CN107967393B - Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition - Google Patents

Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition Download PDF

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CN107967393B
CN107967393B CN201711285993.1A CN201711285993A CN107967393B CN 107967393 B CN107967393 B CN 107967393B CN 201711285993 A CN201711285993 A CN 201711285993A CN 107967393 B CN107967393 B CN 107967393B
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张华�
刘汉武
赵启龙
吴松
洪亚军
柳征勇
唐平
李东颖
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Shanghai Aerospace System Engineering Institute
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Abstract

The spacecraft double-cylinder parallel structure bearing design method based on the multi-constraint condition comprises the following steps: establishing a finite element model of the whole structure of the bearing cylinder; carrying out statics analysis on the finite element model, and extracting the maximum stress of the inner cylinder and the outer cylinder; performing dynamic analysis on the finite element model, and tracking the longitudinal, transverse and torsional first-order main frequencies of the integral structure of the bearing cylinder through modal effective factors; aiming at minimizing the weight of the whole structure of the bearing cylinder, carrying out optimization analysis on the whole structure of the bearing cylinder by using preset stress allowable constraint conditions and frequency constraint conditions to obtain the quality of the bearing cylinder; on the basis of obtaining the weight of the bearing cylinder, carrying out load analysis on the bearing cylinder; and the bearing proportion of the outer cylinder and the inner cylinder is distributed, so that the joint bearing of the outer cylinder and the inner cylinder is realized. The optimization of resource allocation is realized, and meanwhile, the joint of the outer cylinder and the inner cylinder can realize the joint bearing of large-scale effective load.

