CN112896551A - Auxiliary calibration method for installation of aircraft avionics equipment - Google Patents
Auxiliary calibration method for installation of aircraft avionics equipment Download PDFInfo
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Abstract
The invention relates to the technical field of aircraft assembly, in particular to a calibration auxiliary method for installation of aircraft avionics equipment, which comprises the steps of calculating the simulated pose coordinate of an adjusting point by resolving the simulated pose coordinate of the avionics equipment based on a pitch angle and a roll angle; solving a gasket specification model selection optimal scheme of an adjusting point through pose adjustment optimization; finally, the gasket adjustment is carried out according to the optimal embodiment. By the method, the problems of low efficiency, high labor intensity and large artificial error can be effectively solved.
Description
Technical Field
The invention relates to the technical field of aircraft assembly, in particular to a calibration auxiliary method for installation of aircraft avionics equipment.
Background
The calibration work of the installation pose of the aircraft avionics equipment is very important for the performance of the efficiency of the aircraft avionics equipment. The current installation pose calibration work is usually carried out by adopting a method of measuring and adjusting multiple rounds of repetition and successive iteration. Each iteration needs to install a calibration tool, observe the position of the center of the cross reticle in the collimating telescope on the target circle, analyze and calculate the deflection angle of the avionic device, disassemble the tool and adjust the gasket, and finally install the tool and observe the position of the center of the cross reticle in the collimating telescope on the target circle.
The main work content comprises:
(1) yaw angle calibration adjustment
A worker observes the position of the center of the cross in the collimating telescope on the target circle by slightly moving the equipment base, finally adjusts the center of the cross to be close to the center of the target circle, marks the adjusting position of the avionic equipment base by scribing, and completes course adjustment.
(2) Pitch and roll calibration adjustment
The pitching and rolling adjustment difficulty is high, workers can assemble, disassemble and assemble the calibration tool by observing the position of the cross center of the collimating telescope on the target circle on the calibration tool, try to increase and decrease gaskets with different thicknesses at different adjusting points by combining experience and analysis of the deflection angle, recover to assemble the calibration tool, continue to observe the position change of the cross center, repeatedly disassemble and assemble the calibration tool and adjust the quantity and thickness of the gaskets, and finally adjust the pitch angle and the roll angle to the technical indexes.
The adjusting gasket is used for calculating the deflection angle of the avionics equipment according to analysis and increasing and decreasing gaskets with different specifications at different adjusting points according to experience. The set points are located on the equipment mounting base, A, B, C being three set points. The gasket thickness is typically 0.1, 0.2, 0.5 or 0.8 mm. The current method needs multiple iterations, and the iteration times are uncontrollable due to the problems of visual observation errors, insufficient experience of operators and the like, and the working efficiency is low.
Disclosure of Invention
In order to solve the technical problems, the invention provides a calibration auxiliary method for mounting aircraft avionics equipment, which can effectively solve the problems of low efficiency, high labor intensity and large artificial error by automatically calculating the simulation pose coordinates of the adjusting points and solving the specification selection of the washers of the adjusting points.
The invention is realized by adopting the following technical scheme:
an auxiliary calibration method for installation of aircraft avionics equipment is characterized by comprising the following steps: the method comprises the following steps:
a. installing a calibration tool;
b. reading a pitch angle omega and a roll angle lambda;
c. calculating the simulation pose coordinate of the adjusting point through avionics equipment simulation pose coordinate calculation based on the pitch angle and the roll angle;
d. solving a gasket specification model selection optimal scheme of the adjusting points by using the simulated pose coordinates of the adjusting points obtained by calculation and by pose adjustment optimization;
e. and disassembling the calibration tool, and adjusting the gasket according to the optimal scheme.
