CN105677997A - Method and device for determining size of airplane skin unit chemically-milled area - Google Patents
Method and device for determining size of airplane skin unit chemically-milled area Download PDFInfo
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- CN105677997A CN105677997A CN201610021253.6A CN201610021253A CN105677997A CN 105677997 A CN105677997 A CN 105677997A CN 201610021253 A CN201610021253 A CN 201610021253A CN 105677997 A CN105677997 A CN 105677997A
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Abstract
The invention provides a method and device for determining the size of an airplane skin unit chemically-milled area. The method comprises the steps that the first length value, to be calculated, of a skin unit in the X direction is determined; the second length value of the coincident portion of the skin unit and flanges of a rod unit, in the Y direction, corresponding to the skin unit is obtained; the distances between the two edges of the mechanically-milled area of the skin unit in the Y direction and the rod unit in the Y direction are obtained; according to the first length value, the second length value and the distances, the length of the skin unit chemically-milled area in the X direction is determined. By means of the method for determining the size of the airplane skin unit chemically-milled area, the accuracy of the determined size of the skin unit chemically-milled area is high.
Description
Technical field
The present invention relates to aircraft skin structural stability strength analysis technology field, particularly relate to a kind of method and apparatus determining aircraft skin unit milling area size.
Background technology
In aircraft structure strength is analyzed, stability analysis occupies more than the 90% of whole analytical work, and wherein, the analysis of skin stability accounts for again more than the 30% of whole stability analysis work. The stability analysis of eyelid covering is mainly through being analyzed drawing analysis result to the milling area size of eyelid covering, non-milling area size, thickness, material parameter and boundary condition. In above-mentioned parameter, the thickness of eyelid covering, material and boundary condition are all that fixing being easier to obtains parameter.
And the whole eyelid covering of aircaft configuration is made up of multiple irregular eyelid covering unit, in order to alleviate the weight of aircraft self, the state that each eyelid covering unit actually presents is: four limit needs of eyelid covering unit are attached with stringer or frame (being referred to as bar unit), owing to needing enough intensity therefore thicker with the segment thickness that stringer frame is connected, and eyelid covering central area can alleviate construction weight by a part of thickness of mode mill off of milling. It is to say, each eyelid covering unit comprises milling region and non-milling region.
In reality in machine structural strength analysis, the overall dimension of each eyelid covering unit can directly obtain, but the milling region of eyelid covering unit and non-milling region but cannot directly obtain, correspondingly the milling area size of whole eyelid covering and the determination of non-milling area size are more difficult.
At present when determining the milling area size of eyelid covering unit and non-milling area size, scheme is as follows respectively mainly to have two kinds to determine:
The first, ignore the impact in milling region, say, that all regards whole eyelid covering unit as non-milling region, so will cause that the weight of calculated eyelid covering unit is more than actual weight, and ultimately resulting in aircraft structure strength, to analyze result inaccurate.
The second, artificial remove numerical value corresponding to lookup eyelid covering unit milling area size by original three-dimensional CAD model, and the numerical value that non-milling area size is corresponding, then according to searching the numerical computations each eyelid covering unit milling area size and non-milling area size that obtain. Due in actual mechanical process, it is necessary to the milling region of a large amount of eyelid covering unit and the size in non-milling region are determined, therefore, this kind of method is adopted to need to consume substantial amounts of human resources and consuming time. Moreover, owing to numerical value each through manual record and calculates, therefore, in the reading of numerical value, calculating process, there will be mistake unavoidably, the milling area size of the eyelid covering that impact is determined and the accuracy of non-milling area size, ultimately result in aircraft structure strength analysis result inaccurate.
Summary of the invention
In view of the milling area size of above-mentioned existing eyelid covering determines the problem that scheme needs to expend a large amount of human resources, length consuming time and poor accuracy, it is proposed that the present invention is to provide a kind of determination aircraft skin unit milling area size method and apparatus overcoming the problems referred to above or solving the problems referred to above at least in part.
According to one aspect of the present invention, it is provided that a kind of method determining aircraft skin unit milling area size, comprise determining that eyelid covering unit to be calculated the first length value in X direction; Obtain the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection; Obtain two edges along Y-direction, the milling region of described eyelid covering unit and described distance between the bar unit of Y-direction; Described eyelid covering unit milling region length in X direction is determined according to described first length value, the second length value and described distance.
Preferably, described method also comprises determining that eyelid covering unit to be calculated the 3rd length value along Y-direction; Obtain the flange of bar unit in X direction corresponding to described eyelid covering unit and the 4th length value of described eyelid covering unit intersection; Obtain two edges in X direction, the milling region of described eyelid covering unit and the distance between described bar unit in X direction; The described eyelid covering unit milling region length along Y-direction is determined according to described 3rd length value, the 4th length value and described distance.
Preferably, described determine that the step of described eyelid covering unit milling region length in X direction includes according to described first length value, the second length value and described distance: calculate the sum of described second length value and described distance; Calculate described first length value with described and difference, described difference is defined as described eyelid covering unit milling region length in X direction.
