CN111027245B - Helicopter corrugated beam and design method of corrugated section of corrugated beam - Google Patents
Helicopter corrugated beam and design method of corrugated section of corrugated beam Download PDFInfo
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Abstract
The invention belongs to the field of basic application of aircrafts, and particularly relates to a corrugated beam of a helicopter and a design method of a corrugated section of the corrugated beam. The weak link of the composite material corrugated beam structure is designed into a small circular arc transition form between the two ends of the structure and the flange, and a layer of composite material is laid around the web plate for a few times, so that the initial damage of the structure can be ensured to start from the end part; straight sections can be arranged at intervals of the waveform sections of the waveform beam and used for equipment installation interfaces, and the waveform sections are in a group of three waves, so that good crushing performance is guaranteed, and the material ratio energy absorption capacity is high.
Description
Technical Field
The invention belongs to the field of basic application of aircrafts, and particularly relates to a corrugated beam of a helicopter and a design method of a corrugated section of the corrugated beam.
Background
When the helicopter crashes in an accident, the crash-resistant structure of the helicopter body is required to absorb the crash energy and reduce the peak load during the crash impact, thereby achieving the purpose of saving the lives of passengers.
The traditional helicopter structure is designed to absorb energy through the falling impact of the metal structure of the lower component of the helicopter body, or is designed to absorb energy through simply adopting a composite material structure. However, for the design of the traditional metal structure for resisting falling and collision impact, the design structure is generally heavier, and because the composite material is a brittle material, the energy absorption capacity of the material is relatively weaker, and the good energy absorption effect is difficult to realize for the general composite material configuration design.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a corrugated beam of a helicopter and a design method of a corrugated section of the corrugated beam. Meanwhile, the web plates are not easy to destabilize and damage, the beam structure has good rigidity, and the beam has the characteristics of light structure weight, simple manufacture, low cost and the like.
The technical scheme of the invention is as follows:
in a first aspect, there is provided a helicopter waveform beam comprising: an upper edge strip plate 1, a corrugated web plate 2, a lower edge strip plate 3 and filling wires 4, wherein one end of the corrugated web plate 2 is connected with the upper edge strip plate 1, the other end of the corrugated web plate 2 is connected with the lower edge strip plate 3, the filling wires 4 are arranged at the connecting corner of the corrugated web plate 2 and the upper edge strip plate 1 and the connecting corner of the corrugated web plate 2 and the lower edge strip plate 3,
the binding surfaces between the upper edge strip plate 1, the lower edge strip plate 3 and the web plate 2 are overlapped by the same material cloth as the materials of the upper edge strip plate 1 and the lower edge strip plate 3 and are co-cured in a hot pressing furnace to form an integral structure,
the corrugated web 2 comprises corrugated and flat sections.
Optionally, the filler wire 4 is a styrofoam plate and a carbon wire.
In a second aspect, a method for designing a corrugated section of a corrugated beam of a helicopter is provided, which is characterized by comprising the following steps:
determining a beam height value L according to the overall arrangement of the helicopter;
calculating the height amplitude ratio and the wavelength amplitude ratio of the waveform beam according to the height value L;
determining the amplitude A and the wavelength lambda according to the height amplitude ratio and the wavelength amplitude ratio;
setting an initial value of a fillet radius R of the corrugated web plate as an amplitude A, establishing a physical model of the corrugated beam structure according to the initial values of a beam height value L, the amplitude A, a wavelength lambda and the fillet radius R, then determining the property of a material, and carrying out finite element simulation on the physical model of the corrugated beam structure by using the property of the material to obtain a load-time curve and an energy-time curve;
calculating specific energy absorption by using a specific energy absorption calculation formula according to the load-time curve and the energy-time curve;
according to a preset step length, carrying out iterative solution on the fillet radius R to obtain a solution R with the largest energy absorption value;
and determining the waveform beam structure according to the beam height value L, the amplitude A, the wavelength lambda and the maximum R value.
Optionally, calculating a height amplitude ratio and a wavelength amplitude ratio of the waveform beam according to the height value L specifically includes:
simplifying the waveform of the waveform beam into a triangular wave;
and (3) obtaining a relation (1) by operation according to the inertia moment definition formula:
wherein f is 1 As a process function, δ is the thickness of the corrugated beam, a is the amplitude of the triangular wave, and λ is the wavelength of the triangular wave;
according to the formula (2),
L/ρ＜20(2)，
to obtain formula (3):
FL 2 ＝f 2 (A,ω,δ)L 2 <400I x (3)
wherein, f 2 (a, ω, δ) is the area of the triangular waveform, and is specifically formula (4):
obtaining a height amplitude ratio and wavelength amplitude ratio correlation according to the formulas (1) to (4):
wherein A is the wave amplitude, lambda is the wavelength, F is the crushing cross-sectional area, delta is the thickness of the corrugated beam,
the radius of the section of the corrugated beam, and L is the height value of the corrugated beam;
and taking the minimum value of the height amplitude ratio value range as the height amplitude ratio, and taking the maximum value of the wavelength amplitude ratio as the wavelength amplitude ratio.
