CN111209521B - Double-plane three-channel expansion method for single-plane double-channel pneumatic data - Google Patents
Double-plane three-channel expansion method for single-plane double-channel pneumatic data Download PDFInfo
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- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- G—PHYSICS
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Abstract
The invention provides a double-plane three-channel expansion method of single-plane double-channel six-component pneumatic data, which can acquire double-plane three-channel pneumatic data based on single-plane double-channel axisymmetric pneumatic data. According to the invention, the longitudinal plane resistance coefficient and the rolling moment coefficient are split, a zero-liter coefficient part and an induction coefficient part are obtained, and then the zero-liter coefficient, the longitudinal plane induction coefficient and the lateral plane induction coefficient are synthesized to obtain the corresponding resistance coefficient and the rolling moment coefficient of the body part and the rolling rudder part; and obtaining longitudinal force and moment coefficients in the existing longitudinal plane, and simultaneously obtaining corresponding lateral force and moment coefficients by utilizing axisymmetric characteristics to replace attack angles with sideslip angles and yaw channel rudder deflection to replace pitch channel rudder deflection. The method can be universally applied to various axisymmetric shape guided ammunition which only single-plane double-channel six-component pneumatic data are required but double-plane three-channel six-degree-of-freedom trajectory calculation is required.
Description
Technical Field
The invention belongs to the technical field of pneumatic data, and particularly relates to a double-plane three-channel expansion method of single-plane double-channel six-component pneumatic data.
Background
Pneumatic data sources are generally classified into numerical computation and blowing test, wherein the numerical computation has extremely high requirements on computing resources and takes a long time for a single computing state point, and the blowing test has extremely high cost for a single test state point. Therefore, when project progress or expenditure is tension, the calculation or test state point specification is remarkably reduced by considering that the single-plane double-channel six-component pneumatic data is compared with the double-plane three-channel six-component pneumatic data, so that the pneumatic project group generally only gives the single-plane double-channel six-component pneumatic data. However, in the guided ammunition trajectory six-degree-of-freedom trajectory calculation, the bi-plane three-channel six-component pneumatic data needs to be acquired, so how to acquire the bi-plane three-channel six-component pneumatic data based on the single-plane two-channel six-component axisymmetric pneumatic data needs to be studied.
Disclosure of Invention
In view of the above, the invention provides a double-plane three-channel expansion method for single-plane double-channel six-component pneumatic data, which can acquire double-plane three-channel pneumatic data based on single-plane double-channel axisymmetric pneumatic data.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the invention relates to a biplane three-channel expansion method based on single-plane two-channel six-component pneumatic data, which is characterized in that the single-plane two-channel six-component pneumatic data comprises expansion of a resistance coefficient, a rolling moment coefficient, a longitudinal force coefficient, a longitudinal moment coefficient, a lateral force coefficient and a lateral moment coefficient to obtain the biplane three-channel six-component pneumatic data, wherein the resistance coefficient and the rolling moment coefficient in the existing single longitudinal plane are split into zero liter and an induction part, and then the characteristic quantity of the biplane, namely attack angle and sideslip angle, are taken into consideration in the induction part; and the main components of the lateral force and the moment coefficient in the missing lateral plane are obtained by utilizing axisymmetric characteristics and using sideslip angles to replace attack angles, yaw channel rudder deflection to replace pitch channel rudder deflection and combining rolling channel rudder deflection and zero rudder deflection values in the existing single longitudinal plane.
The specific way of taking the biplane feature quantity, namely the attack angle and the sideslip angle into consideration in the induction part is as follows: and synthesizing the zero-lift resistance coefficient, the longitudinal plane and the lateral plane induced resistance coefficient to obtain the deflection resistance coefficient of the body and the rolling channel rudder, and interpolating to obtain the deflection corresponding resistance coefficients of the pitching and yawing channels rudder.
The beneficial effects are that:
according to the invention, the longitudinal plane resistance coefficient and the rolling moment coefficient are split, a zero-liter coefficient part and an induction coefficient part are obtained, and then the zero-liter coefficient, the longitudinal plane induction coefficient and the lateral plane induction coefficient are synthesized to obtain the corresponding resistance coefficient and the rolling moment coefficient of the body part and the rolling rudder part; and obtaining longitudinal force and moment coefficients in the existing longitudinal plane, and simultaneously obtaining corresponding lateral force and moment coefficients by utilizing axisymmetric characteristics to replace attack angles with sideslip angles and yaw channel rudder deflection to replace pitch channel rudder deflection. The method can be universally applied to various axisymmetric shape guided ammunition which only single-plane double-channel six-component pneumatic data are required but double-plane three-channel six-degree-of-freedom trajectory calculation is required.
Drawings
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a graph of typical six degree of freedom ballistic biplane angles versus three channel rudder deflection curves of the present invention.
Wherein, fig. 2 (a) is a biplane angle curve; fig. 2 (b) is a three-way rudder deflection curve.
FIG. 3 is a graph of typical six degrees of freedom ballistic longitudinal force versus moment coefficient for the present invention.
