CN114212264A - Helicopter platform blotter and buffering support - Google Patents
Helicopter platform blotter and buffering support Download PDFInfo
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- CN114212264A CN114212264A CN202111472873.9A CN202111472873A CN114212264A CN 114212264 A CN114212264 A CN 114212264A CN 202111472873 A CN202111472873 A CN 202111472873A CN 114212264 A CN114212264 A CN 114212264A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F1/00—Springs
- F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
- F16F1/40—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers consisting of a stack of similar elements separated by non-elastic intermediate layers
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Abstract
The embodiment of the invention discloses a helicopter platform cushion and a cushion bracket, wherein the cushion comprises a steel top plate and a steel bottom plate; a stiffening steel plate is arranged between every two adjacent rubber sheets, the rubber sheets and the stiffening steel plate are arranged between the steel top plate and the steel bottom plate, each rubber sheet in the rubber sheets is integrally vulcanized and bonded with the stiffening steel plate, the steel top plate and the steel bottom plate, and the peel strength of a rubber cushion formed by bonding is not less than 10 kN/m; the length of steel roof and steel bottom plate all is greater than the length of every sheet rubber, and the steel roof be equipped with in the part that stretches out the sheet rubber be used for with the upper portion platform fixed connection's of helicopter platform first coupling assembling, the steel bottom plate be equipped with in the part that stretches out the sheet rubber be used for with the lower part bearing structure fixed connection's of helicopter platform second coupling assembling. The cushion pad and the cushion support can play a role in buffering and reducing the stress on the upper part of the helicopter platform.
Description
Technical Field
The invention relates to the technical field of ship manufacturing, in particular to a cushion pad and a cushion bracket for a helicopter platform.
Background
At present, helicopter decks are used in marine structures & ships (such as drilling platforms, jacket platforms, residential platforms, wind power platforms, etc.) and some offshore off-island cruise ship hotel research and development designs, in order to avoid a fire caused by helicopter falling (CAP437 landing zone is 180 ° unobstructed), helicopter decks are generally arranged on the top of a building, and most of the helicopter decks are in the form of half-cantilever beams or full-cantilever beams (see fig. 1). The helicopter platform main structure comprises an upper helicopter deck and a lower supporting structure, the upper structure and the lower structure are generally rigidly connected by welding or bolts, and the lower supporting structure is integrally supported on the upper built outer wall or partially supported on the main hull deck. Under the working conditions of towing, self-propulsion or fixing of the platform or the ship, the helicopter platform can be influenced by wind loads (measured in tons) in different degrees except the dead weight, the wind load stress can be transmitted to the whole upper building or even the main hull, the helicopter impacts and lands to generate dynamic load instantly, and the whole airplane platform generates a great shearing force for the lower support and the upper building connection point. If the reinforcement in the design stage is insufficient, the noise exceeds the standard due to the vibration of the whole building, and the health of crew is damaged; even resonance can be caused, so that the whole ship vibrates, welding looseness is caused, and the structure of the ship body is damaged; if sufficient reinforcement is considered, the construction costs will be increased considerably. There is a need to design a new helicopter deck connection to solve the above problems in practical applications.
Disclosure of Invention
In view of the above problems in the prior art, embodiments of the present invention provide a cushion pad and a cushion bracket for a helicopter platform, which solve the problem of vibration caused by direct wind-borne force on the platform or a ship due to rigid connection between the deck and a support of the existing helicopter platform, and play a role in buffering and reducing the force transmitted from the upper deck of the helicopter platform to a lower support structure and in the whole building process.
The embodiment of the invention provides a cushion pad of a helicopter platform, which comprises:
a steel top plate and a steel bottom plate;
a stiffening steel plate is arranged between every two adjacent rubber sheets, the rubber sheets and the stiffening steel plate are arranged between the steel top plate and the steel bottom plate, each rubber sheet in the rubber sheets is bonded with the adjacent steel plate in a vulcanization mode, the rubber sheets are integrally bonded with the stiffening steel plate, the steel top plate and the steel bottom plate in a vulcanization mode respectively, and the peel strength of a rubber cushion pad formed after bonding is not less than 10 kN/m;
the steel roof with the length of steel bottom plate all is greater than the length of every sheet rubber, just the steel roof is equipped with the first coupling assembling that is used for with the upper portion platform fixed connection of helicopter platform in the part that stretches out the sheet rubber, the steel bottom plate be equipped with in the part that stretches out the sheet rubber be used for with the second coupling assembling of the lower part bearing structure fixed connection of helicopter platform.
In some embodiments of the invention, the heliplatform cushion further comprises:
the safety connecting assemblies penetrate through the steel top plate and the steel bottom plate simultaneously, the safety connecting assemblies arranged on two sides of the plurality of rubber sheets are located between the plurality of rubber sheets and the connecting pieces on the corresponding sides, and the safety connecting assemblies are arranged close to the plurality of rubber sheets;
wherein, the steel roof with the steel bottom plate all offers on corresponding position and is used for wearing to establish safety connection subassembly's mounting hole, the mounting hole can prevent to wear to establish safety connection subassembly wherein and follow the length direction of steel roof removes, and can restrict to wear to establish safety connection subassembly wherein and follow the width direction of steel roof removes in predetermineeing the within range.
In some embodiments of the invention, the steel top plate and the steel bottom plate are made of AH36 ship plates or steel plates with the same strength as the AH36 ship plates;
the stiffening steel plate is an S235 steel plate or a steel plate with the strength not lower than that of the S235 steel plate;
the safety connection assembly is equipped with a locking member.
In some embodiments of the present invention, the width of each of the stiffening steel plates is greater than the length of each of the rubber sheets, and the portions of each of the stiffening steel plates extending out of each of the rubber sheets in the width direction of each of the rubber sheets are equal in length and are symmetrical.
An embodiment of the present invention further provides a helicopter platform buffer support, including:
an upper platform;
a lower support structure;
the helicopter platform cushion of the above embodiment, said cushion being fixedly attached to said upper platform by a steel top plate and to said lower support structure by a steel bottom plate;
wherein the helicopter platform is in the form of a half cantilever beam or a full cantilever beam.
In some embodiments of the invention, the number of the cushions is determined based on a combination of the weight of the helicopter and the operation conditions, wherein the combination of the operation conditions at least comprises the wind load stress, the docking state of the helicopter and the towing state of the ship.
In some embodiments of the invention, the wind load force is calculated by:
Fw＝0.613∑(CsChA)Vw 2 formula 1
Wherein the content of the first and second substances,
FW is wind power; cSTaking the shape coefficient as 1.5 for the helicopter, 1.25 for the airplane platform and 0.6 for the truss; chTaking 1.2 as height coefficient; a is the vertical projection area of each wind receiving surface; vWTo design the wind speed.
In some embodiments of the present invention, the number of cushions is determined based on a combination of factors including the weight of the helicopter and the operating conditions, and includes:
determining a vertical deformation and a shear deformation of the cushion pad, wherein,
vertical deformation Vc, calculated by the following equation 2:
Vc＝∑(Fz*ti/A1)*(1/5/G/S1 2+1/Eb) Formula 2
In the formula, FzVertical bearing capacity; t is tiIs the rubber thickness; a. the1Is the effective area of the rubber layer; g is the rubber shear modulus; s1Is the structural shape factor of rubber; ebIs the bulk modulus of elasticity of the rubber;
wherein the content of the first and second substances,
S1＝A1/(lp*te) Formula 3
In the formula IpIs the circumference of the rubber; t is teIs the effective thickness of the rubber; shear deformation Hc：
Hc＝Fw/KbFormula 4
In the formula, FWIs wind power; kbIs horizontal stiffness;
wherein the content of the first and second substances,
Kb＝G*A1/tqformula 5
In the formula, A1Is the effective area of the rubber layer; g is the rubber shear modulus; t is tqThe total thickness of the rubber layer.
In some embodiments of the present invention, the number of cushions is determined based on a combination of factors including the weight of the helicopter and the operating conditions, and further includes:
analyzing the horizontal shear force applied to the cushion pad.
In some embodiments of the present invention, the number of cushions is determined based on a combination of factors including the weight of the helicopter and the operating conditions, and further includes:
and carrying out stress analysis on the first connecting assembly and the second connecting assembly of the cushion pad and the safety connecting assembly of the cushion pad.
Compared with the prior art, the helicopter platform cushion pad and the cushion bracket provided by the embodiment of the invention have the beneficial effects that: the cushion pad is used as a transition connection mode between the upper deck and the lower support of the helicopter. The cushion pad is formed by vulcanizing and bonding a plurality of layers of rubber sheets and steel plates, has enough vertical rigidity and vertical bearing capacity, and simultaneously has good elasticity and shear deformation to adapt to horizontal displacement and corner displacement generated under the stress of an upper structure.
Helicopter upper deck forces are transmitted through the cushion to the lower support structure and the entire upper structure. In the process of load stress transmission, the buffer pad absorbs part of the force to play roles of buffering and reducing, thereby reducing the shearing force applied to the welding point between the lower supporting structure and the upper building or the main ship body.
The cushion has a certain damping effect and can slow down vibration and impact generated when the helicopter lands.
The bolt is convenient to connect and disassemble, low in price and reusable, and the service life of the bolt is not less than 20 years. Particularly, if the upper aluminum airplane deck and the lower steel support which are conventionally adopted are connected by brazing, the process is complex, and for convenience, a steel-aluminum composite plate is adopted for transition, so that the material is high in price and is generally imported. The embodiment adopts the nylon insulating isolation sleeve and the nylon gasket, can prevent dissimilar metal from being corroded due to contact, and has low cost and simple process.
