CN114065394A - Helicopter body main load-carrying structure stress analysis method - Google Patents
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Abstract
The invention discloses a helicopter body main bearing structure stress analysis method, which comprises the following steps: carrying out grid discretization on a main load-bearing structure of the helicopter body under a helicopter body coordinate system, and selecting a corresponding unit type to simulate a corresponding structure; defining the attribute of a unit for simulating a corresponding structure according to the material attribute and the section geometric attribute of a main bearing structure of a helicopter body; respectively dispersing each component on the helicopter into mass points, then taking the position of the gravity center of each mass point as the input of a geometric coordinate, creating reference points of the mass points in batches, taking a single reference point as a unit, creating a reference point group in batches, and adding nodes in the unit into the group; calculating the inertial load at the gravity center of a single reference point of the whole helicopter and distributing the inertial load to nodes; and calculating the displacement and the node force of the node under different load working conditions. The method effectively improves the stress analysis precision and the calculation efficiency of the main bearing structure of the helicopter body.
Description
Technical Field
The invention belongs to the field of helicopter strength design, and relates to a helicopter body main bearing structure stress analysis method.
Background
Along with the higher requirement on the economy of the design of the main bearing structure of the helicopter body, the reasonability of the arrangement of the main bearing structure of the helicopter body is established on the basis of the stress analysis result of the main bearing structure of the helicopter body, the conventional method is to simplify and disperse the structure of the helicopter body into a rough grid, and solve the displacement of unit nodes by a finite unit method so as to form a unit stress state.
However, the number of the extensive grids is small, and the stress distribution state of the main bearing structure of the helicopter cannot be met, so that the obtained analysis result is not enough to reflect the real loaded distribution of the structure.
Disclosure of Invention
The invention aims to provide a method for analyzing the stress of a main load-bearing structure of a helicopter body, which is used for improving the stress analysis precision and the calculation efficiency of the main load-bearing structure of the helicopter body.
In order to realize the task, the invention adopts the following technical scheme:
a helicopter body main bearing structure stress analysis method comprises the following steps:
carrying out grid discretization on a main load-bearing structure of the helicopter body under a helicopter body coordinate system, and selecting a corresponding unit type to simulate a corresponding structure;
defining the attribute of a unit for simulating a corresponding structure according to the material attribute and the section geometric attribute of a main bearing structure of a helicopter body;
respectively dispersing each component on the helicopter into mass points, and then taking the gravity center position of each mass Point as the input of a geometric coordinate to establish reference points (points) of the mass points in batches, wherein the reference points are used for making the gravity center position of the mass points explicit, and have relative coordinate positions in a helicopter body coordinate system;
establishing a reference Point Group in batches by taking a single reference Point as a unit;
selecting a single node or a plurality of nodes capable of transmitting the inertial load of the single reference Point on a unit simulating the main bearing structure by taking the single reference Point as a reference position according to the principle of a reasonable force transmission route, and adding the selected single node or the plurality of nodes into the created reference Point Group of the reference Point;
calculating the inertial load at the gravity center of a single reference Point of the whole helicopter through the external load information born by the helicopter and the mass information of all parts of the whole helicopter;
distributing the calculated inertial load at the gravity center of the single reference Point to a single node or a plurality of nodes in a reference Point Group corresponding to the single reference Point;
according to different load combination states of different flight loads and ground loads, creating a load working condition aiming at each load combination state;
and calculating all the created load working conditions to obtain the displacement and the node force of the unit node under each load working condition.
Further, the method further comprises:
and performing visual post-processing on the calculated unit node displacement and node force to display the stress or strain state of the main load-bearing structure of the helicopter body under each working condition.
Furthermore, the main bearing structure comprises a bulkhead, a longitudinal beam, a floor, a skin, a power system mounting platform, a horizontal tail and a vertical tail; and for the main bearing structure, a shear plate unit, a shell unit, a beam unit and a rod unit are selected.
Further, in the case of a metal material, the shear plate unit is used to simultaneously impart the elastic modulus and the unit thickness to the material.
Further, for the composite material, the elastic modulus and poisson's ratio, the cell direction, and the cell thickness of each layer of the core material are also given by the shell cells.
Further, for the bending-bearing structure, the beam unit is given a sectional shape, a sectional area, a material elastic modulus, and a poisson's ratio.
Further, for the structure which only bears tension and compression, the area of the cross section of the rod unit, the elastic modulus of the material and the poisson's ratio are given.
Further, the calculating the inertial load at the gravity center of the helicopter full-aircraft single reference Point includes:
calculating the rotational inertia and the inertia product at the center of gravity of the whole computer according to the rotational inertia and the inertia product of the mass body of the whole computer, and calculating the rotational inertia I of the rotational inertia at the center of gravity of the reference Point at the center of gravity of the whole computer around the xyz axisxic、Iyic、Izic(ii) a The product of inertia at the gravity center of the reference Point is translated to the product of inertia at the gravity center of the whole machine and is Ixyic，Iyyic，Izyic(ii) a The rotational inertia and the inertia product at the center of gravity of the whole machine are respectively Ixc、Ixyc；
Calculating overload n at the gravity center of the whole computer according to resultant force and resultant moment at the gravity center of the whole computer and the rotational inertia and inertia product at the gravity center of the whole computerxc、nyc、nzcAnd calculating the rotation overload Wx at the center of gravity of the whole computer, analogizing other axial directions, and finally calculating the overload and the inertia load at the reference Point of the mass body of the whole computer according to the translation overload and the rotation overload at the center of gravity of the whole computer to obtain the overload n in the directions of x, y and z at the reference Point of the mass body of the whole computerxi、nyi、nziAnd calculating the inertial load of the x, y and z directions at the gravity center of the Point of reference Point of the full computer mass body.
Further, the distributing the calculated inertial load at the gravity center of the single reference Point to the single node or a plurality of nodes in the created reference Point Group corresponding to the single reference Point includes:
firstly, calculating the geometric central point of all nodes in each reference point group, and calculating the inertial load including inertial force F at the gravity center of the corresponding reference point of the reference point group1(x,y,z)And moment of inertia M1(x,y,z)Distribution by means of the principle of static equivalenceTo said geometric center point, wherein the relative position of the center of gravity of the reference point and the geometric center point is e(x,y,z)The weight factor of a single node in a unit is ωiFor example, as shown in formula (1), the inertial force F at the geometric center point is weighted by different weighting factors according to the actual application requirement2(x,y,z)And moment of inertia M2(x,y,z)Distributing the data to each node in the unit; wherein the relative position of the geometric center point and the single node is ri(x,y,z)The inertial force F calculated by the equations (2) and (3) is expressed by the equations (2) and (3), respectively2i(x,y,z)a、F2i(x,y,z)bPerforming superposition processing to obtain an inertia force F distributed to the node (2) of the finite element model2i(x,y,z)I.e. the inertial load at the junction:
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z) (1)
compared with the prior art, the invention has the following technical characteristics:
the invention can accurately simulate the main bearing structure arrangement of the helicopter body, accurately and conveniently position the gravity center position of each mass body of the helicopter, the grid size and the calculated number of the mass bodies can be adjusted according to the calculation precision requirement, the inertia load calculation and the node load secondary distribution are fully automatic, the calculation speed is high, the operation efficiency is high, the visualization effect is strong, the reasonability of the main bearing structure arrangement scheme of the helicopter body is judged, the quick iteration of the main bearing structure size of the helicopter body is realized, and the precision of the stress analysis of the main bearing structure of the helicopter body can be greatly improved.
