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CN113086243A - Distribution method for inertial load of full-aircraft mass body of helicopter - Google Patents

Distribution method for inertial load of full-aircraft mass body of helicopter Download PDF

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CN113086243A
CN113086243A CN202110427246.7A CN202110427246A CN113086243A CN 113086243 A CN113086243 A CN 113086243A CN 202110427246 A CN202110427246 A CN 202110427246A CN 113086243 A CN113086243 A CN 113086243A
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mass
inertia
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CN113086243B (en
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吴松楠
查丁平
陈国军
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China Helicopter Research and Development Institute
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China Helicopter Research and Development Institute
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Abstract

The invention belongs to the technical field of helicopter strength design, and particularly relates to a distribution method of inertial load of a whole helicopter mass body. The method comprises the following steps: based on the whole-machine finite element model environment of the helicopter, the gravity center position coordinate of a single mass body is positioned under a machine body coordinate system, the gravity center position coordinate is used as a reference point, the inertial load at the gravity center is distributed to a machine body structure connected with the mass body according to the static force equivalent principle of the force system, and the effective transmission of the inertial load of the mass body is realized by establishing a reasonable load transmission path.

Description

Distribution method for inertial load of full-aircraft mass body of helicopter
Technical Field
The invention belongs to the technical field of helicopter strength design, and particularly relates to a distribution method of inertial load of a whole helicopter mass body.
Background
With the requirement for the accuracy degree of the helicopter whole-aircraft mass body being improved, when calculating the helicopter whole-aircraft load, the inertial load of each mass body forming a helicopter system needs to be calculated at first and is distributed to an aircraft body force transmission structure. But after distributing the inertial load to the outer edge of the frame, the structural stress obtained in this way is not sufficient to correspond to the true loaded state of the structure.
The invention avoids the excessive simplification of the inertial load sharing mode, reasonably distributes the inertial load of each mass body to the structure connected with the mass body, and can improve the accuracy of the stress analysis of the machine body structure.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects of the prior art, the invention provides a method for distributing the inertial load of the whole helicopter mass body, so as to provide more accurate load distribution of a fuselage structure, and further improve the stress analysis precision of the whole helicopter structure.
The technical scheme of the invention is as follows: in order to achieve the above object, a method for distributing inertial load of a full-aircraft mass body of a helicopter is provided, which comprises the following steps:
s1, establishing a full-machine finite element model, and establishing a mass body reference point 1;
s2, calculating the inertial load; calculating the inertial load at the gravity center of each mass reference point 1 according to the full-machine external load file, the full-machine mass file and the full-machine mass rotational inertia;
s3, creating a node group; respectively establishing node groups between the mass body reference points 1 established in the step S1 and the fuselage finite element model nodes 2 for carrying; the finite element model of the fuselage for load transfer comprises a front frame 3, a rear frame 4, side platforms 5 and longitudinal beams 6; the node 2 refers to a node of a finite element model grid unit; the node group is a combination of the mass body reference point 1 and the node 2 which participate in transmitting the inertial load of the mass body reference point 1;
s4, dividing the load of the inertial load; based on the principle of static force equivalence of the force system, the distribution of the inertial load of the mass reference point 1 to the finite element model node 2 in the node group created in step S3 is realized through the PCL command in PATRAN.
In a possible embodiment, in step S1, under the body coordinate system, using PCL commands in PATRAN, barycentric coordinates of each mass reference point 1 are imported in batch into the environment of the full-machine finite element model of the helicopter, and each mass reference point 1 is created.