Drawings
FIG. 1 is a schematic illustration of a prior art cantilevered aircraft platform;
FIG. 2 is a schematic structural view of a helicopter platform employing a helicopter platform cushion and cushion support in accordance with an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of A-A in FIG. 2;
FIG. 4 is a schematic diagram of a configuration of a helicopter platform cushion of an embodiment of the present invention;
FIG. 5 is a schematic cross-sectional view of B-B in FIG. 4;
FIG. 6 is another schematic illustration of a helicopter platform cushion in accordance with an embodiment of the present invention;
fig. 7 is a schematic sectional structure view of C-C in fig. 6.
Reference numerals
1. A steel top plate; 2. a steel bottom plate; 3. a rubber sheet; 4. a stiffened steel plate; 5. a first connection assembly; 6. a second connection assembly; 7. a safety connection assembly; 8. a cushion pad.
Detailed Description
In order to make the technical solutions of the present invention better understood, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
Various aspects and features of the present application are described herein with reference to the drawings.
These and other characteristics of the present application will become apparent from the following description of preferred forms of embodiment, given as non-limiting examples, with reference to the attached drawings.
It should also be understood that, although the present application has been described with reference to some specific examples, a person of skill in the art shall certainly be able to achieve many other equivalent forms of application, having the characteristics as set forth in the claims and hence all coming within the field of protection defined thereby.
The above and other aspects, features and advantages of the present application will become more apparent in view of the following detailed description when taken in conjunction with the accompanying drawings.
Specific embodiments of the present application are described hereinafter with reference to the accompanying drawings; however, it is to be understood that the disclosed embodiments are merely exemplary of the application, which can be embodied in various forms. Well-known and/or repeated functions and structures have not been described in detail so as to not unnecessarily obscure the present application with unnecessary or unnecessary detail. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present application in virtually any appropriately detailed structure.
The specification may use the phrases "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," which may each refer to one or more of the same or different embodiments in accordance with the application.
An embodiment of the present invention provides a cushion pad for a helicopter platform, wherein the helicopter platform is specifically in a form of a half-cantilever beam or a full-cantilever beam, and the cushion pad is disposed between an upper platform and a lower support structure of the helicopter platform, as shown in fig. 1 to 7, and specifically includes:
a steel top plate 1 and a steel bottom plate 2;
a plurality of rubber sheets 3, a stiffening steel plate 4 is arranged between two adjacent rubber sheets 3, and the plurality of rubber sheets 3 and the stiffening steel plate 4 are both arranged between the steel top plate 1 and the steel bottom plate 2, wherein each rubber sheet 3 of the plurality of rubber sheets 3 is connected with the adjacent steel plate in a vulcanization mode, and the peel strength of a rubber cushion pad 8 formed by vulcanizing the plurality of rubber sheets 3 with the stiffening steel plate 4, the steel top plate 1 and the steel bottom plate 2 is not less than 10 kN/m; specifically, the rubber sheet 3 at the top of the plurality of rubber sheets 3 is vulcanized with the steel top plate 1 and the stiffening steel plate 4, the rubber sheet 3 at the bottom of the plurality of rubber sheets 3 is vulcanized with the steel bottom plate 2 and the stiffening steel plate 4, and the other rubber sheets 3 of the plurality of rubber sheets 3 are vulcanized with the adjacent stiffening steel plate 4; the rubber sheets 3 are vulcanized with the adjacent steel plates to form a cushion pad 8 which is bonded together, has enough vertical rigidity and vertical bearing capacity, has good elasticity and shearing deformation to adapt to the horizontal displacement and the corner displacement of the upper structure of the helicopter platform, has a certain damping effect, and plays roles of buffering and reducing when the stress of the upper deck of the helicopter platform is transmitted to the lower supporting structure and the whole upper building process;
It can be seen that the helicopter platform cushion 8 with the above structure can transfer the stress of the upper platform (platform deck) of the helicopter to the lower support structure, and can play a role in buffering and reducing the helicopter in the whole process of landing and taking off.
Further, according to the different structural forms of the heliplatform, in some embodiments of the invention, the heliplatform cushion 8 further comprises:
the safety connection assemblies 7 penetrate through the steel top plate 1 and the steel bottom plate 2 at the same time, the safety connection assemblies 7 arranged on two sides of the plurality of rubber sheets 3 are all positioned between the plurality of rubber sheets 3 and the connecting pieces on the corresponding sides, and the safety connection assemblies 7 are all arranged close to the plurality of rubber sheets 3; specifically, this safe coupling assembling 7 can be the rigidity intensity bolt assembly, or the double-screw bolt subassembly, and the bottom nut of adoption be lock nut, and simultaneously, first coupling assembling 5, second coupling assembling 6 and corresponding safe coupling assembling 7 that the blotter 8 adopted all can adopt the mode of evenly arranging to set up to the demand to intensity when satisfying the installation.