Preferably, determine that described eyelid covering unit milling region includes along the step of the length of Y-direction according to described 3rd length value, the 4th length value and described distance: calculate the sum of described 4th length value and described distance; Calculate described 3rd length value with described and difference, described difference is defined as the described eyelid covering unit milling region length along Y-direction.
Preferably, the step obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection includes: determine two flanges of described bar unit and the length value of described eyelid covering unit intersection respectively; By two length values and be defined as described second length value.
According to another aspect of the present invention, it is provided that a kind of device determining aircraft skin unit milling area size, including: first determines module, for determining eyelid covering unit to be calculated the first length value in X direction; First acquisition module, for obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection; Second acquisition module, for obtaining two edges along Y-direction, the milling region of described eyelid covering unit, and described distance between the bar unit of Y-direction; Second determines module, for determining described eyelid covering unit milling region length in X direction according to described first length value, the second length value and described distance.
Preferably, described device also includes: the 3rd determines module, for determining eyelid covering unit to be calculated the 3rd length value along Y-direction; 3rd acquisition module, for obtaining the flange of bar unit in X direction corresponding to described eyelid covering unit and the 4th length value of described eyelid covering unit intersection; 4th acquisition module, for obtaining two edges in X direction, the milling region of described eyelid covering unit, and the distance between described bar unit in X direction; 4th determines module, for determining the described eyelid covering unit milling region length along Y-direction according to described 3rd length value, the 4th length value and described distance.
Preferably, described second determines that module includes: first and determine module, for calculating the sum of described second length value and described distance; First difference determine module, for calculate described first length value with described and difference, described difference is defined as described eyelid covering unit milling region length in X direction.
Preferably, the described 4th determines that module includes: second and determine module, for calculating the sum of described 4th length value and described distance; Second difference determine module, for calculate described 3rd length value with described and difference, described difference is defined as the described eyelid covering unit milling region length along Y-direction.
Preferably, when the first acquisition module obtains the second length value of the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and described eyelid covering unit intersection: determine two flanges of described bar unit and the length value of described eyelid covering unit intersection respectively; By two length values and be defined as described second length value.
The scheme of the embodiment of the present invention provides determination aircraft skin unit milling area size, the flange of the bar unit along Y-direction that equipment directly obtains eyelid covering unit to be calculated the first length value in X direction in the memory area of data base or the machine, eyelid covering unit is corresponding and the second length value of eyelid covering unit intersection and the milling region of eyelid covering unit, along two distances between edge and bar unit of Y-direction, can be automatically determined described eyelid covering unit milling region length in X direction by equipment according to the value obtained. Adopting corresponding scheme, namely can determine that the eyelid covering unit milling region length along Y-direction, the length according to eyelid covering unit milling region length in X direction and along Y-direction can determine the size in milling region. The scheme of the embodiment of the present invention provides determination aircraft skin unit milling area size is directly obtained calculating parameter by equipment by program, human resources can not only be saved, it is also possible to promote treatment effeciency compared to the existing scheme needing artificial enquiry cad model to obtain calculating parameter. In addition, the scheme of the invention process provides determination aircraft skin unit milling area size, owing to being directly obtained calculating parameter carry out correlation computations by program by equipment, no matter calculate the acquisition of parameter or calculate and be all not susceptible to mistake, accordingly, it is determined that the accuracy of eyelid covering unit milling area size high.
Described above is only the general introduction of technical solution of the present invention, in order to better understand the technological means of the present invention, and can be practiced according to the content of description, and in order to above and other objects of the present invention, feature and advantage can be become apparent, below especially exemplified by the specific embodiment of the present invention.
Accompanying drawing explanation
By reading hereafter detailed description of the preferred embodiment, various other advantage and benefit those of ordinary skill in the art be will be clear from understanding. Accompanying drawing is only for illustrating the purpose of preferred implementation, and is not considered as limitation of the present invention. And in whole accompanying drawing, it is denoted by the same reference numerals identical parts. In the accompanying drawings:
Fig. 1 is the flow chart of steps of a kind of method determining aircraft skin unit milling area size of according to embodiments of the present invention;
Fig. 2 is the flow chart of steps of a kind of method determining aircraft skin unit milling area size of according to embodiments of the present invention two;
Fig. 3 is the side view that aircraft skin unit is arranged on fuselage;
Fig. 4 is frame unit bonding pad schematic diagram;
Fig. 5 is the structured flowchart of a kind of device determining aircraft skin unit milling area size of according to embodiments of the present invention three;
Fig. 6 is the structured flowchart of a kind of device determining aircraft skin unit milling area size of according to embodiments of the present invention four.
Detailed description of the invention
It is more fully described the exemplary embodiment of the disclosure below with reference to accompanying drawings. Although accompanying drawing showing the exemplary embodiment of the disclosure, it being understood, however, that may be realized in various forms the disclosure and should do not limited by embodiments set forth here. On the contrary, it is provided that these embodiments are able to be best understood from the disclosure, and complete for the scope of the present disclosure can be conveyed to those skilled in the art.
