CN114239139A - Automatic creating method for standard process boss of aircraft structural part - Google Patents
Automatic creating method for standard process boss of aircraft structural part Download PDFInfo
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- CN114239139A CN114239139A CN202111527989.8A CN202111527989A CN114239139A CN 114239139 A CN114239139 A CN 114239139A CN 202111527989 A CN202111527989 A CN 202111527989A CN 114239139 A CN114239139 A CN 114239139A
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Abstract
The invention belongs to the technical field of machining and manufacturing, and particularly relates to an automatic creation method of a standard process boss of an airplane structural part, which comprises the following steps: selecting a certain web plate surface in the structural member as a projection surface; projecting all projection surfaces and finding out a maximum profile envelope curve; the maximum outline enveloping line deviates to the outer side of the part to obtain a deviated outline curve, the position of the center point of the first process boss is determined on the outline curve, and the center points P of the process bosses are sequentially generated along the clockwise direction i And L i (ii) a The profile surface is obtained at the point L i Normal vector of (C)T i (ii) a Vector of normalT i Projecting on the projection surface to obtain projection componentsτ i Creating a standard process boss main body; and respectively generating process boss connecting areas aiming at the single-sided part and the double-sided part to finish the process boss creation. The invention can be used for numerical control of airplane structural partsThe processing provides an automatic creating method of a standard process boss, which can improve the reasonability of the process boss and reduce the repetitive labor of process personnel.
Description
Technical Field
The invention belongs to the technical field of machining and manufacturing, and particularly relates to an automatic creation method of a standard process boss of an airplane structural part.
Background
The airplane structural member is composed of a large number of grooves, ribs and other characteristics, belongs to a thin-wall weak-rigidity part, and generally adopts a mode of pressing a process boss to increase the rigidity of the part in the processing process and ensure the processing quality of the part. The reasonability of the process boss directly influences the part processing result, the process boss of the existing aircraft structural part mainly depends on manual experience, the reasonability cannot be effectively guaranteed, and the repetitive labor of process personnel is increased.
The patent ZL201310103524.9 discloses an automatic clamping method, which comprises the steps of firstly evaluating the integral rigidity of an aircraft structural part, and formulating a corresponding clamping scheme according to a rigidity evaluation result, wherein the clamping scheme comprises specific clamping positions and distribution; the creation of the process boss is involved, but the distribution principle of the process boss is only explained briefly, and the specific creation method of the process boss is not explained.
The patent ZL201310268008.1 discloses a method for creating a process boss positioned in a structural part, which comprises the steps of boss boundary extraction, boss parameter determination and the like, but does not relate to the creation of the process boss positioned on the periphery of an outline.
In order to improve the reasonability of the process boss setting and reduce the repetitive labor of process personnel, a method capable of realizing automatic creation of the process boss is needed.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide an automatic creation method of a standard process boss of an aircraft structural part, which improves the creation rationality of the process boss and reduces the repetitive workload of process personnel.
In order to achieve the purpose, the invention adopts the technical scheme that:
an automatic creating method for a standard process boss of an aircraft structural part is characterized by comprising the following steps:
step one, selecting a certain web plate surface in a structural part as a projection surface M;
projecting all the contour surfaces of the structural part to a projection surface M, and finding out a maximum contour envelope line from all the contour surface projection lines;
step three, shifting the maximum outline envelope line to the outer side of the partD+W2+10mm, a profile curve after deflection is obtained, whereinDThe diameter of the tool used for the profiling of the structural part,Wthe width of the process boss;
fourthly, determining the position of the center point of the first process boss on the contour curve, and sequentially generating the center points P of the process bosses along the clockwise direction i Whereini=n，nThe number of the process bosses;
step five, finding the center point P of the process boss on the contour surface of the structural member in sequence i Closest point L i ；
Step six, sequentially obtaining the outline surface point L i Normal vector of (C)T i ；
Step seven, vector of the lawT i Projecting on the projection plane M to obtain projection componentsτ i I.e. the process boss creates a width extension direction；
Step eight, setting the geometric parameters of the boss main body of the standard process;
step nine, according to the geometric parameters and vectors of the process bossτ i Creating a standard process boss main body;
step ten, setting geometrical parameters of a process boss connecting area;
step eleven, respectively generating process boss connecting areas aiming at the single-sided part and the double-sided part, and finishing the process boss creation.
