CN114781234A - Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test - Google Patents
Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test Download PDFInfo
- Publication number
- CN114781234A CN114781234A CN202210697077.3A CN202210697077A CN114781234A CN 114781234 A CN114781234 A CN 114781234A CN 202210697077 A CN202210697077 A CN 202210697077A CN 114781234 A CN114781234 A CN 114781234A
- Authority
- CN
- China
- Prior art keywords
- thickness
- equivalent
- target panel
- determining
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a method for determining the thickness of an equivalent target of a vulnerable structure for an airplane impact dynamics test, and belongs to the technical field of airplane tests. The method comprises the following steps: s1, determining an equivalent model; s2, determining bullet materials and sizes; s3, determining the size of the plug hole and the size of the collapsing reinforcing ribs; s4, calculating the dimensionless equivalent thickness; s5, fitting a residual velocity formula coefficient according to the test result; and S6, comparing the simulation result with an empirical formula to verify the thickness determination method. The method solves the problem that a method for calculating the equivalent thickness of the structural target panel with the reinforcing ribs is not available at present, realizes the projectile power assessment test by using the cheap homogeneous metal target panel to replace a reinforcing rib plate frame structure in engineering, and greatly reduces the difficulty of physical experiments.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a method for determining the thickness of an equivalent target of a vulnerable structure for airplane impact dynamics testing.
Background
An aircraft engine unconfinement event can result in a serious air crash of a crash of man and aircraft. Dangerous fragments with high speed and high energy penetrate through a casing and fly out to damage a cabin, an oil tank, a hydraulic pipeline, an electric appliance control circuit and the like of an airplane, so that secondary damages such as cabin decompression, oil tank fire, airplane control failure and the like are caused, and air crash accidents are possibly caused.
The stiffened plate is widely applied to an airplane casing structure, after an engine rotor is broken or a blade is broken, the casing is firm enough to contain fragments in the casing, so that the fragments which are thrown outwards are avoided, and the stiffened plate has important significance in the field of airplane flight safety design. The most direct method for researching the containment of the case is to carry out a real airplane impact dynamics test, and foreign aeroengine companies often use a special outdoor test bed frame to carry out the airplane impact dynamics test of the fan blades at the end of the development of a novel engine.
The test for testing the impact dynamics of the real airplane has the characteristics of high cost and unrepairable and reusable engine. In order to reduce the cost and research difficulty, the mechanism of impact and damage of the high-speed centrifugal flight blade on the casing is researched from the aspects of material mechanical property, high-speed impact damage and the like through a target test and a numerical simulation method, and the method has a great reference value for the casing inclusion design method.
When actual target practice tests and numerical simulations are performed, the engine fan blade fragment and casing containment regions are usually simplified into flat strip blades and metal target plates. When the flat strip blade impacts the stiffened plate, the stiffened plate mainly has failure modes of local shearing impact plug, integral elastic-plastic deformation, back petal-shaped damage, tearing along the reinforcing rib, transverse tearing of the target plate and the like. The calculation method for simplifying the reinforcing ribs into the plates with equivalent thickness in engineering is feasible.
Due to the existence of the reinforcing ribs, the method for determining the thickness of the structural target panel has certain difficulty, and a method for calculating the equivalent thickness of the structural target panel with the reinforcing ribs is lacked at present.
Therefore, the method for determining the thickness of the vulnerable structure equivalent target for the aircraft impact dynamics test has important significance for the containment design of the aircraft engine case and the structural optimization of the stiffened plate.
Disclosure of Invention
The invention solves the technical problems that: at present, a method for calculating the equivalent thickness of the structural target panel with the reinforcing ribs is lacked.
In order to solve the problems, the technical scheme of the invention is as follows:
the method for determining the thickness of the vulnerable structure equivalent target for the aircraft impact dynamics test comprises the following steps:
s1, determining an equivalent model
Simplifying fragments of fan blades of an engine and a housing containing area of a casing in the non-inclusive event of the aero-engine into an equivalent model of a structural target panel combination with a plurality of reinforcing ribs which is punctured by flat blades;
s2, determining bullet materials and sizes;
s3, determining the size of the plug hole and the size of the collapsing reinforcing ribs;
s4, calculating the dimensionless equivalent thickness
Assuming length of the punched or collapsed ribs and thickness of the slat blades
Equal, the shape and size of the punched plug hole of the structural target panel are the same as the cross-sectional area of the flat plate strip blade, and the dimensionless equivalent thickness
The calculation formula is as follows:
in the above-mentioned formula, the compound has the following structure,
in order to have a dimensionless equivalent thickness,
is the thickness of the blade of the flat plate strip,
for the quality of the ram or the collapse stiffened plate,
the length of the blade of the flat plate strip,
equivalent thickness of structural target panel in aircraft impact dynamics test
The calculation formula of (2) is as follows:
in the above formula, the first and second carbon atoms are,
for the equivalent thickness of the structural target panel in the aircraft impact dynamics test,
in order to have a dimensionless equivalent thickness,
the thickness of the structural target panel;
s5, fitting a residual velocity formula coefficient according to the test result;
and S6, comparing the simulation result with an empirical formula to verify the thickness determination method.