Embodiment one
With reference to Fig. 1, it is shown that the embodiment of the present invention one a kind of determines the flow chart of steps of the method for aircraft skin unit milling area size.
The method of the determination aircraft skin unit milling area size of the embodiment of the present invention comprises the following steps:
Step S102: determine eyelid covering unit to be calculated the first length value in X direction.
Milling area size already installed on the eyelid covering unit on fuselage, wing is determined by the embodiment of the present invention. In the making and installation process of eyelid covering unit, have predetermined that the relevant parameter of eyelid covering unit, and be stored in respective stored space, for instance: in data base, or in computing equipment local disk space. The non-milling area size of the overall dimensions of eyelid covering unit, the milling area size of eyelid covering unit, eyelid covering unit is may determine that by these relevant parameters. It is to say, before determining the milling area size operation of eyelid covering unit in the embodiment of the present invention, in respective stored space, storage has the relevant parameter of eyelid covering unit.
When the relevant parameter of the locally stored each eyelid covering unit of data base or computing equipment, a mark can be respectively provided with for each eyelid covering unit, the relevant parameter of corresponding eyelid covering unit can also be arranged to carry this mark, so when obtaining the relevant parameter of eyelid covering unit, the mark corresponding by eyelid covering unit to be calculated can find relevant parameter. Or, directly the relevant parameter of each eyelid covering unit is stored separately, and it is carried out corresponding with eyelid covering unit marks. So, the relevant parameter prestored can be found by eyelid covering unit marks.
Wherein, relevant parameter includes but not limited to: eyelid covering unit the first length value in X direction, flange and second length value of eyelid covering unit intersection of the bar unit along Y-direction that eyelid covering unit is corresponding, eyelid covering unit milling region along two edges of Y-direction, and along the distance between the bar unit of Y-direction.
Eyelid covering unit is the object with real area, eyelid covering unit comprises four nodes, four nodes are according to sequence counter-clockwise arrangement respectively 1,2,3 and 4, the line of eyelid covering unit interior joint 1,2 is X-direction, the line of node 1,4 is Y-direction, namely defines rectangular coordinate system in eyelid covering unit by the way. Correspondingly, eyelid covering unit overall length in X direction then may be defined as eyelid covering unit length value in X direction, and eyelid covering unit then may be defined as the eyelid covering unit length value along Y-direction along the overall length of Y-direction. Correspondingly, then need when determining eyelid covering unit milling region length in X direction to obtain eyelid covering unit length value in X direction. Should determine that the eyelid covering unit milling region length along Y-direction mutually according to the method in the present embodiment, then need the length value obtaining eyelid covering unit along Y-direction.
The overall length angle value in X direction of eyelid covering unit the first length value in X direction and eyelid covering unit. In this step, it is possible to first determine the mark of eyelid covering unit to be calculated, then pass through and the memory space being identified to storage relevant parameter is searched the relevant parameter that this mark is corresponding, and then the required design parameter value obtained in obtaining step S102 to step S106.
Step S104: obtain the flange of the bar unit along Y-direction corresponding to eyelid covering unit and the second length value of eyelid covering unit intersection.
Eyelid covering unit is fixed by reinforcement when being arranged on fuselage, wing, and reinforcement includes bar unit in X direction and the bar unit along Y-direction, is the unit in X direction or bar unit along Y-direction all has flange. And when eyelid covering unit is arranged in reinforcement, can with in X direction and partially overlap along the flange of the bar unit of Y-direction, the part overlapped with flange in eyelid covering unit is the part of non-milling.
Step S106: obtain the milling region of eyelid covering unit along two edges of Y-direction, and along the distance between the bar unit of Y-direction.
In order to ensure aircraft structure strength, except the needs guarantee of each eyelid covering unit does not carry out milling except the flange intersection with the bar unit along Y-direction, also to reserve a part of region more and not carry out milling, this region distance in X direction is then the edge along Y-direction, the milling region of eyelid covering unit, with adjacent distance between the bar unit of Y-direction.
Step S108: determine eyelid covering unit milling region length in X direction according to the first length value, the second length value and distance.
Wherein, first length is eyelid covering unit total length in X direction, the flange of the bar unit along Y-direction that eyelid covering unit is corresponding and eyelid covering unit intersection and along the flange top of bar unit of Y-direction milling region from eyelid covering unit along the edge setpoint distance of Y-direction all without milling, therefore, adopt total length to deduct and be milling region length in X direction without the length of milling.
Eyelid covering unit milling region length in X direction is had determined that by step S108, so, adopt currently existing scheme or adopt scheme corresponding with such scheme namely to can determine that the eyelid covering unit milling region length along Y-direction, the size in milling region can be determined by milling region length in X direction and milling region along the length of Y-direction.
Repeat the mode described in the embodiment of the present invention, the milling area size of each eyelid covering unit on fuselage is determined namely can determine that the milling area size of whole eyelid covering, utilizes the size of whole eyelid covering to deduct the size i.e. size in non-milling region in milling region. After the size of the milling area size and non-milling region that determine whole eyelid covering, according to the thickness of eyelid covering, material parameter and boundary condition parameter, aircraft structure strength can be analyzed.