Further, the process boss comprises a process boss main body and a process boss connecting area;
furthermore, at least 1 process boss is arranged at the open web, and 1 process boss is additionally arranged at intervals of 100 mm and 150 mm.
Furthermore, the single-side opening rib is provided with process bosses 20mm away from the opening end, and 1 process boss is additionally arranged at intervals of 150-200 mm.
Furthermore, the two-side opening rib is provided with process bosses 20mm away from the opening end, and 1 process boss is additionally arranged at each interval of 100-150 mm.
Further, when the height-thickness ratio of the structural member edge strip exceeds 20, 1 process boss is arranged at intervals of 200mm and 250 mm;
furthermore, 1 process boss is arranged at each interval of 250-300mm of other characteristic parts.
Furthermore, the central points of all the process bosses need to avoid the contour depression area.
Further, the geometric parameters of the standard process boss main body comprise the parameters of the length, the width and the height of the process boss main body, the screw aperture, the socket depth and the socket diameter;
the geometric parameters of the process boss connecting area comprise the thickness and width parameters of the connecting area;
the process boss connecting areas are generated aiming at the single-sided part and the double-sided part respectively, specifically, when the parts are double-sided parts, the process boss connecting areas are located in the middle of a process boss main body and are divided by a projection plane M in an average manner; when the part is a single-side part, the process boss connecting area is positioned at the top of the rib top of the frame surface of the part, and the lower surface of the connecting area is higher than the rib topThe top surfaceT R +2mm, whereinT R The radius of the bottom corner of the cutter adopted for the outline processing.
The invention has the beneficial effects that:
the invention can provide an automatic standard process boss creating method for the numerical control machining of the aircraft structural part, can improve the reasonability of process boss setting and reduce the repetitive labor of process personnel.
Drawings
FIG. 1 is a schematic illustration of a maximum profile envelope of a typical aircraft structural member.
Fig. 2-3 are schematic views of typical features of an aircraft structural member.
FIG. 4 is a schematic diagram of a standard process boss creation.
FIG. 5 is a schematic view of a standard process boss.
Fig. 6-7 are schematic views of the process boss attachment area.
FIG. 8 is a schematic view of a typical aircraft structural component standard process boss.
Detailed Description
The following examples are given for the detailed implementation and specific operation of the present invention, but the scope of the present invention is not limited to the following examples.
The invention is further described below with reference to the accompanying drawings.
Example 1
An automatic creating method for a standard process boss of an aircraft structural part is characterized by comprising the following steps:
step one, selecting a certain web plate surface in a structural part as a projection surface M;
projecting all the contour surfaces of the structural part to a projection surface M, and finding out a maximum contour envelope line from all the contour surface projection lines;
step three, shifting the maximum outline envelope line to the outer side of the partD+W2+10mm, a profile curve after deflection is obtained, whereinDThe diameter of the tool used for the profiling of the structural part,Wthe width of the process boss;
fourthly, determining the position of the center point of the first process boss on the contour curve, and sequentially generating the center points P of the process bosses along the clockwise direction i Whereini=n，nThe number of the process bosses;
step five, finding the center point P of the process boss on the contour surface of the structural member in sequence i Closest point L i ；
Step six, sequentially obtaining the outline surface point L i Normal vector of (C)T i ；
Step seven, vector of the lawT i Projecting on the projection plane M to obtain projection componentsτ i Namely, the width extending direction of the process boss is established;
step eight, setting the geometric parameters of the boss main body of the standard process;
step nine, according to the geometric parameters and vectors of the process bossτ i Creating a standard process boss main body;
step ten, setting geometrical parameters of a process boss connecting area;
step eleven, respectively generating process boss connecting areas aiming at the single-sided part and the double-sided part, and finishing the process boss creation.
