in the Z-axisThe device is arranged in the way that the device is arranged,
respectively represent Z 1 And Z 2 Mass of fan-shaped annular wall thickness structure->
Respectively represent Z 1 And Z 2 Centroid position of fan-shaped annular wall thickness structure, R 6 、R 7 Respectively represent Z 1 And Z 2 Outer circle radius of fan-shaped wall thickness structure +.>
Respectively indicate->
And->
Inner circle radius of fan-shaped annular wall thickness structure, L 6 、L 7 Respectively represent Z 1 And Z 2 Length of fan-shaped wall thickness structure->
Denoted as Z 1 And Z 2 The same density, theta, used for the fan-shaped annular wall thickness structure 6 、θ 7 Respectively represent Z 1 And Z 2 Angle of sector ring section, M z Expressed as the design quality of the Z-axis.
Product design mass, centroid, moment of inertia (Y-axis) and Y 1 ，Y 2 ，Y 3 The equilibrium equation for the dimensional parameters can be expressed as:
wherein Y is y Expressed as Y-axis design centroid position, Y represents initial centroid position of Y-axis, Y x Represented as X 1 And X 2 The centroid position of the total fan-shaped annular wall thickness structure on the Y axis after the addition, yz represents Z 1 And Z 2 The total fan-shaped wall thickness structure after the addition is YThe centroid position of the shaft,
、/>
、/>
respectively is Y 1 、Y 2 、Y 3 The circular wall thickness structure is at the centroid position of the Y axis, R 3 、R 4 、R 5 Respectively is Y 1 、Y 2 、Y 3 Outer circle radius of circular wall thickness structure +.>
Respectively is Y 1 、Y 2 、Y 3 Inner circle radius of circular wall thickness structure, L 3 、L 4 、L 5 Respectively is Y 1 、Y 2 、Y 3 Length of annular wall thickness structure->
Denoted as Y 1 、Y 2 、Y 3 The same density adopted by the circular wall thickness structure is J is the initial moment of inertia of the Y axis, J x Is X 1 And X 2 The total moment of inertia, J, acting on the Y-axis after the fan-ring wall thickness structures are added up z Is Z 1 And Z 2 The total moment of inertia, M, of the Y-axis is acted on after the fan-shaped annular wall thickness structures are added up y Is the design quality of the Y axis.
Wherein, the design quality of the whole product can be expressed as:
in conclusion, the dimensional parameters and the mass of the fan-shaped wall thickness structure and the circular wall thickness structure, the mass center and the rotational inertia have quantitative relations, and the mass center positions of the fan-shaped wall thickness structure and the circular wall thickness structure are respectively positioned on the symmetry axis. When the structural size parameter of the circular wall thickness is regulated, the centroid position only falls on the Y axis, and the size parameter form a quantitative relation; the centroid position will only change on the symmetry axis when the dimensional parameters of the fan-shaped annular wall thickness structure are adjusted. With these characteristics, the present embodiment can execute the following steps according to the above formula:
and S10, constructing a balance equation of mass and mass center based on moment balance and mass balance according to known basic parameters of the first fan-shaped wall thickness structure and the second fan-shaped wall thickness structure, and obtaining solving results corresponding to parameters to be solved of the first fan-shaped wall thickness structure and the second fan-shaped wall thickness structure respectively. Specific examples are: and constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining the inner circle radius corresponding to the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure according to the target mass center position of the X axis, the known outer circle radius of the fan-shaped annular wall thickness structure corresponding to the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure respectively and other known basic parameters.
And S20, constructing a balance equation of mass and mass center based on moment balance and mass balance according to known basic parameters of the third annular wall thickness structure and the fourth annular wall thickness structure, and obtaining solving results respectively corresponding to parameters to be solved of the third annular wall thickness structure and the fourth annular wall thickness structure. Specific examples are: and constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining the inner circle radius corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure according to the target mass center position of the Z axis, the known outer circle radius of the fan annular wall thickness structure corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure respectively and other known basic parameters.
And S30, calculating Y-axis rotational inertia of the first fan-shaped wall thickness structure, the second fan-shaped wall thickness structure, the third fan-shaped wall thickness structure and the fourth fan-shaped wall thickness structure according to solving results respectively corresponding to parameters to be solved of the four fan-shaped wall thickness structures.
And S40, constructing balance equations of mass, centroid and rotational inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and rotational inertia balance, and solving the solving results of the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure according to the Y-axis rotational inertia of the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure and other known basic parameters.