Further, in step S1, the rib has the same shape as the rib on the actual casing accommodating area.
Furthermore, the reinforcing ribs are cuboid or trapezoidal cubes.
Further, step S1 also includes the following:
an equivalent target thickness determination method was constructed based on the following assumptions:
when the flat strip blade penetrates the reinforcing ribs, the mass of the reinforcing ribs which are penetrated by the flat strip blade and are punched or collapsed is the mass of the contact part of the flat strip blade and the structural target panel,
when the reinforcing ribs are penetrated by the flat plate strip blades, the equivalent thickness of the reinforcing ribs is the quotient of the volume of the punched or collapsed reinforcing ribs in the punching hole and the cross-sectional area of the bullet hole, and the total equivalent thickness penetrated by the bullet body is the sum of the thickness of the structural target panel and the equivalent thickness of the reinforcing ribs.
Still further, step S2 includes the following:
determining bullets with the same material, shape and size as the fragments of the fan blades of the engine according to the parameters of the fragments of the fan blades of the engine simulated by the aircraft impact dynamics test, and setting the material, shape and size of the flat strip blades in the equivalent model according to the material, shape and thickness of the bullets.
Preferably, step S3 specifically includes the following steps:
s3-1, setting a structural target panel;
s3-2, setting a plug hole formed in the front surface of the structural target panel when the flat strip blade penetrates the reinforcing rib, wherein the size and the shape of the plug hole are the same as those of the cross section of the flat strip blade obtained in the step S2;
s3-3, setting a plurality of reinforcing ribs on the back of the structural target panel, wherein the length of each reinforcing rib is equal to the thickness of each flat batten blade.
Preferably, in step S4,
quality of ram or caving ribbed plate
The calculation formula of (a) is as follows:
in the above formula, the first and second carbon atoms are,
for the quality of the ram or the collapse stiffened plate,
as to the density of the reinforcing ribs,
the thickness of the reinforcing rib is taken as the thickness,
is the thickness of the flat strip blade.
Preferably, step S5 includes the following:
based on the bullet material, size determined in step S2, the equivalent thickness of the structural target panel determined in step S4
Carrying out a targeting test and obtaining a targeting test result to obtain bullet speed data equivalent to the flat strip blade, and obtaining a residual speed calculation formula when the flat strip blade penetrates into the reinforcing ribs according to a Recht-Ipson formula as follows:
in the above formula, the first and second carbon atoms are,
the residual speed of the flat strip blade is obtained,
the initial speed of the flat strip blade is the initial speed,
in order to obtain the ballistic limit velocity,
in order to be a mass coefficient,
in order to be a coefficient of speed,
for the equivalent thickness of a structural target panel in an aircraft impact dynamics test,
the length of the blade of the flat plate strip,
the amount of the blade of the flat plate strip is,
is the plug mass.
Further preferably, step S6 specifically includes the following steps:
s6-1, determining the equivalent thickness of the structural target panel determined in step S4
Fitting the residual velocity formula coefficient by combining the step S5 to obtain the structural target panel ballistic limit of the theoretically calculated equivalent model;
s6-2, establishing a finite element simulation model with the same parameters as the equivalent model through finite element simulation software, and carrying out numerical simulation on the finite element simulation model to obtain the structural target panel trajectory limit of the numerically-simulated equivalent model;
s6-3, comparing the structural target panel ballistic limit of the equivalent model calculated theoretically with the structural target panel ballistic limit of the equivalent model simulated numerically, and verifying the correctness of the vulnerable structure equivalent target thickness determination method.