Wherein, steel roof 1 with steel bottom plate 2 all offers on corresponding position and is used for wearing to establish safety coupling assembling 7's mounting hole, the mounting hole can prevent to wear to establish safety coupling assembling 7 wherein and follow the length direction of steel roof 1 removes, and can restrict to wear to establish safety coupling assembling 7 wherein and follow the width direction of steel roof 1 removes in predetermineeing the within range, and then makes safety coupling assembling 7 can carry out corresponding adjustment according to the 8 displacements of blotter, and wherein, this mounting hole can adopt oval, or be the rectangular hole that the both ends were arc to set up. At this time, the cushion pad 8 equipped with the safety link assembly 7 may be referred to as an RB-II type.
Meanwhile, for the RB-I type and RB-II type cushion pads 8, when the corresponding steel top plate 1 and steel bottom plate 2 are connected with the upper platform (deck) and the lower supporting structure of the helicopter, a welding mode cannot be adopted, so that rubber bonding failure caused by heat radiation generated by high welding temperature is avoided.
In this embodiment, the steel top plate 1 and the steel bottom plate 2 are made of AH36 ship plates or steel plates having the same strength as the AH36 ship plates; the stiffening steel plate 4 is an S235 steel plate or a steel plate with the strength not lower than that of the S235 steel plate; the safety connection assembly 7 is equipped with a locking member.
In this embodiment, the width of each of the stiffening steel plates 4 is greater than the length of each of the rubber sheets 3, and the portions of each of the stiffening steel plates 4 extending out of the rubber sheet 3 in the width direction of each of the rubber sheets 3 are equal in length and are symmetrical.
The embodiment of the invention also provides a helicopter platform buffer bracket, which comprises:
an upper platform;
a lower support structure;
the helicopter platform cushion 8 according to the above embodiment, said cushion 8 is fixedly connected to said upper platform by a steel top plate 1 and fixedly connected to said lower support structure by a steel bottom plate 2;
wherein the helicopter platform is in the form of a half cantilever beam or a full cantilever beam.
In some embodiments of the present invention, the number of the cushions 8 is determined based on a combination of the weight of the helicopter and the operation conditions, wherein the combination of the operation conditions at least comprises the wind load stress, the docking state of the helicopter and the towing state of the ship.
In some embodiments of the invention, the wind load force is calculated by:
Fw＝0.613∑(CsChA)Vw 2formula 1
Wherein the content of the first and second substances,
FW is wind power; cSTaking the shape coefficient as 1.5 for the helicopter, 1.25 for the airplane platform and 0.6 for the truss; chTaking 1.2 as height coefficient; a is the vertical projection area of each wind receiving surface; vWTo design the wind speed.
In some embodiments of the present invention, the number of cushions 8 is determined based on a combination of factors including the weight of the helicopter and the operating conditions, including:
determining the vertical and shear deformations of the cushioning pad 8, wherein,
vertical deformation Vc, calculated by the following equation 2:
Vc＝∑(Fz*ti/A1)*(1/5/G/S1 2+1/Eb) Formula 2
In the formula, FzVertical bearing capacity; t is tiIs the rubber thickness; a. the1Is the effective area of the rubber layer; g is the rubber shear modulus; s1Is the structural shape factor of rubber; ebIs the bulk modulus of elasticity of the rubber;
wherein the content of the first and second substances,
S1＝A1/(lp*te) Formula 3
In the formula IpIs the circumference of the rubber; t is teIs the effective thickness of the rubber; shear deformation Hc：
Hc＝Fw/KbFormula 4
In the formula, FWIs wind power; kbIs horizontal stiffness;
wherein the content of the first and second substances,
Kb＝G*A1/tqformula 5
In the formula, A1Is the effective area of the rubber layer; g is the rubber shear modulus; t is tqThe total thickness of the rubber layer.
In some embodiments of the present invention, the number of the cushions 8 is determined based on a combination of the weight of the helicopter and the operation conditions, and further comprises:
the cushion pad 8 is analyzed for horizontal shear forces.
In some embodiments of the present invention, the number of the cushions 8 is determined based on a combination of the weight of the helicopter and the operation conditions, and further comprises:
the first connecting member 5 and the second connecting member 6 of the cushion pad 8 and the safety connecting member 7 of the cushion pad 8 are analyzed.
In order to facilitate understanding of the above technical solutions, a self-elevating platform JU2000E is specifically described as an example. As can be seen in fig. 2, the aircraft platform D has a value of 22.2m, model Sikosky S61N.