This step may specifically be, for example: and establishing balance equations of mass, centroid and moment of inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and moment of inertia balance, and solving inner circle radiuses corresponding to the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure respectively according to Y-axis moment of inertia of the first circular wall thickness structure, the second circular wall thickness structure and the fourth circular wall thickness structure, respectively known outer circle radiuses of the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure and other known basic parameters.
The above process is further described in connection with one embodiment as follows:
assuming the mass, centroid (X/Y/Z axis) and moment of inertia in the direction of interest (e.g., Y axis) of a given on-board plug-in product design requirement are:
M total (S) =7060kg，X x =2mm，Y y =4600 mm (from head position), Z z =3mm。
J y = 969000000kg·m 2
The known basic parameters of the circular ring shape, the fan-shaped wall thickness and the product are respectively as follows:
the specific invention comprises the following steps:
firstly, carrying out mass distribution on the fan-shaped wall thickness and the circular wall thickness according to the design quality:
M xyz =658.939kg， M x =56kg，M y = 402.939 kg，M z =200kg
secondly, according to the design quality of the X axis of the product, the mass center and X 1 ，X 2 Inner circle radius (r) 1 ，r 2 ) To find X 1 And X 2 Is defined by the inner radius of:
r 1 =360.997mm, r 2 =332.887mm
again according to the design quality of the Z axis of the product, the mass center and Z 1 ，Z 2 Inner circle radius (r) 6 ，r 7 ) To find Z 1 And Z 2 Is defined by the inner radius of:
r 6 =322.105mm，r 7 =261.762mm
then according to calculation and measurement, obtaining fan-shaped wall thickness X 1 ，X 2 ，Z 1 And Z 2 The Y-axis moment of inertia of (c):
J x =7506698.136 kg·m 2 ，J z = 13852536.443 kg·m 2
finally, according to the design mass, mass center, rotational inertia and Y of the Y axis of the product 1 ，Y 2 ，Y 3 Inner circle radius (r) 3 ，r 4 ，r 5 ) To find Y 1 ，Y 2 ，Y 3 Is defined by the inner radius of:
r 3 =339.120mm，r 4 =353.710mm，r 5 =116.809mm
the mass, mass center (X/Y/Z axis) and rotational inertia (Y axis) of the designed product are measured as follows:
M total (S) =7060kg，X x =1.97mm，Y y =4599.9mm，Z z =3.007mm，J= 968998941 kg·m 2
The measurement result is basically consistent with parameters required by product design, which means that the method of the embodiment realizes quick, reliable and accurate calculation of the wall thickness of the airborne store by comprehensively considering the quality, the mass center (X/Y/Z axis) and the moment of inertia (Y axis) of the product. The calculated product can be used for actual measurement for further verification.
Example 2
Corresponding to embodiment 1 above, this embodiment discloses an airborne store wall thickness calculation system targeting multiple physical parameters, including a memory, a processor, and a computer program stored on the memory and executable on the processor, which when executed implements the method described above.
In summary, according to the above embodiment of the present invention, the four fan-shaped annular wall thickness structures and the three annular wall thickness structures have symmetry, and when the dimensional parameters of each component are adjusted, the centroid will change on the symmetry axis and will have a quantitative relationship with the dimensional parameters; thereby simplifying the solved data processing process; at the same time, the centroid will vary on the symmetry axis and will be quantitatively related to the dimensional parameters; the wall thickness meeting a plurality of physical parameters can be solved by constructing equations of mass, mass center, rotational inertia and size parameters of each component. In the solving process, firstly determining parameters solved by the four fan-shaped annular wall thickness structures, then calculating the rotational inertia generated by the four fan-shaped annular wall thickness structures on the Y axis, and enabling the solving result of the three annular wall thickness structures to simultaneously meet the target requirements common to the quality, the quality and the rotational inertia in a logically reasonable sequence without carrying out secondary iteration on the determined parameters solved by the four fan-shaped annular wall thickness structures; the design of the wall thickness of each component can be completed once.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. An airborne store wall thickness calculation method with multiple physical parameters as targets is characterized by comprising the following steps:
establishing a three-dimensional coordinate system by taking a rotational inertia focus attention direction as a Y axis, wherein the three-dimensional coordinate system takes a tubular airborne store head end point as an origin, the axial direction is the Y axis, and the radial direction is an X axis and a Z axis respectively;
respectively disposing a first fan-shaped annular wall thickness structure and a second fan-shaped annular wall thickness structure, wherein the symmetry axis of the first fan-shaped annular wall thickness structure is parallel to the X axis, each section perpendicular to the Y axis in the first fan-shaped annular wall thickness structure is a fan ring with a first dimension specification, and each section perpendicular to the Y axis in the second fan-shaped annular wall thickness structure is a fan ring with a second dimension specification;
