CN112906142B - Design and processing method suitable for extremely light mass putting model - Google Patents
Design and processing method suitable for extremely light mass putting model Download PDFInfo
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Abstract
The invention belongs to a design and processing method suitable for an extremely light mass putting model, which is characterized in that the flow sequence of the whole method is a design module, a component additive manufacturing and component assembling, wherein the design module comprises two subprograms of a mass characteristic calculation module and a mass characteristic design module, the mass characteristic calculation module calculates the weight, the gravity center and the rotational inertia of the model according to the model scaling ratio and the power similarity criterion, and takes the calculated weight, the gravity center and the rotational inertia as target parameters of the mass characteristic design module, and the core idea of the mass characteristic calculation module is as follows: the middle of the solid model is hollowed to form a shell, the hollowed part is continuous, the requirement of the basic thickness of the shell needs to be guaranteed, and the shape of the shell is not limited. And adopting a means of placing a filling part in the hollow part, and adopting a self-adaptive program to iteratively solve the outline shapes of the hollow part and the filling part, thereby configuring the weight, the gravity center and the rotational inertia of the model so as to meet the requirement of a design target.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a design and processing method suitable for an extremely light weight delivery model.
Background
When external objects such as an auxiliary fuel tank, a missile, a bomb, a meteorological detector, an air transportation material and the like are thrown from the aircraft, the external objects are positioned in an aircraft interference flow field at the initial stage of separating from the aircraft, and the characteristics of the interference flow field are closely related to factors such as the appearance of the aircraft, the flight speed of the aircraft, the flight height of the aircraft, the attitude of the aircraft, the appearance of the external objects, the installation position and the attitude of the external objects on the aircraft, the initial throwing speed and the like. Therefore, the motion trail and the posture of the throwing object at the initial moment of leaving the carrier are difficult to accurately obtain by a theoretical or simulation calculation method. In order to know the motion track and the posture of the thrown object at the initial throwing stage, the throwing wind tunnel test is generally needed to judge the throwing safety problem at the initial throwing moment. The external hanging object throwing wind tunnel test mainly comprises four methods: the dynamic similarity method is most widely applied due to the reasons that a test result is well matched with a real situation, the influence of interference is less, the servo mechanism is not limited and the like. The dynamic similarity method comprises the steps of generally reducing a carrier and a throwing object according to a certain proportion according to wind tunnel expansion limit and wind tunnel blockage limit, keeping a model and a real object to be geometrically similar, considering the influence of a gravity field under a certain speed or Mach number, obtaining a dynamic similarity criterion between the throwing model and the real object, designing and processing the throwing model according to the geometric similarity criterion and the dynamic similarity criterion, throwing the throwing object model in a test, and recording the motion track and the posture of the throwing model in the test by adopting a high-speed camera or multiple exposure photography.
The design and processing of the throwing model in the dynamic similarity method ensure that the geometric appearance, weight, gravity center and rotational inertia of the throwing model and a real object meet the geometric similarity and dynamic similarity criteria. At present, the design and processing method of the throwing model uses design software such as CATIA, SolidWorks and the like, hollows the middle of a throwing model entity, keeps a shell of the throwing model, places small blocks with different materials and regular shapes on the hollow part in the middle, and manually adjusts the weight, the gravity center and the rotational inertia of the throwing model, so that the quality characteristic of the designed model meets the requirements of the test. In the processing process, the quality characteristic configuration and the verification need to be manually carried out, and the test requirements can be met through multiple rounds of iteration. When the model shell is processed, the model shell is processed by a conventional material reducing manufacturing mode, and then the position and the size of the small block are adjusted by a master worker in the shell, so that the test requirements are met. The whole design and processing process is time-consuming and labor-consuming, generally, one state design of the release model needs several days or even longer time, and the time for designing and processing the whole release model can be as long as several months. The model design and the processing quality are greatly influenced by the experience of operators, and the quality control is unstable. The method is only suitable for the throwing model with relatively large mass, and is not suitable for the throwing model with extremely light mass after scaling.