In a possible embodiment, in the step S2, the method specifically includes the following steps:
s201: calculating the total mass of the whole computer according to the whole computer mass body file, wherein the total mass M of the whole computer is calculated according to the following formula I:
Figure BDA0003028687810000021
m in formula IiThe mass of the ith mass body reference point (1) is indicated, and n mass body reference points 1 are provided;
s202: then, the total mass of the whole computer is used to calculate the gravity center of the whole computer, and the gravity center (x) of the whole computer is calculatedc,yc,zc) Calculated according to the following two:
Figure BDA0003028687810000022
(x) in the formula IIi,yi,zi) Refers to the center of gravity of the ith mass reference point 1;
s203: then according to the whole-aircraft external load file, concentrating the whole-aircraft external load to the gravity center of the whole aircraft, wherein the external load comprises a flight load and/or a landing load, and respectively calculating the force and moment at the gravity center of the whole aircraft according to the following formula III-formula VIII to obtain the component force and moment in each direction of the force and moment at the gravity center of the whole aircraft in a body coordinate system:
Figure BDA0003028687810000023
Figure BDA0003028687810000024
Figure BDA0003028687810000025
Figure BDA0003028687810000031
Figure BDA0003028687810000032
Figure BDA0003028687810000033
f in formula III, formula IV and formula Vxi、Fyi、FziIs the component force of the whole machine external load of the ith mass reference point 1 in the machine body coordinate system, Fx、Fy、FzThe component force of the external load of the whole machine at the gravity center of the whole machine under a machine body coordinate system; m in formula six, formula seven and formula eightxi、Myi、MziIs the partial moment of the whole machine external load, M, of the ith mass reference point 1 in the machine body coordinate systemx、My、MzThe partial moment of the external load of the whole machine at the gravity center of the whole machine under a machine body coordinate system;
s204: according to the moment of inertia of the whole machine mass body, according to the moment of inertia (I) of each mass body reference point 1xi,Iyi,Izi) Product of inertia (I)xyi,Iyzi,Ixzi) Calculating the moment of inertia (I) at the center of gravity of the whole computerxc,Iyc,Izc) Product of inertia (I)xyc,Iyzc,Ixzc)；
The moment of inertia of the ith mass body reference point 1 around the x axis, the y axis and the z axis at the center of gravity of the whole machine is calculated according to the formula nine-formula eleven:
Ixic＝Ixi+Mi[(yi-yc)2+(zi-zc)2]nine-degree of expression
Iyic＝Iyi+Mi[(xi-xc)2+(zi-zc)2]Formula ten
Izic＝Izi+Mi[(yi-yc)2+(xi-xc)2]Formula eleven
The moment of inertia at the center of gravity of the whole machine is calculated according to the formula twelve-fourteen:
Figure BDA0003028687810000034
Figure BDA0003028687810000035
Figure BDA0003028687810000036
s205: the product of inertia at the center of gravity of the ith mass reference point 1 is translated to the product of inertia at the full aircraft center of gravity by the fifteen-seventeen equation:
Ixyio＝Ixyi+Mi(xi-xc)(yi-yo) Fifteen formula
Iyzic＝Iyzi+Mi(yi-yc)(zi-zc) Sixteen formula
Ixzic＝Ixzi+Mi(xi-xc)(zi-zc) Seventeen formula
And calculating according to an eighteen-equation to obtain an inertia product at the gravity center of the whole machine:
Figure BDA0003028687810000041
Figure BDA0003028687810000042
Figure BDA0003028687810000043
s206: according to the force F at the centre of gravity of the whole machinex、Fy、FzAnd (3) calculating the translation overload at the gravity center of the whole machine according to the formula twenty-one-formula twenty-three and the total mass M of the whole machine:
Figure BDA0003028687810000044
Figure BDA0003028687810000045
Figure BDA0003028687810000046
s207: according to the moment M at the center of gravity of the whole machinex、My、MzMoment of inertia (I) at center of gravity of the whole machinexc，Iyc，Izc) Product of inertia (I)xyc，Iyzc，Ixzc) Calculating the rotation overload at the gravity center of the whole computer, and calculating the rotation overload at the gravity center of the whole computer by the twenty-four formula and twenty-six formula:
Figure BDA0003028687810000047
Figure BDA0003028687810000048
Figure BDA0003028687810000049
wherein, IxxIs the self-moment of inertia, I, of a single mass body around the x-axis in a body coordinate systemyyIs the self-moment of inertia, I, of a single mass body around the y axis in a body coordinate systemzzThe single mass body is wound under a body coordinate systemSelf moment of inertia of z-axis, Ixy，Izx，IyzIs the product of inertia of a single mass in the body coordinate system.