The beneficial effects of the invention are:
(1) the invention provides a method for calculating equivalent thickness of a structural target panel with reinforcing ribs based on a mass equivalent calculation based on a flat strip blade impact metal reinforced target plate model, two assumptions are provided, the metal reinforced target plate is equivalent to a target plate with homogeneous thickness by the mass equivalent method and combining simulation analysis and a residual velocity calculation formula, and the evaluation of target penetrating capability by using a homogeneous target plate to replace a given reinforced plate frame structure in engineering is realized;
(2) the invention provides a method for determining the equivalent target thickness of a reinforced target by combining a mass equivalent combination residual speed calculation formula and simulation analysis;
(3) the invention provides an equivalent target thickness calculation formula and a conventional flow for checking the equivalent target thickness calculation method, establishes an equivalent relation between a reinforced plate frame structure and a homogeneous target plate, and verifies the feasibility of the equivalent target thickness calculation method through simulation analysis and a residual speed calculation formula;
(4) the invention realizes the shot power assessment test by using the cheap homogeneous metal target plate to replace the reinforced plate frame structure in engineering, and greatly reduces the difficulty of physical experiments. The method has wide applicability and simple actual operation, can meet the requirements of the inclusive design of the aeroengine case and the rapid design and optimization of the stiffened plate structure, and shortens the design period.
Drawings
FIG. 1 is a flow chart of a method for determining the thickness of an equivalent target of a vulnerable structure for an aircraft impact dynamics test according to example 1;
FIG. 2 is a schematic view of an equivalent model in example 1;
FIG. 3 is a schematic diagram showing the equivalent model state when the blade of the flat plate strip penetrates the reinforcing ribs in embodiment 1;
FIG. 4 is a schematic structural view of an equivalent model in example 2.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, and "a plurality" typically includes at least two.
Example 1
The embodiment is a method for determining the thickness of a vulnerable structure equivalent target for aircraft impact dynamics test, and as shown in fig. 1, the method comprises the following steps:
s1, determining an equivalent model
Simplifying the fragments of the fan blades of the engine and the containing area of the casing in the non-inclusive event of the aeroengine into an equivalent model formed by punching flat blades through a structural target panel with five reinforcing ribs, wherein the equivalent model is shown in figure 2, the reinforcing ribs have the same shape as the reinforcing ribs on the containing area of the actual casing, the reinforcing ribs are cuboids,
and constructing an equivalent target thickness determination method based on the following assumptions:
when the flat strip blade penetrates the reinforcing ribs, the mass of the reinforcing ribs which are penetrated by the flat strip blade and are punched or collapsed is the mass of the contact part of the flat strip blade and the structural target panel,
when the flat plate strip blade penetrates the reinforcing ribs, the equivalent thickness of the reinforcing ribs is the quotient of the volume of the punched or collapsed reinforcing ribs in the punching hole and the cross-sectional area of the bullet hole, the total equivalent thickness penetrated by the bullet body is the sum of the thickness of the structural target panel and the equivalent thickness of the reinforcing ribs, and the equivalent model state is shown in fig. 3;
s2, determining bullet material and size
Determining bullets with the same material, shape and size as the fragments of the fan blades of the engine according to the parameters of the fragments of the fan blades of the engine simulated by the aircraft impact dynamics test, and setting the material, shape and size of the flat strip blades in the equivalent model according to the material, shape and thickness of the bullets;
s3, determining the size of the plug hole and the size of the collapse reinforcing rib, and specifically comprising the following steps:
s3-1, setting a structural target panel,
s3-2, setting a plug hole on the front surface of the structural target panel when the flat strip blade penetrates the reinforcing rib, wherein the size and shape of the plug hole are the same as the size and shape of the cross section of the flat strip blade obtained in the step S2,
s3-3, setting five reinforcing ribs on the back of the structural target panel, wherein the length of each reinforcing rib is equal to the thickness of each flat plate strip blade;
s4, calculating the dimensionless equivalent thickness
Assuming length of the punched or collapsed ribs and thickness of the slat blades
Equal and structural target panelThe shape and size of the plug hole are the same as the cross section area of the flat strip blade, and the dimensionless equivalent thickness is obtained
The calculation formula is as follows:
in the above formula, the first and second carbon atoms are,
in order to have a dimensionless equivalent thickness,
is the thickness of the blade of the flat plate strip,
for the quality of the ram or the collapse stiffened plate,
the length of the blade of the flat plate strip,
wherein the mass of the ram or the collapse stiffened plate
The calculation formula of (a) is as follows:
in the above-mentioned formula, the compound has the following structure,
for the quality of the ram or the collapse stiffened plate,