Disclosure of Invention
In order to make up for the technical blank that the design and the processing of the ultra-light mass putting model cannot be realized in the prior art, the invention provides a method suitable for the design and the processing of the ultra-light mass putting model, and the smooth operation of the ultra-light mass putting model test is ensured. The design method is suitable for designing and processing all mass input models, and is particularly suitable for designing and processing extremely light mass input models. The design realizes the full automated design of computer, and the design quality is high, and stability is good, and the design efficiency is high, can practice thrift a large amount of human costs. The processing adopts the additive manufacturing technology, the processing and the forming of parts with irregular shapes can be easily realized regardless of the shapes of the machined parts, the design method is effectively served, and the assembly of the parts is simple and quick.
A design and processing method suitable for an extremely light weight delivery model is characterized by comprising the following steps of design and processing, and is characterized by comprising the following modules: the design method comprises the following steps of:
(1) firstly, partitioning the component, defining a model entity without any operation as a solid component, defining a cut-out part as a hollow component, and defining a filling part as a filling component;
(2) then, respectively describing the cross-sectional profile and the axial profile of the solid part by using a profile formed by a point Ai and a profile formed by a point a, respectively describing the cross-sectional profile and the axial profile of the hollow part by using a profile formed by a point Bi and a profile formed by a point b, respectively describing the cross-sectional profile and the axial profile of the filling part by using a profile formed by a point Ci and a profile formed by a point c, and respectively describing the cross-sectional profile of each part in the axial direction;
(3) randomly selecting parameters in a density library to assign initial densities to each part;
(4) initial values are given to the section profile and the axial profile of each part, initial weight, gravity center and rotational inertia of the solid part, the hollow part and the filling part are respectively obtained through integral operation according to formulas 1 to 10, and then the initial weight, gravity center and rotational inertia of the model are calculated through addition and subtraction operation according to formulas 11 to 17;
(5) comparing the calculated weight, gravity center and rotary inertia with target parameters, judging whether the calculation result meets the national military standard requirements through formulas 18-24, judging whether profile parameters of each component meet given limits through formulas 25-30, returning to the step 3 to re-assign the values of density, section profile and axial profile along the direction of reducing the residual error if the profile parameters do not meet the given limits, returning to the step 4 to calculate the weight, gravity center and rotary inertia of the component and the model again, and iterating until the calculation result and the profile parameter requirements are completely met, thereby completing the design work;
the processing steps are as follows:
(6) the part additive manufacturing is to process the shell part and the filling part according to the final density, section profile and axial profile result parameters provided by the quality characteristic design module;
(7) the method comprises the steps that material powder with corresponding density is selected, the three-dimensional data of a part drives an additive manufacturing system to stack and adhere the powder, and additive manufacturing of the part is finally completed;
(8) the mold assembly is to combine the shell member and the filling member by a simple adhesion technique, i.e., to complete the assembly of the components.