Drawings
FIG. 1 is a schematic diagram of the stress analysis step of a main bearing structure of a helicopter body;
FIG. 2 is a schematic diagram of a main load-bearing structure of a helicopter body (1 bulkhead, 2 longitudinal beams, 3 floors, 4 skins, 5 power system mounting platforms, 6 horizontal tails and 7 vertical tails);
FIG. 3 is a schematic diagram of a helicopter body main load-carrying structure finite element mesh (8 main load-carrying structure finite element mesh);
FIG. 4 is a schematic diagram of reference points of various masses of a helicopter (9 reference points of masses);
FIG. 5 is a schematic diagram of creating mass reference points (8 main load-carrying structure finite element grids, 9 mass reference points) in an organism coordinate system;
fig. 6 is a schematic diagram of adding a node to a mass reference Point group (9 mass reference points, 10 nodes);
FIG. 7 is a schematic view of the stress distribution of the main load-carrying structure of the helicopter body under a certain working condition 1;
fig. 8 is a schematic diagram of the stress distribution of the main load-bearing structure of the helicopter body under a certain working condition 2.
Detailed Description
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.
The invention provides a method for analyzing the stress of a main bearing structure of a helicopter body, which is based on a finite element method, establishes a finite element model of the main bearing structure of the helicopter body in an MSC.Patran software environment, realizes the rapid processing of mass data through a PCL command, performs load input, the establishment of various working conditions, inertial load conversion and loading in batch, and finally realizes the stress distribution display of the main bearing structure of the helicopter body through post-processing, wherein the method comprises the following specific steps:
And 2, creating the unit attribute. Defining the attribute of the unit which is created in the step 1 and used for simulating the corresponding structure according to the material attribute and the section geometric attribute of the main load-bearing structure of the helicopter body; for metal materials, a shear plate unit is used for simultaneously endowing the elastic modulus and the unit thickness of the material; for the composite material, the shell unit is used for endowing the elastic modulus and Poisson's ratio, unit direction and unit thickness of each layer of the composite material; for a bending-bearing structure, endowing the beam unit with the section shape, the section area, the material elastic modulus and the Poisson ratio; for the structure only bearing tension and compression, the area of the section of the rod unit, the elastic modulus of the material and the Poisson's ratio are given.
And 3, creating a reference point. Under a helicopter body coordinate system, firstly respectively dispersing each component on a helicopter into mass points, then taking the gravity center position of each mass Point as the input of a geometric coordinate, and establishing reference points of the mass points in batches by utilizing a PCL (personal computer) command of MSC.Patran software, and referring to an attached figure 4; the reference point is used for making the gravity center position of the mass point explicit, and the reference point has a relative coordinate position in a helicopter body coordinate system.
And 4, creating a reference point group. And (3) under a helicopter body coordinate system, taking the single reference Point created in the step (3) as a unit, and creating a reference Point Group in batches. Referring to fig. 5, an empty reference Point Group is created in units of each reference Point.
And 5, adding a reference point group. And (3) under a helicopter body coordinate system, taking a single reference Point as a reference position, selecting a single node or a plurality of nodes capable of transmitting the inertial load of the single reference Point on a unit (a shear plate unit, a shell unit, a beam unit and a rod unit) of the simulated main bearing structure according to the principle of a reasonable force transmission route, and adding the selected single node or the plurality of nodes into the reference Point Group of the reference Point created in the step (4). See figure 6.
And 6, calculating the inertial load. And (3) calculating the inertial load at the gravity center of the single reference Point of the whole helicopter in the step 3 according to the external load information born by the helicopter and the mass information of all parts of the whole helicopter.
Calculating the inertia load at the gravity center of each reference Point according to the whole machine external load file, the whole machine mass file and the rotational inertia of each mass body of the whole machine, and specifically comprising the following steps:
calculating the rotational inertia and the inertia product at the center of gravity of the whole computer according to the rotational inertia and the inertia product of the mass body of the whole computer, and calculating the rotational inertia I of the rotational inertia at the center of gravity of the reference Point at the center of gravity of the whole computer around the xyz axisxic、Iyic、Izic(ii) a The product of inertia at the gravity center of the reference Point is translated to the product of inertia at the gravity center of the whole machine and is Ixyic，Iyyic，Izyic(ii) a The rotational inertia and the inertia product at the center of gravity of the whole machine are respectively Ixc、Ixyc。
Calculating overload n at the gravity center of the whole computer according to resultant force and resultant moment at the gravity center of the whole computer and the rotational inertia and inertia product at the gravity center of the whole computerxc、nyc、nzcAnd calculating the rotation overload Wx at the center of gravity of the whole computer, analogizing other axial directions, and finally calculating the overload and the inertia load at the reference Point of the mass body of the whole computer according to the translation overload and the rotation overload at the center of gravity of the whole computer to obtain the overload n in the directions of x, y and z at the reference Point of the mass body of the whole computerxi、nyi、nziSo as to calculate the inertial load in the x, y and z directions (wherein the inertial force is respectively F) at the gravity center of the reference Point of the full-computer mass bodyxi、Fyi、FziThe moment of inertia is Mxi、Myi、Mzi)。
And 7, distributing the load. And under a helicopter body coordinate system, distributing the inertial load at the gravity center of the single reference Point calculated in the step 6 to a single node or a plurality of nodes in the reference Point Group corresponding to the single reference Point created in the step 5.