S208: respectively calculating and obtaining the overload in the x direction, the y direction and the z direction at the reference point 1 of each mass body by the twenty-seven-twenty-nine formula:
nxi＝nxc+Wy*(zi-zc)-Wz*(yi-yc) Twenty seven of the formula
nyi＝nyc+Wz*(xi-xc)-Wx*(zi-zc) Twenty eight of the formula
nzi＝nzc+Wx*(yi-yc)-Wy*(xi-xc) Twenty nine formula
S209: the x-direction, y-direction and z-direction inertia load component forces at the reference point 1 of each mass body are respectively calculated by a formula of thirty-two:
Fxi＝Mi*g*nxithirty formula
Fyi＝Mi*g*nyiFormula thirty-one
Fzi＝Mi*g*nziFormula thirty-two
S210: the x-direction, y-direction and z-direction inertia load partial moments at the reference point 1 of each mass body are respectively calculated through the thirty-three formula:
Mxi＝Ixi*Wx*g-Ixyi*Wy*g-Izxi*Wzg type thirty-three
Myi＝-Ixyi*Wx*g+Iyi*Wy*g-Iyzi*WzG type thirty-four
Mzi＝-Izxi*Wx*g-Iyzi*Wy*g+Izi*WzG type thirty-five
In one possible embodiment, in the step S3, the gravity center position of the single mass reference point 1 is displayed separately, the body structure capable of transmitting the inertial load and the transmission path thereof connected to the mass reference point 1 are found, the structural member finite element model node 2 constituting the transmission path is added to the node group where the mass reference point 1 is located, and the relative spatial position relationship between the mass reference point and the node is established for the load distribution of the inertial load at the gravity center of the mass reference point 1.
In a possible embodiment, in step S4, the inertial load at the gravity center of the mass reference point 1 is converted to the finite element model node 2 of the body structure mesh, and finally the full-machine finite element model is calculated, so as to realize the stress state analysis of the full-machine structure.
In a possible embodiment, in the step S4, the method specifically includes the following steps:
s401, firstly, calculating the geometric center point inertia force F of the finite element model node 22(x,y,z)And moment of inertia M2(x,y,z)Inertial load F at the center of gravity of mass reference point 11(x,y,z)And M1(x,y,z)Distributing the mass body to the geometric center point of the finite element model node 2 by a force system static force equivalent principle, wherein the relative position of the gravity center of the mass body reference point 1 and the geometric center point of the finite element model node 2 is e(x,y,z)The weighting factor of node 2 of the single finite element model is ωiCalculating to obtain the inertia force F according to the formula2(x,y,z)And moment of inertia M2(x,y,z)；
S402, according to the node weight principle, the inertia force F on the geometric center point of the finite element model node 2 is processed2(x,y,z)And moment of inertia M2(x,y,z)Distributing the node to a finite element model node 2, wherein the relative position of the geometric central point of the finite element model node 2 and a single node is ri(x,y,z)The inertia forces calculated by the formulas thirty-seven and thirty-eight are superposed to obtain the inertia force F distributed to the node 2 of the finite element model2i(x,y,z)I.e. the inertial load.
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z)Thirty-six formula
Figure BDA0003028687810000061
Figure BDA0003028687810000062
The invention has the beneficial effects that: the invention can accurately position the gravity center of a single mass body under the full-helicopter coordinate system, more accurately distribute the inertial load at the gravity center to the main force transmission structure of the helicopter body, and establish a reasonable load transmission path, thereby improving the precision of the stress analysis of the helicopter body structure and realizing more reasonable structural dimension definition.