The invention can provide an automatic standard process boss creating method for the numerical control machining of the aircraft structural part, can improve the reasonability of process boss setting and reduce the repetitive labor of process personnel.
Example 2
An automatic creating method for a standard process boss of an aircraft structural part comprises the following steps:
step one, aiming at a typical airplane structural part shown in figure 1, selecting one of plane web surfaces as a projection surface M; in fig. 1, M is a projection plane, and S1 is a maximum profile envelope curve.
Projecting all the contour surfaces of the structural part to a projection surface M, and finding out a maximum contour envelope line from all contour surface projection curves;
step three, the diameter of a cutter adopted for processing the structural part profile is 20mm, and the width of a boss in the standard process is 40mm, so that the maximum profile envelope line obtained in the step two deviates 60mm towards the outer side of the part to obtain a deviated profile curve S1;
fig. 2-3 are typical characteristic diagrams of the aircraft structural member, wherein S2 is a single-edge open rib, S3 is an open web, and S4 is a double-edge open rib. FIG. 4 is a schematic view of a standard process panel creation, wherein S5 is the main body of the process panel, S6 is the attachment area of the process panel, P i Is the center point of the process boss, L i Is the center point P of the technological boss on the contour surface i The point that is the closest to the point of interest,T i is a contour surface at the point L i The normal vector of (a) to (b),τ i is given by the vector of FarnetT i The projection onto the projection plane M is such that,din order to obtain the width of the connecting area of the process lug boss,lis the thickness of the process boss connection area.
Step four, determining the position P of the center point of the first process boss on the contour curve S1 according to the principle of setting the center point of the process boss1And sequentially generating a process boss central point P along the clockwise direction1-P14(ii) a The center points of all the process bosses meet the following principle:
at least 1 process boss is arranged at the open web, and 1 boss is additionally arranged at intervals of 100-150 mm;
the single-side opening rib is provided with process bosses 20mm away from the opening end, and 1 boss is additionally arranged at intervals of 150-200 mm;
the two-side opening rib is provided with process bosses 20mm away from the opening end, and 1 boss is additionally arranged at intervals of 100 mm and 150 mm;
when the height-thickness ratio of the structural member edge strip exceeds 20, 1 process boss is arranged at intervals of 200-250 mm;
1 process boss is arranged at each distance of 250-300mm of other characteristic parts;
the central points of all the process bosses need to avoid the contour sunken area;
in the principle, the distance between the center points of the process bosses is the distance along the profile curve S1 instead of the straight line distance between the center points of the adjacent process bosses;
step five, with P10For example, a standard process boss creation process is described, at the structural member profileFinding the center point P of the boss10Closest point L10；
Step six, obtaining the outline point L of the structural part10Normal vector of (C)T 10；
Step seven, vector of the lawT 10Projecting on the projection plane M to obtain projection componentsτ 10Namely, the width extending direction of the process boss is established;
step eight, as shown in fig. 5, setting the geometric parameters of the standard process boss main body, including the process boss heightHWidth of the technological bossWLength of the technological bossLDepth parameter of boss pit of artUDiameter parameter of boss pit of artKHole diameter parameter of process boss screwh；
Step nine, according to the geometric parameters and vectors of the process bossτ 10Creating a standard process boss main body;
step ten, setting geometrical parameters of the process boss connecting area, including the width of the process boss connecting areadThickness of the connection area of the craft bossl(ii) a Fig. 6-7 are schematic views of the attachment area of the process boss where S7 overlaps the middle of the process boss and S8 is at the top of the frame rib of the part.
Eleventh, the aircraft structural member shown in fig. 1 is a double-sided part, double-sided processing is required, the process boss connection area is located in the middle of the process boss main body and is divided evenly by the projection plane M, the process boss connection area is created according to the geometric parameters of the process boss connection area, and creation of the process boss is completed, as shown in fig. 8.
