CN112660410A - Estimation method for weight of high-aspect-ratio wing - Google Patents
Estimation method for weight of high-aspect-ratio wing Download PDFInfo
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Abstract
The invention belongs to the field of optimization design of airplane structures, and relates to a method for estimating the weight of a high-aspect-ratio wing. The method comprises the following steps: equating a target wing with a large aspect ratio and weight to be estimated to an I-shaped cantilever beam with a fixed and supported equal section at one end, and determining the length and the average height of the I-shaped cantilever beam with the equal section; parameters of all sections in the spanwise direction of the I-shaped cantilever beam with the equal sections are completely the same; the preset reference wing is also equivalent to a reference equal-section I-shaped cantilever beam fixedly supported at one end; determining the length and average height of the reference equal-section I-shaped cantilever beam; obtaining equivalent total bending moment load of a target wing with a high aspect ratio and equivalent total bending moment load of a reference wing; the weight of the target wing with high aspect ratio is estimated.
Description
Technical Field
The invention belongs to the field of optimization design of airplane structures, and relates to a method for estimating the weight of a high-aspect-ratio wing.
Background
In the design stage of the airplane scheme, the comprehensive optimization design of aerodynamic appearance, structural arrangement and strength and rigidity of the airplane wings is needed, and the wing weight is an extremely important index for multi-scheme evaluation and comparison. The wing weights of different schemes are estimated by adopting a finite element model method and a conversion coefficient between a model and a real structure. However, the design parameters of the wing are numerous, more possible schemes need to be compared, a finite element method is adopted for all structural schemes in the scheme stage, high estimation accuracy can be obtained, the period is long, the economy is poor, and the continuous change rule of the weight of the wing and the sensitive parameters cannot be given.
Disclosure of Invention
The purpose of the invention is as follows: for the high-aspect-ratio wing, in order to realize rapid evaluation and comparison among different schemes in the scheme stage and provide a continuous change rule between the wing weight and sensitive parameters, a method for rapidly estimating the wing weight based on the engineering beam theory is provided. The weight of the target wing can be estimated by using a simple estimation formula according to the relative relation of geometric parameters, loads and the like between the target wing and the reference wing.
The technical scheme is as follows:
a method of estimating high aspect ratio wing weight, comprising:
equating a target wing with a large aspect ratio and weight to be estimated to an I-shaped cantilever beam with a fixed and supported equal section at one end, and determining the length and the average height of the I-shaped cantilever beam with the equal section; parameters of all sections in the spanwise direction of the I-shaped cantilever beam with the equal sections are completely the same;
the preset reference wing is also equivalent to a reference equal-section I-shaped cantilever beam fixedly supported at one end; determining the length and average height of the reference equal-section I-shaped cantilever beam;
obtaining equivalent total bending moment load of a target wing with a high aspect ratio and equivalent total bending moment load of a reference wing;
and estimating the weight of the high aspect ratio target wing according to the length and the average height of the equal-section I-shaped cantilever beam, the length and the average height of the reference equal-section I-shaped cantilever beam, the equivalent total bending moment load of the high aspect ratio target wing, the equivalent total bending moment load of the reference wing, the material density and the material allowable stress level of the high aspect ratio target wing, the material density and the material allowable stress level of the reference wing and the weight of the reference wing.
Estimating the weight of the high-aspect-ratio target wing according to the length and the height of the equal-section I-shaped cantilever beam, the length and the height of the reference equal-section I-shaped cantilever beam, the equivalent total bending moment load of the high-aspect-ratio target wing, the equivalent total bending moment load of the reference wing, the material density and the allowable material stress level of the high-aspect-ratio target wing, the material density and the allowable material stress level of the reference wing and the weight of the reference wing, wherein the estimating comprises the following steps:
W＝αWRwherein
W is the weight of the target wing with high aspect ratio to be estimated, WRFor reference wing weight, α is the weight proportionality coefficient; m is the equivalent total bending moment load of the target wing with high aspect ratio, MRFor reference of wing equivalent total moment loads, alphaMThe equivalent total bending moment load proportionality coefficient; l is the length of the target wing with high aspect ratio, LRFor reference to the length of the wing, αLIs a length scale factor; h is the average height of the target wing with high aspect ratio, HRFor reference to the average height of the wing, alphaHIs an averaged height scale factor; rho is the density of the target wing material with high aspect ratio, rhoRFor reference to wing material density, αρIs the material density proportionality coefficient; sigma is the allowable stress level of the material of the target wing with high aspect ratio, sigmaRFor reference to permissible stress level of wing material, alphaσAllowing for a stress proportionality coefficient for the material.
The length of the cantilever beam is the connecting line length of 50 percent chord length position of each streamlining section of the wing.
The average height of the wing is the height between the central planes of the upper and lower edge strips of the cantilever beam, namely the ratio of the volume of a space surrounded by the shape of the wing to the projection area of the wing on a chord plane.
Obtaining an equivalent total moment load of the wing, comprising:
averaging the existing aerodynamic and inertial total bending moment load envelope of the wing, namely drawing a curve of the total bending moment along with the relative span length, and then obtaining the area enclosed by the curve and a transverse shaft as the equivalent total bending moment of the wing;
or if the aerodynamic and inertial total bending moment load envelope of the wing does not exist, the maximum bending moment of the wing root section obtained through estimation is used as the equivalent total bending moment of the wing.
In the change curve, the Y axis is the total bending moment, and the X axis is the relative extension.
The estimated reference wings need to select the wings of one reference airplane with similar overall layout and approximately equivalent takeoff weight.
A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the above-mentioned method.
Has the advantages that: the method of the invention adopts a simple estimation formula, can quickly estimate the structural weight of the wing with a large aspect ratio, shortens the scheme evaluation period, saves the design cost, and can provide the continuous change rule between the weight of the wing and the sensitive parameter.
Drawings
FIG. 1 is a schematic view of a high aspect ratio wing;
FIG. 2 is a schematic view of an iso-section I-shaped cantilever;
FIG. 3 is a graph of total bending moment as a function of relative span length.
Detailed Description
The invention provides a method for estimating the weight of a high-aspect-ratio wing, which comprises the following steps:
(1) the I-shaped section cantilever beam is simplified. The target wing with high aspect ratio and needing to estimate the weight is shown in figure 1, and the equivalent constant-section I-shaped cantilever beam with one end fixedly supported is shown in figure 2 (all section parameters in the spanwise direction are identical). Assuming equal areas of the upper and lower edge strips, the area of the web is negligible; the length of the cantilever beam is the connecting line length L of 50 percent chord length position of each streamlining section of the wing; the height between the central planes of the upper and lower edge strips of the cantilever beam is the average height H of the wing, namely the ratio of the volume of a space enclosed by the shape of the wing to the projection area of the wing on a chord plane;
(2) equivalent total moment loading of the wing. The aerodynamic and inertial total bending moment load envelope of the wing is averaged, i.e. a curve of the total bending moment along with the relative span length is drawn (the total bending moment is the Y axis, and the relative span length is the X axis), and then the area enclosed by the curve and the X axis is calculated and obtained as M shown in fig. 3. When the accurate relevant data is not available, the maximum bending moment of the wing root section obtained through estimation can be used as M, and subsequent calculation and analysis can be carried out.
(3) And (4) material performance. The density of the target wing structural material to be estimated is ρ and the allowable stress level is σ.
(4) And selecting a reference wing. Taking the wing of a reference airplane with similar overall layout and approximately equivalent takeoff weight as an estimated reference wing, and knowing the structural weight and relevant geometric physical parameters (wing length L) of the reference wingRAnd the average height HRThe area of the curve of the homogenized total bending moment or the maximum bending moment M of the rootRMaterial density ρRAllowable stress level of material sigmaR)。
(5) The weight of the target wing is estimated. And (3) taking the equivalent I-shaped cantilever beam with the equal section as an object, neglecting the structural bending rigidity and the structural weight of the web plate, and assuming that the gradients of the normal stresses of the upper edge strip and the lower edge strip of the I-shaped cantilever beam in the height direction are zero and the stress levels are equivalent, estimating the weight of the wing.