Description

Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a bearing design method of a double-cylinder parallel structure of a spacecraft based on a multi-constraint condition.
Background
The spacecraft structure platform loaded with the large-scale payload can meet the requirements of some special fields, no related similar spacecraft structure platform can be used for design reference at present, and a novel double-cylinder parallel structure scheme for integrally bearing the payload and the spacecraft structure platform is required to be designed according to actual requirements.
The large-scale effective load has strong structure, good rigidity, larger volume and mass and slender appearance, and belongs to a large-scale load system. According to the design of the traditional spacecraft, the effective load and the platform structure are completely separated, the platforms pursue serialization and generalization, one platform can bear various loads, the utilization rate of the platform is improved, the development time and the cost of the platform are reduced, and the reliability is improved. However, the design is not optimized according to the actual bearing requirements of the payload, precious volume and weight resources are wasted, and the existing mature platform cannot meet the bearing requirements of large-size payloads with large volume, large mass and large slenderness ratio. Therefore, according to the characteristic that the structure of the large-scale payload system has strong bearing capacity, the technical approach of taking the large-scale payload system as a part of the main structure of the spacecraft to participate in bearing is adopted, the purposes of reducing the volume of the spacecraft and the weight of the system can be achieved, and the large-scale payload system can enter the space through load bearing proportion distribution.
Disclosure of Invention
The application provides a spacecraft double-cylinder parallel structure bearing design method based on multi-constraint conditions, wherein a bearing cylinder of a double-cylinder parallel structure comprises an outer cylinder, an inner cylinder and a supporting structure, the top of the outer cylinder and the top of the inner cylinder which pass through the outer cylinder are connected in parallel through an upper flange and a bolt, the lower part of the outer cylinder is connected in parallel through a lower flange and a bolt, the supporting structure is connected with the lower part of the outer cylinder through a lower flange and a bolt, and the bearing cylinder jointly bears the weight of the spacecraft by the design method which comprises the:
establishing a finite element model of the whole structure of the bearing cylinder;
carrying out statics analysis on the finite element model, and extracting the maximum stress of the inner cylinder and the outer cylinder;
performing dynamic analysis on the finite element model, and tracking the longitudinal, transverse and torsional first-order main frequencies of the integral structure of the bearing cylinder through modal effective factors;
aiming at minimizing the weight of the whole structure of the bearing cylinder, carrying out optimization analysis on the maximum stress of the inner cylinder and the outer cylinder under preset stress permission constraint conditions, and carrying out optimization analysis on the longitudinal, transverse and torsional first-order main frequency of the whole structure of the bearing cylinder under preset frequency constraint conditions to obtain the quality of the bearing cylinder;
on the basis of obtaining the weight of the bearing cylinder, carrying out load analysis on the bearing cylinder;
and the bearing proportion of the outer cylinder and the inner cylinder is distributed, so that the joint bearing of the outer cylinder and the inner cylinder is realized.
In one embodiment, the method for establishing the finite element model of the integral structure of the bearing cylinder comprises the following steps:
simplifying the bolt flange connection with the pre-tightening load into a beam-spring mathematical model;
establishing a finite element model of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the supporting structure;
and connecting the finite element models of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the supporting structure according to the actual physical structure through the beam-spring mathematical model to form a finite element model of the whole structure of the bearing cylinder.
In one embodiment, performing a static analysis on the finite element model to extract maximum stresses of the inner cylinder and the outer cylinder specifically includes:
applying interface load and acceleration overload load to a finite element model of the integral structure of the bearing cylinder;
and (4) carrying out statics analysis on the interface load and the acceleration overload load, and extracting the maximum stress of the inner cylinder and the maximum stress of the outer cylinder.
In one embodiment, the method aims at minimizing the overall structure weight of the bearing cylinder to obtain the mass of the bearing cylinder, and simultaneously comprises the step of obtaining a design value of the thickness of the outer cylinder wall and a design value of the thickness of the inner cylinder wall.
In one embodiment, after the bearing cylinder is subjected to load analysis, bending moment, axial force and shearing force of the outer cylinder load and the inner cylinder load are obtained.
In one embodiment, the method for distributing the bearing proportion of the outer cylinder and the inner cylinder to realize the combined bearing of the outer cylinder and the inner cylinder comprises the following steps:
taking the thickness of the upper flange as a design variable;
calculating and analyzing the loads of the outer cylinder and the inner cylinder;
and calculating the load size under different thickness changes through the thickness change of the upper flange so as to realize the distribution of the bearing proportion of the outer cylinder and the inner cylinder.
According to the design method for the combined bearing of the force bearing cylinder of the spacecraft of the embodiment, the outer cylinder and the inner cylinder of the force bearing cylinder are subjected to load matching design, so that when the outer cylinder and the inner cylinder form a whole, the overall rigidity of the spacecraft is improved, the resource allocation optimization is realized, meanwhile, the combination of the outer cylinder and the inner cylinder can realize the combined bearing of a large-scale effective load, the purposes of reducing the size of the spacecraft and reducing the weight of the system can be realized, and the large-scale effective load system can enter the space through the load bearing proportion distribution.
Drawings
FIG. 1 is a schematic view of a parallel bearing structure of bearing cylinders;
FIG. 2 is a flow chart of a load and structure design analysis;
FIG. 3 is a schematic diagram of a beam-spring equivalent mathematical model;
FIG. 4 is a diagram of an external force-displacement model;
fig. 5 is a schematic view of load extraction.
Detailed Description
The present invention will be described in further detail with reference to the following detailed description and accompanying drawings.
The embodiment provides a bearing design method of a double-cylinder parallel structure of a spacecraft based on a multi-constraint condition, wherein for convenience of description, the whole of the double-cylinder parallel structure is called a bearing cylinder, the structural diagram of the bearing cylinder is shown in fig. 1 and comprises an outer cylinder 1, an inner cylinder 2 and a supporting structure 3, the tops of the outer cylinder 1 and the inner cylinder 2 are connected in parallel through an upper flange 4 and a bolt, the lower parts of the outer cylinder 1 and the inner cylinder 2 are connected in parallel through a lower flange 5 and a bolt, the supporting structure 3 and the lower part of the outer cylinder 1 are connected through a lower flange 5 and a bolt, and the supporting structure 3 connects the outer cylinder 1 and the inner cylinder 2 with.
The method for optimally designing the load carried by the double-cylinder parallel structure comprises the following steps, and the flow chart is shown in fig. 2.
S1: and establishing a finite element model of the whole structure of the bearing cylinder.
The specific mode of the step is as follows:
1) and simplifying the bolt flange connection with the pre-tightening load into a beam-spring mathematical model.
Because the bolt flange connection structure has the tension and compression rigidity E in the connection axial directionL、EC(ELIs tensile stiffness, ECFor compressive stiffness) to a reasonable beam-spring mathematical model, as shown in fig. 3, as follows:
under the tension state of the bolt flange, the balance equation is as the formula (1) and the formula (2):
Fa+Fc-Fb＝0 (1)；
Fb(rc-rb)-Frc＝0 (2)；
load FaSlit width rcAnd initial pre-tightening force F of bolt0The relationship between the two is shown in formula (3):
Figure GDA0002727656450000031
wherein E is1、I1The elastic modulus and the moment of inertia of the flange; e2、A2The modulus of elasticity and the cross-sectional area of the bolt are shown; f0For bolt pretension, t1Is the flange thickness. The axial displacement of the bolt flange connecting structure under the action of the external load and the spring force of the end part is shown in a formula (4):
Figure GDA0002727656450000032
axial deformation of the bolted flange connection structure under compression of the bolted flange is shown in formula (5), t2The thickness of the cylinder wall (when the flange is connected with the outer cylinder, the thickness of the outer cylinder can be represented, and when the flange is connected with the inner cylinder, the thickness of the inner cylinder can be represented, and the outer cylinder is connected for example in the text).
Figure GDA0002727656450000041
Preferably, the relationship curve between the external force and the displacement of the spring characteristic with different tension and compression stiffness is shown in fig. 4, and the tension and compression stiffness value of the bolt is calculated through a formula (4) and a formula (5).
2) And establishing a finite element model of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the supporting structure.
3) And connecting the finite element models of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the support structure through a beam-spring mathematical model according to an actual physical structure to form a finite element model of the whole structure of the bearing cylinder.
S2: and (4) carrying out statics analysis on the finite element model, and extracting the maximum stress of the inner cylinder and the outer cylinder.
Specifically, an interface load and an acceleration overload load are applied to a finite element model of the integral structure of the force cylinder; in the example, a combined inertial load of 1.0g in the transverse direction (in the example, the Y direction) and 6.1g in the longitudinal direction (in the example, the Z direction) is applied to the whole structure to simulate the loading condition of the launching section of the spacecraft. Extracting maximum stress sigma of inner cylinder from statics analysis resultmax_inAnd maximum stress sigma of outer cylindermax_out。
S3: and performing dynamic analysis on the finite element model, and tracking the longitudinal, transverse and torsional first-order main frequencies of the integral structure of the bearing cylinder through the modal effective factors.
E.g. tracking the longitudinal, transverse, torsional dominant frequency (typically first order) ω of the overall structure by the modal activity factorL、ωH、ωT。
S4: and aiming at minimizing the weight of the integral structure of the bearing cylinder, carrying out optimization analysis on the maximum stress of the inner cylinder and the outer cylinder under preset stress permission constraint conditions, and carrying out optimization analysis on the longitudinal, transverse and torsional first-order main frequencies of the integral structure of the bearing cylinder under preset frequency constraint conditions to obtain the quality of the bearing cylinder.
The analysis results σ obtained in step S2 and step S3max_in、σmax_out、ωL、ωH、ωTRespectively carrying out real-time comparison iterative analysis with preset stress permission constraint conditions and frequency maximization constraint conditions, and outputting design values of thicknesses of inner barrel wall and outer barrel wall of the bearing barrel parallel structure when the minimum target of mass m of the bearing barrel parallel structure is met, wherein the design values are hin、hout。
S5: and carrying out load analysis on the bearing cylinder on the basis of obtaining the weight of the bearing cylinder.
On the basis that the mass m of the bearing cylinder parallel structure meets the minimum target result, extracting the inner cylinder load and the outer cylinder load in the bearing cylinder parallel structure, wherein the inner cylinder load is shown in figure 5, and the inner cylinder load comprises: bending moment MinAxial force FinShear force QinAnd the outer cylinder load comprises: bending moment MoutAxial force FoutShear force Qout；
S6: and the bearing proportion of the outer cylinder and the inner cylinder is distributed, so that the joint bearing of the outer cylinder and the inner cylinder is realized.
Specifically, the thickness of the upper flange is used as a design variable, namely the thickness of the upper flange connected with the inner cylinder and the outer cylinder is set as a design variable delta, the load of the inner cylinder and the load of the outer cylinder are calculated and analyzed according to a figure 5 and a formula (6), the load under different thickness changes can be calculated through the thickness change of the delta, the bearing proportion distribution of the inner cylinder and the outer cylinder is realized, and finally the combined bearing of the parallel structure of the bearing cylinders is realized.
Figure GDA0002727656450000051
Table 1 shows the load and distribution ratio of the inner and outer cylinders when the inner cylinder thickness is 1mm, the outer cylinder thickness is 0.5mm, and delta is 20mm in this example. It follows that the greater delta is achieved, the greater the bearing ratio of the outer barrel.
TABLE 1Y, Z combination of the loads of the inner and outer cylinders under the action of the inertial load and the distribution ratio
Figure GDA0002727656450000052
The design method can realize the mechanical load and the structural design of the spacecraft with the force bearing cylinder parallel structure, is applied to the load and the structural design of the spacecraft in the field of space safety in China, and lays a foundation for the space foundation of large loads.
The present invention has been described in terms of specific examples, which are provided to aid understanding of the invention and are not intended to be limiting. For a person skilled in the art to which the invention pertains, several simple deductions, modifications or substitutions may be made according to the idea of the invention.

Claims (6)

1. The method for designing the bearing of the double-cylinder parallel structure of the spacecraft based on the multi-constraint condition is characterized in that the method for designing the joint bearing of the double-cylinder parallel structure of the spacecraft comprises the following steps of:
establishing a finite element model of the whole structure of the bearing cylinder;
carrying out statics analysis on the finite element model, and extracting the maximum stress of the inner cylinder and the outer cylinder;
performing dynamic analysis on the finite element model, and tracking the longitudinal, transverse and torsional first-order main frequencies of the integral structure of the bearing cylinder through modal effective factors;
aiming at minimizing the weight of the whole structure of the bearing cylinder, carrying out optimization analysis on the maximum stress of the inner cylinder and the outer cylinder under preset stress permission constraint conditions, and carrying out optimization analysis on the longitudinal, transverse and torsional first-order main frequencies of the whole structure of the bearing cylinder under preset frequency constraint conditions to obtain the quality of the bearing cylinder;
on the basis of obtaining the weight of the bearing cylinder, carrying out load analysis on the bearing cylinder;
and distributing the bearing proportion of the outer cylinder and the inner cylinder to realize the combined bearing of the outer cylinder and the inner cylinder.
2. The method for designing the double-cylinder parallel structure of the spacecraft as claimed in claim 1, wherein the establishing of the finite element model of the whole structure of the bearing cylinder comprises the following steps:
simplifying the bolt flange connection with the pre-tightening load into a beam-spring mathematical model;
establishing a finite element model of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the supporting structure;
and connecting the finite element models of the outer cylinder, the inner cylinder, the upper flange, the lower flange and the support structure according to an actual physical structure through the beam-spring mathematical model to form a finite element model of the integral structure of the bearing cylinder.
3. A spacecraft double-cylinder parallel structure bearing design method as claimed in claim 1, wherein said performing statics analysis on finite element model to extract maximum stress of said inner and outer cylinders specifically comprises:
applying interface load and acceleration overload load to a finite element model of the bearing cylinder integral structure;
and carrying out statics analysis on the interface load and the acceleration overload load, and extracting the maximum stress of the inner cylinder and the maximum stress of the outer cylinder.
4. The spacecraft double-cylinder parallel structure bearing design method as claimed in claim 1, wherein the method further comprises the step of obtaining the design value of the thickness of the outer cylinder wall and the design value of the thickness of the inner cylinder wall while obtaining the mass of the bearing cylinder with the aim of minimizing the overall structural weight of the bearing cylinder.
5. The spacecraft double-cylinder parallel structure bearing design method as claimed in claim 1, wherein after the bearing cylinder is subjected to load analysis, bending moment, axial force and shearing force of the outer cylinder load and the inner cylinder load are obtained.
6. The method for designing the bearing of the twin-tube parallel structure of the spacecraft as claimed in claim 1, wherein the step of distributing the bearing proportion of the outer tube and the inner tube to realize the joint bearing of the outer tube and the inner tube comprises the following steps:
taking the thickness of the upper flange as a design variable;
calculating and analyzing the loads of the outer cylinder and the inner cylinder;
and calculating the load size under different thickness changes through the thickness change of the upper flange so as to realize the distribution of the bearing proportion of the outer cylinder and the inner cylinder.
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