as to the density of the reinforcing ribs,
the thickness of the reinforcing rib is taken as the thickness,
is the thickness of the blade of the flat plate strip,
equivalent thickness of structural target panel in aircraft impact dynamics test
The calculation formula of (c) is:
in the above-mentioned formula, the compound has the following structure,
for the equivalent thickness of the structural target panel in the aircraft impact dynamics test,
in order to have a dimensionless equivalent thickness,
the thickness of the structural target panel;
s5, fitting residual velocity formula coefficients according to test results
Based on the bullet material, size determined in step S2, the equivalent thickness of the structural target panel determined in step S4
Carrying out a targeting test and obtaining a targeting test result to obtain bullet speed data equivalent to the flat strip blade, and obtaining a residual speed calculation formula when the flat strip blade penetrates into the reinforcing ribs according to a Recht-Ipson formula as follows:
in the above formula, the first and second carbon atoms are,
is a flat leafThe speed of the sheet remaining is such that,
the initial speed of the slat blades is the flat strip,
in order to obtain the ballistic limit velocity,
in order to be a mass coefficient of the material,
in order to be the speed factor,
for the equivalent thickness of the structural target panel in the aircraft impact dynamics test,
the length of the blade of the flat plate strip,
the blade amount of the flat plate strip is measured,
is the plug mass;
s6, comparing the simulation result with an empirical formula to verify the thickness determination method, which specifically comprises the following steps:
s6-1, determining the equivalent thickness of the structural target panel determined in step S4
Fitting the residual velocity formula coefficient by combining the step S5 to obtain the structural target panel ballistic limit of the theoretically calculated equivalent model;
s6-2, establishing a finite element simulation model with the same parameters as the equivalent model through finite element simulation software, carrying out numerical simulation on the finite element simulation model to obtain the structural target panel ballistic limit of the numerically simulated equivalent model,
s6-3, comparing the structural target panel ballistic limit of the equivalent model calculated theoretically with the structural target panel ballistic limit of the equivalent model simulated numerically, and verifying the correctness of the vulnerable structure equivalent target thickness determination method.
Example 2
This embodiment is different from embodiment 1 in that:
in step S1, the reinforcing ribs are trapezoidal cubes.
Claims (9)
1. The method for determining the thickness of the vulnerable structure equivalent target for the aircraft impact dynamics test is characterized by comprising the following steps of:
s1, determining an equivalent model
Simplifying the fragments of the fan blades of the engine and the containing area of the casing in the non-inclusive event of the aircraft engine into an equivalent model of a structural target panel combination with a plurality of reinforcing ribs which is punctured by a flat blade;
s2, determining bullet materials and sizes;
s3, determining the size of the plug hole and the size of the collapsing reinforcing ribs;
s4, calculating the dimensionless equivalent thickness
Assuming length of the punched or collapsed ribs and thickness of the slat blades
Equal, the shape and size of the punched plug hole of the structural target panel are the same as the cross section area of the flat plate strip blade, and the dimensionless equivalent thickness
The calculation formula is as follows:
in the above formula, the first and second carbon atoms are,
in order to have a dimensionless equivalent thickness,
is the thickness of the blade of the flat plate strip,
for the quality of the ram or the collapse stiffened plate,
the length of the blade of the flat plate strip,
equivalent thickness of structural target panel in aircraft impact dynamics test
The calculation formula of (2) is as follows:
in the above formula, the first and second carbon atoms are,
for the equivalent thickness of the structural target panel in the aircraft impact dynamics test,
in order to have a dimensionless equivalent thickness,
the thickness of the structural target panel;
s5, fitting a residual velocity formula coefficient according to the test result;
and S6, comparing the simulation result with an empirical formula to verify the thickness determination method.
2. The method of claim 1, wherein the reinforcement rib of step S1 is the same shape as the reinforcement rib of the actual housing region.
3. The method for determining the thickness of the vulnerable structure equivalent target for aircraft impact dynamics testing according to claim 2, wherein the reinforcing ribs are cuboid or trapezoidal cubes.
4. The method of claim 1, wherein the step S1 further comprises the following steps:
an equivalent target thickness determination method was constructed based on the following assumptions:
when the flat strip blade penetrates the reinforcing rib, the mass of the reinforcing rib which is penetrated by the flat strip blade and is filled or collapsed is the mass of the contact part of the flat strip blade and the structural target panel,
when the reinforcing ribs are penetrated by the flat plate strip blades, the equivalent thickness of the reinforcing ribs is the quotient of the volume of the punched or collapsed reinforcing ribs in the punching hole and the cross-sectional area of the bullet hole, and the total equivalent thickness penetrated by the bullet body is the sum of the thickness of the structural target panel and the equivalent thickness of the reinforcing ribs.