The formulas 1 to 30 are as follows: v. ofi (solid)∑ a Ai formula (1)
vi (hollowed out)∑ b Bi formula (2)
vi (filling)∑ c Ci formula (3)
m(k)＝∑ρ(k)vi(k)Formula (4)
Gx(k)＝∑ρ(k)vi(k)dxi(k)/∑ρ(k)vi(k)Formula (5)
Gy(k)＝∑ρ(k)vi(k)dyi(k)/∑ρ(k)vi(k)Formula (6)
Gz(k)＝∑ρ(k)vi(k)dzi(k)/∑ρ(k)vi(k)Formula (7)
Ix(k)＝∑ρ(k)vi(k)dxi(k) 2Formula (8)
Iy(k)＝∑ρ(k)vi(k)dyi(k) 2Formula (9)
Iz(k)＝∑ρ(k)vi(k)dzi(k) 2Formula (10)
(where k is solid/hollowed/filled)
m＝m(solid)-m(hollowing out)+m(filling)Formula (11)
Gx＝(m(solid)×Gx(solid)-m(hollowing out)×Gx(hollowing out)+m(filling)×Gx(filling)) /m equation (12)
Gy＝(m(solid)×Gy(solid)-m(hollowing out)×Gy(hollowing out)+m(filling)×Gy(filling)) /m equation (13)
Gz＝(m(solid)×Gz(solid)-m(hollowing out)×Gz(hollowing out)+m(filling)×Gz(filling)) M formula (14)
Ix＝Ix(solid)+m(solid)×(Gx(solid)-Gx)2-Ix(hollowing out)-m(hollowing out)×(Gx(hollowing out)-Gx)2+Ix(filling)+m(filling)×(Gx(filling)-Gx)2
Formula (15)
Iy＝Iy(solid)+m(solid)×(Gy(solid)-Gx)2-Iy(hollowing out)-m(hollowing out)×(Gy(hollowing out)-Gy)2+Iy(filling)+m(filling)×(Gy(filling)-Gy)2
Formula (16)
Iz＝Iz(solid)+m(solid)×(Gz(solid)-Gz)2-Iz(hollowing out)-m(hollowing out)×(Gz(hollowing out)-Gz)2+Iz(filling)+m(filling)×(Gz(filling)-Gz)2
Formula (17)
0.99×mModel (model)≤m≤1.01×mModel (model)Formula (18)
0.99×LxModel (model)≤Gx-GxModel (model)≤LxModel (model)Formula (19)
0.99×LyModel (model)≤Gy-GyModel (model)≤LyModel (model)Formula (20)
0.99×LzModel (model)≤Gz-GzModel (model)≤LzModel (model)Formula (21)
0.95×IxModel (model)≤Ix≤1.05×IxModel (model)Formula (22)
0.95×IyModel (model)≤Iy≤1.05×IyModel (model)Formula (23)
0.95×IzModel (model)≤Iz≤1.05×IxModel (model)Formula (24)
Ai is not less than Bi formula (25)
a is more than or equal to b formula (26)
Formula (27) that Bi is not less than Ci
b is not less than c formula (28)
a-b is more than or equal to the minimum thickness requirement formula (29)
Ai-Bi is more than or equal to the minimum thickness requirement formula (30)
The quality characteristic calculation module: calculating parameters such as weight, gravity center and rotary inertia of the throwing model according to a scaling ratio and a power similarity principle, and taking a calculation result as a design target parameter;
the quality characteristic design module: and hollowing the middle of the solid model to form a shell, wherein the hollow part is continuous and the shape is not limited, and the outline shapes of the hollow part and the filled part are iteratively solved by adopting an optimization search algorithm self-adaptive program by means of placing the filled part in the hollow part, so that the configuration of the weight, the gravity center and the rotational inertia of the model is carried out, and the requirement of a design target is met.
The filling part can adopt substances with different densities, and the filling part is continuous and is not limited in shape.
The optimization algorithm is self-contained in matlab, a corresponding mathematical model is established aiming at the method, and the optimization design is carried out by adopting an optimization search algorithm.
In the mass characteristic calculation module, the configuration values of the weight, the gravity center and the rotary inertia of theoretical requirements calculated according to the scaling ratio and the power similarity principle meet the requirements of GJB 180A-2006 on the weight, the gravity center and the rotary inertia, namely that the mass error of the external object model is not more than 1.0%, the error of the position of the mass center is not more than 1.0% of the characteristic length, and the error of the rotary inertia is not more than 5.0%.
The formulas (1) to (7) are calculation formulas applied to the weight, the center of gravity, and the moment of inertia of the component.
The formulas (8) to (14) are calculation formulas of the model weight, the center of gravity, and the moment of inertia.
The formulas (15) to (21) are designed such that the weight, the center of gravity and the moment of inertia need to meet the requirements of the national military standard.