Optionally, determining the amplitude a and the wavelength λ according to the height amplitude ratio and the wavelength amplitude ratio specifically includes:
calculating the amplitude A according to the height L and the height amplitude ratio;
and calculating the wavelength lambda according to the amplitude A and the wavelength amplitude ratio.
Optionally, establishing a solid model of the wave beam structure according to initial values of the beam height value L, the amplitude a, the wavelength λ, and the fillet radius R, specifically including:
and establishing a physical model of the wave-shaped beam structure by using three-dimensional engineering design software according to the initial values of the beam height value L, the wave amplitude A, the wavelength lambda and the fillet radius R.
Optionally, the predetermined step size is half of the amplitude.
Optionally, iteratively solving the R solution with the largest energy absorption value for the fillet radius R specifically includes:
and according to a preset step size, iterating to obtain a maximum R solution that the fillet radius R of the corrugated web meets R epsilon [ A0, 3A0 ].
The invention has the beneficial effects that:
the corrugated beam structure has the following advantages:
1. the corrugated web has good normal stiffness, can obtain great out-of-plane stiffness and shear buckling strength by using a thin thickness without reinforcing ribs, can effectively save materials, can be provided with other system components in a corrugated beam form, has good connectivity, and is beneficial to practical application in engineering practice.
2. The energy absorption device has the advantages that the ratio of the average crushing load to the initial peak load is improved on the premise of higher specific energy absorption capacity, the impact on drivers and passengers is reduced, and large fragments cannot be generated after the structure is damaged to influence the life safety of passengers.
3. The composite material corrugated beam has the characteristics of simple structure, light weight, simple manufacture, low cost and the like
4. The design method selects optimized design parameters through multiple rounds of iteration, improves the specific energy absorption capacity of the material, reduces peak load and achieves a high specific energy absorption effect of the material.
5. The wave-shaped design is beneficial to increasing the stable crushing process, can stably and more fully absorb a large amount of energy, and is an ideal choice for designing the falling and impacting performance of the composite material structure.
6. Under the condition of limited weight, the design of a beam or frame structure is beneficial to improving the vertical crashworthiness of the aircraft.
Drawings
FIG. 1 is a block diagram of a corrugated beam according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a corrugated beam taken along line A-A in accordance with an embodiment of the present invention;
FIG. 3 is a cross-sectional view of a corrugated beam taken along line B-B in accordance with an embodiment of the present invention;
FIG. 4 is a view of a layer structure of a corrugated beam according to an embodiment of the present invention;
FIG. 5 is a flow chart of a method of designing a corrugated section of a corrugated beam of a helicopter in accordance with an embodiment of the present invention;
FIG. 6 shows the critical stress σ of the material cr Curve of length-to-slenderness ratio L/rho of rod
Wherein, the upper edge strip 1, the corrugated web 2, the lower edge strip 3 and the filling wire 4.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying 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 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 corrugated beam structure of the invention is a laminated plate integrated structure as shown in figure 1, and comprises an upper edge strip plate 1, a corrugated web plate 2, a lower edge strip plate 3 and a carbon filling wire 4. Corrugated web 2 sets up between last border slat 1 and lower border slat 3, web 2 and last border slat 1, it has polystyrene foam plastics panel to fill between web 2 and the lower border slat 3 and also can replace into the carbon silk, it fills in to ensure that edge slat and web overlap joint inner chamber is gas-free, the binding face between upper edge slat 1, lower border slat 3 and web 2 passes through the overlap joint of edge slat carbon cloth and carries out the curing together of autoclave and form overall structure, go up border slat 1, the thickness of lower border slat 3 is 2mm, the thickness of web 2 is 1.5 mm. The overlapping amount of the edge strip plate 1, the lower edge strip plate 3 and the web plate 2 is 25mm, as shown in figure 4. The weight and strength effects of the invention are better by setting the thickness of each layer.