Firstly, the geometric center point of all the nodes in each reference point group is calculated, and the inertial load (inertial force F) at the gravity center of the corresponding reference point of the reference point group is calculated1(x,y,z)And moment of inertia M1(x,y,z)) Is distributed to the geometric center point by the principle of static equivalence, wherein the relative position of the gravity center of the reference point and the geometric center point is e(x,y,z)The weight factor of a single node in a unit is ωiFor example, as shown in formula (1), the inertial force F at the geometric center point is weighted by different weighting factors according to the actual application requirement2(x,y,z)And moment of inertia M2(x,y,z)Distributing the data to each node in the unit; wherein the relative position of the geometric center point and the single node is ri(x,y,z)The inertial force F calculated by the equations (2) and (3) is expressed by the equations (2) and (3), respectively2i(x,y,z)a、F2i(x,y,z)bPerforming superposition processing to obtain an inertia force F distributed to the node (2) of the finite element model2i(x,y,z)I.e. the inertial load at the junction.
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z) (1)
And 8, creating a load working condition. And according to different flight loads and different load combination states of the ground load, creating a load working condition aiming at each load combination state.
And 9, calculating each working condition. And (4) calculating all the load working conditions created in the step (8) to obtain the displacement and the node force of the unit node under each load working condition.
And step 10, carrying out result post-processing. And performing visual post-processing on the calculated unit node displacement and node force to display the stress or strain state of the main load-bearing structure of the helicopter body under each working condition. See fig. 7 and 8.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.
Claims (9)
1. A helicopter body main bearing structure stress analysis method is characterized by comprising the following steps:
carrying out grid discretization on a main load-bearing structure of the helicopter body under a helicopter body coordinate system, and selecting a corresponding unit type to simulate a corresponding structure;
defining the attribute of a unit for simulating a corresponding structure according to the material attribute and the section geometric attribute of a main bearing structure of a helicopter body;
respectively dispersing each component on the helicopter into mass points, and then taking the gravity center position of each mass Point as the input of a geometric coordinate to establish reference points (points) of the mass points in batches, wherein the reference points are used for making the gravity center position of the mass points explicit, and have relative coordinate positions in a helicopter body coordinate system;
establishing a reference Point Group in batches by taking a single reference Point as a unit;
selecting a single node or a plurality of nodes capable of transmitting the inertial load of the single reference Point on a unit simulating the main bearing structure by taking the single reference Point as a reference position according to the principle of a reasonable force transmission route, and adding the selected single node or the plurality of nodes into the created reference Point Group of the reference Point;
calculating the inertial load at the gravity center of a single reference Point of the whole helicopter through the external load information born by the helicopter and the mass information of all parts of the whole helicopter;
distributing the calculated inertial load at the gravity center of the single reference Point to a single node or a plurality of nodes in a reference Point Group corresponding to the single reference Point;
according to different load combination states of different flight loads and ground loads, creating a load working condition aiming at each load combination state;
and calculating all the created load working conditions to obtain the displacement and the node force of the upper node of the unit under each load working condition.
2. The helicopter body main load-carrying structure stress analysis method according to claim 1, characterized by further comprising:
and performing visual post-processing on the calculated unit node displacement and node force to display the stress or strain state of the main load-bearing structure of the helicopter body under each working condition.
3. The helicopter body main load-carrying structure stress analysis method according to claim 1, wherein the main load-carrying structure comprises a bulkhead, a longitudinal beam, a floor, a skin, a power system mounting platform, a horizontal tail and a vertical tail; and for the main bearing structure, a shear plate unit, a shell unit, a beam unit and a rod unit are selected.
4. The helicopter body main load-carrying structure stress analysis method according to claim 1, characterized in that for a metal material, shear plate units are used to simultaneously give the material an elastic modulus and a unit thickness.
5. The helicopter body main force-bearing structure stress analysis method of claim 1, characterized in that for composite materials, the shell units are also used to give the elastic modulus and poisson's ratio, unit direction and unit thickness to each layer of the re-core material.
6. The helicopter body main force-bearing structure stress analysis method of claim 1, characterized by that, for a bending-bearing structure, the beam unit section shape, the section area, the material elastic modulus and the poisson ratio are given.
7. The helicopter body main force-bearing structure stress analysis method of claim 1, characterized by that, for the structure only bearing tension and compression, the area of the rod unit cross section, the material elastic modulus and the poisson's ratio are given.
8. The helicopter body main load-carrying structure stress analysis method according to claim 1, wherein said calculating the inertial load at the center of gravity of a single Point of reference of the helicopter includes:
calculating the rotational inertia and the inertia product at the center of gravity of the whole computer according to the rotational inertia and the inertia product of the mass body of the whole computer, and calculating the rotational inertia I of the rotational inertia at the center of gravity of the reference Point at the center of gravity of the whole computer around the xyz axisxic、Iyic、Izic(ii) a The product of inertia at the gravity center of the reference Point is translated to the product of inertia at the gravity center of the whole machine and is Ixyic，Iyyic，Izyic(ii) a The rotational inertia and the inertia product at the center of gravity of the whole machine are respectively Ixc、Ixyc；
Calculating overload n at the gravity center of the whole computer according to resultant force and resultant moment at the gravity center of the whole computer and the rotational inertia and inertia product at the gravity center of the whole computerxc、nyc、nzcAnd calculating the rotation overload Wx at the center of gravity of the whole computer, analogizing other axial directions, and finally calculating the overload and the inertia load at the reference Point of the mass body of the whole computer according to the translation overload and the rotation overload at the center of gravity of the whole computer to obtain the overload n in the directions of x, y and z at the reference Point of the mass body of the whole computerxi、nyi、nziAnd calculating the inertial load of the x, y and z directions at the gravity center of the Point of reference Point of the full computer mass body.
9. The helicopter body main load-carrying structure stress analysis method according to claim 1, wherein said distributing the calculated inertial load at the center of gravity of a single reference Point to a single node or a plurality of nodes in a reference Point Group created to correspond to this single reference Point comprises:
firstly, calculating the geometric central point of all nodes in each reference point group, and calculating the inertial load including inertial force F at the gravity center of the corresponding reference point of the reference point group1(x,y,z)And moment of inertia M1(x,y,z)Is distributed to the geometric center point by the principle of static equivalence, wherein the relative position of the gravity center of the reference point and the geometric center point is e(x,y,z)The weight factor of a single node in a unit is ωiFor example, as shown in formula (1), the inertial force F at the geometric center point is weighted by different weighting factors according to the actual application requirement2(x,y,z)And moment of inertia M2(x,y,z)Distributing the data to each node in the unit; wherein the relative position of the geometric center point and the single node is ri(x,y,z)The inertial force F calculated by the equations (2) and (3) is expressed by the equations (2) and (3), respectively2i(x,y,z)a、F2i(x,y,z)bPerforming superposition processing to obtain an inertia force F distributed to the node (2) of the finite element model2i(x,y,z)I.e. the inertial load at the junction:
F2(x,y,z)＝F1(x,y,z)，M2(x,y,z)＝M1(x,y,z)+F2(x,y,z)·e(x,y,z) (1)
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