Wind load force analysis
According to the regulations, the minimum wind speed is 36m/s for normal offshore operation conditions, 51.5m/s (16-class hurricane) for self-storing conditions, and the minimum wind speed can be reduced to 25.8m/s for sheltered waters. The method is summarized according to the actual conditions of various airplane platforms, the transverse wind area is the largest, and therefore the transverse wind load stress is mainly analyzed. And the invention is designed mainly for the purpose that the cushion pad 8 plays a role in buffering and reducing the stress transmitted from the upper deck of the helicopter to the lower supporting structure and the whole building process, so that the wind load stress analysis is mainly performed on the upper deck (part with the height of about 3 m) of the helicopter:
Fw＝0.613∑(CsChA)Vw 2formula 1
Wherein the content of the first and second substances,
FW-wind power (N);
CSthe shape coefficient is 1.5 for the helicopter, 1.25 for the airplane platform and 0.6 for the truss;
Ch-height factor, calculated vertical distance of the centre of the component to the design water line. Considering the air gap to take 1.2;
a is the vertical projection area of each wind receiving surface, and the side area of the Sikosky S61N model is about 59m2The side area of the upper deck of the helicopter is about 62m2；
VW-design wind speed.
Remarking: the helicopter does not stop in the actual towing state of the platform, and the wind load reference value of other ships in the navigation state is considered.
(II) structural design analysis of cushion 8
The cushion pad 8 is structurally designed by referring to a plate type rubber support EN 1337-3. The cushion pad 8 designed by the invention is shown in fig. 4 to 6, and the main parameters are as follows:
watch two
| Name (R) | Number of | Length x width (mm) | Thickness (mm) | Remarks for |
| Rubber composition | ||||
| 4 | 400x300 | 16 | ||
| |
3 | |
3 | |
| |
2 | 700x400 | 20 | |
| |
2 | 800x400 | 20 | Bolt with safety |
Note: the above parameters were checked for stiffened steel plate thickness, design strain and buckling stability according to EN 1337-3, all within range values.
The maximum vertical force of the helicopter upper deck is about 103.25t when the helicopter platform upper deck has a D value of 22.2m, the steel structure is about 80t (according to actual ship parameters), the aluminum structure is about 26t (according to manufacturer data), and the self weight of the helicopter of the embodiment is about 9.3t (the dynamic impact loads generated by normal landing and emergency landing of the helicopter are respectively: 1.5 × 9.3 ═ 13.95t and 2.5 × 9.3 ═ 23.25 t). According to the parameters, the vertical bearing capacity of the cushion pad 8 designed by the invention is designed to be 50 t/multiple (the cushion pads 8 bear together), the rubber hardness is 60 +/-5, and the number of the cushion pads 8 is determined according to the comprehensive factors of the weight of the helicopter structure and the working condition, and is analyzed and explained later by an embodiment.
The above embodiments of the present invention mainly require analysis of vertical deformation (rubber stressed outer drum) and shear deformation (horizontal displacement) of the cushion pad 8:
vertical deformation vc (mm):
Vc＝∑(Fz*ti/A1)*(1/5/G/S1 2+1/Eb) 0.55(mm) formula 2
In the formula (I), the compound is shown in the specification,
Fzvertical bearing capacity, 500 kN;
ti-rubber thickness, 16 mm;
A1effective area of rubber layer (mm)2),300*400＝120000mm2；
G-shear modulus of rubber (N/mm)2)，0.9；
S1-structural shape factor of rubber, 5;
Eb-bulk modulus of elasticity of the rubber, 2000 MPa;
wherein the content of the first and second substances,
S1＝A1/(lp*te) Formula 3 ═ 5
In the formula (I), the compound is shown in the specification,
lprubber circumference, 2 × 1400mm (300+ 400);
te-effective thickness of rubber, 16 mm;
shear deformation Hc(mm)：
Hc＝Fw/KbFormula 4
In the formula (I), the compound is shown in the specification,
FW-wind power (N);
Kbhorizontal stiffness (kN/mm)
Wherein the content of the first and second substances,
Kb＝G*A1/tq1.69(kN/mm) formula 5
In the formula (I), the compound is shown in the specification,
A1-rubber layer effective area (mm2),300 × 400 ═ 120000mm 2;
g-shear modulus of rubber (N/mm)2)，0.9；
tq-total thickness of rubber layers, 4 × 16 ═ 64 mm;
third, according to different working conditions and wind speeds of the platform or the ship, the shear deformation (horizontal displacement) cannot be simply considered only by considering the wind load, and further analysis is needed, in the following embodiment, the shear stress analysis is performed on the cushion pad 8 by taking 30 cushion pads 8 uniformly distributed on the platform as an example, and specifically, as shown in fig. 3:
if the upper deck of the helicopter is of a steel construction, then,
at a wind speed of 25.8m/s, the cushion pad 8 is subjected to shear stress analysis as shown in table three,
at a wind speed of 36m/s, the cushion pad 8 was subjected to shear stress analysis as shown in table four,
at a wind speed of 51.5m/s, the cushion pad 8 was subjected to shear stress analysis as shown in table five,
if the upper deck of the helicopter is of an aluminium construction, then,