Description of the drawings:
FIG. 1 is a schematic diagram of the step of load sharing of the inertial load of the whole helicopter mass;
FIG. 2 is a schematic view of a helicopter gross mass reference point 1;
FIG. 3 is a schematic diagram of a set of nodes consisting of a helicopter mass reference point and a node;
FIG. 4 is a schematic diagram of the mass points and the nodes of the grid of the main force transfer structure;
FIG. 5 is a schematic view of nodal inertial loads;
FIG. 6 is a schematic diagram of the maximum shear stress of the structure;
wherein:
1, mass reference point; 2, connecting points; 3, a front frame; 4, a rear frame; 5, a side platform; 6, longitudinal beams; 7, the X-direction component of the inertial load; 8, the inertia load Y-direction component; 9, the Z-component of the inertial load.
The specific implementation mode is as follows:
the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, the present invention provides a method for distributing inertial load of a full-aircraft mass body of a helicopter, comprising the following steps:
s1, establishing a full-machine finite element model, and establishing a mass body reference point 1;
s2, calculating the inertial load; calculating the inertial load at the gravity center of each mass reference point 1 according to the full-machine external load file, the full-machine mass file and the full-machine mass rotational inertia;
s3, creating a node group; respectively establishing node groups between the mass body reference points 1 established in the step S1 and the fuselage finite element model nodes 2 for carrying; the finite element model of the fuselage for load transfer comprises a front frame 3, a rear frame 4, side platforms 5 and longitudinal beams 6; the node 2 refers to a node of a finite element model grid unit; the node group is a combination of the mass body reference point 1 and the node 2 which participate in transmitting the inertial load of the mass body reference point 1;
s4, dividing the load of the inertial load; and based on the principle of static force equivalence of the force system, realizing the distribution of the inertial load of the mass body reference point 1 to the finite element model nodes 2 in the node group created in the step S3 through a PCL command.
In one possible embodiment, as shown in fig. 2, in step S1, mass center coordinates of each mass reference point 1 are introduced into the environment of the full-aircraft finite element model of the helicopter in batch by using PCL commands in PATRAN under the body coordinate system, and each mass reference point 1 is created.
In a possible embodiment, in the step S2, the method specifically includes the following steps:
s201: calculating the total mass of the whole computer according to the whole computer mass body file, wherein the total mass M of the whole computer is calculated according to the following formula I:
Figure BDA0003028687810000081
m in formula IiThe mass of the ith mass body reference point 1 is indicated, and n mass body reference points 1 are provided;
s202: then the total mass of the whole machine is used for calculating the gravity center of the whole machineCenter of gravity (x)c,yc,zc) Calculated according to the following two:
Figure BDA0003028687810000082
(x) in the formula IIi,yi,zi) Refers to the center of gravity of the ith mass reference point 1;
s203: then according to the whole-aircraft external load file, concentrating the whole-aircraft external load to the gravity center of the whole aircraft, wherein the external load comprises a flight load and/or a landing load, and respectively calculating the force and moment at the gravity center of the whole aircraft according to the following formula III-formula VIII to obtain the component force and moment in each direction of the force and moment at the gravity center of the whole aircraft in a body coordinate system:
Figure BDA0003028687810000083
Figure BDA0003028687810000084
Figure BDA0003028687810000085
Figure BDA0003028687810000086
Figure BDA0003028687810000087
Figure BDA0003028687810000088