The invention relates to a helicopter corrugated beam, comprising: an upper edge strip plate 1, a corrugated web plate 2, a lower edge strip plate 3 and a filling wire 4, wherein one end of the corrugated web plate 2 is connected with the upper edge strip plate 1, the other end of the corrugated web plate 2 is connected with the lower edge strip plate 3, the filling wire 4 is arranged at the connecting corner of the corrugated web plate 2 and the upper edge strip plate 1 and the connecting corner of the corrugated web plate 2 and the lower edge strip plate 3,
the binding surfaces between the upper edge strip plate 1, the lower edge strip plate 3 and the web plate 2 are overlapped by the same material cloth as the materials of the upper edge strip plate 1 and the lower edge strip plate 3 and are co-cured in a hot pressing furnace to form an integral structure,
the corrugated web 2 comprises corrugated and flat sections.
Alternatively, the filler wire 4 is a styrofoam plate and a carbon wire.
The invention relates to a design method of a corrugated section of a helicopter corrugated beam, which comprises the following steps:
determining a beam height value L according to the overall arrangement of the helicopter;
calculating the height amplitude ratio and the wavelength amplitude ratio of the waveform beam according to the height value L;
determining the amplitude A and the wavelength lambda according to the height amplitude ratio and the wavelength amplitude ratio;
setting an initial value of the fillet radius R of the corrugated web plate as an amplitude A, establishing a wave-shaped beam structure entity model according to a beam height value L, the amplitude A, the wavelength lambda and the initial value of the fillet radius R, then determining the property of a material, and performing finite element simulation on the wave-shaped beam structure entity model by using the material property to obtain a load-time curve and an energy-time curve;
calculating specific energy absorption by using a specific energy absorption calculation formula according to the load-time curve and the energy-time curve;
according to a preset step length, carrying out iterative solution on the fillet radius R to obtain a solution R with the largest energy absorption value;
and determining the waveform beam structure according to the beam height value L, the amplitude A, the wavelength lambda and the maximum R value.
Optionally, calculating a height amplitude ratio and a wavelength amplitude ratio of the waveform beam according to the height value L specifically includes:
simplifying the waveform of the waveform beam into a triangular wave;
and (3) obtaining a relation (1) by operation according to the inertia moment definition formula:
wherein f is 1 As a process function, δ is the thickness of the corrugated beam, a is the amplitude of the triangular wave, and λ is the wavelength of the triangular wave;
according to the formula (2),
l/rho < 20(2), to obtain formula (3):
obtaining an L/rho crushing area judgment condition, namely a formula (2), according to a curve graph (figure 6) of a critical stress equation (Euler formula) of the uniform-section rod under the action of a central axial compression load;
FL 2 ＝f 2 (A,ω,δ)L 2 <400I x (3)
wherein f is 2 (a, ω, δ) is the area of the triangular waveform, and is specifically formula (4):
according to the formulae (1) to (4) Obtaining the correlation of the height amplitude ratio and the wavelength amplitude ratio:
wherein A is the wave amplitude, lambda is the wavelength, F is the crushing cross-sectional area, delta is the thickness of the corrugated beam,
the radius of the section of the corrugated beam, and L is the height value of the corrugated beam;
and taking the minimum value of the height amplitude ratio value range as the height amplitude ratio, and taking the maximum value of the wavelength amplitude ratio as the wavelength amplitude ratio.
Optionally, determining the amplitude a and the wavelength λ according to the height amplitude ratio and the wavelength amplitude ratio specifically includes:
calculating the amplitude A according to the height L and the height amplitude ratio;
and calculating the wavelength lambda according to the amplitude A and the wavelength amplitude ratio.
Optionally, establishing a wave-shaped beam structure solid model according to initial values of the beam height value L, the amplitude a, the wavelength λ, and the fillet radius R, specifically including:
and establishing a physical model of the waved beam structure by using three-dimensional engineering design software according to initial values of the beam height value L, the wave amplitude A, the wavelength lambda and the fillet radius R.
Optionally, the predetermined step size is half the amplitude.
Optionally, the iterative solution of the fillet radius R to the R solution with the largest energy absorption value specifically includes:
and according to a preset step size, iterating to obtain a maximum R solution that the fillet radius R of the corrugated web meets R epsilon [ A0, 3A0 ].
The key points of the invention are as follows:
the weak link of the composite material corrugated beam structure is designed into a small circular arc transition form between the two ends of the structure and the flange, and a layer of composite material is laid around the web plate for a circle, so that the initial damage of the structure can be ensured to start from the end part;
straight sections can be arranged at intervals of the wave sections of the wave-shaped beam for equipment installation interfaces, and the wave sections are in a group of three waves, so that good crushing performance is ensured, and the wave-shaped beam has high material ratio energy absorption capacity;
the design parameter correlation obtained by the design method is as follows:
finally determining 3 key design parameters which are the beam height L, the single wavelength lambda of the corrugated web and the wave amplitude A respectively;
the constitutive equation, damage judgment and stiffness reduction of each layer of the unidirectional fiber reinforced composite material are realized through a user-defined material subprogram VUMAT in ABAQUS/Explicit (commercial software). And iterating R in the range of the A, 3A according to the step length A/2 to obtain the R solution with the maximum specific energy absorption value as a determined design parameter value, and designing the waveform beam structure according to the design parameter.