Wherein, FIG. 3 (a) is a longitudinal force coefficient curve; fig. 3 (b) is a longitudinal force moment coefficient curve.
FIG. 4 is a graph of typical six degrees of freedom ballistic lateral force versus moment coefficient of the present invention.
Wherein, fig. 4 (a) is a lateral force coefficient curve; fig. 4 (b) is a plot of lateral force distance coefficients.
FIG. 5 is a graph of typical six degrees of freedom ballistic drag coefficient versus roll moment coefficient of the present invention.
Wherein, fig. 5 (a) is a drag coefficient curve; fig. 5 (b) is a roll moment coefficient curve.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
According to the method for acquiring the biplane three-channel pneumatic data, the uniplane two-channel axisymmetric pneumatic data are expanded into the biplane three-channel pneumatic data, and the method can be universally applied to various axisymmetric shape guided ammunition which only the uniplane two-channel six-component pneumatic data are required but the biplane three-channel six-degree-of-freedom trajectory calculation is required.
According to the invention, the main components of the corresponding longitudinal force and moment coefficients are obtained by using the attack angle and the rudder deflection and zero rudder deflection values of the existing double channels (pitching channel and rolling channel) in the existing single plane (longitudinal plane); secondly, utilizing axisymmetric characteristics to obtain main components of corresponding lateral force and moment coefficients by using sideslip angles to replace attack angles, yaw channel rudder deflection to replace pitch channel rudder deflection and combining rolling channel rudder deflection and zero rudder deflection values in the existing single longitudinal plane; then splitting the resistance coefficient to obtain a zero-lift coefficient part and an induction coefficient part, and further synthesizing the zero-lift resistance coefficient, the longitudinal plane and the lateral plane induction resistance coefficient to obtain a rudder deflection resistance coefficient of the body of a bullet and a rolling channel, and obtaining a corresponding resistance coefficient of a pitching and yawing channel rudder deflection by the same processing as the above; the rolling moment coefficient and the resistance coefficient are treated in the same way; and finally, carrying out force coefficient, moment coefficient and rudder deflection on the obtained six-component pneumatic data. The biplane three-channel using method based on the biplane two-channel six-component axisymmetric pneumatic data is universal in structure and strong in engineering practice capability, and can be widely applied to various axisymmetric shape guided ammunition which only the monoplane two-channel six-component pneumatic data is required but the biplane three-channel six-degree-of-freedom trajectory calculation is required.
The method specifically comprises the following steps:
the single-plane dual-channel six-component axisymmetric aerodynamic data are generally six force and moment component data in a longitudinal plane (attack angle alpha), a pitching channel (pitching rudder dz), a rolling channel (rolling rudder dx) and are expressed as cx1, cy1, cz1, mx1, my1 and mz1. Wherein, the interpolation table alpha_b is an m-dimensional vector, the Mach number Ma_b is an n-dimensional vector, the dx_b is an x-dimensional vector, and the dz_b is a y-dimensional vector;
the corresponding six-component data cx1_dx, cy1_dx, cz1_dx, mx1_dx, my1_dx, mz1_dx is m x dimension array; cx1_dz, cy1_dz, cz1_dz, mx1_dz, my1_dz, mz1_dz is an m×n×y dimensional array.
Two-dimensional interpolation function is defined as interpolation 2, and three-dimensional interpolation function is defined as interpolation 3.
the three channel resistance coefficients include a hull resistance coefficient, a pitch rudder resistance coefficient, a roll rudder resistance coefficient, and a yaw rudder resistance coefficient.
Compared with the longitudinal force and the lateral force, the body resistance coefficient and the rudder rolling resistance coefficient are special in that the values are generated by biplanes (attack angle alpha and sideslip angle beta), and the biplanes are respectively interpolated and overlapped to cause the error repeated superposition of the zero-liter resistance coefficient, so that the zero-liter resistance coefficient and the induced resistance coefficient in the resistance coefficient are required to be split and extracted, and the zero-liter resistance coefficient is extracted as follows:
the corresponding extraction induced drag coefficients are as follows:
wherein i=1:m, j=1:x.