f in formula III, formula IV and formula Vxi、Fyi、FziIs the component force of the external load of the whole machine under the body coordinate system of the ith mass reference point 1,Fx、Fy、Fzthe component force of the external load of the whole machine at the gravity center of the whole machine under a machine body coordinate system; m in formula six, formula seven and formula eightxi、Myi、MziIs the partial moment of the whole machine external load, M, of the ith mass reference point 1 in the machine body coordinate systemx、My、MzThe partial moment of the external load of the whole machine at the gravity center of the whole machine under a machine body coordinate system is as follows:
s204: according to the moment of inertia of the whole machine mass body, according to the moment of inertia (I) of each mass body reference point 1xi，Iyi，Izi) Product of inertia (I)xyi，Iyzi，Ixzi) Calculating the moment of inertia (I) at the center of gravity of the whole computerxc，Iyc，Izc) Product of inertia (I)xyc，Iyzc，Ixzc)；
The moment of inertia of the ith mass body reference point 1 around the x axis, the y axis and the z axis at the center of gravity of the whole machine is calculated according to the formula nine-formula eleven:
Ixic＝Ixi+Mi[(yi-yc)2+(zi-zc)2]nine-degree of expression
Iyic＝Iyi+Mi[(xi-xc)2+(zi-zc)2]Formula ten
Izic＝Izi+Mi[(yi-yc)2+(xi-xc)2]Formula eleven
The moment of inertia at the center of gravity of the whole machine is calculated according to the formula twelve-fourteen:
Figure BDA0003028687810000091
Figure BDA0003028687810000092
Figure BDA0003028687810000093
s205: the product of inertia at the center of gravity of the mass reference point 1 is translated to the product of inertia at the full aircraft center of gravity by the fifteen-seventeen equation:
Ixyic＝Ixyi+Mi(xi-xc)(yi-yo) Fifteen formula
Iyzic＝Iyzi+Mi(yi-yc)(zi-zc) Sixteen formula
Ixzic＝Ixzi+Mi(xi-xc)(zi-zc) Seventeen formula
And calculating according to an eighteen-equation to obtain an inertia product at the gravity center of the whole machine:
Figure BDA0003028687810000094
Figure BDA0003028687810000095
Figure BDA0003028687810000101
s206: according to the force F at the centre of gravity of the whole machinex、Fy、FzAnd (3) calculating the translation overload at the gravity center of the whole machine according to the formula twenty-one-formula twenty-three and the total mass M of the whole machine:
Figure BDA0003028687810000102
Figure BDA0003028687810000103
Figure BDA0003028687810000104
s207: according to the moment M at the center of gravity of the whole machinex、My、MzMoment of inertia (I) at center of gravity of the whole machinexc,Iyc,Izc) Product of inertia (I)xyc,Iyzc,Ixzc) Calculating the rotation overload at the gravity center of the whole computer, and calculating the rotation overload at the gravity center of the whole computer by the twenty-four formula and twenty-six formula:
Figure BDA0003028687810000105
Figure BDA0003028687810000106
Figure BDA0003028687810000107
wherein, IxxIs, IyyIs, IzzIs, IxyIs, IzxIs, IyzIs that
S208: respectively calculating and obtaining the overload in the x direction, the y direction and the z direction at the reference point 1 of each mass body by the twenty-seven-twenty-nine formula:
nxi＝nxc+Wy*(zi-zc)-Wz*(yi-yc) Twenty seven of the formula
nyi＝nyc+Wz*(xi-xc)-Wx*(zi-zc) Twenty eight of the formula
nzi＝nzc+Wx*(yi-yc)-Wy*(xi-xc) Twenty nine formula
S209: the x-direction, y-direction and z-direction inertia load component forces at the reference point 1 of each mass body are respectively calculated by a formula of thirty-two:
Fxi＝Mi*g*nxithirty formula
Fyi＝Mi*g*nyiFormula thirty-one
Fzi＝Mi*g*nziFormula thirty-two
S210: the x-direction, y-direction and z-direction inertia load partial moments at the reference point 1 of each mass body are respectively calculated through the thirty-three formula:
Mxi＝Ixi*Wx*g-Ixyi*Wy*g-Izxi*Wzg type thirty-three
Myi＝-Ixyi*Wx*g+Iyi*Wy*g-Iyzi*WzG type thirty-four
Mzi＝-Izxi*Wx*g-Iyzi*Wy*g+Izi*WzG type thirty-five
In one possible embodiment, as shown in fig. 3, in the step S3, by separately displaying the gravity center position of a single mass reference point 1, finding the body structure capable of transferring the inertial load and the transfer path thereof connected to the mass reference point 1, adding the node 2 of the finite element model of the structural member constituting the transfer path into the node group where the mass reference point 1 is located, and establishing the relative spatial position relationship between the mass reference point and the node for the load distribution of the inertial load at the gravity center of the mass reference point 1.