at a wind speed of 25.8m/s, the cushion pad 8 was subjected to shear stress analysis as shown in table six,
at a wind speed of 36m/s, the cushion pad 8 was subjected to shear stress analysis as shown in table seven,
at a wind speed of 51.5m/s, the cushion pad 8 was subjected to shear stress analysis as shown in table eight,
according to table three to eight to the design wind speed and the helicopter upper portion deck atress condition under different states of self-existing operating mode wind speed, promptly, cushion 8 receives the horizontal shear force and carries out the analysis and reachs:
when the platform or the ship rolls for 15 degrees and the helicopter lands, the cushion pad 8 is subjected to the maximum shearing force;
after the platform is lifted and fixed, the shearing force of a single cushion pad 8 is the same no matter the helicopter deck is made of steel or aluminum, namely, the single cushion pad is only influenced by wind load;
in the rolling state, the self weight of the platform can increase the shearing deformation of the cushion pad 8. The fourth table and the fifth table show that the steel deck is obviously larger than the aluminum deck in shearing force, and the composite displacement of the cushion pad 8 is larger than or equal to 10 mm;
the number of cushions 8 is directly related to the shear deformation value;
wind velocity plays a crucial role in the shear deformation of the cushion pad 8.
The cushion pad 8 is designed according to the minimum requirements of the ultimate horizontal displacement shear test: the minimum value of the ultimate shear deformation can reach 1/2 rubber thickness, namely 32mm in the embodiment, and the rubber can be reset.
Thus, the number of cushions 8 may be adjusted (increased or decreased) based on the composite displacement value. For the present embodiment, the design should be based on the stress analysis under the worst self-existing condition of 51.5m/s wind speed: the number of the cushion pads 8 can be increased properly on the steel helicopter deck; the number of the aluminum helicopter decks does not need to be increased or decreased; sheltering the water, whether steel or aluminum helicopter decks, can reduce the number of cushions 8 to reduce cost.
(IV) analysis of bolted connections
As shown in fig. 4 and 5, cushion 8 is not provided with a safety bolt assembly, and the helicopter upper deck and lower support are flexibly connected only by cushion 8.
The RB-I type bolt soft connection mode is suitable for a shielded water area which is small in wind wave and not influenced by rolling, or the upper deck of the helicopter is of an aluminum structure, and shearing change is not large in the rolling state (as long as the number of the cushion pads 8 is adjusted, a stable safety redundancy is achieved).
Of course, the bolts are high-strength bolts. When the upper deck of the helicopter is of an aluminum structure, the contact surface of the cushion pad 8 and the upper deck needs to be provided with an insulating gasket (such as a nylon gasket), and the bolt needs to be provided with an insulating isolation sleeve and the nylon gasket to prevent dissimilar metal from being corroded due to contact, so that the service life is shortened.
As shown in figures 6 and 7, the length of each side of the stiffening steel plate 4 is 10mm greater than that of rubber, so that when the vertical stress is too large, the rubber outer drum is controlled in the upper and lower stiffening steel plates 4, and the rubber service life is shortened due to the fact that the rubber outer drum is serious. According to the calculation result of equation 2, the theoretical value of the vertical deformation of the cushion pad 8 in this embodiment is less than 1mm, and can be ignored.
The RB-II type cushion pad 8 is provided with a safety stud assembly, and the connection is to avoid the overturning of the helicopter platform caused by the failure of rubber bonding due to the overlarge shearing force.
Taking this embodiment as an example: under the self-existing working condition of 51.5m/s wind speed and the rolling state (table five), although the shear deformation value (horizontal displacement) is within a safe range, the shear deformation value exceeds 10 mm. The use of a safety stud assembly is an economical option, since it increases construction costs if only increasing the number of cushions 8 to increase safety redundancy is considered.
Again, the elliptical hole design requires special attention to the following 2 points: firstly, the trompil is greater than the double-screw bolt diameter several millimeters, and 20mm adjustment allowance (this length is confirmed according to the biggest displacement value of calculation) is reserved to the long limit direction, and the double-screw bolt of being convenient for cuts corresponding aversion when moving according to blotter 8, and can not reduce the cushioning effect of blotter 8, and when the shearing force subducts, blotter 8 reset process, the bolt can shift along with answering. And secondly, the long side direction of the elliptical hole is perpendicular to the port and the starboard, because the transverse shear force is the largest, the heading is mainly influenced by wind load, the influence on rolling or pitching is small, and the adjustment allowance can be reduced.
(Note: for offshore structures, quasi-static and dynamic analysis acceptance criteria mooring verification, which is related to reference (North China sea) for 50 years, is performed in a 50-year directional storm environment, whereas offshore China conforms to the ocean standards and is governed by the northeast quarterly wind regime from 5 months to 10 months during the winter from 11 months to 3 months and during the southwest quarterly wind, northeast quarterly wind is generally more severe, wind speeds are measured hourly, with an average wind speed of 12.9m/s for 1 year in the quarterly wind period, 24.9m/s for 10 years, an average wind speed of 30.2m/s for 1 year in the typhoon period, 35m/s for 10 years, 38.2m/s for 25 years, 40.8m/s for 50 years, and 43.4m/s for 100 years, so the present invention is designed primarily based on self-existing operating condition values)
In summary, the cushion pad 8 and the cushion bracket designed by the present invention have the following advantages compared with the prior art:
firstly, a cushion pad 8 is used as a transitional connection between the upper deck and the lower support of the helicopter. The cushion pad 8 is formed by vulcanizing and bonding a plurality of layers of rubber sheets 3 and steel plates, has enough vertical rigidity and vertical bearing capacity, and simultaneously has good elasticity and shear deformation to adapt to horizontal displacement and corner displacement generated under the stress of an upper structure.
The forces on the helicopter upper deck are transmitted through the cushion 8 to the lower support structure and the whole upper structure. In the process of load stress transmission, the buffer cushion 8 absorbs part of the force to play roles of buffering and reducing, thereby reducing the shearing force applied to the welding point between the lower supporting structure and the upper building or the main ship body.
The cushion pad 8 has a certain damping effect and can slow down vibration and impact generated when the helicopter lands.
The bolt is convenient to connect and disassemble, low in price and reusable, and the service life of the bolt is not less than 20 years. Particularly, if the upper aluminum airplane deck and the lower steel support which are conventionally adopted are connected by brazing, the process is complex, and for convenience, a steel-aluminum composite plate is adopted for transition, so that the material is high in price and is generally imported. The embodiment adopts the nylon insulating isolation sleeve and the nylon gasket, can prevent dissimilar metal from being corroded due to contact, and has low cost and simple process.
The above embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and the scope of the present invention is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present invention, and such modifications and equivalents should also be considered as falling within the scope of the present invention.
Claims (10)
1. A helicopter platform cushion comprising:
a steel top plate and a steel bottom plate; a stiffening steel plate is arranged between every two adjacent rubber sheets, the rubber sheets and the stiffening steel plate are arranged between the steel top plate and the steel bottom plate, each rubber sheet in the rubber sheets is bonded with the adjacent steel plate in a vulcanization mode, the rubber sheets are integrally bonded with the stiffening steel plate, the steel top plate and the steel bottom plate in a vulcanization mode respectively, and the peel strength of a rubber cushion pad formed after bonding is not less than 10 kN/m;
the steel roof with the length of steel bottom plate all is greater than the length of every sheet rubber, just the steel roof is equipped with the first coupling assembling that is used for with the upper portion platform fixed connection of helicopter platform in the part that stretches out the sheet rubber, the steel bottom plate be equipped with in the part that stretches out the sheet rubber be used for with the second coupling assembling of the lower part bearing structure fixed connection of helicopter platform.
2. A heliplatform cushion as set forth in claim 1, further comprising:
the safety connecting assemblies penetrate through the steel top plate and the steel bottom plate simultaneously, the safety connecting assemblies arranged on two sides of the plurality of rubber sheets are located between the plurality of rubber sheets and the connecting pieces on the corresponding sides, and the safety connecting assemblies are arranged close to the plurality of rubber sheets;
wherein, the steel roof with the steel bottom plate all offers on corresponding position and is used for wearing to establish safety connection subassembly's mounting hole, the mounting hole can prevent to wear to establish safety connection subassembly wherein and follow the length direction of steel roof removes, and can restrict to wear to establish safety connection subassembly wherein and follow the width direction of steel roof removes in predetermineeing the within range.
3. A heliplatform cushion as set forth in claim 2,
the steel top plate and the steel bottom plate are made of AH36 ship plates or steel plates with the same strength as the AH36 ship plates;
the stiffening steel plate is an S235 steel plate or a steel plate with the strength not lower than that of the S235 steel plate;
the safety connection assembly is equipped with a locking member.
4. A heliplatform cushion as set forth in claim 1,
every the width of stiffening steel plate is greater than the length of every sheet rubber, and every the stiffening steel plate is in the part that stretches out the sheet rubber on the width direction of every sheet rubber is isometric and symmetrical.