The formulas (22) to (27) are limitations on profile parameters of the hollow member and the filling member.
The invention has the beneficial effects that:
1. the invention greatly expands the design and processing range of the throwing model, is not only suitable for the design and processing of the conventional mass throwing model, but also suitable for the design and processing of the extremely light mass throwing model, and has the advantages of light mass of the model up to several grams and higher precision.
2. The invention adopts computer full-automatic design and additive manufacturing technology, does not depend on manual configuration and verification of weight, gravity center and rotational inertia of the throwing model, obviously improves design and processing efficiency and saves a large amount of labor cost. The design period and the processing period respectively need at least one month and two months before, and the whole design and processing period can be shortened to about 20 days after the method is adopted, so that the design and processing time is saved.
3. The method adopts an optimization search algorithm, ensures the optimal control of the overall parameters, simultaneously considers the optimal important parameters, effectively ensures the design quality, can meet the national military standard requirements with extremely high quality by applying the model quality characteristics of the design method, and has the advantages of high stability, small individual difference and accurate precision.
4. The invention is based on the additive manufacturing technology, the part processing is not limited to a specific shape, the design limitation requirement is lower, and the flexibility and the simplicity of the design form are powerfully supported.
Drawings
FIG. 1 is a flow chart of the overall process of the present invention;
FIG. 2 is a flow diagram of a mass characteristic calculation module of the present invention;
FIG. 3 is a flow chart of a quality characteristic design module of the present invention;
FIG. 4 is a profile view of a cross section of a model of the present invention. Wherein the cross section of the shell part is described by a contour formed by a point Ai, the cross section of the hollowed part is described by a contour formed by a point Bi, and the cross section of the filled part is described by a contour formed by a point Ci;
FIG. 5 is a profile view of the inventive model along an axis. Wherein the shell member axial profile is described by a profile formed by a point a, the cored-out member axial profile is described by a profile formed by a point b, and the filled-in member axial profile is described by a profile formed by a point c;
FIG. 6 is a symbolic illustration of the present invention.
Detailed Description
The invention is described in detail below with reference to the following figures and formulas:
example 1:
the flow sequence of the whole method is design module-part additive manufacturing-part assembling. The design module comprises two subprograms of a quality characteristic calculation module and a quality characteristic design module.
The mass characteristic calculation module calculates the weight, the gravity center and the rotary inertia of the model according to the scale ratio of the model and the power similarity criterion, and the calculated weight, the gravity center and the rotary inertia are used as target parameters of the mass characteristic design module.
The core idea of the quality characteristic calculation module is as follows: the middle of the solid model is hollowed to form a shell, the hollowed part is continuous, the requirement on the basic thickness of the shell needs to be guaranteed, and the shape of the shell is not limited. And placing a filling part in the hollow part, wherein the filling part can adopt substances with different densities, is continuous and does not exceed the area of the hollow part, and adopts a mode of unlimited form to iteratively solve the outline shapes of the hollow part and the filling part by adopting a self-adaptive program so as to configure the weight, the gravity center and the rotational inertia of the model to meet the requirement of a design target. The specific program implementation process is as follows:
(1) firstly, partitioning the components, defining a model entity without any operation as a solid component, defining a cut part as a hollow component, and defining a filling part as a filling component;
(2) then, describing the cross-sectional profile and the axial profile of the solid part by using a profile formed by a point Ai and a profile formed by a point a, describing the cross-sectional profile and the axial profile of the hollow part by using a profile formed by a point Bi and a profile formed by a point b, describing the cross-sectional profile and the axial profile of the filling part by using a profile formed by a point Ci and a profile formed by a point c, wherein the cross-sectional profile of each part can be changed in the axial direction, the cross-sectional profile of the part is schematically shown in figure 4, and the axial profile of the part is schematically shown in figure 5;
(3) randomly selecting parameters in a density library to assign initial densities to each part;
(4) initial values are given to the section profile and the axial profile of each part, initial weight, gravity center and rotational inertia of the solid part, the hollow part and the filling part are respectively obtained through integral operation according to formulas 1 to 10, and then the initial weight, gravity center and rotational inertia of the model are calculated through addition and subtraction operation according to formulas 11 to 17;
(5) and comparing the calculated weight, the gravity center and the rotary inertia with target parameters, judging whether the calculation result meets the national military standard requirements through formulas 18-24, judging whether the contour parameters of each part meet given limits through formulas 25-30, returning to the step 3 to re-assign the values of the density, the section contour and the axial contour along the direction of reducing the residual error if the contour parameters of each part do not meet the given limits, returning to the step 4 to calculate the weight, the gravity center and the rotary inertia of the part and the model again, and iterating until the calculation result and the contour parameter requirements are completely met, thereby completing the design work.
The part additive manufacturing is to process the shell part and the filling part according to the final density, the section profile and the axial profile result parameters provided by the quality characteristic design module,
the method mainly comprises the steps of selecting material powder with corresponding density, driving an additive manufacturing system to stack and adhere the powder by three-dimensional data of the part, and finally finishing additive manufacturing of the part.
The mold assembly is to join the shell member and the filler member together by a simple adhesion technique, i.e., to complete the assembly of the members.
Example 2:
a design and processing method suitable for an extremely light weight putting model is characterized by comprising the steps of design and processing, and is characterized by comprising the following modules: the method comprises a quality characteristic calculation module, a quality characteristic design module, component additive manufacturing and model assembly, and comprises the following design method steps:
(1) firstly, partitioning the component, defining a model entity without any operation as a solid component, defining a cut-out part as a hollow component, and defining a filling part as a filling component;
(2) then, the cross-sectional profile and the axial profile of the solid member are described by a profile formed by a point Ai and a profile formed by a point a, the cross-sectional profile and the axial profile of the hollowed member are described by a profile formed by a point Bi and a profile formed by a point b, the cross-sectional profile and the axial profile of the filling member are described by a profile formed by a point Ci and a profile formed by a point c, respectively, and the cross-sectional profile of each member is variable in the axial direction;
(3) randomly selecting parameters in a density library to assign initial densities to each part;
(4) initial values are given to the section profile and the axial profile of each part, the initial weight, the gravity center and the rotational inertia of the solid part, the hollow part and the filling part are respectively obtained through integral operation according to formulas 1 to 10, and then the initial weight, the gravity center and the rotational inertia of the model are calculated through addition and subtraction operation according to formulas 11 to 17;
(5) comparing the calculated weight, gravity center and rotary inertia with target parameters, judging whether the calculation result meets the national military standard requirements through formulas 18-24, judging whether profile parameters of each component meet given limits through formulas 25-30, returning to the step 3 to re-assign the values of density, section profile and axial profile along the direction of reducing the residual error if the profile parameters do not meet the given limits, returning to the step 4 to calculate the weight, gravity center and rotary inertia of the component and the model again, and iterating until the calculation result and the profile parameter requirements are completely met, thereby completing the design work;
the processing steps are as follows:
(6) the part additive manufacturing is to process the shell part and the filling part according to the final density, section profile and axial profile result parameters provided by the quality characteristic design module;
(7) the method comprises the steps that material powder with corresponding density is selected, the additive manufacturing system is driven by three-dimensional data of a part to stack and adhere the powder, and additive manufacturing of the part is finally completed;
(8) the mold assembly is to join the shell member and the filler member together by a simple adhesion technique, i.e., to complete the assembly of the members.
The equations 1-30 are as follows: v. ofi (solid)∑ a Ai equation (1)
vi (hollowed out)∑ b Bi formula (2)
vi (filling)∑ c Ci formula (3)
m(k)＝∑ρ(k)vi(k)Formula (4)
Gx(k)＝∑ρ(k)vi(k)dxi(k)/∑ρ(k)vi(k)Formula (5)
Gy(k)＝∑ρ(k)vi(k)dyi(k)/∑ρ(k)vi(k)Formula (6)
Gz(k)＝∑ρ(k)vi(k)dzi(k)/∑ρ(k)vi(k)Formula (7)
Ix(k)＝∑ρ(k)vi(k)dxi(k) 2Formula (8)
Iy(k)＝∑ρ(k)vi(k)dyi(k) 2Formula (9)
Iz(k)＝∑ρ(k)vi(k)dzi(k) 2Formula (10)
(where k is solid/hollowed/filled)
m＝m(solid)-m(hollowing out)+m(filling)Formula (11)
Gx＝(m(solid)×Gx(solid)-m(hollowing out)×Gx(hollowing out)+m(filling)×Gx(filling)) Formula/m (12)
Gy＝(m(solid)×Gy(solid)-m(hollowing out)×Gy(hollowing out)+m(filling)×Gy(filling)) /m equation (13)
Gz＝(m(solid)×Gz(solid)-m(hollowing out)×Gz(hollowing out)+m(filling)×Gz(filling)) M formula (14)
Ix＝Ix(solid)+m(solid)×(Gx(solid)-Gx)2-Ix(hollowing out)-m(hollowing out)×(Gx(hollowing out)-Gx)2+Ix(filling)+m(filling)×(Gx(filling)-Gx)2
Formula (15)
Iy＝Iy(solid)+m(solid)×(Gy(solid)-Gx)2-Iy(hollowing out)-m(hollowing out)×(Gy(hollowing out)-Gy)2+Iy(filling)+m(filling)×(Gy(filling)-Gy)2
Formula (16)
Iz＝Iz(solid)+m(solid)×(Gz(solid)-Gz)2-Iz(hollowing out)-m(hollowing out)×(Gz(hollowing out)-Gz)2+Iz(filling)+m(filling)×(Gz(filling)-Gz)2
Formula (17)
0.99×mModel (model)≤m≤1.01×mModel (model)Formula (18)
0.99×LxModel (model)≤Gx-GxModel (model)≤LxModel (model)Formula (19)
0.99×LyModel (model)≤Gy-GyModel (model)≤LyModel (model)Formula (20)
0.99×LzModel (model)≤Gz-GzModel (model)≤LzModel (model)Formula (21)
0.95×IxModel (model)≤Ix≤1.05×IxModel (model)Formula (22)
0.95×IyModel (model)≤Iy≤1.05×IyModel (model)Formula (23)
0.95×IzModel (model)≤Iz≤1.05×IxModel (model)Formula (24)
Ai is more than or equal to Bi formula (25)
a is not less than b formula (26)
Formula (27) that Bi is not less than Ci
b is not less than c formula (28)
a-b is more than or equal to the minimum thickness requirement formula (29)
The Ai-Bi is more than or equal to the minimum thickness requirement formula (30).
The quality characteristic calculation module: calculating parameters such as weight, gravity center and rotational inertia of the throwing model according to a scaling ratio and a power similarity principle, and taking a calculation result as a design target parameter;
the quality characteristic design module: hollowing the middle of the solid model to form a shell, wherein the hollow part is continuous and the shape is not limited, and the outline shapes of the hollow part and the filling part are iteratively solved by adopting an optimization search algorithm self-adaptive program by means of placing the filling part in the hollow part, so that the configuration of the weight, the gravity center and the rotational inertia of the model is carried out to meet the requirement of a design target;
the filling part can adopt substances with different densities, and the filling part is continuous and is not limited in shape.
The optimization algorithm is self-contained in matlab, a corresponding mathematical model is established aiming at the method, and the optimization design is carried out by adopting an optimization search algorithm.