W＝αWRWherein α ═ αMαLαρ/(αHασ)，αM＝M/MR，αL＝L/LR，αH＝H/HR，αρ＝ρ/ρR，ασ＝σ/σR。
Claims (8)
1. A method for estimating the weight of a high aspect ratio wing, comprising:
equating a target wing with a large aspect ratio and weight to be estimated to an I-shaped cantilever beam with a fixed and supported equal section at one end, and determining the length and the average height of the I-shaped cantilever beam with the equal section; parameters of all sections in the spanwise direction of the I-shaped cantilever beam with the equal sections are completely the same;
the preset reference wing is also equivalent to a reference equal-section I-shaped cantilever beam fixedly supported at one end; determining the length and average height of the reference equal-section I-shaped cantilever beam;
obtaining equivalent total bending moment load of a target wing with a high aspect ratio and equivalent total bending moment load of a reference wing;
and estimating the weight of the high aspect ratio target wing according to the length and the average height of the equal-section I-shaped cantilever beam, the length and the average height of the reference equal-section I-shaped cantilever beam, the equivalent total bending moment load of the high aspect ratio target wing, the equivalent total bending moment load of the reference wing, the material density and the material allowable stress level of the high aspect ratio target wing, the material density and the material allowable stress level of the reference wing and the weight of the reference wing.
2. The method of claim 1, wherein estimating the weight of the high aspect ratio target wing based on the length and height of the constant profile "I" cantilever beam, the length and height of the reference constant profile "I" cantilever beam, the equivalent total bending moment load of the high aspect ratio target wing, the equivalent total bending moment load of the reference wing, the material density and the material allowable stress level of the high aspect ratio target wing, the material density and the material allowable stress level of the reference wing, and the weight of the reference wing comprises:
W＝αWRwherein
W is the weight of the target wing with high aspect ratio to be estimated, WRFor reference wing weight, α is the weight proportionality coefficient; m is the equivalent total bending moment load of the target wing with high aspect ratio, MRFor reference of wing equivalent total moment loads, alphaMThe equivalent total bending moment load proportionality coefficient; l is the length of the target wing with high aspect ratio, LRFor reference to the length of the wing, αLIs a length scale factor; h is the average height of the target wing with high aspect ratio, HRFor reference to the average height of the wing, alphaHIs an averaged height scale factor; rho is the density of the target wing material with high aspect ratio, rhoRFor reference to wing material density, αρIs the material density proportionality coefficient; sigma is the allowable stress level of the material of the target wing with high aspect ratio, sigmaRFor reference to permissible stress level of wing material, alphaσAllowing for a stress proportionality coefficient for the material.
3. The method of claim 2, wherein the cantilever beam has a length that is the length of a line joining 50% of the chord length of each streamwise section of the airfoil.
4. The method of claim 2, wherein the average height of the airfoil is the height between the respective central planes of the upper and lower flanges of the outrigger, i.e., the ratio of the volume of the space enclosed by the profile of the airfoil to the projected area of the airfoil on the chord plane.
5. The method of claim 1, wherein obtaining a wing equivalent total bending moment load comprises:
averaging the existing aerodynamic and inertial total bending moment load envelope of the wing, namely drawing a curve of the total bending moment along with the relative span length, and then obtaining the area enclosed by the curve and a transverse shaft as the equivalent total bending moment of the wing;
or if the aerodynamic and inertial total bending moment load envelope of the wing does not exist, the maximum bending moment of the wing root section obtained through estimation is used as the equivalent total bending moment of the wing.
6. The method of claim 5, wherein the variation is characterized by a total bending moment on the Y-axis and a relative span on the X-axis.
7. The method of claim 1, wherein the estimated reference wings are selected from wings of a reference aircraft having a similar overall layout and a substantially equivalent takeoff weight.
8. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the method according to any one of claims 1 to 7.
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| CN113761667A (en) * | 2021-09-26 | 2021-12-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Empty weight estimation method for supersonic passenger plane |
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