The method of the determination aircraft skin unit milling area size provided by the embodiment of the present invention, the flange of the bar unit along Y-direction that equipment directly obtains eyelid covering unit to be calculated the first length value in X direction in the memory area of data base or the machine, eyelid covering unit is corresponding and the second length value of eyelid covering unit intersection and the milling region of eyelid covering unit, along the distance between two edges and the frame unit of Y-direction, can be automatically determined described eyelid covering unit milling region length in X direction by equipment according to the value obtained. Adopting corresponding scheme, namely can determine that the eyelid covering unit milling region length along Y-direction, the length according to eyelid covering unit milling region length in X direction and along Y-direction can determine the size in milling region. The method of the embodiment of the present invention provides determination aircraft skin unit milling area size is directly obtained calculating parameter by equipment by program, human resources can not only be saved, it is also possible to promote treatment effeciency compared to the existing scheme needing artificial enquiry cad model to obtain calculating parameter. In addition, the method of the invention process provides determination aircraft skin unit milling area size, owing to being directly obtained calculating parameter carry out correlation computations by program by equipment, no matter calculate the acquisition of parameter or calculate and be all not susceptible to mistake, accordingly, it is determined that the accuracy of eyelid covering unit milling area size high.
Embodiment two
With reference to Fig. 2, it is shown that the embodiment of the present invention two a kind of determines the flow chart of steps of the method for aircraft skin unit milling area size.
The method of the determination aircraft skin unit milling area size of the embodiment of the present invention specifically includes following steps:
Step S202: computing equipment determines eyelid covering unit to be calculated the first length value in X direction.
Milling area size already installed on the eyelid covering unit on fuselage, wing is determined by the embodiment of the present invention. In the making and installation process of eyelid covering unit, have predetermined that the relevant parameter of eyelid covering unit, and be stored in respective stored space, for instance: in data base or in computing equipment local disk space. The non-milling area size of the overall dimensions of eyelid covering unit, the milling area size of eyelid covering unit, eyelid covering unit is may determine that by these relevant parameters. It is to say, before determining the milling area size operation of eyelid covering unit in the embodiment of the present invention, in respective stored space, storage has the relevant parameter of eyelid covering unit.
Being provided with the computer program performing to determine aircraft skin unit milling area size flow process in computing equipment, computing equipment can automatically determine eyelid covering unit milling area size by calling the computer program of setting.
Wherein, relevant parameter includes but not limited to: eyelid covering unit the first length value in X direction, eyelid covering unit is along the 4th length value of Y-direction, second length value of the flange of the bar unit along Y-direction that eyelid covering unit is corresponding and eyelid covering unit intersection, 3rd length value of the flange of the bar unit along Y-direction that eyelid covering unit is corresponding and eyelid covering unit intersection, two edges along Y-direction, the milling region of eyelid covering unit and the milling region along the distance between the bar unit of Y-direction and eyelid covering unit two edges in X direction, and the distance between bar unit in X direction.
Referring to Fig. 3, it is determined for the milling area size to the eyelid covering unit shown in Fig. 3, the subsequent step of the embodiment of the present invention is illustrated.
As it is shown on figure 3, eyelid covering unit the first length value in X direction and Lx.
Step S204: obtain the flange of the bar unit along Y-direction corresponding to eyelid covering unit and the second length value of eyelid covering unit intersection.
The mode of the flange of the bar unit along Y-direction that a kind of preferred acquisition eyelid covering unit is corresponding and the second length value of eyelid covering unit intersection is:
S1: determine two flanges of the bar unit along Y-direction and the length value of eyelid covering unit intersection respectively;
As it is shown on figure 3, the bar unit along Y-direction comprises two flanges, the part corresponding for a respectively marked in Fig. 3. Wherein, the length of two shown in Fig. 3 flange is a, and when eyelid covering unit is arranged in bar unit, can arrange each flange and have the region of 1/2nd and overlap with eyelid covering unit in actual installation process, it is to say, the length value of each flange and eyelid covering unit intersection is a/2.
S2: by two length values and be defined as the second length value.
Two of bar unit along Y-direction flanges are the flange of frame unit corresponding to eyelid covering unit and the second length value of eyelid covering unit intersection with the summation of the length value of eyelid covering unit intersection. Second length value is a in figure 3.
Step S206: obtain the milling region of eyelid covering unit along two edges of Y-direction, and along the distance between the bar unit of Y-direction.
As shown in Figure 3,4, the milling zone length of eyelid covering unit is Lh, the milling region of eyelid covering unit is along two edges of Y-direction and along respectively L1 and L2 of the distance between the bar unit of Y-direction.
It is to say, in eyelid covering unit with the left hand edge of bar at a distance of L2 distance in all non-milling of part, in eyelid covering unit with the right hand edge of bar at a distance of L1 distance in all non-milling of part.
Step S208: according to the first length value, the second length value and eyelid covering unit milling region along two edges of Y-direction and along the distance between the bar unit of Y-direction, it is determined that the length in eyelid covering unit milling region.