5. A helicopter platform buffering support, comprising:
an upper platform;
a lower support structure;
a heliplatform cushion as claimed in any one of claims 1 to 4, fixedly connected to the upper platform by a steel top plate and fixedly connected to the lower support structure by a steel bottom plate;
wherein the helicopter platform is in the form of a half cantilever beam or a full cantilever beam.
6. A heliplatform buffering support according to claim 5, characterised in that the number of cushions arranged between the upper platform and the lower supporting structure of the helicopter is determined on the basis of the weight of the helicopter and the combination of operating conditions, which include at least wind load, helicopter parking status and vessel towing status.
7. A helicopter platform damping mount according to claim 6,
the wind load force is calculated by the following formula:
Fw＝0.613∑(CsChA)Vw 2formula 1
Wherein the content of the first and second substances,
FW is wind power; cSTaking the shape coefficient as 1.5 for the helicopter, 1.25 for the airplane platform and 0.6 for the truss; chTaking 1.2 as height coefficient; a is the vertical projection area of each wind receiving surface; vWTo design the wind speed.
8. A helicopter platform damping support according to claim 7, wherein the number of said damping pads is determined based on a combination of factors dependent upon the weight of the helicopter and the operating conditions, including:
determining a vertical deformation and a shear deformation of the cushion pad, wherein,
vertical deformation Vc, calculated by the following equation 2:
Vc＝∑(Fz*ti/A1)*(1/5/G/S1 2+1/Eb) Formula 2
In the formula, FzVertical bearing capacity; t is tiIs the rubber thickness; a. the1Is the effective area of the rubber layer; g is the rubber shear modulus; s1Is the structural shape factor of rubber; ebIs the bulk modulus of elasticity of the rubber;
wherein the content of the first and second substances,
S1＝A1/(lp*te) Formula 3
In the formula IpIs the circumference of the rubber; t is teIs the effective thickness of the rubber; shear deformation Hc：
Hc＝Fw/KbFormula 4
In the formula, FWIs wind power; kbIs horizontal stiffness;
wherein the content of the first and second substances,
Kb＝G*A1/tqformula 5
In the formula, A1Is the effective area of the rubber layer; g is the rubber shear modulus; t is tqThe total thickness of the rubber layer.
9. A helicopter platform buffer support as claimed in claim 8, wherein said number of cushions is determined based on a combination of factors dependent upon the weight of the helicopter and the operating conditions, and further comprising:
analyzing the horizontal shear force applied to the cushion pad.
10. A helicopter platform buffer support as claimed in claim 9, wherein said number of cushions is determined based on a combination of factors dependent upon the weight of the helicopter and the operating conditions, and further comprising:
and carrying out stress analysis on the first connecting assembly and the second connecting assembly of the cushion pad and the safety connecting assembly of the cushion pad.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111472873.9A CN114212264A (en) | 2021-12-04 | 2021-12-04 | Helicopter platform blotter and buffering support |
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| CN202111472873.9A CN114212264A (en) | 2021-12-04 | 2021-12-04 | Helicopter platform blotter and buffering support |
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| GB469554A (en) * | 1936-01-23 | 1937-07-23 | Reginald Alfred Charles Brie | Landing and launching device for aircraft |
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| WO2011043242A1 (en) * | 2009-10-06 | 2011-04-14 | オイレス工業株式会社 | Laminated rubber body joining members, as well as laminated rubber body and structure using such joining members |
| JP2016223586A (en) * | 2015-06-02 | 2016-12-28 | 株式会社フジタ | Lamination rubber support |
| CN108082517A (en) * | 2017-12-15 | 2018-05-29 | 成都千里之行科技有限公司 | A kind of unmanned plane lifting platform |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB469554A (en) * | 1936-01-23 | 1937-07-23 | Reginald Alfred Charles Brie | Landing and launching device for aircraft |
| JPH11241750A (en) * | 1997-11-21 | 1999-09-07 | Kaimon:Kk | Sliding type elastic support device for structure and high supporting pressure load supporting member |
| JP2000081087A (en) * | 1998-09-03 | 2000-03-21 | Sumitomo Rubber Ind Ltd | Base isolation device |
| JP2009156284A (en) * | 2007-12-25 | 2009-07-16 | Kawaguchi Metal Industries Co Ltd | Laminated rubber equipped with load sensing function, its manufacturing method, and rubber bearing |
| WO2011043242A1 (en) * | 2009-10-06 | 2011-04-14 | オイレス工業株式会社 | Laminated rubber body joining members, as well as laminated rubber body and structure using such joining members |
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| CN108082517A (en) * | 2017-12-15 | 2018-05-29 | 成都千里之行科技有限公司 | A kind of unmanned plane lifting platform |
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