In a possible embodiment, in step S4, the inertial load at the gravity center of the mass reference point 1 is converted to the finite element model node 2 of the body structure mesh, and finally the full-machine finite element model is calculated, so as to realize the stress state analysis of the full-machine structure.
In a possible embodiment, in the step S4, the method specifically includes the following steps:
s401, firstly, calculating the geometric center point inertia force F of the finite element model node 22(x,y,z)And moment of inertia M2(x,y,z)Inertial load F at the center of gravity of mass reference point 11(x,y,z)And M1(x,y,z)Distributing the mass body to the geometric center point of the finite element model node 2 by a force system static force equivalent principle, wherein the relative position of the gravity center of the mass body reference point 1 and the geometric center point of the finite element model node 2 is e(x,y,z)The weighting factor of node 2 of the single finite element model is ωiCalculating to obtain the inertia force F according to the formula2(x,y,z)And moment of inertia M2(x,y,z)；
S402, according to the node weight principle, the inertia force F on the geometric center point of the finite element model node 2 is processed2(x,y,z)And moment of inertia M2(x,y,z)Distributing the node to a finite element model node 2, wherein the relative position of the geometric central point of the finite element model node 2 and a single node is ri(x,y,z)For example, the inertia forces calculated by the equations thirty-seven and thirty-eight are superimposed to obtain the inertia force F distributed to the node 2 of the finite element model2i(x,y,z)I.e. the inertial load.
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z)Thirty-six formula
Figure BDA0003028687810000121
Figure BDA0003028687810000122
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention.

Claims (8)

1. A method for distributing inertial load of a full-aircraft mass body of a helicopter is characterized by comprising the following steps:
s1, establishing a full-machine finite element model, and establishing a mass body reference point (1);
s2, calculating the inertial load; calculating the inertial load at the gravity center of each mass reference point (1) according to the full-machine external load file, the full-machine mass file and the full-machine mass rotational inertia;
s3, creating a node group; respectively establishing node groups between the mass body reference points (1) established in the step S1 and the fuselage finite element model nodes (2) for transmission; the finite element model of the fuselage for load transfer comprises a front frame (3), a rear frame (4), side platforms (5) and longitudinal beams (6); the nodes (2) refer to nodes of the finite element model grid unit; the node group refers to the combination of the mass body reference point (1) and the nodes (2) which participate in the transmission of the inertial load of the mass body reference point (1);
s4, dividing the load of the inertial load; and based on the principle of static force equivalence of the force system, realizing the distribution of the inertial load of the mass body reference point (1) to the finite element model nodes (2) in the node group created in the step S3 through a PCL command.
2. Method for helicopter whole body inertial load distribution according to claim 1 characterized by that in said step S1, mass center coordinates of each mass reference point (1) are introduced into the whole body finite element model environment of the helicopter in bulk using PCL commands in PATRAN under the body coordinate system, creating each mass reference point (1).