The process boss connecting area is generated for the single-sided part and the double-sided part respectively, specifically, when the parts are double-sided parts, the process boss connecting area is located in the middle of a process boss main body and is divided by a projection plane M in an average manner; when the part is a single-side part, the process boss connecting area is positioned at the top of the rib top of the frame surface of the part, and the lower surface of the connecting area is higher than the top surface of the rib topT R +2mm, whereinT R The radius of the bottom corner of the cutter adopted for the outline processing.
The parts not involved in the present invention are the same as or can be implemented using the prior art.
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. 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 application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present application, it should be noted that the terms "upper", "vertical", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally arranged when products of the application are used, or orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of description and simplification of the description, but do not indicate or imply that the devices or elements that are referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the application. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Claims (10)
1. An automatic creating method for a standard process boss of an aircraft structural part is characterized by comprising the following steps:
step one, selecting a certain web plate surface in a structural part as a projection surface M;
projecting all the contour surfaces of the structural part to a projection surface M, and finding out a maximum contour envelope line from all the contour surface projection lines;
step three, shifting the maximum outline envelope line to the outer side of the partD+W2+10mm, a profile curve after deflection is obtained, whereinDThe diameter of the tool used for the profiling of the structural part,Wthe width of the process boss;
fourthly, determining the position of the center point of the first process boss on the contour curve, and sequentially generating the center points P of the process bosses along the clockwise direction i Whereini=n，nThe number of the process bosses;
step five, finding the center point P of the process boss on the contour surface of the structural member in sequence i Closest point L i ；
Step six, sequentially obtaining the outline surface point L i Normal vector of (C)T i ；
Step seven, vector of the lawT i Projecting on the projection plane M to obtain projection componentsτ i Namely, the width extending direction of the process boss is established;
step eight, setting the geometric parameters of the boss main body of the standard process;
step nine, according to the geometric parameters and vectors of the process bossτ i Creating a standard process boss main body;
step ten, setting geometrical parameters of a process boss connecting area;
step eleven, respectively generating process boss connecting areas aiming at the single-sided part and the double-sided part, and finishing the process boss creation.
2. The automatic creation method of a standard craft boss for aircraft structural members as recited in claim 1, wherein the craft boss comprises two parts, a craft boss main body and a craft boss connection region.
3. The automatic creation method of the standard process boss of the aircraft structural member as claimed in claim 1, wherein at least 1 process boss is arranged at the open web, and 1 process boss is additionally arranged every 100-150 mm.
4. The method as claimed in claim 3, wherein the single-side open rib has a process boss 20mm away from the open end, and 1 process boss is added every 150-200 mm.
5. The method as claimed in claim 4, wherein the double-side opening rib is provided with a process boss 20mm away from the opening end, and 1 process boss is added every 100-150 mm.
6. The automatic creation method of the standard process boss of the aircraft structural part as claimed in claim 5, wherein when the height-thickness ratio of the structural part bead exceeds 20, 1 process boss is arranged every 200 and 250mm apart.
7. The automatic creation method of the standard process boss of the aircraft structural part as recited in claim 6, wherein 1 process boss is arranged at intervals of 250-300mm for other characteristic parts.
8. The automatic creation method of the standard process boss of the aircraft structural part as claimed in claim 1, wherein the central point of all the process bosses needs to avoid the contour depression area.
9. The automatic creating method of the standard process boss of the aircraft structural part as claimed in claim 1, wherein the geometric parameters of the main body of the standard process boss comprise the parameters of length, width and height of the main body of the process boss, and the parameters of the diameter, depth and diameter of the screw; the geometric parameters of the process boss connecting area comprise the thickness and the width parameters of the connecting area.
10. The automatic creating method of the standard process boss of the aircraft structural part as claimed in claim 1, wherein the step of respectively generating the process boss connecting areas for the single-sided part and the double-sided part specifically means that when the part is a double-sided part, the process boss connecting areas are located in the middle of the process boss main body and are evenly divided by the projection plane M; when the part is a single-side part, the process boss connecting area is positioned at the top of the rib top of the frame surface of the part, and the lower surface of the connecting area is higher than the top surface of the rib topT R +2mm, whereinT R The radius of the bottom corner of the cutter adopted for the outline processing.
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