The body resistance coefficient comprises a zero rudder deflection zero lift resistance coefficient, a zero rudder deflection longitudinal plane induced resistance coefficient and a zero rudder deflection lateral plane induced resistance coefficient, and no lateral plane (sideslip angle beta) is arranged in original pneumatic data, and the zero rudder deflection lateral plane induced resistance coefficient considers axisymmetric pneumatic data characteristics, so that the zero rudder deflection lateral plane induced resistance coefficient is replaced by adopting the sideslip angle beta and the induced resistance coefficient generated by a rolling channel rudder in the zero rudder deflection longitudinal plane, and the body resistance coefficient is comprehensively interpolated as follows:
cx_0＝interp2(Ma_b,dx_b,cx1_dx_ls,Ma,0)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,0)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,0)
the roll rudder resistance coefficient comprises a roll rudder zero-lift resistance coefficient, a roll rudder longitudinal plane induced resistance coefficient and a roll rudder lateral plane induced resistance coefficient, no lateral plane (sideslip angle beta) exists in original aerodynamic data, and the axisymmetric aerodynamic data characteristic is considered, so that the roll rudder lateral plane induced resistance coefficient is replaced by adopting the sideslip angle beta and the roll rudder dx to interpolate the induced resistance coefficient generated by the roll rudder in the longitudinal plane, and the comprehensive interpolation is as follows:
cx_dx＝interp2(Ma_b,dx_b,cx1_dx_ls,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,dx)
the pitch rudder drag coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,0)
the yaw rudder resistance coefficient is generated by a yaw rudder in a longitudinal plane, a yaw channel (yaw rudder dy) is not arranged in the original aerodynamic data, and the characteristics of axisymmetric aerodynamic data are considered, so that the yaw rudder resistance coefficient is replaced by a resistance coefficient generated by a pitch rudder in the longitudinal plane through interpolation of a sideslip angle beta and the yaw rudder dy, and the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,0)
considering drag coefficient pull deflection k cx Rudder efficiency pull-off k dx The resistance coefficients of the comprehensively available biplane three channels are as follows:
cx＝cx_0*k cx +...
[cx_dx-cx_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,0)]*k dx
+...[interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,0)]*k dx
the three-channel longitudinal force coefficient comprises a body longitudinal force coefficient, a pitching rudder longitudinal force coefficient, a rolling rudder longitudinal force coefficient and a yawing rudder longitudinal force coefficient, wherein the body longitudinal force coefficient is generated in a longitudinal plane, and zero rudder deflection values are adopted as follows:
cy_0＝interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,0)
the pitch rudder longitudinal force coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,dz)-cy_0
the roll rudder longitudinal force coefficient is generated by the roll rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dx_b,cy1_dx,α,Ma,dx)-cy_0
the first three terms can be directly interpolated from the single-plane two-channel six-component data. The yaw rudder longitudinal force coefficient is generated by the yaw rudder in the longitudinal plane, a yaw channel (yaw rudder dy) is not arranged in the original aerodynamic data, and the axial symmetry aerodynamic data characteristic is considered, so that the side slip angle beta and the yaw rudder dy are adopted to interpolate the lateral force coefficient generated by the pitch rudder in the longitudinal plane to replace, and the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cz1_dz,-β,Ma,-dy)
consideration of longitudinal force coefficient pull deflection k cy Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is comprehensively obtained as follows:
cy＝cy_0*k cy +...
[interp3(α_b,Ma_b,dx_b,cy1_dx,α,Ma,dx)-cy_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,dz)-cy_0]*k dx +...
interp3(α_b,Ma_b,dz_b,cz1_dz,-β,Ma,-dy)*k dx
the three-channel lateral force coefficients comprise a body lateral force, a yaw rudder lateral force, a roll rudder lateral force and a pitch rudder lateral force, wherein the body lateral force is generated in a lateral plane, no lateral plane (sideslip angle beta) exists in original pneumatic data, and the axisymmetric pneumatic data characteristics are considered, so that the sideslip angle beta is adopted, the longitudinal force coefficient generated by a pitch channel rudder in a longitudinal plane is interpolated as follows:
cz_0＝interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,0)
the yaw rudder lateral force is generated by the yaw rudder in a lateral plane, and the original aerodynamic data have no lateral plane (sideslip angle beta) and yaw channel (yaw rudder dy), and the axial symmetry aerodynamic data characteristics are considered, so that the sideslip angle beta and the yaw rudder dy are adopted to interpolate the longitudinal force coefficient generated by the pitch channel rudder in the longitudinal plane to replace the longitudinal force coefficient, and the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,-dy)-cz_0
the roll rudder lateral force is generated by the roll rudder in a lateral plane, the original aerodynamic data has no lateral plane (sideslip angle beta), and the axisymmetric aerodynamic data characteristics are considered, so that the sideslip angle beta and the roll rudder dx are adopted to interpolate the longitudinal force coefficient generated by the roll channel rudder in the longitudinal plane to replace, and the interpolation is as follows:
interp3(α_b,Ma_b,dx_b,cy1_dx,-β,Ma,dx)-cz_0
the side force of the pitching rudder is generated by the pitching rudder in the longitudinal plane, and can be directly interpolated by single-plane double-channel six-component data as follows:
interp3(α_b,Ma_b,dz_b,cz1_dz,α,Ma,dz)
considering the lateral force coefficient and drawing the offset k cz Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is comprehensively obtained as follows:
cz＝cz_0*k cz +...
[interp3(α_b,Ma_b,dx_b,cy1_dx,-β,Ma,dx)-cz_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,-dy)-cz_0]*k dx +...
interp3(α_b,Ma_b,dz_b,cz1_dz,α,Ma,dz)*k dx
the three-channel rolling moment is composed of a body rolling moment, a pitching rudder rolling moment, a rolling rudder rolling moment and a yawing rudder rolling moment. Compared with the longitudinal moment and the lateral moment, the body roll moment and the roll rudder roll moment are characterized in that the values are generated by biplanes (attack angle alpha and sideslip angle beta), and the error repeated superposition of zero-lift roll moment can be caused by the interpolation superposition of the biplanes respectively, so that the zero-lift roll moment and the induced roll moment in the resistance coefficient are required to be split and extracted, and the zero-lift roll moment coefficient is extracted as follows:
the corresponding extraction induced roll moment coefficients are as follows:
where i=1:m, j=1:x.