3. The method for distributing the inertial load of the full-aircraft mass body of the helicopter of claim 2, wherein in the step S2, the method specifically comprises the following steps:
s201: calculating the total mass of the whole computer according to the whole computer mass body file, wherein the total mass M of the whole computer is calculated according to the following formula I:
Figure FDA0003028687800000011
m in formula IiRefer to the ith mass referenceMass of point (1), n mass reference points (1) in total;
s202: then, the total mass of the whole computer is used to calculate the gravity center of the whole computer, and the gravity center (x) of the whole computer is calculatedc,yc,zc) Calculated according to the following two:
Figure FDA0003028687800000021
(x) in the formula IIi,yi,zi) Refers to the center of gravity of the ith mass body reference point (1);
s203: then according to the whole-aircraft external load file, concentrating the whole-aircraft external load to the gravity center of the whole aircraft, wherein the external load comprises a flight load and/or a landing load, and respectively calculating the force and moment at the gravity center of the whole aircraft according to the following formula III-formula VIII to obtain the component force and moment in each direction of the force and moment at the gravity center of the whole aircraft in a body coordinate system:
Figure FDA0003028687800000022
Figure FDA0003028687800000023
Figure FDA0003028687800000024
Figure FDA0003028687800000025
Figure FDA0003028687800000026
Figure FDA0003028687800000027
f in formula III, formula IV and formula Vxi、Fyi、FziIs the component force of the external load of the whole machine under the body coordinate system of the ith mass body reference point (1), Fx、Fy、FzThe component force of the external load of the whole machine at the gravity center of the whole machine under a machine body coordinate system; m in formula six, formula seven and formula eightxi、Myi、MziIs the partial moment of the external load of the whole machine under the coordinate system of the machine body, Mx、My、MzThe partial moment of the external load of the whole machine at the gravity center of the whole machine under the coordinate system of the machine body.
4. A method for helicopter full body inertial load distribution according to claim 3, characterized by further comprising the step of, in said step S2:
s204: according to the moment of inertia of the whole machine mass body, according to the moment of inertia (I) of each mass body reference point (1)xi,Iyi,Izi) Product of inertia (I)xyi,Iyzi,Ixzi) Calculating the moment of inertia (I) at the center of gravity of the whole computerxc,Iyc,Izc) Product of inertia (I)xyc,Iyzc,Ixzc)；
The moment of inertia of the ith mass body reference point 1 around the x axis, the y axis and the z axis at the center of gravity of the whole machine is calculated according to the formula nine-formula eleven:
Ixic＝Ixi+Mi[(yi-yc)2+(zi-zc)2]nine-degree of expression
Iyic＝Iyi+Mi[(xi-xc)2+(zi-zc)2]Formula ten
Izic＝Izi+Mi[(yi-yc)2+(xi-xc)2]Formula eleven
The moment of inertia at the center of gravity of the whole machine is calculated according to the formula twelve-fourteen:
Figure FDA0003028687800000031
Figure FDA0003028687800000032
Figure FDA0003028687800000033
s205: the product of inertia at the center of gravity of the mass reference point 1 is translated to the product of inertia at the full aircraft center of gravity by the fifteen-seventeen equation:
Ixyic＝Ixyi+Mi(xi-xo)(yi-yo) Fifteen formula
Iyzic＝Iyzi+Mi(yi-yc)(zi-zc) Sixteen formula
Ixzic＝Ixzi+Mi(xi-xc)(zi-zc) Seventeen formula
And calculating according to an eighteen-equation to obtain an inertia product at the gravity center of the whole machine:
Figure FDA0003028687800000034
Figure FDA0003028687800000035
Figure FDA0003028687800000036
。
5. a method for helicopter full body inertial load distribution according to claim 4, characterized by that in said step S2, it further comprises the steps of:
s206: according to the force F at the centre of gravity of the whole machinex、Fy、FzAnd (3) calculating the translation overload at the gravity center of the whole machine according to the formula twenty-one-formula twenty-three and the total mass M of the whole machine:
Figure FDA0003028687800000041
Figure FDA0003028687800000042
Figure FDA0003028687800000043