In the mass characteristic calculation module, the configuration values of the weight, the gravity center and the rotational inertia which are theoretically required and calculated according to the scaling proportion and the power similarity principle meet the requirements of GJB 180A-2006 on the weight, the gravity center and the rotational inertia, namely that the mass error of the external hanging object model is not more than 1.0%, the position error of the mass center is not more than 1.0% of the characteristic length, and the rotational inertia error is not more than 5.0%.
Claims (5)
1. A design and processing method suitable for an extremely light weight delivery model is characterized by comprising the following steps of design and processing, and is characterized by comprising the following modules: the mass characteristic calculation module calculates weight, gravity center and rotational inertia parameters of the throwing model according to a scaling ratio and a power similarity principle, and takes a calculation result as a design target parameter; the mass characteristic design module hollows the middle of the solid model to form a shell, the hollow part is continuous and the shape is not limited, the filling part is placed in the hollow part, and the outline shapes of the hollow part and the filling part are iteratively solved by adopting an adaptive program of an optimized search algorithm, so that the configuration of the weight, the gravity center and the rotational inertia of the model is carried out to meet the requirement of a design target; the design method comprises the following steps:
1) firstly, partitioning the components, defining a model entity without any operation as a solid component, defining a cut part as a hollow component, and defining a filling part as a filling component;
2) then, the cross-sectional profile and the axial profile of the solid member are described by a profile formed by a point Ai and a profile formed by a point a, the cross-sectional profile and the axial profile of the hollowed member are described by a profile formed by a point Bi and a profile formed by a point b, the cross-sectional profile and the axial profile of the filling member are described by a profile formed by a point Ci and a profile formed by a point c, respectively, and the cross-sectional profile of each member is variable in the axial direction;
3) randomly selecting parameters in a density library to assign initial densities to each part;
4) initial values are given to the section profile and the axial profile of each part, initial weights, centers of gravity and rotational inertia of the solid part, the hollowed part and the filling part are respectively obtained through integral operation of formulas (1) - (10), and then the initial weights, the centers of gravity and the rotational inertia of the model are calculated through addition and subtraction operation of formulas (11) - (17);
5) comparing the calculated weight, gravity center and moment of inertia with target parameters, and judging whether the calculation result meets the national military standard requirement through the following formulas (18) - (24); judging whether the contour parameters of each part meet given limits through formulas (25) to (30), if not, returning to the step 3) to re-assign the values of the density, the section contour and the axial contour along the direction of reducing the residual error, returning to the step 4) to calculate the weight, the gravity center and the rotational inertia of the part and the model again, and iterating until the calculation result and the contour parameter requirements are completely met, thereby completing the design work; the formulas (1) to (30) are as follows:
(solid)∑ a Ai equation (1)
vi (hollowed out)∑ b Bi formula (2)
vi (filling)∑ c Ci formula (3)
m(k)＝∑ρ(k)vi(k)Formula (4)
Gx(k)＝∑ρ(k)vi(k)dxi(k)/∑ρ(k)vi(k)Formula (5)
Gy(k)＝∑ρ(k)vi(k)dyi(k)/∑ρ(k)vi(k)Formula (6)
Gz(k)＝∑ρ(k)vi(k)dzi(k)/∑ρ(k)vi(k)Formula (7)
Ix(k)＝∑ρ(k)vi(k)dxi(k) 2Formula (8)
Iy(k)＝∑ρ(k)vi(k)dyi(k) 2Formula (9)
Iz(k)＝∑ρ(k)vi(k)dzi(k) 2Formula (10)
Wherein k is solid/hollowed/filled;
m＝m(solid)-m(hollowing out)+m(filling)Formula (11)