The step c specifically comprises the following steps:
c1connecting three adjusting points A, B and C on the mounting base to determine a plane ABC, and determining a normal vector of the plane ABC according to the pitch angle omega and the roll angle lambda
Solving is carried out to obtain the normal vector of the plane ABC
；
c2Let B adjust point locate at coordinate origin, Y axis direction be aircraft course direction, let xC=xB=0；
c3I.e. B = (x)B，yB，zB）=（0，0，0），C=（xC，yC，zC）=（0，yC，zC），A=（xA，yA，zA) Then, there is a system of equations:
wherein a and B are known quantities, a is the square of the distance between the adjusting point A and the adjusting point B and the distance between the adjusting point A and the adjusting point C, and B is the square of the distance between the adjusting point B and the adjusting point C, and the unit is mm2；
c4The specific equation is as follows:
solving a set of A, C coordinate values satisfying the condition, namely B = (0, 0, 0) and the solved A = (x) according to the equationA，yA，zA）、C=（0，yC，zC）。
Said step c1The method specifically comprises the following steps:
c11abstracting the installation base to be a plane ABC, wherein the pitch angle is an included angle omega between the projection of a normal vector of the plane ABC on the YOZ surface and the Z axis under the aircraft coordinate, and the roll angle is an included angle lambda between the projection of a normal vector of the plane ABC on the XOZ surface and the Z axis under the aircraft coordinate;
c12making an included angle omega between the auxiliary plane alpha and the Z axis, wherein the auxiliary plane alpha is vertical to the plane YOZ and the plane alpha equation is as follows: y-z · tan ω =0, normal vector
；
c13Making an included angle lambda between an auxiliary plane beta and a beta vertical plane XOZ and a Z axis, wherein the plane beta equation is as follows: x-z · tan λ =0, normal vector
；
c14Normal vector of plane ABC
Calculating the normal vector of the plane ABC for the intersection direction of the plane alpha and the plane beta
。
The step d specifically comprises the following steps:
d1a, B, C solving for the adjustment of the setpoint;
d2solving for a minimum gasket combination number.
Said step d1The method specifically comprises the following steps:
d11from the simulated pose coordinates of the adjustment points, i.e.:
A=（xA，yA，zA）、B=（0，0，0）、C=（0，yC，zC) And the point C is the coordinate of a point which is close to the adjusting point of the machine head side, and the coordinate after the adjustment by adding the gasket is as follows:
A′=(xA′，yA′，zA′)=（xA，yA，zA+TA），
B′=(xB′，yB′，zB′)=（0，0，TB），
C′=(xC′，yC′，zC′)=（0，yC，zC+TC），
wherein, TA、TB、TCA, B, C, the adjustment amount of each adjustment point is less than 3mm, let TA=0.1k1，TB=0.1k2，TC=0.1k3And k is1、k2、k3Is a non-negative integer no greater than 30;
d12establishing an objective function:
wherein the content of the first and second substances,
，zA′=zA+0.1k1，zB′=0.1k2，zC′=zC+0.1k3substituting to obtain information about the variable k1、k2、k3The objective function of (1);
d13setting the constraint conditions:
wherein m = -xA，n=yC-yA，p=-xA，q=-yA，xA、yA、zA、yCAnd zCThe value of the signal is known and,
HA′B′=zA-zB+0.1(k1-k2)，
HA′C′=zA–zC+0.1(k1-k3)，
substituting into the constraint to obtain the variable k1、k2、k3The constraint function of (2);
d14solving the optimal solution of the objective function according to the constraint condition.
Said step d14The method specifically comprises the following steps:
step 1: given S2Setting an initial value S2 0=1000；
Step 2: traverse k1、k2、k3=int，0≤k1、k2、k3All values less than 30 are substituted into the constraint condition, and the total traversal 30 is carried out3(ii) a condition; wherein int refers to the integer;
step 3: determining the obtained k1、k2、k3Whether all constraints are satisfied, if so, k at that time1、k2、k3Substituting the value of (A) into the objective function, entering the next step, otherwise, continuing to obtain the target functionCirculating;
step 4: judging whether S is present2 i＜S2 i-1If true, the objective function is assigned a value of S2 iOtherwise, continue to loop through all k1、k2、k3After the value is taken, k which enables the objective function to be minimum is finally obtained1、k2、k3And taking the value of an integer.
Said step d2The solving of the minimum gasket combination number specifically comprises the following steps:
d21according to step d1The adjustment amount of each adjustment point obtained by the solution in (1), namely TA=0.1k1=t1，TB=0.1k2=t2，TC=0.1k3=t3；
d22Order:
t1=0.1a1+0.2b1+0.5c1+0.8d1，
t2=0.1a2+0.2b2+0.5c2+0.8d2，
t3=0.1a3+0.2b3+0.5c3+0.8d3，
wherein, ai、bi、ci、diI =1, 2, 3, the parameter represents the number of washers with different specifications at different adjusting points, and 0.1, 0.2, 0.5, 0.8 are the specifications of the washers respectively;
d23establishing an objective function: gi=min(ai+bi+ci+di) I is an adjustment point;
d24setting the constraint conditions:
ti=0.1ai+0.2bi+0.5ci+0.8di；
d25solving the optimal solution of the objective function according to the constraint condition.
Said step d25The solving method of (2) is as follows:
Step1：ai=INT(ti/0.8)；
step 2: judgment of mu1=MOD（ti0.8) is zero, if it is, Gi=aiOtherwise, entering the next step;
Step3：bi=INT(μ1/0.5)；
step 4: judgment of mu2=MOD（μ10.5) is zero, if it is, Gi=ai+biOtherwise, entering the next step;
Step5：ci=INT(μ2/0.2)；
step 6: judgment of mu3=MOD（μ20.2) is zero, if it is, Gi=ai+bi+ciOtherwise, entering the next step;
Step7：di=INT(μ30.1), then Gi=ai+bi+ci+diSo as to obtain the quantity of the washers with different specifications at each adjusting point;
wherein INT denotes the integer: the integer part of the result obtained by dividing the two numbers, MOD being the remainder: the fractional part of the result of the division of the two numbers is multiplied by the divisor.
Compared with the prior art, the invention has the beneficial effects that:
1. the auxiliary method can quickly form an optimal gasket adjusting scheme through automatic calculation, guides pose calibration operation, enables single adjustment to meet the requirement of installation technical indexes, does not need multiple iterations, is high in efficiency, and can effectively solve the problem that iteration times are uncontrollable due to naked eye observation errors, insufficient experience of operators and the like.
2. An accurate optimized mathematical model is established according to the actual condition of the equipment cushioning adjustment quantity, an optimized equation is solved by a node traversing method, and a global optimal solution can be found at reasonable calculation cost.
3. In the method, the purpose of least resource configuration is adopted, an optimized model is established according to the constraint relation between the gasket specification and the adjustment amount, and the optimal gasket configuration global optimal scheme is solved according to the principle that the gasket specification is large first and then small.
4. In the method, a set of coordinates of the adjusting points A and B, C are determined according to the read pitch angle omega and roll angle lambda to simulate the pose of the avionics equipment base, so that basic data are provided for a subsequent washer adjusting method, the data source is more accurate, and the accuracy of a subsequent calculation result is ensured.
5. In the method, a group of simulation coordinates of the attitude of the installation base are given by the normal vector of the plane ABC, so that the problem that the specific coordinates of the adjusting point relative to the aircraft coordinate system cannot be obtained can be effectively solved.
6. In the method, the gasket adjusting algorithm specifically comprises the steps of solving the adjusting quantity of the adjusting pad and solving the minimum gasket combination number, so that the result is more accurate.
Drawings
The invention will be described in further detail with reference to the following description taken in conjunction with the accompanying drawings and detailed description, in which:
FIG. 1 is a schematic flow diagram of the present invention;
FIG. 2 is a schematic diagram of a simulation coordinate system and adjustment points according to the present invention;
FIG. 3 is a schematic diagram of determining a plane ABC normal vector in the present invention.
Detailed Description
Example 1
As a basic embodiment of the invention, the invention comprises a calibration assistance method for the installation of an aircraft avionics device, comprising the following steps:
a. and (6) installing a calibration tool.
b. Observing the position of the center of a cross reticle in the collimating telescope on a target circle, and reading a pitch angle omega and a roll angle lambda; the pitch angle is an included angle omega between the projection of a normal vector of a plane where the avionics equipment base is located on an YOZ plane and a Z axis under the aircraft coordinate; the roll angle is an included angle lambda between the projection of a normal vector of a plane where the avionics device base is located and an XOZ plane under the aircraft coordinate and a Z axis.
c. And calculating the simulation pose coordinate of the adjusting point by the avionics equipment simulation pose coordinate calculation based on the pitch angle and the roll angle.
d. And solving the optimal gasket specification model selection scheme of the adjusting points by using the simulated pose coordinates of the adjusting points obtained by calculation and by pose adjustment optimization.
e. And disassembling the calibration tool, and implementing gasket adjustment according to the optimal scheme to finish calibration.
Example 2
As a preferred embodiment of the invention, the invention comprises a calibration assistance method for the installation of an aircraft avionics device, with reference to the attached figure 1 of the specification, comprising the following steps:
a. and (6) installing a calibration tool.
b. The pitch angle ω and roll angle λ are read.
c. And calculating the simulation pose coordinate of the adjusting point by the avionics equipment simulation pose coordinate calculation based on the pitch angle and the roll angle. The method comprises the following specific steps:
c1three set points A, B on the mounting base are connected to a plane ABC, defined as reference to the description of FIG. 2 and the description of FIG. 3, (where point A is not necessarily in the plane XOY; point C is in the YOZ plane, but not necessarily in the Y axis, since the yaw angle has been calibrated). Normal vector to plane ABC according to pitch angle omega and roll angle lambda
Solving is carried out for describing the space state of the installation base, and the method specifically comprises the following steps:
c11abstracting the installation base to be a plane ABC, wherein the pitch angle is an included angle omega between the projection of a normal vector of the plane ABC on the YOZ surface and the Z axis under the aircraft coordinate, and the roll angle is an included angle lambda between the projection of a normal vector of the plane ABC on the XOZ surface and the Z axis under the aircraft coordinate;
c12making an included angle omega between the auxiliary plane alpha and the auxiliary plane alpha vertical to the plane YOZ and the Z axis, and according to the definition of the pitch angle, obtaining a plane alpha equation as follows: y-z @ tan ω =0, normal vector
；
c13Making an included angle lambda between the auxiliary plane beta and the auxiliary plane beta vertical to the XOZ and the Z axis, and according to the roll angle definition, obtaining a plane beta equation as follows: x-z. tan. lambda =0, normal vector
；
c14Normal vector of plane ABC
Calculating the normal vector of the plane ABC for the intersection direction of the plane alpha and the plane beta
。
c2A, B, C for three adjustment points on the mounting base, since no specific coordinates of the adjustment points are available with respect to the aircraft coordinate system, but normal vectors that can pass through plane ABC are possible
A set of simulated coordinates of the mounting base pose is given. At this time, the B adjusting point can be positioned at the origin of coordinates, the Y-axis direction is the aircraft course direction, and the yaw angle is adjusted by slight shaking, so that the yaw angle is approximate to xC=xB=0。
c3The coordinate system is in agreement with the aircraft coordinate system, only the origin of coordinates is translated. Let B = (x)B，yB，zB）=（0，0，0），C=（xC，yC，zC）=（0，yC，zC），A=（xA，yA，zA) Then, there is a system of equations:
wherein a and B are known quantities, a is the square of the distance between the adjusting point A and the adjusting point B and the distance between the adjusting point A and the adjusting point C, and B is the square of the distance between the adjusting point B and the adjusting point C, and the unit is mm2。
c4The specific equation is as follows:
solving a set of A, C coordinate values satisfying the condition, namely B = (0, 0, 0) and the solved A = (x) according to the equationA，yA，zA）、C=（0，yC，zC）。
d. And solving the optimal gasket specification model selection scheme of the adjusting points by using the simulated pose coordinates of the adjusting points obtained by calculation and by pose adjustment optimization. The method specifically comprises the following steps:
d1a, B, C solving for the adjustment of the setpoint;
d2solving for a minimum gasket combination number.
Wherein said step d1The solving algorithm is as follows:
model object: the avionics equipment is adjusted to be as horizontal as possible by increasing the thickness of the adjusting point gasket;
and (3) model constraint: the adjustment amount of each adjusting point is less than 3 mm; the adjusted pitch angle and roll angle meet the given design requirements, namely the adjusted pitch angle and yaw angle are less than 3'.
The method specifically comprises the following steps:
d11from the simulated pose coordinates of the adjustment points, i.e.:
A=（xA，yA，zA）、B=（0，0，0）、C=（0，yC，zC) And the point C is a coordinate close to a machine head side adjusting point, and in order to ensure that the normal vector direction of the plane ABC obtained subsequently points to the upper side of the plane XOY, the coordinate after adjustment by adding a gasket is as follows:
A′=(xA′，yA′，zA′)=（xA，yA，zA+TA），
B′=(xB′，yB′，zB′)=（0，0，TB），
C′=(xC′，yC′，zC′)=（0，yC，zC+TC），
wherein, TA、TB、TCA, B, C points, each of which is a minimum washer thickness of 0.1mmThe adjustment amount of (2) is less than 3mm, let TA=0.1k1，TB=0.1k2，TC=0.1k3And k is1、k2、k3Is a non-negative integer no greater than 30.
d12Abstracting an objective function according to the model objective as:
wherein the content of the first and second substances,
，
，
the constraint conditions are as follows:
（1）k1、k2、k3int, all are non-negative integers, and k is not less than 01、k2、k3< 30; wherein int refers to the integer;
(2) the technical requirement is that the adjusted pitch and roll angles are less than 3 ', i.e. | ω | < η, | λ | < η, η = 3',
the final mathematical expression of the specific constraints is solved as follows:
let-xA=m，yC-yA=n，zC-zA+TC-TA=HA′C′，-xA=p，-yA=q，-zA+TB-TA=HA′B′，
Wherein m, n, p, q are known constants,
HA′B′=zA-zB+0.1(k1-k2)，
HA′C′=zA–zC+0.1(k1-k3)，
normal vector of plane ABC:
(Vector)
The included angle between the Z axis and the Z axis is the pitch angle
，
(Vector)
The included angle between the Z axis and the Z axis is the transverse roll angle
，
According to the technical requirements | ω | < η, | λ | < η, η = 3'.
Finally, the adjustment problem of the shim is abstracted to the following optimization problem:
an objective function:
wherein
，zA′=zA+0.1k1，zB′=0.1k2，zC′=zC+0.1k3Substituting to obtain information about the variable k1、k2、k3The objective function of (1);
d13setting the constraint conditions:
wherein m = -xA，n=yC-yA，p=-xA，q=-yA，xA、yA、zA、yCAnd zCThe value of the signal is known and,
HA′B′=zA-zB+0.1(k1-k2)，
HA′C′=zA–zC+0.1(k1-k3) Substituted into the constraint to obtain the variable k1、k2、k3The constraint function of (2).
d14Solving the optimal solution of the objective function according to the constraint conditions, which comprises the following specific steps:
step 1: given S2Setting an initial value S2 0=1000；
Step 2: traverse k1、k2、k3=int，0≤k1、k2、k3All values less than 30 are substituted into the constraint condition, and the total traversal 30 is carried out3(ii) a condition; wherein int refers to the integer;
step 3: determining the obtained k1、k2、k3Whether all constraints are satisfied, if so, k at that time1、k2、k3Substituting the value of the target function into the target function, entering the next step, and otherwise, continuing to circulate;
step 4: judging whether S is present2 i＜S2 i-1If true, the objective function is assigned a value of S2 iOtherwise, continue to loop through all k1、k2、k3After the value is taken, k which enables the objective function to be minimum is finally obtained1、k2、k3And taking the value of an integer.
Wherein said step d2The solving of the minimum gasket combination number specifically comprises the following steps:
d21according to step d1The adjustment amount of each adjustment point obtained by the solution in (1), namely TA=0.1k1=t1，TB=0.1k2=t2，TC=0.1k3=t3；
d22Order:
t1=0.1a1+0.2b1+0.5c1+0.8d1，
t2=0.1a2+0.2b2+0.5c2+0.8d2，
t3=0.1a3+0.2b3+0.5c3+0.8d3，
wherein, ai、bi、ci、diI =1, 2, 3, the parameter representing the number of washers of each specification at different set points, said 0.1, 0.2, 0.5, 0.8 being the washer specification, respectively, as set forth in the following table:
d23establishing an objective function: gi=min(ai+bi+ci+di) I is an adjustment point;
d24setting the constraint conditions:
ti=0.1ai+0.2bi+0.5ci+0.8di ；
d25solving the optimal solution of the objective function according to the constraint conditions, wherein the specific solving method comprises the following steps:
Step1：ai=INT(ti/0.8)；
step 2: judgment of mu1=MOD（ti0.8) is zero, if it is, Gi=aiOtherwise, entering the next step;
Step3：bi=INT(μ1/0.5)；
step 4: judgment of mu2=MOD（μ10.5) is zero, if it is, Gi=ai+biOtherwise, entering the next step;
Step5：ci=INT(μ2/0.2)；
step 6: judgment of mu3=MOD（μ20.2) is zero, if it is, Gi=ai+bi+ciOtherwise, entering the next step;
Step7：di=INT(μ30.1), then Gi=ai+bi+ci+diThereby obtaining the quantity of the washers with different specifications at each adjusting point. Wherein INT denotes the integer: the integer part of the result obtained by dividing the two numbers, MOD being the remainder: the fractional part of the result of the division of the two numbers is multiplied by the divisor.
e. And disassembling the calibration tool, and adjusting the gasket according to the optimal scheme.
In summary, after reading the present disclosure, those skilled in the art should make various other modifications without creative efforts according to the technical solutions and concepts of the present disclosure, which are within the protection scope of the present disclosure.
Claims (8)
1. An auxiliary calibration method for installation of aircraft avionics equipment is characterized by comprising the following steps: the method comprises the following steps:
a. installing a calibration tool;
b. reading a pitch angle omega and a roll angle lambda;
c. calculating the simulation pose coordinate of the adjusting point through avionics equipment simulation pose coordinate calculation based on the pitch angle and the roll angle;
d. solving a gasket specification model selection optimal scheme of the adjusting points by using the simulated pose coordinates of the adjusting points obtained by calculation and by pose adjustment optimization;
e. and disassembling the calibration tool, and adjusting the gasket according to the optimal scheme.
2. An aircraft avionics installation calibration aiding method as claimed in claim 1, characterized in that: the step c specifically comprises the following steps:
c1connecting three adjusting points A, B and C on the mounting base to determine a plane ABC, and determining a normal vector of the plane ABC according to the pitch angle omega and the roll angle lambda
Solving is carried out to obtain the normal vector of the plane ABC
；
c2Let B adjust point locate at coordinate origin, Y axis direction be aircraft course direction, let xC=xB=0；
c3I.e. B = (x)B，yB，zB）=（0，0，0），C=（xC，yC，zC）=（0，yC，zC），A=（xA，yA，zA) Then, there is a system of equations:
wherein a and B are known quantities, a is the square of the distance between the adjusting point A and the adjusting point B and the distance between the adjusting point A and the adjusting point C, and B is the square of the distance between the adjusting point B and the adjusting point C, and the unit is mm2；
c4The specific equation is as follows:
solving a set of A, C coordinate values satisfying the condition, namely B = (0, 0, 0) and the solved A = (x) according to the equationA，yA，zA）、C=（0，yC，zC）。
3. An aircraft avionics installation calibration aiding method as claimed in claim 2, characterized in that: said step c1The method specifically comprises the following steps:
c11abstracting the installation base to be a plane ABC, wherein the pitch angle is an included angle omega between the projection of a normal vector of the plane ABC on the YOZ surface and the Z axis under the aircraft coordinate, and the roll angle is an included angle lambda between the projection of a normal vector of the plane ABC on the XOZ surface and the Z axis under the aircraft coordinate;
c12making an included angle omega between the auxiliary plane alpha and the Z axis, wherein the auxiliary plane alpha is vertical to the plane YOZ and the plane alpha equation is as follows: y-z @ tan ω =0, normal vector
；
c13Making an included angle lambda between an auxiliary plane beta and a beta vertical plane XOZ and a Z axis, wherein the plane beta equation is as follows: x-z. tan. lambda =0, normal vector
；
c14Normal vector of plane ABC
Calculating the normal vector of the plane ABC for the intersection direction of the plane alpha and the plane beta
。
4. An aircraft avionics installation calibration aiding method as claimed in any one of claims 1 or 3, characterized in that: the step d specifically comprises the following steps:
d1a, B, C adjustmentSolving the adjustment quantity of the adjustment points;
d2solving for a minimum gasket combination number.
5. An aircraft avionics installation calibration aiding method as claimed in claim 4, characterized in that: said step d1The method specifically comprises the following steps:
d11from the simulated pose coordinates of the adjustment points, i.e.
A=（xA，yA，zA）、B=（0，0，0）、C=（0，yC，zC) And the point C is the coordinate of a point which is close to the adjusting point of the machine head side, and the coordinate after the adjustment by adding the gasket is as follows:
A′=(xA′，yA′，zA′)=（xA，yA，zA+TA），
B′=(xB′，yB′，zB′)=（0，0，TB），
C′=(xC′，yC′，zC′)=（0，yC，zC+TC），
wherein, TA、TB、TCA, B, C, the adjustment amount of each adjustment point is less than 3mm, let TA=0.1k1，TB=0.1k2，TC=0.1k3And k is1、k2、k3Is a non-negative integer no greater than 30;
d12establishing an objective function:
wherein the content of the first and second substances,
，zA′=zA+0.1k1，zB′=0.1k2，zC′=zC+0.1k3substitution intoGet about variable k1、k2、k3The objective function of (1);
d13setting the constraint conditions:
wherein m = -xA，n=yC-yA，p=-xA，q=-yA，xA、yA、zA、yCAnd zCThe value is known;
HA′B′=zA-zB+0.1(k1-k2)，
HA′C′=zA–zC+0.1(k1-k3)，
substituting into the constraint to obtain the variable k1、k2、k3The constraint function of (2);
d14solving the optimal solution of the objective function according to the constraint condition.
6. An aircraft avionics installation calibration aiding method as claimed in claim 5, characterized in that: said step d14The method specifically comprises the following steps:
step 1: given S2Setting an initial value S2 0=1000；
Step 2: traverse k1、k2、k3=int，0≤k1、k2、k3All values less than 30 are substituted into the constraint condition, and the total traversal 30 is carried out3(ii) a condition; wherein int refers to the integer;
step 3: determining the obtained k1、k2、k3Whether all constraints are satisfied, if so, k at that time1、k2、k3Substituting the value of the target function into the target function, entering the next step, and otherwise, continuing to circulate;
step 4: judging whether S is present2 i＜S2 i-1If true, the objective function is assigned a value of S2 iOtherwise, continue to loop through all k1、k2、k3After the value is taken, k which enables the objective function to be minimum is finally obtained1、k2、k3And taking the value of an integer.
7. An aircraft avionics installation calibration aiding method as claimed in any one of claims 5 or 6, characterized in that: said step d2The solving of the minimum gasket combination number specifically comprises the following steps:
d21according to step d1The adjustment amount of each adjustment point obtained by the solution in (1), namely TA=0.1k1=t1，TB=0.1k2=t2，TC=0.1k3=t3；
d22Order:
t1=0.1a1+0.2b1+0.5c1+0.8d1，
t2=0.1a2+0.2b2+0.5c2+0.8d2，
t3=0.1a3+0.2b3+0.5c3+0.8d3，
wherein, ai、bi、ci、diI =1, 2, 3, the parameter represents the number of washers with different specifications at different adjusting points, and 0.1, 0.2, 0.5, 0.8 are the specifications of the washers respectively;
d23establishing an objective function: gi=min(ai+bi+ci+di) I is an adjustment point;
d24setting the constraint conditions: t is ti=0.1ai+0.2bi+0.5ci+0.8di；
d25Solving the optimal solution of the objective function according to the constraint condition.
8. An aircraft avionics installation calibration aiding method as claimed in claim 7, characterized in that: said step d25The solving method of (2) is as follows:
Step1：ai=INT(ti/0.8)；
step 2: judgment of mu1=MOD（ti0.8) is zero, if it is, Gi=aiOtherwise, entering the next step;
Step3：bi=INT(μ1/0.5)；
step 4: judgment of mu2=MOD（μ10.5) is zero, if it is, Gi=ai+biOtherwise, entering the next step;
Step5：ci=INT(μ2/0.2)；
step 6: judgment of mu3=MOD（μ20.2) is zero, if it is, Gi=ai+bi+ciOtherwise, entering the next step;
Step7：di=INT(μ30.1), then Gi=ai+bi+ci+diSo as to obtain the quantity of the washers with different specifications at each adjusting point;
wherein INT denotes the integer: the integer part of the result of the division of the two numbers; MOD is taking the rest: the fractional part of the result of the division of the two numbers is multiplied by the divisor.
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