s207: according to the moment M at the center of gravity of the whole machinex、My、MzMoment of inertia (I) at center of gravity of the whole machinexc,Iyc,Izc) Product of inertia (I)xyc,Iyzc,Ixzc) Calculating the rotation overload at the gravity center of the whole computer, and calculating the rotation overload at the gravity center of the whole computer by the twenty-four formula and twenty-six formula:
Figure FDA0003028687800000044
Figure FDA0003028687800000045
Figure FDA0003028687800000046
wherein, IxxIs the self-moment of inertia, I, of a single mass body around the x-axis in a body coordinate systemyyIs the self-moment of inertia, I, of a single mass body around the y axis in a body coordinate systemzzIs the self-moment of inertia, I, of a single mass body around the z-axis in a body coordinate systemxy，Izx，IyzThe inertia product of a single mass body in a body coordinate system is obtained;
s208: respectively calculating and obtaining the overload in the x direction, the y direction and the z direction at the reference point 1 of each mass body by the twenty-seven-twenty-nine formula:
nxi＝nxc+Wy*(zi-zc)-Wz*(yi-yc) Twenty seven of the formula
nyi＝nyc+Wz*(xi-xc)-Wx*(zi-zc) Twenty eight of the formula
nzi＝nzc+Wx*(yi-yc)-Wy*(xi-xc) Twenty nine formula
S209: the x-direction, y-direction and z-direction inertia load component forces at the reference point 1 of each mass body are respectively calculated by a formula of thirty-two:
Fxi＝Mi*g*nxithirty formula
Fyi＝Mi*g*nyiFormula thirty-one
Fzi＝Mi*g*nziFormula thirty-two
S210: the moment of inertia load components in the x direction, the y direction and the z direction at the reference point 1 of each mass body are respectively calculated by the thirty-three formula
Mxi＝Ixi*Wx*g-Ixyi*Wy*g-Izxi*WzG type thirty-three
Myi＝-Ixyi*Wx*g+Iyi*Wy*g-Iyzi*WzG type thirty-four
Mzi＝-Izxi*Wx*g-Iyzi*Wy*g+Izi*WzG formula thirty five.
6. The method for distributing the inertial load of the whole helicopter mass according to claim 5, wherein in step S3, the center of gravity position of a single mass reference point (1) is displayed separately, the body structure capable of transmitting the inertial load and the load transmission path thereof connected to the mass reference point (1) are found, the structural member finite element model nodes (2) constituting the load transmission path are added to the node group where the mass reference point (1) is located, and the relative spatial position relationship between the reference points and the nodes is established for the load distribution of the inertial load at the center of gravity of the mass reference point (1).
7. Method for the distribution of the inertial loads of the whole helicopter mass according to claim 6, characterized in that in step S4, the inertial loads at the barycenter of the mass reference point (1) are transformed onto the finite element model nodes (2) of the airframe structure mesh, and finally the whole finite element model is calculated to realize the stress state analysis of the whole airframe structure.
8. The method for distributing the inertial load of the full-aircraft mass of a helicopter of claim 7, wherein in the step S4, in the step S4, the method specifically comprises the following steps:
s401, firstly, calculating the geometric center point inertia force F of the finite element model node 22(x,y,z)And moment of inertia M2(x,y,z)Inertial load F at the center of gravity of mass reference point 11(x,y,z)And M1(x,y,z)Distributing the mass body to the geometric center point of the finite element model node 2 by a force system static force equivalent principle, wherein the relative position of the gravity center of the mass body reference point 1 and the geometric center point of the finite element model node 2 is e(x,y,z)Single limitation ofThe weight factor of the metamodel node 2 is ωiCalculating to obtain the inertia force F according to the formula2(x,y,z)And moment of inertia M2(x,y,z)；
S402, according to the node weight principle, the inertia force F on the geometric center point of the finite element model node 2 is processed2(x,y,z)And moment of inertia M2(x,y,z)Distributing the node to a finite element model node 2, wherein the relative position of the geometric central point of the finite element model node 2 and a single node is ri(x,y,z)The inertia forces calculated by the formulas thirty-seven and thirty-eight are superposed to obtain the inertia force F distributed to the node 2 of the finite element model2i(x,y,z)I.e. the inertial load.
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z)Thirty-six formula
Figure FDA0003028687800000061
Figure FDA0003028687800000062
。
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