The roll moment of the body of the bullet can be composed of three parts, namely zero rudder deflection zero lift moment, zero rudder deflection longitudinal plane induced roll moment and zero rudder deflection lateral plane induced roll moment, and the original pneumatic data do not have a lateral plane (sideslip angle beta), and the axisymmetric pneumatic data characteristics are considered, so that the roll moment is replaced by adopting sideslip angle beta and an induced roll moment coefficient generated by a roll channel rudder in the zero rudder deflection longitudinal plane, and the comprehensive interpolation is as follows:
mx_0＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,0)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,0)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,0)
the roll rudder roll moment can be composed of three parts of zero roll moment of the roll rudder, roll moment induced by a longitudinal plane of the roll rudder and roll moment induced by a lateral plane of the roll rudder, and the original pneumatic data has no lateral plane (sideslip angle beta), and the axisymmetric pneumatic data characteristics are considered, so that the roll moment is replaced by adopting the sideslip angle beta and the roll rudder dx to interpolate the induced roll moment coefficient generated by the roll channel rudder in the longitudinal plane, and the comprehensive interpolation is as follows:
mx_dx＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,dx)
the pitch rudder roll moment is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,0)
the yaw rudder rolling moment is generated by a yaw rudder in a longitudinal plane, a yaw channel (yaw rudder dy) is not arranged in original aerodynamic data, and the axial symmetry aerodynamic data characteristic is considered, so that the yaw angle beta and the yaw rudder dy are used for interpolating a rolling moment coefficient generated by a pitch rudder in the longitudinal plane to replace the rolling moment coefficient, and interpolation is as follows:
interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,0)
considering the rolling moment coefficient and pulling the deflection k cx Rudder efficiency pull-off k dx The three-channel roll torque coefficients are comprehensively obtained as follows:
mx＝mx_0*k mx +...
[mx_dx-mx_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,0)]*k dx
+...[interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,0)]*k dx
the three-channel lateral force distance coefficient comprises a bullet body lateral force distance coefficient, a yaw rudder lateral force distance coefficient, a roll rudder lateral force distance coefficient and a pitch rudder lateral force distance coefficient, wherein the bullet body lateral force distance coefficient is generated in a lateral plane, no lateral plane (sideslip angle beta) exists in original pneumatic data, and the characteristics of axisymmetric pneumatic data are considered, so that the sideslip angle beta is adopted, the longitudinal force distance coefficient generated by a pitch channel rudder in a longitudinal plane is replaced by zero rudder deflection value, and the interpolation is as follows:
my_0＝interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,0)
the yaw rudder lateral force distance coefficient is generated by a yaw rudder in a lateral plane, and the original aerodynamic data have no lateral plane (sideslip angle beta) and yaw channel (yaw rudder dy), and the axial symmetry aerodynamic data characteristic is considered, so that the sideslip angle beta and the yaw rudder dy are adopted to interpolate the longitudinal force distance coefficient generated by a pitch channel rudder in a longitudinal plane to replace the longitudinal force distance coefficient, and the interpolation is as follows:
-interp3(α_b,Ma_b,dz_b,mz1_dz,-β,Ma,-dy)+my_0
the roll rudder lateral force distance coefficient is generated by the roll rudder in a lateral plane, the original aerodynamic data has no lateral plane (sideslip angle beta), and the axisymmetric aerodynamic data characteristic is considered, so that the sideslip angle beta and the roll rudder dx are adopted to interpolate the longitudinal force distance coefficient generated by the roll channel rudder in a longitudinal plane to replace the longitudinal force distance coefficient, and the interpolation is as follows:
-interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,dx)+my_0
the pitch rudder side moment coefficient is generated by the pitch rudder in the longitudinal plane, and can be directly interpolated by single-plane double-channel six-component data as follows:
-interp3(α_b,Ma_b,dz_b,my1_dz,α,Ma,dz)
consider the lateral moment coefficient to pull the deflection k my Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is comprehensively obtained as follows:
my＝-my_0*k my -...
[interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,dx)-my_0]*k dx -...
[interp3(α_b,Ma_b,dz_b,mz1_dz,-β,Ma,-dy)-my_0]*k dx -...
interp3(α_b,Ma_b,dz_b,my1_dz,α,Ma,dz)*k dx
the three-channel longitudinal force and distance coefficient comprises a body longitudinal force and distance coefficient, a pitch rudder longitudinal force and distance coefficient, a roll rudder longitudinal force and distance coefficient and a yaw rudder longitudinal force and distance coefficient, wherein the body longitudinal force and distance coefficient is only generated in a longitudinal plane, and zero rudder deflection values are adopted as follows:
mz_0＝interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,0)
the pitch rudder longitudinal moment coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,dz)-mz_0
the roll rudder longitudinal moment coefficient is generated by the roll rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dx_b,mz1_dx,α,Ma,dx)-mz_0
the yaw rudder longitudinal force distance coefficient is generated by the yaw rudder in a longitudinal plane, a yaw channel (yaw rudder dy) is not arranged in the original aerodynamic data, and the axial symmetry aerodynamic data characteristic is considered, so that the side slip angle beta and the yaw rudder dy are adopted to interpolate the lateral force distance coefficient generated by the pitch channel rudder in the longitudinal plane to replace, and the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,my1_dz,-β,Ma,-dy)
considering longitudinal moment coefficient pull deflection k mz Rudder efficiency pull-off k dx The longitudinal force and distance coefficients of the three channels can be obtained comprehensively as follows:
mz＝mz_0*k mz +...
[interp3(α_b,Ma_b,dx_b,mz1_dx,α,Ma,dx)-mz_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,dz)-mz_0]*k dx +...
interp3(α_b,Ma_b,dz_b,my1_dz,-β,Ma,-dy)*k dx
wherein, each step sequence from step 2 to step 7 is interchangeable.
The method combines a certain guided rocket weapon system, gives out single-plane double-channel six-component data based on aerodynamic CFD numerical calculation, adopts a double-plane three-channel aerodynamic data acquisition method, and specifically comprises the following steps:
alpha_b= [ -16-14-12-10-8-6-4-2 0 2 4 6 8 10 12 14 16] is a 17-dimensional vector;
ma_b= [0.4 0.7 0.9 1.15 1.5 2 2.5 3 4] is a 9-dimensional vector;
dx_b= [ -10 0 10] is a 3-dimensional vector;
dz_b= [ -20-15-10-5 0 5 10 15 20] is a 9-dimensional vector;
cx1_dx, cy1_dx, cz1_dx, mx1_dx, my1_dx, mz1_dx is a 17 x 9 x 3 d array;
cx1_dz, cy1_dz, cz1_dz, mx1_dz, my1_dz, mz1_dz is a 17 x 9 dimension array;
cx＝cx_0*k cx +...
[cx_dx-cx_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,0)]*k dx
+...[interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,0)]*k dx
wherein cx1_dx_yd (i, j) =cx1_dx (i, j) -cx1_dx (9, j),
cx_0＝dinterp2(Ma_b,dx_b,cx1_dx_ls,Ma,0)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,0)+...，
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,0)
cx_dx＝interp2(Ma_b,dx_b,cx1_dx_ls,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,dx)+...。
interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,dx)
cy＝cy_0*k cy +...
[interp3(α_b,Ma_b,dx_b,cy1_dx,α,Ma,dx)-cy_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,dz)-cy_0]*k dx +...
interp3(α_b,Ma_b,dz_b,cz1_dz,-β,Ma,-dy)*k dx
where cy_0=inter 3 (α_b, ma_b, dx_b, cy1_dx, α, ma, 0).
cz＝cz_0*k cz +...
[interp3(α_b,Ma_b,dx_b,cy1_dx,-β,Ma,dx)-cz_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,-dy)-cz_0]*k dx +...
interp3(α_b,Ma_b,dz_b,cz1_dz,α,Ma,dz)*k dx
where cz—0=inter 3 (α_b, ma_b, dx_b, cy1_dx, - β, ma, 0).
mx＝mx_0*k mx +...
[mx_dx-mx_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,0)]*k dx
+...[interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,0)]*k dx wherein mx1_dx_yd (i, j) =mx1_dx (i, j) -mx1_dx (9, j),
mx_0＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,0)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,0)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,0)，
mx_dx＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,dx)+...
interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,dx)。
my＝-my_0*k my -...
[interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,dx)-my_0]*k dx -...
[interp3(α_b,Ma_b,dz_b,mz1_dz,-β,Ma,-dy)-my_0]*k dx -...
interp3(α_b,Ma_b,dz_b,my1_dz,α,Ma,dz)*k dx
where my—0=inter 3 (α_b, ma_b, dx_b, mz1_dx, - β, ma, 0).
mz＝mz_0*k mz +...
[interp3(α_b,Ma_b,dx_b,mz1_dx,α,Ma,dx)-mz_0]*k dx +...
[interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,dz)-mz_0]*k dx +...
interp3(α_b,Ma_b,dz_b,my1_dz,-β,Ma,-dy)*k dx
where mz0=inter 3 (α_b, ma_b, dx_b, mz1_dx, α, ma, 0).