A kind of preferred determine that the mode of eyelid covering unit milling region length in X direction is as follows according to described first length value, the second length value and described distance:
First, calculate the milling region of the second length value and eyelid covering unit along two edges of Y-direction and along the distance between the bar unit of Y-direction and;
Then, calculate the first length value with described and difference, difference is defined as the length in eyelid covering unit milling region.
Such as: the first length value is Lx, the second length value is a, two edges and along respectively L1 and L2 of the distance between the bar unit of Y-direction, the length Lh in eyelid covering unit milling region, then, Lh=Lx-a-L1-L2.
Step S210: determine eyelid covering unit to be calculated the 3rd length value along Y-direction.
Eyelid covering unit is along the 3rd length value of Y-direction and eyelid covering unit along the overall length angle value of Y-direction. Such as characterize the eyelid covering unit length along Y-direction with Ly, then, Ly=the 3rd length value.
Step S212: obtain the flange of bar unit in X direction corresponding to eyelid covering unit and the 4th length value of eyelid covering unit intersection.
The bar unit principle along Y-direction corresponding with eyelid covering unit is identical, and when fixing eyelid covering unit, eyelid covering unit is also required to the part that two flanges existence of the bar unit in X direction corresponding with eyelid covering unit overlap.
Accordingly, it would be desirable to determine the length of eyelid covering unit and two flange intersection of bar unit in X direction respectively, then, two length summations are the 4th length.
Under normal circumstances, eyelid covering unit is identical with the length of the two of bar unit in X direction flange intersection, is the half of flange length, and therefore, the 4th length value is the length value of a flange.
Step S214: two edges in X direction, the milling region of acquisition eyelid covering unit, and the distance between bar unit in X direction.
Similar to the bar unit principle along Y-direction, with all non-milling of part in the top edge first distance of bar in X direction in eyelid covering unit, with all non-milling of part in the lower limb second distance of bar in X direction in eyelid covering unit.
So the first distance and second distance sum are then milling region two distances between edge and bar unit in X direction in X direction of eyelid covering unit.
Step S216: the milling region of foundation the 3rd length value, the 4th length value and eyelid covering unit two distances between edge and bar unit in X direction in X direction, it is determined that the width in eyelid covering unit milling region.
Wherein, 3rd length value is the eyelid covering unit total length along Y-direction, all without milling in the edge setpoint distance in X direction of the milling region from eyelid covering unit, the flange top of the flange of the bar unit in X direction that eyelid covering unit is corresponding and eyelid covering unit intersection and bar unit in X direction, therefore, adopt total length to deduct and be the milling region length along Y-direction without the width of milling.
The milling region of a kind of preferred foundation the 3rd length value, the 4th length value and eyelid covering unit two distances between edge and bar unit in X direction in X direction, it is determined that eyelid covering unit milling region along the mode of the length of Y-direction is:
First, calculate the milling region of the 4th length value and eyelid covering unit two distances between edge and bar unit in X direction in X direction and;
Then, calculate the 3rd length value with described and difference, the difference obtained is defined as the eyelid covering unit milling region length along Y-direction.
Such as: the 3rd length value is Ly, the 4th length value is a, two respectively L1 and L2 of the distance between edge and bar unit in X direction, the length Lw in eyelid covering unit milling region, then, Lw=Ly-a-L1-L2.
Step S218: the length according to eyelid covering unit milling region length in X direction and along Y-direction determines the size in eyelid covering unit milling region.
Preferably, it is possible to using the product of length value and the width value area as eyelid covering unit milling region and size.
Repeated execution of steps S202 to step S218 can travel through each eyelid covering unit on fuselage and determine the milling area size of each eyelid covering unit respectively. The size in each milling region is sued for peace, then passes through the size of whole eyelid covering on fuselage and deduct the difference of this and gained and be the size in non-milling region. After the size of the milling area size and non-milling region that determine whole eyelid covering, according to the thickness of eyelid covering, material parameter and boundary condition parameter, aircraft structure strength can be analyzed.
It should be noted that, step S201 to step S208 is the first pass determining eyelid covering unit milling region length in X direction, and step S209 to step S216 is the second procedure determining eyelid covering unit milling region along the length of Y-direction, in implementing process, second procedure is not limited to after first pass to perform, second procedure can perform before first pass, it is also possible to first pass executed in parallel.
The method of the determination aircraft skin unit milling area size provided by the embodiment of the present invention, the flange of the bar unit along Y-direction that equipment directly obtains eyelid covering unit to be calculated the first length value in X direction in the memory area of data base or the machine, eyelid covering unit is corresponding and the second length value of eyelid covering unit intersection and the milling region of eyelid covering unit, along two edges of Y-direction and along the distance between the bar unit of Y-direction, can be automatically determined described eyelid covering unit milling region length in X direction by equipment according to the value obtained. Adopting corresponding scheme, namely can determine that the eyelid covering unit milling region length along Y-direction, the length according to eyelid covering unit milling region length in X direction and along Y-direction can determine the size in milling region. The method of the embodiment of the present invention provides determination aircraft skin unit milling area size is directly obtained calculating parameter by equipment by program, human resources can not only be saved, it is also possible to promote treatment effeciency compared to the existing scheme needing artificial enquiry cad model to obtain calculating parameter. In addition, the method of the invention process provides determination aircraft skin unit milling area size, owing to being directly obtained calculating parameter carry out correlation computations by program by equipment, no matter calculate the acquisition of parameter or calculate and be all not susceptible to mistake, accordingly, it is determined that the accuracy of eyelid covering unit milling area size high.