respectively disposing a third fan-shaped annular wall thickness structure and a fourth fan-shaped annular wall thickness structure, wherein the symmetry axis of the third fan-shaped annular wall thickness structure is parallel to the Z axis, each section perpendicular to the Y axis in the third fan-shaped annular wall thickness structure is a fan ring with a third dimension specification, and each section perpendicular to the Y axis in the fourth fan-shaped annular wall thickness structure is a fan ring with a fourth dimension specification;
in the positive direction of the Y axis, a first annular wall thickness structure, a second annular wall thickness structure and a third annular wall thickness structure which are symmetrical in the Y axis and are respectively arranged at the front, middle and back of the Y axis are respectively arranged; each section perpendicular to the Y axis in the first annular wall thickness structure is a circular ring with a first dimension, each section perpendicular to the Y axis in the second annular wall thickness structure is a circular ring with a second dimension, and each section perpendicular to the Y axis in the third annular wall thickness structure is a circular ring with a third dimension;
according to the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure, constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining solving results corresponding to parameters to be solved of the first fan-shaped annular wall thickness structure and the second fan-shaped annular wall thickness structure respectively;
according to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure, constructing a balance equation of mass and mass center based on moment balance and mass balance, and obtaining solving results corresponding to parameters to be solved of the third fan annular wall thickness structure and the fourth fan annular wall thickness structure respectively;
calculating Y-axis rotational inertia of the first fan-shaped annular wall thickness structure, the second fan-shaped annular wall thickness structure, the third fan-shaped annular wall thickness structure and the fourth fan-shaped annular wall thickness structure according to solving results respectively corresponding to parameters to be solved of the four fan-shaped annular wall thickness structures;
establishing balance equations of mass, centroid and moment of inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and moment of inertia balance, and solving results respectively corresponding to parameters to be solved of the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure according to Y-axis moment of inertia of the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure;
the above solution results specifically include:
setting up a balance equation of mass and mass center based on moment balance and mass balance, and obtaining inner circle radiuses respectively corresponding to the first fan-shaped wall thickness structure and the second fan-shaped wall thickness structure according to a target mass center position of an X axis and known outer circle radiuses of the fan-shaped ring structures respectively corresponding to the first fan-shaped ring thickness structure and the second fan-shaped ring thickness structure;
setting up a balance equation of mass and mass center based on moment balance and mass balance, and obtaining inner circle radiuses respectively corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure according to a target mass center position of a Z axis and known outer circle radiuses of the fan annular wall thickness structures respectively corresponding to the third fan annular wall thickness structure and the fourth fan annular wall thickness structure;
calculating Y-axis moment of inertia of the first, second, third, and fourth fan-ring wall thickness structures of the determined dimensions;
and establishing balance equations of mass, mass center and rotational inertia related to the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure based on moment balance, mass balance and rotational inertia balance, and solving inner circle radiuses corresponding to the first circular wall thickness structure, the second circular wall thickness structure, the third circular wall thickness structure and the fourth circular wall thickness structure respectively according to Y-axis rotational inertia of the first circular wall thickness structure, the second circular wall thickness structure and the fourth circular wall thickness structure and the known outer circle radiuses of the first circular wall thickness structure, the second circular wall thickness structure and the third circular wall thickness structure respectively.
2. The method of on-board pylon wall thickness calculation for multiple physical parameters according to claim 1, further comprising:
and determining the mass, mass center and rotational inertia of the final product according to the inner ring radius calculated by the four fan-shaped annular wall thickness structures and the three annular wall thickness structures respectively.
3. The method of on-board pylon wall thickness calculation targeting multiple physical parameters according to any one of claims 1 to 2, wherein the basic structural parameters include: profile related data of the pylon, properties of the counterweight material, target values consisting of overall mass, X-axis centroid position, Y-axis centroid position and Z-axis centroid position and Y-axis moment of inertia; and material density and deployment coordinate information corresponding to the four fan-shaped annular wall thickness structures and the three annular wall thickness structures respectively.
4. An on-board store wall thickness calculation system targeting multiple physical parameters, comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the method of any of the preceding claims 1 to 3 when executing the computer program.
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