Gx＝(m(solid)×Gx(solid)-m(hollowing out)×Gx(hollowing out)+m(filling)×Gx(filling))/m
Formula (12)
Gy＝(m(solid)×Gy(solid)-m(hollowing out)×Gy(hollowing out)+m(filling)×Gy(filling))/m
Formula (13)
Gz＝(m(solid)×Gz(solid)-m(hollowing out)×Gz(hollowing out)+m(filling)×Gz(filling))/m
Formula (14)
Ix＝Ix(solid)+m(solid)×(Gx(solid)-Gx)2-Ix(hollowing out)-m(hollowing out)×(Gx(hollowing out)-Gx)2+Ix(filling)+m(filling)×(Gx(filling)-Gx)2Formula (15)
Iy＝Iy(solid)+m(solid)×(Gy(solid)-Gx)2-Iy(hollowing out)-m(hollowing out)×(Gy(hollowing out)-Gy)2+Iy(filling)+m(filling)×(Gy(filling)-Gy)2Formula (16)
Iz＝Iz(solid)+m(solid)×(Gz(solid)-Gz)2-Iz(hollowing out)-m(hollowing out)×(Gz(hollowing out)-Gz)2+Iz(filling)+m(filling)×(Gz(filling)-Gz)2Formula (17)
0.99×mModel (model)≤m≤1.01×mModel (model)Formula (18)
0.99×LxModel (model)≤Gx-GxModel (model)≤LxModel (model)Formula (19)
0.99×LyModel (model)≤Gy-GyModel (model)≤LyModel (model)Formula (20)
0.99×LzModel (model)≤Gz-GzModel (model)≤LzModel (model)Formula (21)
0.95×IxModel (model)≤Ix≤1.05×IxModel (model)Formula (22)
0.95×IyModel (model)≤Iy≤1.05×IyModel (model)Formula (23)
0.95×IzModel (model)≤Iz≤1.05×IxModel (model)Formula (24)
Ai is more than or equal to Bi formula (25)
a is not less than b formula (26)
Formula (27) that Bi is not less than Ci
b is not less than c formula (28)
a-b is more than or equal to the minimum thickness requirement formula (29)
Ai-Bi ≧ minimum thickness requirement formula (30)
Where m represents weight, Gx represents x-direction center of gravity, Gy represents y-direction center of gravity, Gz represents z-direction center of gravity, Ix represents moment of inertia relative to the x-axis, Iy represents moment of inertia relative to the y-axis, Iz represents moment of inertia relative to the z-axis, v represents volume, ρ represents density, dx represents the distance of a point relative to the x-axis, dy represents the distance of a point relative to the y-axis, dz represents the distance of a point relative to the z-axis, and L represents model feature length;
the processing steps are as follows:
6) the part additive manufacturing is to process the shell part and the filling part according to the final density, section profile and axial profile result parameters provided by the quality characteristic design module;
7) the method comprises the steps that material powder with corresponding density is selected, the additive manufacturing system is driven by three-dimensional data of a part to stack and adhere the powder, and additive manufacturing of the part is finally completed;
8) the mold assembly is to join the shell member and the filling member together by a simple adhesion technique, i.e., mold assembly.
2. The method for designing and processing the ultra-light weight launching model according to claim 1, characterized in that: the filling part can adopt substances with different densities, and the filling part is continuous and is not limited in shape.
3. The method for designing and processing the ultra-light weight launching model according to claim 1, characterized in that: the optimization algorithm is self-contained by matlab, a corresponding mathematical model is established, and optimization design is carried out by adopting an optimization search algorithm.
4. The method for designing and processing the ultra-light weight launching model according to claim 1, characterized in that: in the mass characteristic calculation module, the configuration values of the theoretically required weight, the gravity center and the moment of inertia calculated according to the scaling ratio and the power similarity principle meet the requirements of GJB 180A-2006 on the weight, the gravity center and the moment of inertia.
5. The method for designing and processing the ultra-light weight delivery model according to claim 3, wherein: the configuration value meets the requirements of GJB 180A-2006 on weight, gravity center and rotational inertia, specifically, the mass error of the external hanging object model is not more than 1.0%, the mass center position error is not more than 1.0% of the characteristic length, and the rotational inertia error is not more than 5.0%.
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