Embodiment three
With reference to Fig. 5, it is shown that the embodiment of the present invention three a kind of determines the structured flowchart of the device of aircraft skin unit milling area size.
The device of the determination aircraft skin unit milling area size of the embodiment of the present invention includes: first determines module 501, for determining eyelid covering unit to be calculated the first length value in X direction; First acquisition module 502, for obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection; Second acquisition module 503, for obtaining two edges along Y-direction, the milling region of described eyelid covering unit, and described distance between the bar unit of Y-direction; Second determines module 504, for determining described eyelid covering unit milling region length in X direction according to described first length value, the second length value and described distance.
The device of the determination aircraft skin unit milling area size provided by the embodiment of the present invention, in the memory area of data base or the machine, directly obtain eyelid covering unit to be calculated the first length value in X direction, the flange of the bar unit along Y-direction that eyelid covering unit is corresponding and the second length value of eyelid covering unit intersection and the milling region of eyelid covering unit along two edges of Y-direction and along the distance between the bar unit of Y-direction, described eyelid covering unit milling region length in X direction can be automatically determined according to the value obtained. Adopting corresponding scheme, namely can determine that the eyelid covering unit milling region length along Y-direction, the length degree according to eyelid covering unit milling region length in X direction and along Y-direction can determine the size in milling region. The device of the embodiment of the present invention provides determination aircraft skin unit milling area size directly obtains calculating parameter by program, human resources can not only be saved, it is also possible to promote treatment effeciency compared to the existing scheme needing artificial enquiry cad model to obtain calculating parameter. In addition, the device of the invention process provides determination aircraft skin unit milling area size, owing to directly being obtained calculating parameter by program and carrying out correlation computations, no matter calculate the acquisition of parameter or calculate and be all not susceptible to mistake, accordingly, it is determined that the accuracy of eyelid covering unit milling area size high.
Embodiment four
With reference to Fig. 6, it is shown that the embodiment of the present invention four a kind of determines the structured flowchart of the device of aircraft skin unit milling area size.
The device of the determination aircraft skin unit milling area size of the embodiment of the present invention includes: first determines module 601, for determining eyelid covering unit to be calculated the first length value in X direction; First acquisition module 602, for obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection; Second acquisition module 603, for obtaining two edges along Y-direction, the milling region of described eyelid covering unit, and described distance between the bar unit of Y-direction; Second determines module 604, for determining described eyelid covering unit milling region length in X direction according to described first length value, the second length value and described distance.
Preferably, described device also includes: the 3rd determines module 605, for determining eyelid covering unit to be calculated the 3rd length value along Y-direction; 3rd acquisition module 606, for obtaining the flange of bar unit in X direction corresponding to described eyelid covering unit and the 4th length value of described eyelid covering unit intersection; 4th acquisition module 607, for obtaining two edges in X direction, the milling region of described eyelid covering unit, and described distance between bar unit in X direction; 4th determines module 608, for determining the described eyelid covering unit milling region length along Y-direction according to described 3rd length value, the 4th length value and described distance.
Preferably, described second determines that module 604 includes: first and determine module 6041, for calculating the sum of described second length value and described distance; First difference determine module 6042, for calculate described first length value with described and difference, described difference is defined as described eyelid covering unit milling region length in X direction.
Preferably, the described 4th determines that module 608 includes: second and determine module 6081, for calculating the sum of described 4th length value and described distance; Second difference determine module 6082, for calculate described 3rd length value with described and difference, described difference is defined as the described eyelid covering unit milling region length along Y-direction.
Preferably, when the first acquisition module 602 obtains the second length value of the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and described eyelid covering unit intersection: determine two flanges of the described bar unit along Y-direction and the length value of described eyelid covering unit intersection respectively; By two length values and be defined as described second length value.
The device of the determination aircraft skin unit milling area size of the present embodiment method for realizing determining accordingly in previous embodiment one and embodiment two aircraft skin unit milling area size, and there is the beneficial effect of corresponding embodiment of the method, do not repeat them here.
Not intrinsic to any certain computer, virtual system or miscellaneous equipment relevant in the scheme of the determination aircraft skin unit milling area size of this offer. Various general-purpose systems can also with use based on together with this teaching. As described above, construct the structure required by the system with the present invention program to be apparent from. Additionally, the present invention is also not for any certain programmed language. It is understood that, it is possible to utilize various programming language to realize the content of invention described herein, and the description above language-specific done is the preferred forms in order to disclose the present invention.
In description mentioned herein, describe a large amount of detail. It is to be appreciated, however, that embodiments of the invention can be put into practice when not having these details. In some instances, known method, structure and technology it are not shown specifically, in order to do not obscure the understanding of this description.
