CN111639419A - Method for judging problem of cabin implosion small deformation plastic damage mode - Google Patents

Method for judging problem of cabin implosion small deformation plastic damage mode Download PDF

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CN111639419A
CN111639419A CN202010387695.9A CN202010387695A CN111639419A CN 111639419 A CN111639419 A CN 111639419A CN 202010387695 A CN202010387695 A CN 202010387695A CN 111639419 A CN111639419 A CN 111639419A
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cabin
judging
damage
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plastic deformation
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CN111639419B (en
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姚熊亮
王逸南
王治
王志凯
洪峰
吴子奇
郑健
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Harbin Engineering University
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Abstract

The invention belongs to the technical field of explosion damage assessment, and particularly relates to a method for judging a cabin implosion small-deformation plastic damage mode problem. The small-deformation damage mode judgment method is based on the basic principle of plastic dynamics, deduces a damage mode judgment method under the condition of small deformation, provides an estimation formula of different load factors for final deflection response of the center of the plate frame structure, and provides numerical verification for theoretical calculation results. On the one hand, it is possible to predict quickly what damage pattern occurs in the individual tanks after a given load. On the other hand, when designing the cabin explosion test, the cabin structure design and the selection of the drug amount can be preliminarily estimated according to the expected damage effect.

Description

Method for judging problem of cabin implosion small deformation plastic damage mode
Technical Field
The invention belongs to the technical field of explosion damage assessment, and particularly relates to a method for judging a cabin implosion small-deformation plastic damage mode problem.
Background
Nowadays, the types of weapons are more and more, the threat is more and more intensified, and the frequency of the internal explosion of the cabin is increased. And much research has been conducted on the damage mode of the plate frame structure of the cabin implosion. According to the method, Eftis J simultaneously considers the geometric nonlinearity problems of transverse shear film force, nonlinear dynamic strain strengthening effect and large material deformation of a ship plate frame structure under the action of transient explosive impact load, the effectiveness of the method is verified by means of combining experimental means and theoretical calculation, and the calculation of explosive impact problems of Bodner-Partom and Chaboche material constitutive models is provided. The Thangwen and Yong and the like are based on a structural rigidity-plasticity model and are solved by an energy method, the plasticity response characteristic of the framework structure under the impact of the explosion impact load in an exponential form is derived, and a corresponding judgment equation and an empirical calculation formula of the deflection of the framework are given.
In the process of cabin implosion, shock waves generated by explosion can cause the plate frame structure to generate a plurality of failure modes, and the possibility of crevasses, plastic zones, shear fracture, curling and the like exists. At present, the small deformation damage mode of the cabin implosion is analyzed, so that the research on the relation and the difference among different modes is few. The forecasting and judgment of the damage mode of the plate frame structure of the ship body under small deformation are rare and precious.
Disclosure of Invention
The invention aims to provide a method for judging the problem of a cabin implosion small-deformation plastic damage mode.
The purpose of the invention is realized by the following technical scheme: the method comprises the following steps:
step 1: calculating the equivalent overpressure P of the shock wave load according to a pressure time-course curve measured by a pressure sensor in the center of the cabin grillage after explosion1；
Figure BDA0002484674790000011
Wherein p (t) is measured by a pressure sensor; t is t0The time of positive pressure action of shock wave;
step 2: equivalent overpressure P according to shock wave load1And equivalent slat beam tape width B1Calculating the load P0；
P0＝P1B1
Wherein, B1＝2Lb，LbIs the stringer pitch;
and step 3: according to load P0Calculating the counter force f borne by the stringerR；
Figure BDA0002484674790000021
Wherein M is0b＝σ0bh2/4，σ0B and h are the width and height of the beam, respectively, for yield limit; l is the spacing between the strong ribs; n is the number of cabin cross members;
and 4, step 4: calculating the static load failure pressure P of the stringercbAnd the static load destructive pressure P of the strong ribcL；
Figure BDA0002484674790000022
PcL＝4M0L/L2
Wherein M is0L＝σ0BH2(ii)/4; h is the height of the stringer; b is A/H; a is the cross-sectional area of the beam;
and 5: judging the damage modes of the common reinforcing ribs and the strong members;
if Pcb≤P0≤3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates small deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd P iscL≤fR≤3PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component generates small plastic deformation;
if P is satisfied0＞3PcbAnd f isR＞3PcLAnd judging that the common reinforcing rib generates large-area plastic deformation and the strong component generates large-area plastic deformation.
The invention has the beneficial effects that:
the small-deformation damage mode judgment method is based on the basic principle of plastic dynamics, deduces a damage mode judgment method under the condition of small deformation, provides an estimation formula of different load factors for final deflection response of the center of the plate frame structure, and provides numerical verification for theoretical calculation results. Because different damage modes are caused by mechanical mechanisms, the characteristics of the different damage modes can be analyzed and a damage mode judgment method can be established from the mechanical mechanisms. Establishing such criteria is of practical significance. On the one hand, it is possible to predict quickly what damage pattern occurs in the individual tanks after a given load. On the other hand, when designing the cabin explosion test, the cabin structure design and the selection of the drug amount can be preliminarily estimated according to the expected damage effect.
Drawings
FIG. 1 is a design flow diagram of the present invention.
Fig. 2(a) is a schematic structural view of a cabin plate frame.
Figure 2(b) is a simplified form of profile schematic.
Fig. 3 is a schematic diagram of a transverse velocity field of weak reinforcing ribs with small deformation and damage.
Fig. 4 is a schematic diagram of the transverse velocity field of large deformation of a weak reinforcing rib.
Fig. 5 is a schematic view of the force applied to the strong member.
FIG. 6 is a diagram of a small deformation verification numerical model.
FIG. 7 is a schematic view of a numerical small deformation damage mode.
Fig. 8 is a profile parameter setting table for each condition.
FIG. 9 is a table of four exemplary operating condition analysis data.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The invention relates to a method for judging a plastic damage mode problem of small deformation caused by cabin implosion, which mainly aims at forecasting, analyzing and judging small plastic deformation caused by shock waves and mainly performs the work of a damage mode judging method under the small deformation of a plate frame structure. The method can be directly applied to the prediction of the cabin implosion small deformation damage mode, and has important guiding significance for the design of the ship cabin.
A method for judging the problem of a cabin implosion small deformation plastic damage mode comprises the following steps:
step 1: calculating the equivalent overpressure P of the shock wave load according to a pressure time-course curve measured by a pressure sensor in the center of the cabin grillage after explosion1；
Figure BDA0002484674790000031
Wherein p (t) is measured by a pressure sensor; t is t0The time of positive pressure action of shock wave;
step 2: equivalent overpressure P according to shock wave load1And equivalent slat beam tape width B1Calculating the load P0；
P0＝P1B1
Wherein, B1＝2Lb，LbIs the stringer pitch;
and step 3: according to load P0Calculating the counter force f borne by the stringerR；
Figure BDA0002484674790000032
Wherein M is0b＝σ0bh2/4，σ0B and h are the width and height of the beam, respectively, for yield limit; l is the spacing between the strong ribs; n is the number of cabin cross members;
and 4, step 4: calculating the static load failure pressure P of the stringercbAnd the static load destructive pressure P of the strong ribcL；
Figure BDA0002484674790000041
PcL＝4M0L/L2
Wherein M is0L＝σ0BH2(ii)/4; h is the height of the stringer; b is A/H; a is the cross-sectional area of the beam;
and 5: judging the damage modes of the common reinforcing ribs and the strong members;
if Pcb≤P0≤3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates small deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd P iscL≤fR≤3PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component generates small plastic deformation;
if P is satisfied0＞3PcbAnd f isR＞3PcLAnd judging that the common reinforcing rib generates large-area plastic deformation and the strong component generates large-area plastic deformation.
Because different damage modes are caused by mechanical mechanisms, the characteristics of the different damage modes can be analyzed and a damage mode judgment method can be established from the mechanical mechanisms. Establishing such criteria is of practical significance. On the one hand, it is possible to predict quickly what damage pattern occurs in the individual tanks after a given load. On the other hand, when designing the cabin explosion test, the cabin structure design and the selection of the drug amount can be preliminarily estimated according to the expected damage effect.
And determining the load characteristics borne by the plate frame structure aiming at the damage mode of the hull plate frame structure under the action of the cabin implosion load, and carrying out corresponding simplified analysis. The standard cabin implosion load is simplified into a two-stage rectangular load, and the key points comprise the following parameters: overpressure peak P1And time of positive pressure action τ+；
The overpressure convergence effect at the complex corner in the cabin implosion can cause the borne load to be obviously increased compared with other positions, so that the load is corrected by an impulse equivalent method;
and (4) selecting a calculation model of the small-deformation plastic plate frame. When the damage degree of the cabin is calculated, the grillage forming the cabin needs to be selected and set as a response calculation model, as shown in fig. 2. The section is set to be in a rectangular beam form, and the ultimate bending moment of the rectangular beam is ensured to be consistent with that of a target section; the boundary condition is set as rigid around;
determining four types of damage mode generation judgment method based on plastic dynamics, and determining four types of damage modes through load P0Sum reaction force FR：
(1) When P is satisfiedcb≤P0≤3PcbAnd f isR≤PcLWhen the first mode of damage occurs, the common reinforcing rib generates small deformation, and the strong component does not generate plastic deformation, as shown in figure 3. Wherein: p0＝P1B1，P1For shock wave loading equivalent overpressure, B1To be equivalent to the slat width of the slat beam,
Figure BDA0002484674790000051
M0b＝σ0bh2/4，σ0to yield limit, b and h are the width and height of the beam, respectively, LbIs the stringer pitch. As shown in FIG. 3, the distance between two simply-supported fixed triangle signs is the equivalent slat beam bandwidth B1，B1Has a value of 2Lb。
P1Generated by impact load P over a period of time tEquivalent calculation of impulse
Figure BDA0002484674790000052
Wherein P (t) is measured by a pressure sensor, the pressure sensor is added in the center of the cabin plate frame, and a pressure time-course curve is obtained by measuring after explosion, wherein t0The time for positive pressure action of the shock wave is calculated by the following formula
Figure BDA0002484674790000053
Wherein:
Figure BDA0002484674790000054
is the proportional distance, W is the charge, R is the distance from the measured point to the center of the explosion.
(2) When P is satisfied0＞3PcbAnd f isR≤PcLWhen the second damage mode occurs, the common reinforcing rib generates large-area plastic deformation, and the strong component does not generate plastic deformation, as shown in figure 4;
(3) when P is satisfied0＞3PcbAnd P iscL≤fR≤3PcLIn the process, a third damage mode occurs, the common reinforcing rib generates large-area plastic deformation, and the strong component generates small plastic deformation. The force applied by the strong member is shown in figure 5. Wherein:
Figure BDA0002484674790000055
n represents the number of transverse members, L is the distance between the strong ribs, PcL＝4M0L/L2，M0L＝σ0BH24, B and H are respectively the width and the height of the equivalent rectangular section of the longitudinal girder; the acquisition method comprises the following steps: the width and the height of the longitudinal girder can be obtained through the measuring scale, and the consistency of the H and the actual height is ensured, namely the H is the height of the longitudinal girder. And then ensuring that the equivalent longitudinal girders have the same ultimate bending moment as the original structure.
M0＝(∫∫ydA-Az)σs＝M
In the formula: mUltimate bending moment of the original structure, M0Is equivalent longitudinal girder ultimate bending moment sigmasAnd z is the height of the beam section neutral axis, namely H/2, and y is the distance from the selected point to the bottom of the structure. A is the area of the cross section, and the width B of the equivalent rectangular cross section of the stringer is A/H according to the formula.
(4) When P is satisfied0＞3PcbAnd f isR＞3PcLWhen the reinforcing rib is damaged, the common reinforcing rib generates large-area plastic deformation and the strong component generates large-area plastic deformation;
and 5, calculating the dynamic responses of the four typical sectional materials under different TNT equivalent weights based on a finite element method, wherein the dynamic responses comprise a load factor, the size of a plastic region and the final displacement change, and checking the effectiveness and the accuracy of the judgment method.
The method for judging the damage mode under the small deformation of the cabin implosion provided by the invention is researched based on the basic principle of plastic dynamics, the method for judging the damage mode under the small deformation condition is deduced, an estimation formula of final deflection response of different load factors to the center of a plate frame structure is given, and a numerical verification is given to a theoretical calculation result. The purpose of the invention is as follows: because different damage modes are caused by mechanical mechanisms, the characteristics of the different damage modes can be analyzed and a damage mode judgment method can be established from the mechanical mechanisms. Establishing such criteria is of practical significance. On the one hand, it is possible to predict quickly what damage pattern occurs in the individual tanks after a given load. On the other hand, when designing the cabin explosion test, the cabin structure design and the selection of the drug amount can be preliminarily estimated according to the expected damage effect.
In order to verify the accuracy of the method, the inventor carries out a plurality of tests, and the following briefly describes the test process:
through mechanical analysis of the above 4 typical small-deformation damage modes, 4 typical working condition profile settings are designed according to criterion conditions as shown in fig. 8, wherein in the first working condition, calculation is performed under the equivalent of 0.15Kg TNT. In the second working condition, numerical simulation is carried out under the equivalent of 1.5Kg TNT. In the third and fourth working conditions, the explosive equivalent at the explosion source is 4 KgTNT.
A numerical model of a typical cabin structure was created as shown in fig. 6. The cabin extends 0.5m when the size of the cabin is 2m multiplied by 2m boundary, and the free boundary is fixedly supported. The size of the grid of the plate frame structure is 0.1m, and the size of the grid of the drainage basin is 0.05 m. The material is ordinary steel Q235.
The deck strain cloud chart under each working condition is extracted and is shown in the attached figure 7. From the strain cloud chart of each typical working condition under the condition of small deformation, the red area part is a large plastic deformation area. From the working condition I, under the condition of small equivalent TNT implosion damage, the plate frame structure only has a plastic strain area in a longitudinal bone distribution area at the corner, and in the working condition II, along with the increase of the equivalent of the explosive source TNT, the corner has large-area plastic deformation and the longitudinal girder has large-area plastic deformation. And under the third working condition, the longitudinal bone distribution plastic area continues to increase along with the continuous increase of the TNT equivalent, and the small-range plastic area also appears on the beam. And in the fourth working condition, the limit load of the cross beam is weakened, and a large-area plastic deformation area begins to appear.
The structural response analysis is carried out on the deck under four typical working conditions, and for the typical deck working conditions, the longitudinal beams are considered to be weak reinforcing ribs, and the strong cross beams are considered to be strong members. The analysis for four exemplary conditions is shown in FIG. 9. With the gradual increase of the load factor of the strong component, the plasticity range of the strong component is larger and larger, and the analysis combined with the strain cloud chart can show that the theoretical criterion condition is met under the typical small deformation damage mode.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (1)

