CN112528406B - Geometric parameterization modeling method and device for aircraft fuselage frame structure - Google Patents

Geometric parameterization modeling method and device for aircraft fuselage frame structure Download PDF

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CN112528406B
CN112528406B CN202011432773.9A CN202011432773A CN112528406B CN 112528406 B CN112528406 B CN 112528406B CN 202011432773 A CN202011432773 A CN 202011432773A CN 112528406 B CN112528406 B CN 112528406B
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曲林锋
左林玄
郭子铭
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Abstract

The application belongs to the technical field of geometric modeling, and particularly relates to a geometric parametric modeling method and device for an airplane fuselage frame structure. The method comprises the following steps: a curve is cut out on the geometry of an inner shape surface and the geometry of an outer shape surface of the frame of the machine body according to a frame position plane to obtain a first geometric curve of the inner shape surface and a first geometric curve of the outer shape surface; constructing a first characteristic equation of the inner surface and the outer surface, intercepting discrete point coordinates on a first inner surface geometric curve and a first outer surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation to obtain a second inner surface geometric curve and a second outer surface geometric curve; constructing a coefficient control equation, respectively adjusting the second inner profile geometrical curve and the second outer profile geometrical curve, and obtaining a profile curve of the frame of the airplane body according to the two adjusted curves; and constructing a second characteristic equation, intercepting nodes on the outline curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as positions for arranging the reinforcing ribs of the frame.

Description

Geometric parameterization modeling method and device for aircraft fuselage frame structure
Technical Field
The application belongs to the technical field of geometric modeling, and particularly relates to a geometric parameterization modeling method and device for an airplane fuselage frame structure.
Background
Due to the fact that the military aircraft has high requirements for performances such as pneumatics, stealth and propulsion, the geometry of the external pneumatic profile and the internal air inlet channel profile is complex, and the geometry of the internal supporting aircraft body frame structure is difficult to be regular.
The traditional method needs a method of manually taking points and establishing lines to establish a geometric model: the first step is as follows: intercepting the inner and outer surfaces of the airplane geometrically according to a frame position plane to obtain two curves; the second step is that: each curve is closed by manually adjusting the break points in the curves; the third step: establishing a contour geometric model of a frame structure by using two closed curves in a plane; the fourth step: points are uniformly taken on the frame structure, and the positions of the frame reinforcing ribs are arranged. When a curve is geometrically intercepted by adopting a traditional method, manual connection is probably needed to close the curve due to model precision; after the inner and outer shapes of the airplane are adjusted, manually intercepting is needed again, and all work is restarted; the traditional spline point adjustment mode is adopted to adjust too many variables, so that the requirement of the specific surface of the airplane is difficult to meet; the manual modeling cannot be associated with the subsequent finite element modeling analysis, so that the efficiency of structural design analysis is greatly reduced.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a geometric parameterization modeling method of an airplane fuselage frame structure so as to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a first aspect of the present application provides a method for geometrically parameterized modeling of an aircraft fuselage frame structure, comprising:
the steps of,
Intercepting a curve on the inner profile geometry of the frame of the machine body according to the frame position plane to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to a frame position plane to obtain a first outer surface geometry curve;
step two,
Constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
step three, constructing a coefficient control equation, respectively adjusting a second inner shape surface geometric curve and a second outer shape surface geometric curve, and obtaining a contour curve of the frame of the airplane body according to the two adjusted curves;
and fourthly, constructing a second characteristic equation, intercepting nodes on the contour curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the reinforcing ribs of the layout frame.
Optionally, in the third step, the constructing a coefficient control equation, adjusting the second inner shape surface geometric curve and the second outer shape surface geometric curve respectively, and obtaining the profile curve of the airframe frame according to the two adjusted curves includes:
s301, constructing a coefficient control equation of an inner surface and a coefficient control equation of an outer surface;
S302、
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and the amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometric adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to the coefficient control equation, and obtaining the adjusted second outline geometric curve;
and S303, obtaining a contour curve of the frame of the airplane body according to the adjusted second inner-shape surface geometric curve and the adjusted second outer-shape surface geometric curve.
A second aspect of the present application provides an apparatus for geometric parameterisation modelling of an aircraft fuselage frame structure, comprising:
a first curve acquisition module to:
intercepting a curve on the inner profile geometry of the frame of the machine body according to the plane of the frame position to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to a frame position plane to obtain a first outer surface geometry curve;
a second curve acquisition module to:
constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
the adjusting module is used for constructing a coefficient control equation, respectively adjusting the second inner profile geometrical curve and the second outer profile geometrical curve, and obtaining a profile curve of the frame of the airplane body according to the two adjusted curves;
and the frame reinforcing rib position acquisition module is used for constructing a second characteristic equation, intercepting nodes on the outline curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the frame reinforcing ribs.
Optionally, the adjusting module includes:
the coefficient control equation building unit is used for building a coefficient control equation of the inner surface and a coefficient control equation of the outer surface;
an adjustment unit for:
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and the amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometrically adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second outline geometric curve;
and the contour curve acquisition unit of the machine body frame is used for acquiring the contour curve of the machine body frame according to the adjusted second inner-profile geometric curve and the second outer-profile geometric curve.
The invention has at least the following beneficial technical effects:
the geometric parameterization modeling method of the airplane fuselage frame structure is characterized in that two curve characteristic equations of an inner surface and an outer surface are established aiming at a complicated frame structure of the airplane body, a contour of the frame structure is established, a coefficient control function of two contour curve polynomial equations is established, and the adjustment of the contour and the characteristics of a curve is rapidly completed by adjusting the function; the efficiency can be greatly improved, the manual adjustment time is saved, and the randomness and negligence errors of manual modeling are avoided.
Drawings
FIG. 1 is a flow chart of a method for geometric parameterized modeling of an aircraft fuselage frame structure according to one embodiment of the present application;
FIG. 2 is a schematic diagram of an initial cross-sectional shape of a geometric parametric modeling method for an aircraft fuselage frame structure according to an embodiment of the present application;
FIG. 3 is a schematic diagram of an adjusted anteroposterior cross-sectional shape of an inner geometry curve of a geometric parametric modeling method for an aircraft fuselage frame structure according to an embodiment of the present application;
FIG. 4 is a schematic diagram of the shape of the front and back section of the aircraft fuselage frame structure after adjustment of the geometric curve of the outer surface according to the geometric parametric modeling method of the aircraft fuselage frame structure according to an embodiment of the present application;
fig. 5 is a schematic view of a contour curve of a fuselage box according to a geometric parametric modeling method for an aircraft fuselage box structure according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present 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. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 5.
A first aspect of the present application provides a method for geometrically parameterized modeling of an aircraft fuselage frame structure, comprising the steps of:
step one, when modeling is carried out for the first time,
intercepting a curve on the inner profile geometry of the frame of the machine body according to the frame position plane to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to a frame position plane to obtain a first outer surface geometry curve;
step two,
Constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
step three, constructing a coefficient control equation, respectively adjusting a second inner shape surface geometric curve and a second outer shape surface geometric curve, and obtaining a contour curve of the frame of the airplane body according to the two adjusted curves; the inner surface and the outer surface are adjusted, including the outer mold line is expanded or changed into a quadric surface, a coefficient control function of a curve polynomial equation is established, and the function is adjusted to quickly adapt to the change of the curve appearance and characteristics so as to meet the shape requirements of the inner surface and the outer surface.
And fourthly, constructing a second characteristic equation, intercepting nodes on the contour curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the reinforcing ribs of the layout frame.
In an embodiment of the present application, in step three, constructing a coefficient control equation, adjusting the second inner surface geometry curve and the second outer surface geometry curve respectively, and obtaining a contour curve of the fuselage frame according to the two adjusted curves includes:
s301, constructing a coefficient control equation of an inner surface and a coefficient control equation of an outer surface;
S302、
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to a coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometric adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to a coefficient control equation, and obtaining an adjusted second outline geometric curve;
and S303, obtaining a contour curve of the frame of the airplane body according to the adjusted second inner-shape surface geometric curve and the adjusted second outer-shape surface geometric curve.
According to the geometric parameterization modeling method for the aircraft fuselage frame structure, an initial first inner profile geometric curve and a first outer profile geometric curve which are cut according to a frame position plane are shown in figure 2. In one embodiment of the present application, a first characteristic equation of the inner profile and the outer profile is as follows:
first characteristic equation of the inner surface:
y＝0.003322*x^4-0.08415*x^3+0.6252*x2-0.4157*x
first characteristic equation of the profile:
y＝0.003322*x^4-0.08415*x^3+0.6252*x2-0.4157*x-3
the arrangement is as follows:
y＝a*x^4-b*x^3+c*x2-d*x
after the curve is reconstructed through the first characteristic equation, a control point and a control requirement are given:
the control point, the initial point is (0, 0), the end point is (10, 7.5), the curvature is controlled to be theta at 2, 5 and 8 respectively 1 ，θ 2 ，θ 3 ；
Establishing a coefficient control equation:
Figure GDA0002905982220000061
solving the equation to obtain the corresponding a, b, c and d values, a few examples of adjustment are given below, theta is an arc value, the curve comparison diagrams after the initial characteristic and the parameter adjustment are given in fig. 3 to 4, and the outline curve schematic diagram of the airframe frame is given in fig. 5.
Figure GDA0002905982220000062
Figure GDA0002905982220000063
Figure GDA0002905982220000064
A second aspect of the present application provides a geometric parametric modeling apparatus for an aircraft fuselage frame structure, comprising:
a first curve acquisition module to:
intercepting a curve on the inner profile geometry of the frame of the machine body according to the frame position plane to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to a frame position plane to obtain a first outer surface geometry curve;
a second curve acquisition module to:
constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
the adjusting module is used for constructing a coefficient control equation, respectively adjusting the second inner-profile geometric curve and the second outer-profile geometric curve, and obtaining a profile curve of the frame of the airplane body according to the two adjusted curves;
and the frame reinforcing rib position acquisition module is used for constructing a second characteristic equation, intercepting nodes on the outline curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the frame reinforcing ribs.
In one embodiment of the present application, the adjustment module includes:
the coefficient control equation building unit is used for building a coefficient control equation of the inner surface and a coefficient control equation of the outer surface;
an adjustment unit for:
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to a coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometrically adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to a coefficient control equation, and obtaining an adjusted second outline geometric curve;
and the contour curve acquisition unit of the machine body frame is used for acquiring the contour curve of the machine body frame according to the adjusted second inner profile geometric curve and the second outer profile geometric curve.
According to the geometric parameterization modeling method and device for the frame structure of the airplane body, aiming at the complex frame structure of the airplane body, two curve characteristic equations of an inner surface and an outer surface are established, the outline of the frame structure is established, a coefficient control function of two outline curve polynomial equations is established, and the adjustment of the outline and the characteristics of the curve is rapidly completed by adjusting the function; the efficiency can be greatly improved, the manual adjustment time is saved, and the randomness and negligence errors of manual modeling are avoided.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (4)

1. A method of geometrically parameterized modeling of an aircraft fuselage frame structure, comprising:
the first step,
Intercepting a curve on the inner profile geometry of the frame of the machine body according to the plane of the frame position to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to a frame position plane to obtain a first outer surface geometry curve;
step two,
Constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
step three, constructing a coefficient control equation, respectively adjusting a second inner shape surface geometric curve and a second outer shape surface geometric curve, and obtaining a contour curve of the frame of the airplane body according to the two adjusted curves;
and step four, constructing a second characteristic equation, intercepting nodes on the contour curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the reinforcing ribs of the layout frame.
2. The method of claim 1, wherein the step three of constructing the coefficient control equation to adjust the second inner geometry curve and the second outer geometry curve, respectively, and obtaining the profile curve of the fuselage frame according to the adjusted two curves comprises:
s301, constructing a coefficient control equation of an inner surface and a coefficient control equation of an outer surface;
S302、
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and the amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometric adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to the coefficient control equation, and obtaining the adjusted second outline geometric curve;
and S303, obtaining a contour curve of the frame of the airplane body according to the adjusted second inner-shape surface geometric curve and the adjusted second outer-shape surface geometric curve.
3. A device for geometrically parameterized modeling of an aircraft fuselage frame structure, comprising:
a first curve acquisition module to:
intercepting a curve on the inner profile geometry of the frame of the machine body according to the frame position plane to obtain a first inner profile geometry curve;
intercepting a curve on the outer surface geometry of the frame of the machine body according to the plane of the frame position to obtain a first outer surface geometry curve;
a second curve acquisition module to:
constructing a first characteristic equation of the inner surface, intercepting discrete point coordinates on a first inner surface geometric curve, and carrying out curve reconstruction according to the first characteristic equation of the inner surface to obtain a second inner surface geometric curve;
constructing a first characteristic equation of the outer surface, intercepting discrete point coordinates on a geometric curve of the first outer surface, and performing curve reconstruction according to the first characteristic equation of the outer surface to obtain a geometric curve of a second outer surface;
the adjusting module is used for constructing a coefficient control equation, respectively adjusting the second inner-profile geometric curve and the second outer-profile geometric curve, and obtaining a profile curve of the frame of the airplane body according to the two adjusted curves;
and the frame reinforcing rib position acquisition module is used for constructing a second characteristic equation, intercepting nodes on the outline curve of the frame of the airplane body according to the second characteristic equation, and taking the nodes as the positions of the frame reinforcing ribs.
4. The apparatus according to claim 3, wherein the adjustment module comprises:
the coefficient control equation building unit is used for building a coefficient control equation of the inner surface and a coefficient control equation of the outer surface;
an adjustment unit for:
dividing the second inner profile geometric curve into n geometrically adjustable characteristic points, adjusting the positions and the amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second inner profile geometric curve;
dividing the second outline geometric curve into n geometrically adjustable characteristic points, adjusting the positions and amplitudes of the characteristic points according to the coefficient control equation, and obtaining an adjusted second outline geometric curve;
and the contour curve acquisition unit of the machine body frame is used for acquiring the contour curve of the machine body frame according to the adjusted second inner-profile geometric curve and the second outer-profile geometric curve.
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