The foregoing is illustrative of the present invention and is not to be construed as limiting thereof. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. A helicopter waveform beam, comprising: an upper edge strip plate (1), a corrugated web plate (2), a lower edge strip plate (3) and filling wires (4), wherein one end of the corrugated web plate (2) is connected with the upper edge strip plate (1), the other end of the corrugated web plate (2) is connected with the lower edge strip plate (3), the filling wires (4) are arranged at the connecting corner of the corrugated web plate (2) and the upper edge strip plate (1) and the connecting corner of the corrugated web plate (2) and the lower edge strip plate (3),
the binding surfaces between the upper edge strip plate (1), the lower edge strip plate (3) and the web plate (2) are overlapped by a material cloth which is the same as the material of the upper edge strip plate (1) and the lower edge strip plate (3) and are co-cured in a hot pressing furnace to form an integral structure,
the corrugated web (2) comprises a corrugated section and a flat section.
2. A corrugated beam according to claim 1, characterised in that the filler wires (4) are styrofoam plate and carbon wires.
3. A design method of a corrugated section of a helicopter corrugated beam is characterized by comprising the following steps:
determining a beam height value L according to the overall arrangement of the helicopter;
calculating the height amplitude ratio and the wavelength amplitude ratio of the waveform beam according to the height value L, and specifically comprising the following steps:
simplifying the waveform of the waveform beam into a triangular wave;
and (3) obtaining a relation (1) by operation according to the inertia moment definition formula:
wherein f is 1 As a process function, δ is the thickness of the corrugated beam, a is the amplitude of the triangular wave, and λ is the wavelength of the triangular wave;
according to the formula (2),
L/ρ＜20 (2)，
to obtain formula (3):
FL 2 ＝f 2 (A,ω,δ)L 2 ＜400I x (3)
wherein, f 2 (a, ω, δ) is the area of the triangular waveform, and is specifically formula (4):
obtaining a height amplitude ratio and wavelength amplitude ratio correlation according to the formulas (1) to (4):
λ/A＞4，
wherein the content of the first and second substances,a is the wave amplitude, lambda is the wavelength, F is the crushing cross-sectional area, delta is the thickness of the corrugated beam,
the radius of the section of the corrugated beam, and L is the height value of the corrugated beam;
taking the minimum value of the height amplitude ratio value range as the height amplitude ratio, and taking the maximum value of the wavelength amplitude ratio as the wavelength amplitude ratio;
determining the amplitude A and the wavelength lambda according to the height amplitude ratio and the wavelength amplitude ratio;
setting an initial value of a fillet radius R of the corrugated web plate as an amplitude A, establishing a wave beam structure solid model according to the initial values of a beam height value L, the amplitude A, a wavelength lambda and the fillet radius R, then determining the property of a material, and carrying out finite element simulation on the wave beam structure solid model by using the material property to obtain a load-time curve and an energy-time curve;
calculating specific energy absorption by using a specific energy absorption calculation formula according to the load-time curve and the energy-time curve;
according to the preset step length, carrying out iteration on the fillet radius R to solve the R solution with the largest energy absorption value;
and determining the waveform beam structure according to the beam height value L, the amplitude A, the wavelength lambda and the maximum R value.
4. The method according to claim 3, wherein determining the amplitude A and the wavelength λ from the height amplitude ratio and the wavelength amplitude ratio comprises:
calculating the amplitude A according to the height L and the height amplitude ratio;
and calculating the wavelength lambda according to the amplitude A and the wavelength amplitude ratio.
5. The method of claim 3, wherein building a physical model of the waved beam structure from the initial values of the beam height L, amplitude A, wavelength λ, and fillet radius R comprises:
and establishing a physical model of the wave-shaped beam structure by using three-dimensional engineering design software according to the initial values of the beam height value L, the wave amplitude A, the wavelength lambda and the fillet radius R.
6. A method according to claim 3, wherein the predetermined step size is half the amplitude.
7. The method according to claim 3, wherein iteratively solving for the fillet radius R for a R solution that is greater than the energy absorption value comprises:
and according to a preset step length, iterating the maximum R solution that the fillet radius R of the corrugated web meets R epsilon [ A0, 3A0 ].
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180181A (en) * | 2011-03-30 | 2011-09-14 | 中南大学 | Method for realizing collision threshold of special train collision energy-absorbing component |
| CN102556333A (en) * | 2012-03-09 | 2012-07-11 | 北京航空航天大学 | Energy-absorbing scheme of corrugated beam structure at bottom of civil airplane body |
| CN103625555A (en) * | 2013-11-26 | 2014-03-12 | 湖南大学 | High-strength steel automobile front carling energy absorbing structure based on embedded carbon fiber |
| CN203528805U (en) * | 2013-08-08 | 2014-04-09 | 江西洪都航空工业集团有限责任公司 | Plane anti-collision energy-absorbing structure unit |
| JP2015066416A (en) * | 2013-09-28 | 2015-04-13 | 孝典 福元 | Simple stretcher for emergency evacuation |
| US9222260B1 (en) * | 2009-04-10 | 2015-12-29 | Su Hao | Lightweight multi-layer arch-structured armor (LMAR) |
| CN206053160U (en) * | 2016-08-13 | 2017-03-29 | 深圳雅致钢结构工程有限公司 | A kind of node structure of double-deck roof boarding cornice |
| CN108045547A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of composite torsion-box formula anti-crash endergonic structure |
| CN109421915A (en) * | 2017-09-05 | 2019-03-05 | 波音公司 | Energy absorption floor lower body |
| CN109455290A (en) * | 2018-10-25 | 2019-03-12 | 中国民航大学 | A kind of cargo deck lower part endergonic structure unit for fitting pendant property for improving aircraft |
| CN209258409U (en) * | 2018-11-06 | 2019-08-16 | 中国直升机设计研究所 | A kind of resistance to crash structure of helicopter |
-
2019
- 2019-12-04 CN CN201911229144.3A patent/CN111027245B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9222260B1 (en) * | 2009-04-10 | 2015-12-29 | Su Hao | Lightweight multi-layer arch-structured armor (LMAR) |
| CN102180181A (en) * | 2011-03-30 | 2011-09-14 | 中南大学 | Method for realizing collision threshold of special train collision energy-absorbing component |
| CN102556333A (en) * | 2012-03-09 | 2012-07-11 | 北京航空航天大学 | Energy-absorbing scheme of corrugated beam structure at bottom of civil airplane body |
| CN203528805U (en) * | 2013-08-08 | 2014-04-09 | 江西洪都航空工业集团有限责任公司 | Plane anti-collision energy-absorbing structure unit |
| JP2015066416A (en) * | 2013-09-28 | 2015-04-13 | 孝典 福元 | Simple stretcher for emergency evacuation |
| CN103625555A (en) * | 2013-11-26 | 2014-03-12 | 湖南大学 | High-strength steel automobile front carling energy absorbing structure based on embedded carbon fiber |
| CN206053160U (en) * | 2016-08-13 | 2017-03-29 | 深圳雅致钢结构工程有限公司 | A kind of node structure of double-deck roof boarding cornice |
| CN109421915A (en) * | 2017-09-05 | 2019-03-05 | 波音公司 | Energy absorption floor lower body |
| CN108045547A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of composite torsion-box formula anti-crash endergonic structure |
| CN109455290A (en) * | 2018-10-25 | 2019-03-12 | 中国民航大学 | A kind of cargo deck lower part endergonic structure unit for fitting pendant property for improving aircraft |
| CN209258409U (en) * | 2018-11-06 | 2019-08-16 | 中国直升机设计研究所 | A kind of resistance to crash structure of helicopter |
Non-Patent Citations (7)
| Title |
|---|
| A moderate deflection composite helicopter rotor blade model with an improved cross-sectional analysis;Friedmann;《International Journal of Solids and Structures》;20091231;第2186-2200页 * |
| 不同截面形状薄壁梁的轴向吸能特性研究;莫易敏等;《机械设计与制造》;20170708(第07期);第196-199页 * |
| 基于共同规范的散货船槽型横舱壁设计研究;甘水来等;《船舶与海洋工程》;20140225(第01期);第38-44页 * |
| 引发机制对复合材料波形梁吸能性能的影响及其破坏形貌分析;程群峰等;《复合材料学报》;20080215(第01期);第165-171页 * |
| 直升机复合材料波纹梁结构抗坠毁设计技术研究;卢致龙等;《直升机技术》;20150915(第03期);第16-21页 * |
| 程群峰等.引发机制对复合材料波形梁吸能性能的影响及其破坏形貌分析.《复合材料学报》.2008,(第01期), * |
| 高速列车头车吸能排障器设计与仿真研究;丁晨等;《铁道车辆》;20110110(第01期);第5+7-10页 * |
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