1. A method for judging the problem of a cabin implosion small deformation plastic damage mode is characterized by comprising the following steps:
step 1: calculating the equivalent overpressure P of the shock wave load according to a pressure time-course curve measured by a pressure sensor in the center of the cabin grillage after explosion1；
Figure FDA0002484674780000011
Wherein p (t) is measured by a pressure sensor; t is t0The time of positive pressure action of shock wave;
step 2: equivalent overpressure P according to shock wave load1And equivalent slat beam tape width B1Calculating the load P0；
P0＝P1B1
Wherein, B1＝2Lb，LbIs the stringer pitch;
and step 3: according to load P0Calculating the counter force f borne by the stringerR；
Figure FDA0002484674780000012
Wherein M is0b＝σ0bh2/4，σ0B and h are the width and height of the beam, respectively, for yield limit; l is the spacing between the strong ribs; n is the number of cabin cross members;
and 4, step 4: calculating the static load failure pressure P of the stringercbAnd the static load destructive pressure P of the strong ribcL；
Figure FDA0002484674780000013
PcL＝4M0L/L2
Wherein M is0L＝σ0BH2(ii)/4; h is the height of the stringer; b is A/H; a is the cross-sectional area of the beam;
and 5: judging the damage modes of the common reinforcing ribs and the strong members;
if Pcb≤P0≤3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates small deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd f isR≤PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component does not generate plastic deformation;
if P0＞3PcbAnd P iscL≤fR≤3PcLJudging that the common reinforcing rib generates large-area plastic deformation and the strong component generates small plastic deformation;
if P is satisfied0＞3PcbAnd f isR＞3PcLAnd judging that the common reinforcing rib generates large-area plastic deformation and the strong component generates large-area plastic deformation.
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CN118051997A (en) * 2024-02-27 2024-05-17 中国人民解放军92578部队 Calculation method for flexural deformation of cartilage frame reinforcing plate under typical explosion load

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