Similarly, it is to be understood that, one or more in order to what simplify that the disclosure helping understands in each inventive aspect, herein above in the description of the exemplary embodiment of the present invention, each feature of the present invention is grouped together in single embodiment, figure or descriptions thereof sometimes. But, the method for the disclosure should be construed to and reflect an intention that namely the present invention for required protection requires feature more more than the feature being expressly recited in each claim. More precisely, as the following claims reflect, inventive aspect is in that all features less than single embodiment disclosed above. Therefore, it then follows claims of detailed description of the invention are thus expressly incorporated in this detailed description of the invention, wherein each claim itself as the independent embodiment of the present invention.
Those skilled in the art are appreciated that, it is possible to carry out the module in the equipment in embodiment adaptively changing and they being arranged in one or more equipment different from this embodiment. Module in embodiment or unit or assembly can be combined into a module or unit or assembly, and multiple submodule or subelement or sub-component can be put them in addition. Except at least some in such feature and/or process or unit excludes each other, it is possible to adopt any combination that all processes or the unit of all features disclosed in this specification (including adjoint claim, summary and accompanying drawing) and so disclosed any method or equipment are combined. Unless expressly stated otherwise, each feature disclosed in this specification (including adjoint claim, summary and accompanying drawing) can be replaced by the alternative features providing purpose identical, equivalent or similar.
In addition, those skilled in the art it will be appreciated that, although embodiments more described herein include some feature included in other embodiments rather than further feature, but the combination of the feature of different embodiment means to be within the scope of the present invention and form different embodiments. Such as, in detail in the claims, the one of any of embodiment required for protection can mode use in any combination.
The all parts embodiment of the present invention can realize with hardware, or realizes with the software module run on one or more processor, or realizes with their combination. It will be understood by those of skill in the art that the some or all functions of some or all parts in the scheme of the determination aircraft skin unit milling area size that microprocessor or digital signal processor (DSP) can be used in practice to realize according to embodiments of the present invention. The present invention is also implemented as part or all the equipment for performing method as described herein or device program (such as, computer program and computer program). The program of such present invention of realization can store on a computer-readable medium, or can have the form of one or more signal. Such signal can be downloaded from internet website and obtain, or provides on carrier signal, or provides with any other form.
The present invention will be described rather than limits the invention to it should be noted above-described embodiment, and those skilled in the art can design alternative embodiment without departing from the scope of the appended claims. In the claims, any reference marks that should not will be located between bracket is configured to limitations on claims. Word " comprises " and does not exclude the presence of the element or step not arranged in the claims. Word "a" or "an" before being positioned at element does not exclude the presence of multiple such element. The present invention by means of including the hardware of some different elements and can realize by means of properly programmed computer. In the unit claim listing some devices, several in these devices can be through same hardware branch and specifically embody. Word first, second and third use do not indicate that any order. Can be title by these word explanations.
Claims (10)
1. the method determining aircraft skin unit milling area size, it is characterised in that including:
Determine eyelid covering unit to be calculated the first length value in X direction;
Obtain the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection;
Obtain two edges along Y-direction, the milling region of described eyelid covering unit and described distance between the bar unit of Y-direction;
Described eyelid covering unit milling region length in X direction is determined according to described first length value, the second length value and described distance.
2. method according to claim 1, it is characterised in that described method also includes:
Determine eyelid covering unit to be calculated the 3rd length value along Y-direction;
Obtain the flange of bar unit in X direction corresponding to described eyelid covering unit and the 4th length value of described eyelid covering unit intersection;
Obtain two edges in X direction, the milling region of described eyelid covering unit and the distance between described bar unit in X direction;
The described eyelid covering unit milling region length along Y-direction is determined according to described 3rd length value, the 4th length value and described distance.
3. method according to claim 1, it is characterised in that described determine that the step of described eyelid covering unit milling region length in X direction includes according to described first length value, the second length value and described distance:
Calculate the sum of described second length value and described distance;
Calculate described first length value with described and difference, described difference is defined as described eyelid covering unit milling region length in X direction.
4. method according to claim 1, it is characterised in that determine that described eyelid covering unit milling region includes along the step of the length of Y-direction according to described 3rd length value, the 4th length value and described distance:
Calculate the sum of described 4th length value and described distance;
Calculate described 3rd length value with described and difference, described difference is defined as the described eyelid covering unit milling region length along Y-direction.
5. method according to claim 1, it is characterised in that the step obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection includes:
Determine two flanges of described bar unit and the length value of described eyelid covering unit intersection respectively;
By two length values and be defined as described second length value.
6. the device determining aircraft skin unit milling area size, it is characterised in that including:
First determines module, for determining eyelid covering unit to be calculated the first length value in X direction;
First acquisition module, for obtaining the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and the second length value of described eyelid covering unit intersection;
Second acquisition module, for obtaining two edges along Y-direction, the milling region of described eyelid covering unit, and described distance between the bar unit of Y-direction;
Second determines module, for determining described eyelid covering unit milling region length in X direction according to described first length value, the second length value and described distance.