In order to verify the effectiveness of the method, axisymmetric guided rocket biplane three-channel six-degree-of-freedom trajectory deflection calculation is performed by using single-plane two-channel six-component pneumatic data, and curves from fig. 2 to fig. 5 are obtained through digital simulation, wherein fig. 2 is a typical six-degree-of-freedom trajectory biplane angle and three-channel rudder deflection curve, fig. 3 is a typical six-degree-of-freedom trajectory longitudinal force coefficient and moment coefficient curve, fig. 4 is a typical six-degree-of-freedom trajectory lateral force and moment coefficient curve, and fig. 5 is a typical six-degree-of-freedom trajectory resistance coefficient and rolling moment coefficient curve. The calculation of the resistance and roll moment coefficients is compared with the traditional method for generating the body resistance and roll moment coefficients by only considering the single plane attack angle. From the simulation results, it can be seen that: the biplane three-channel using method based on the biplane two-channel six-component axisymmetric pneumatic data ensures six-degree-of-freedom ballistic calculation of guided munitions and reflects the resistance and rolling moment coefficient characteristics more truly than the traditional method.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A biplane three-channel expansion method based on single-plane two-channel six-component pneumatic data is characterized in that the single-plane two-channel six-component pneumatic data comprises expansion of a resistance coefficient, a rolling moment coefficient, a longitudinal force coefficient, a longitudinal moment coefficient, a lateral force coefficient and a lateral moment coefficient to obtain the biplane three-channel six-component pneumatic data, wherein the existing single-longitudinal-plane resistance coefficient and the rolling moment coefficient are split into zero liter and an induction part, and then the characteristic quantity of the biplane, namely an attack angle alpha and a sideslip angle beta, are taken into consideration in the induction part; the axisymmetric characteristic is utilized to replace attack angle with sideslip angle, yaw channel rudder bias replaces pitch channel rudder bias in the existing single longitudinal plane, and lateral force and moment coefficient main components in the missing lateral plane are obtained by combining roll channel rudder bias and zero rudder bias interpolation;
the method specifically comprises the following steps:
step 1, analyzing single-plane double-channel six-component pneumatic data to obtain corresponding six-component data;
the single-plane double-channel six-component axisymmetric pneumatic data are in the form of six force and moment component data of a longitudinal plane, a pitching channel and a rolling channel, and are expressed as cx1, cy1, cz1, mx1, my1 and mz1; the pitching channel is represented by a pitching rudder dz, the rolling channel is represented by a rolling rudder dx, the interpolation number alpha_b is an m-dimensional vector, the Mach number Ma_b is an n-dimensional vector, the dx_b is an x-dimensional vector, and the dz_b is a y-dimensional vector;
the corresponding six-component data cx1_dx, cy1_dx, cz1_dx, mx1_dx, my1_dx, mz1_dx is m x dimension array; cx1_dz, cy1_dz, cz1_dz, mx1_dz, my1_dz, mz1_dz is m x n x y dimensional array;
defining a two-dimensional interpolation function as an interpolation 2, and defining a three-dimensional interpolation function as an interpolation 3;
step 2, obtaining a resistance coefficient of the double-plane three-channel:
the three-channel resistance coefficient comprises a hull resistance coefficient, a pitching rudder resistance coefficient, a rolling rudder resistance coefficient and a yawing rudder resistance coefficient; and splitting and extracting zero liter resistance coefficients and induction resistance coefficients in the resistance coefficients, wherein the extracted zero liter resistance coefficients are as follows:
the corresponding extraction induced drag coefficients are as follows:
wherein i=1:m, j=1:x;
the body resistance coefficient comprises a zero rudder deflection zero lift resistance coefficient, a zero rudder deflection longitudinal plane induced resistance coefficient and a zero rudder deflection lateral plane induced resistance coefficient, the body resistance coefficient adopts an induced resistance coefficient generated by a roll channel rudder in a sideslip angle and zero rudder deflection longitudinal plane to replace the zero rudder deflection lateral plane induced resistance coefficient, and the body resistance coefficient is comprehensively interpolated as follows:
cx_0＝interp2(Ma_b,dx_b,cx1_dx_ls,Ma,0)+...interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,0)+...interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,0)
the roll rudder resistance coefficient comprises a roll rudder zero-lift resistance coefficient, a roll rudder longitudinal plane induced resistance coefficient and a roll rudder lateral plane induced resistance coefficient, the roll rudder lateral plane induced resistance coefficient is replaced by adopting the induced resistance coefficient generated by a roll channel rudder in the roll rudder dx interpolation longitudinal plane of the sideslip angle beta, and the comprehensive interpolation is as follows:
cx_dx＝interp2(Ma_b,dx_b,cx1_dx_ls,Ma,dx)+...interp3(α_b,Ma_b,dx_b,cx1_dx_yd,α,Ma,dx)+...interp3(α_b,Ma_b,dx_b,cx1_dx_yd,-β,Ma,dx)
the pitch rudder drag coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,0)
the yaw rudder resistance coefficient is generated by a yaw rudder in a longitudinal plane, and the yaw rudder resistance coefficient is replaced by a resistance coefficient generated by a pitch rudder in the longitudinal plane through interpolation of a sideslip angle beta and the yaw rudder dy, wherein the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,0)
considering drag coefficient pull deflection k cx Rudder efficiency pull-off k dx Obtaining a biplane three-way resistance systemThe numbers are as follows:
cx＝cx_0*k cx +...[cx_dx-cx_0]*k dx +...[interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,cx1_dz,-β,Ma,0)]*k dx +...[interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,cx1_dz,α,Ma,0)]*k dx
step 3, obtaining three-channel longitudinal force coefficients:
the three-channel longitudinal force coefficient comprises a body longitudinal force coefficient, a pitching rudder longitudinal force coefficient, a rolling rudder longitudinal force coefficient and a yawing rudder longitudinal force coefficient, wherein the body longitudinal force coefficient is generated in a longitudinal plane, and zero rudder deflection values are adopted as follows:
cy_0＝interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,0)
the pitch rudder longitudinal force coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,dz)-cy_0
the roll rudder longitudinal force coefficient is generated by the roll rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dx_b,cy1_dx,α,Ma,dx)-cy_0
the first three items are obtained by direct interpolation of single-plane double-channel six-component data; the yaw rudder longitudinal force coefficient is replaced by a lateral force coefficient generated by a pitch rudder in a longitudinal plane through interpolation of a sideslip angle beta and a yaw rudder dy, and the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cz1_dz,-β,Ma,-dy)
consideration of longitudinal force coefficient pull deflection k cy Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is obtained as follows:
cy＝cy_0*k cy +...[interp3(α_b,Ma_b,dx_b,cy1_dx,α,Ma,dx)-cy_0]*k dx +...[interp3(α_b,Ma_b,dz_b,cy1_dz,α,Ma,dz)-cy_0]*k dx +...interp3(α_b,Ma_b,dz_b,cz1_dz,-β,Ma,-dy)*k dx
step 4, obtaining a biplane three-channel lateral force coefficient:
the three-channel lateral force coefficient comprises a body lateral force, a yaw rudder lateral force, a roll rudder lateral force and a pitch rudder lateral force, wherein the body lateral force is replaced by a sideslip angle beta, and a longitudinal force coefficient generated by a pitch channel rudder in a zero rudder deflection value longitudinal plane is interpolated as follows:
cz_0＝interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,0)
the yaw rudder lateral force is generated by a yaw rudder in a lateral plane, and a longitudinal force coefficient generated by a pitch channel rudder in a longitudinal plane is interpolated by the yaw rudder and the yaw angle beta, wherein the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,-dy)-cz_0
the roll rudder lateral force is generated by the roll rudder in a lateral plane, and is replaced by a longitudinal force coefficient generated by a roll channel rudder in a longitudinal plane by interpolation of a sideslip angle beta and the roll rudder dx, wherein the interpolation is as follows:
interp3(α_b,Ma_b,dx_b,cy1_dx,-β,Ma,dx)-cz_0
the pitch rudder side force is generated by the pitch rudder in the longitudinal plane, and is directly interpolated by the single-plane double-channel six-component data as follows: interp3 (α_b, ma_b, dz_b, cz1_dz, α, ma, dz)
Considering the lateral force coefficient and drawing the offset k cz Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is obtained comprehensively as follows:
cz＝cz_0*k cz +...[interp3(α_b,Ma_b,dx_b,cy1_dx,-β,Ma,dx)-cz_0]*k dx +...[interp3(α_b,Ma_b,dz_b,cy1_dz,-β,Ma,-dy)-cz_0]*k dx +...interp3(α_b,Ma_b,dz_b,cz1_dz,α,Ma,dz)*k dx
step 5, obtaining a double-plane three-channel rolling moment coefficient:
the three-channel rolling moment is composed of a body rolling moment, a pitching rudder rolling moment, a rolling rudder rolling moment and a yawing rudder rolling moment. And splitting and extracting zero lifting rolling moment and induced rolling moment in the resistance coefficient, wherein the extraction of the zero lifting rolling moment coefficient is as follows:
the corresponding extraction induced roll moment coefficients are as follows:
wherein i=1:m, j=1:x;
the roll moment of the body of a bullet is replaced by an induced roll moment coefficient generated by a roll channel rudder in a longitudinal plane through sideslip angle beta and zero rudder deflection value, and the comprehensive interpolation is as follows:
mx_0＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,0)+...interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,0)+...interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,0)
the roll rudder roll moment is replaced by an induced roll moment coefficient generated by a roll channel rudder in a longitudinal plane through interpolation of a sideslip angle beta and a roll rudder dx, and the comprehensive interpolation is as follows:
mx_dx＝interp2(Ma_b,dx_b,mx1_dx_ls,Ma,dx)+...interp3(α_b,Ma_b,dx_b,mx1_dx_yd,α,Ma,dx)+...interp3(α_b,Ma_b,dx_b,mx1_dx_yd,-β,Ma,dx)
the pitch rudder roll moment is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,0)
the yaw rudder rolling moment is generated by a yaw rudder in a longitudinal plane, and the rolling moment coefficient generated by a pitch rudder in the longitudinal plane is interpolated by using a sideslip angle beta and the yaw rudder dy, wherein the interpolation is as follows:
interp3 (α_b, ma_b, dz_b, mx1_dz, - β, ma, -dy) -Interp3 (α_b, ma_b, dz_b, mx1_dz, - β, ma, 0) takes into account the roll moment coefficient pull bias k cx Rudder efficiency pull-off k dx The three-channel rolling moment coefficients are comprehensively obtained as follows:
mx＝mx_0*k mx +...[mx_dx-mx_0]*k dx +...[interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,-dy)-interp3(α_b,Ma_b,dz_b,mx1_dz,-β,Ma,0)]*k dx +...[interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,dz)-interp3(α_b,Ma_b,dz_b,mx1_dz,α,Ma,0)]*k dx
step 6, obtaining a biplane three-channel lateral force distance coefficient:
the three-channel lateral force distance coefficient comprises a body lateral force distance coefficient, a yaw rudder lateral force distance coefficient, a roll rudder lateral force distance coefficient and a pitch rudder lateral force distance coefficient, wherein the body lateral force distance coefficient is generated in a lateral plane, a sideslip angle beta is adopted, a longitudinal force distance coefficient generated by a pitch channel rudder in a longitudinal plane is replaced by a zero rudder deflection value, and the interpolation is as follows:
my_0＝interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,0)
the yaw rudder lateral force distance coefficient is generated by a yaw rudder in a lateral plane, and is replaced by a longitudinal force distance coefficient generated by a pitch channel rudder in a longitudinal plane by interpolation of a sideslip angle beta and the yaw rudder dy, wherein the interpolation is as follows:
-interp3(α_b,Ma_b,dz_b,mz1_dz,-β,Ma,-dy)+my_0
the roll rudder lateral force distance coefficient is generated by the roll rudder in a lateral plane, and is replaced by a longitudinal force distance coefficient generated by a roll channel rudder in a longitudinal plane by interpolation of a sideslip angle beta and the roll rudder dx, wherein the interpolation is as follows:
-interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,dx)+my_0
the pitch rudder side moment coefficient is generated by the pitch rudder in the longitudinal plane, and is obtained by direct interpolation of single-plane double-channel six-component data as follows:
-interp3(α_b,Ma_b,dz_b,my1_dz,α,Ma,dz)
consider the lateral moment coefficient to pull the deflection k my Rudder efficiency pull-off k dx The three-channel longitudinal force coefficient is obtained comprehensively as follows:
my＝-my_0*k my -...[interp3(α_b,Ma_b,dx_b,mz1_dx,-β,Ma,dx)-my_0]*k dx -...[interp3(α_b,Ma_b,dz_b,mz1_dz,-β,Ma,-dy)-my_0]*k dx -...interp3(α_b,Ma_b,dz_b,my1_dz,α,Ma,dz)*k dx
step 7, obtaining a biplane three-channel longitudinal force distance coefficient:
the three-channel longitudinal force and distance coefficient comprises a body longitudinal force and distance coefficient, a pitch rudder longitudinal force and distance coefficient, a roll rudder longitudinal force and distance coefficient and a yaw rudder longitudinal force and distance coefficient, wherein the body longitudinal force and distance coefficient is only generated in a longitudinal plane, and zero rudder deflection values are adopted as follows:
mz_0＝interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,0)
the pitch rudder longitudinal moment coefficient is generated by the pitch rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,dz)-mz_0
the roll rudder longitudinal moment coefficient is generated by the roll rudder in the longitudinal plane, interpolated as follows:
interp3(α_b,Ma_b,dx_b,mz1_dx,α,Ma,dx)-mz_0
the yaw rudder longitudinal force and distance coefficient is generated by a yaw rudder in a longitudinal plane, and the yaw angle beta and the yaw rudder dy are used for interpolating the lateral force and distance coefficient generated by a pitch channel rudder in the longitudinal plane to replace the lateral force and distance coefficient, wherein the interpolation is as follows:
interp3(α_b,Ma_b,dz_b,my1_dz,-β,Ma,-dy)
considering longitudinal moment coefficient pull deflection k mz Rudder efficiency pull-off k dx The longitudinal force-distance coefficients of the three channels are comprehensively obtained as follows:
mz＝mz_0*k mz +...[interp3(α_b,Ma_b,dx_b,mz1_dx,α,Ma,dx)-mz_0]*k dx +...[interp3(α_b,Ma_b,dz_b,mz1_dz,α,Ma,dz)-mz_0]*k dx +...interp3(α_b,Ma_b,dz_b,my1_dz,-β,Ma,-dy)*k dx
wherein, each step sequence from step 2 to step 7 is interchangeable.
2. The expansion method of the biplane three channels based on the single plane two-channel six-component pneumatic data according to claim 1, wherein the specific way of taking the biplane characteristic quantity, namely the attack angle and the sideslip angle into consideration in the induction part is as follows: and synthesizing the zero-lift resistance coefficient, the longitudinal plane and the lateral plane induced resistance coefficient to obtain the deflection resistance coefficient of the body and the rolling channel rudder, and interpolating to obtain the deflection corresponding resistance coefficients of the pitching and yawing channels rudder.
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