5. The method of claim 1, wherein the step S2 comprises the following steps:
determining bullets with the same material, shape and size as the fragments of the fan blades of the engine according to the parameters of the fragments of the fan blades of the engine simulated by the aircraft impact dynamics test, and setting the material, shape and size of the flat strip blades in the equivalent model according to the material, shape and thickness of the bullets.
6. The method for determining the thickness of the target equivalent to the vulnerable structure for the aircraft impact dynamics test according to claim 5, wherein the step S3 specifically comprises the following steps:
s3-1, setting a structural target panel;
s3-2, setting a plug hole formed in the front surface of the structural target panel when the flat strip blade penetrates the reinforcing rib, wherein the size and the shape of the plug hole are the same as those of the cross section of the flat strip blade obtained in the step S2;
s3-3, setting a plurality of reinforcing ribs on the back of the structural target panel, wherein the length of each reinforcing rib is equal to the thickness of each flat batten blade.
7. The method of claim 1, wherein in step S4,
quality of ram or caving ribbed plate
The calculation formula of (c) is as follows:
in the above formula, the first and second carbon atoms are,
for the quality of the ram or the collapse stiffened plate,
in order to determine the density of the reinforcing ribs,
the thickness of the reinforcing rib is taken as the thickness,
is the thickness of the flat strip blade.
8. The method of claim 1, wherein the step S5 comprises the following steps:
according to the bullet material and size determined in the step S2, the equivalent thickness of the structural target panel determined in the step S4
To proceed withThe target practice test and the target practice test result are obtained, the bullet speed data equivalent to the flat strip blade are obtained, and the residual speed calculation formula when the flat strip blade penetrates into the reinforcing rib is obtained according to the Recht-Ipson formula as follows:
in the above formula, the first and second carbon atoms are,
the residual speed of the flat strip blade is obtained,
the initial speed of the slat blades is the flat strip,
in order to obtain the ballistic limit velocity,
in order to be a mass coefficient of the material,
in order to be a coefficient of speed,
for the equivalent thickness of a structural target panel in an aircraft impact dynamics test,
the length of the blade of the flat plate strip,
the blade amount of the flat plate strip is measured,
is the plug mass.
9. The method for determining the thickness of the target equivalent to the vulnerable structure for the aircraft impact dynamics test according to claim 1, wherein the step S6 specifically comprises the following steps:
s6-1, determining the equivalent thickness of the structural target panel determined in step S4
Fitting the residual velocity formula coefficient by combining the step S5 to obtain the structural target panel ballistic limit of the theoretically calculated equivalent model;
s6-2, establishing a finite element simulation model with the same parameters as the equivalent model through finite element simulation software, and carrying out numerical simulation on the finite element simulation model to obtain the structural target panel trajectory limit of the equivalent model of the numerical simulation;
s6-3, comparing the structural target panel ballistic limit of the equivalent model calculated theoretically with the structural target panel ballistic limit of the equivalent model simulated numerically, and verifying the correctness of the vulnerable structure equivalent target thickness determination method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210697077.3A CN114781234B (en) | 2022-06-20 | 2022-06-20 | Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210697077.3A CN114781234B (en) | 2022-06-20 | 2022-06-20 | Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114781234A true CN114781234A (en) | 2022-07-22 |
| CN114781234B CN114781234B (en) | 2022-09-13 |
Family
ID=82420843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210697077.3A Active CN114781234B (en) | 2022-06-20 | 2022-06-20 | Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114781234B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005043107A2 (en) * | 2003-10-30 | 2005-05-12 | Hottinger Baldwin Messtechnik Gmbh | Device for determining strains on fiber composite components |