7. device according to claim 6, it is characterised in that described device also includes:
3rd determines module, for determining eyelid covering unit to be calculated the 3rd length value along Y-direction;
3rd acquisition module, for obtaining the flange of bar unit in X direction corresponding to described eyelid covering unit and the 4th length value of described eyelid covering unit intersection;
4th acquisition module, for obtaining two edges in X direction, the milling region of described eyelid covering unit, and the distance between described bar unit in X direction;
4th determines module, for determining the described eyelid covering unit milling region length along Y-direction according to described 3rd length value, the 4th length value and described distance.
8. device according to claim 6, it is characterised in that described second determines that module includes:
First and determine module, for calculating the sum of described second length value and described distance;
First difference determine module, for calculate described first length value with described and difference, described difference is defined as described eyelid covering unit milling region length in X direction.
9. device according to claim 7, it is characterised in that the described 4th determines that module includes:
Second and determine module, for calculating the sum of described 4th length value and described distance;
Second difference determine module, for calculate described 3rd length value with described and difference, described difference is defined as the described eyelid covering unit milling region length along Y-direction.
10. device according to claim 6, it is characterised in that when the first acquisition module obtains the second length value of the flange of the bar unit along Y-direction corresponding to described eyelid covering unit and described eyelid covering unit intersection:
Determine two flanges of described bar unit and the length value of described eyelid covering unit intersection respectively;
By two length values and be defined as described second length value.
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| CN201610021253.6A CN105677997A (en) | 2016-01-13 | 2016-01-13 | Method and device for determining size of airplane skin unit chemically-milled area |
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| CN201610021253.6A CN105677997A (en) | 2016-01-13 | 2016-01-13 | Method and device for determining size of airplane skin unit chemically-milled area |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106041873A (en) * | 2016-08-22 | 2016-10-26 | 山东太古飞机工程有限公司 | Auxiliary positioning tool for chemical edge milling of aircraft skin |
| CN108817487A (en) * | 2018-06-13 | 2018-11-16 | 江西昌河航空工业有限公司 | A method of thin-wall titanium alloy plate is processed into aircraft skin |
| CN111560614A (en) * | 2020-05-15 | 2020-08-21 | 沈阳飞机工业（集团）有限公司 | Combined chemical milling sample plate and processing method thereof |
| CN112711797A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining reference stress of skin stringer combination calculation unit |
| CN113844659A (en) * | 2021-09-30 | 2021-12-28 | 中航通飞华南飞机工业有限公司 | Double-skin anti-icing cavity structure of airplane and heat exchange method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104476118A (en) * | 2014-11-03 | 2015-04-01 | 陕西飞机工业（集团）有限公司 | Manufacturing method of airplane chemical milling skin three-dimensional chemical milling sample plate |
| CN104951595A (en) * | 2015-06-01 | 2015-09-30 | 江西洪都航空工业集团有限责任公司 | Modeling method for skin part technological lug |
| CN105091825A (en) * | 2015-09-14 | 2015-11-25 | 江西洪都航空工业集团有限责任公司 | Skin milling area thickness detection method |
-
2016
- 2016-01-13 CN CN201610021253.6A patent/CN105677997A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104476118A (en) * | 2014-11-03 | 2015-04-01 | 陕西飞机工业（集团）有限公司 | Manufacturing method of airplane chemical milling skin three-dimensional chemical milling sample plate |
| CN104951595A (en) * | 2015-06-01 | 2015-09-30 | 江西洪都航空工业集团有限责任公司 | Modeling method for skin part technological lug |
| CN105091825A (en) * | 2015-09-14 | 2015-11-25 | 江西洪都航空工业集团有限责任公司 | Skin milling area thickness detection method |
Non-Patent Citations (1)
| Title |
|---|
| 赵稼祥: "国外化铣在航宇上的应用及进展", 《材料工艺》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106041873A (en) * | 2016-08-22 | 2016-10-26 | 山东太古飞机工程有限公司 | Auxiliary positioning tool for chemical edge milling of aircraft skin |
| CN106041873B (en) * | 2016-08-22 | 2018-02-06 | 山东太古飞机工程有限公司 | Aircraft skin chemical contouring edge auxiliary locating tool |
| CN108817487A (en) * | 2018-06-13 | 2018-11-16 | 江西昌河航空工业有限公司 | A method of thin-wall titanium alloy plate is processed into aircraft skin |
| CN111560614A (en) * | 2020-05-15 | 2020-08-21 | 沈阳飞机工业（集团）有限公司 | Combined chemical milling sample plate and processing method thereof |
| CN111560614B (en) * | 2020-05-15 | 2022-02-18 | 沈阳飞机工业（集团）有限公司 | Combined chemical milling sample plate and processing method thereof |
| CN112711797A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining reference stress of skin stringer combination calculation unit |
| CN112711797B (en) * | 2020-12-29 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Determination method for skin stringer combined calculation unit reference stress |
| CN113844659A (en) * | 2021-09-30 | 2021-12-28 | 中航通飞华南飞机工业有限公司 | Double-skin anti-icing cavity structure of airplane and heat exchange method |
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