| CN103454061A (en) * | 2013-08-19 | 2013-12-18 | 北京航空航天大学 | Test system and method for manufacturing metal sheet impact pit with specified dimension |
| CN108647367A (en) * | 2018-03-12 | 2018-10-12 | 南京理工大学 | A kind of Double-layer titanium alloy casing containment curve plotting method |
| CN109255140A (en) * | 2017-11-28 | 2019-01-22 | 南昌航空大学 | A kind of water tank Security Design Methods for aero-engine casing air-tight test |
| CN110532656A (en) * | 2019-08-20 | 2019-12-03 | 哈尔滨工程大学 | A kind of metal framed plate structure equivalent-designing method for injuring similitude based on penetration |
-
2022
- 2022-06-20 CN CN202210697077.3A patent/CN114781234B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005043107A2 (en) * | 2003-10-30 | 2005-05-12 | Hottinger Baldwin Messtechnik Gmbh | Device for determining strains on fiber composite components |
| CN103454061A (en) * | 2013-08-19 | 2013-12-18 | 北京航空航天大学 | Test system and method for manufacturing metal sheet impact pit with specified dimension |
| CN109255140A (en) * | 2017-11-28 | 2019-01-22 | 南昌航空大学 | A kind of water tank Security Design Methods for aero-engine casing air-tight test |
| CN108647367A (en) * | 2018-03-12 | 2018-10-12 | 南京理工大学 | A kind of Double-layer titanium alloy casing containment curve plotting method |
| CN110532656A (en) * | 2019-08-20 | 2019-12-03 | 哈尔滨工程大学 | A kind of metal framed plate structure equivalent-designing method for injuring similitude based on penetration |
Non-Patent Citations (4)
| Title |
|---|
| 梁斌等: "离散杆和EFP组合战斗部对飞机毁伤效应研究", 《弹箭与制导学报》 * |
| 甘宏伟等: "加筋板架结构与均质靶板等效关系的数值分析", 《四川兵工学报》 * |
| 陈长海等: "加筋板架抗动能穿甲的等效防护厚度研究", 《海军工程大学学报》 * |
| 黄晶等: "飞机壁板结构击穿的数值模拟", 《兵器材料科学与工程》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114781234B (en) | 2022-09-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Chelapati et al. | Probabilistic assessment of aircraft hazard for nuclear power plants | |
| CN114781234B (en) | Method for determining thickness of vulnerable structure equivalent target for aircraft impact dynamics test | |
| WO2015163964A2 (en) | Self-shielding tank | |
| Gwaltney | MISSILE GENERATION AND PROTECTION IN LIGHT-WATER-COOLED POWER REACTOR PLANTS. | |
| Feng et al. | Numerical and analytical investigations on projectile perforation on steel–concrete–steel sandwich panels | |
| CN115270334A (en) | Bearing case rigidity simulation piece and design method thereof | |
| Yu et al. | Dynamic response of fully-clamped steel plate under laboratory-simulated sequential fragment impact and blast loading | |
| Wang et al. | Damage behavior of concrete members subjected to underwater contact explosion | |
| Hussein et al. | Blast response of a thin oriented strand board wall | |
| Zhang et al. | Penetration depth of RC panels subjected to the impact of aircraft engine missiles | |
| Nishida et al. | Evaluation of local damage to reinforced concrete panels subjected to oblique impact-Simulation analysis for evaluating perforation phenomena caused by oblique impact of deformable projectiles | |
| Liu et al. | Numerical analyses of a shield building subjected to a large commercial aircraft impact | |
| Cheng et al. | Theoretical and numerical investigation on perforation resistance of monolithic and segmented concrete targets with steel liners under normal penetration | |
| Santini et al. | Numerical simulation of fluid-structure interaction in aircraft fuel tanks subjected to hydrodynamic ram penetration | |
| Li et al. | A case study of the effect of cladding panels on the response of reinforced concrete frames subjected to distant blast loadings | |
| Zahrin et al. | Numerical simulation of oblique impact on structure using finite element method | |
| Xuanneng Gao | Propagation law of shock waves in single layer spherical lattice shell under internal explosion | |
| Hussein | Blast protection wall systems: Literature review | |
| Almomani et al. | Analysis methodology of local damage to dry storage facility structure subjected to aircraft engine crash | |
| Catovic | Review of the estimation methods for external blast loads on structures | |
| Kang et al. | Analytical study of perforation damage in reinforced concrete slabs subjected to oblique impact by projectiles with different nose shapes | |
| Kang et al. | Impact simulations on local damage of reinforced concrete panel influenced by projectile nose shape | |
| Kazuma et al. | Impact simulation of a large commercial aircraft into reinforced concrete walls | |
| Adrees et al. | Numerical Assessment of a Sustainable Blast Protection Wall | |
| Eric et al. | Scabbing And Perforation Of Reinforced Concrete Walls Designed For Aircraft Impact Protection |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |